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The Atlas rocket, originally developed as America's first ICBM, was the basis for most early American space exploration and was that country's most successful medium-lift commercial launch vehicle. It launched America's first astronaut into orbit; the first generations of spy satellites; the first lunar orbiters and landers; the first probes to Venus, Mars, Mercury, Jupiter, and Saturn; and was America's most successful commercial launcher of communications satellites. Its innovative stage-and-a-half and 'balloon tank' design provided the best dry-mass fraction of any launch vehicle ever built. It was retired in 2004 after 576 launches in a 47-year career. Atlas began with a US Army Air Corps request for proposal in October 1945 for long-range missile designs. By 10 January 1946, Consolidated-Vultee’s engineers, under the leadership of Belgian-born Karel Bossart, submitted their proposals for two 6,000-nautical mile missiles: one subsonic, winged, and jet powered; the other supersonic, ballistic, and rocket powered. New technologies proposed for the ballistic missile included extremely low structural weight through use of steel monocoque single-wall construction tanks, kept rigid by internal tank pressure; gimbaled rocket engines; a detachable warhead section; and nearly single-stage to orbit performance through the ‘stage-and-a-half’ approach of jettisoning the booster engines during the ascent. On 19 April Convair received a contract for $1,893,000 to fabricate and test ten MX-774 Hiroc missiles to verify Bossart’s innovative ballistic missile concepts. Captive testing of the MX-774 research rockets began in San Diego in 1947. In June, Consolidated Vultee was notified that it had lost the cruise missile competition; Northrop and Martin received contracts for development of their subsonic jet-powered cruise missile designs. Defense cutbacks forced the Air Force to terminate the MX-774 contract in July 1947, only three months before the first scheduled flight. The remaining contract funds allowed three MX-774's to be test-launched at White Sands Proving Ground in July-December 1947. Further work at Convair was reduced to ‘Mafia’ low-level design activity using company funds. The outbreak of the Korean war and the beginning of the cold war loosened the federal purse strings. Convair received a new contract (MX-1593) in September 1951 to begin design of a ballistic missile incorporating the design features validated by the MX-774. In 1953 the now-Convair Division of General Dynamics presented a plan to the Air Force for an accelerated program. A major propulsion problem in the early 1950's was that liquid rocket motor ignition reliability was less than 50 percent. This led to the stage-and-a-half concept, with all engines ignited prior to lift-off and the booster engines jettisoned during flight. This allowed confirmation that all engines were functioning correctly before releasing the missile for flight. A full go-ahead for the Atlas design was ordered in January 1955 as Weapon System WS107A-l. At Convair the project was known the Model 7 (in Russia, Korolev was working on the competing R-7 ICBM - evidently both sides wanted to use the lucky number). In September 1955, faced with intelligence reports of Russian progress on their ICBM, the Atlas received the highest national development priority. The project became one of the largest and most complex production, testing, and construction programs ever undertaken. The first propulsion system and component tests were conducted in June 1956; the first captive and flight-test missiles were completed later the same year. The first Atlas A flight took place on 11 June 1957. In a tremendous national effort, by 1959 a peak of 33,000 personnel were working on the project. Total cost of the Atlas ICBM program to the United States was $8 billion. About a quarter of this went to Convair to design and develop the missile and launch facilities. The balance was for the tremendous cost of the ICBM launch facilities. For all of this effort, the Atlas was quickly obsolete, and the facilities were closed by 1966 after five years of service. However surplus ICBM's were stored, refurbished, and used as space launch vehicles until the last was flown in 1995 - 33 years after it was manufactured. The first operational missile, the Atlas D, was the basis for launching the Mercury manned spacecraft into orbit. By use of Agena and Centaur upper stages, the Atlas became the medium-lift workhorse of American manned, reconnaissance, planetary, and geosynchronous-orbit space programs. After the retirement of the Atlas-Agena in 1978, the Centaur stage became standard on Atlas launch vehicles. Centaur began with a contract awarded to General Dynamics by the Advanced Research Project Agency in 1958. The first space vehicle to use liquid hydrogen, Centaur was a pioneering project that solved the many technical problems of using the super-cryogenic and highly volatile fuel. Pratt & Whitney Aircraft was awarded the contract to develop Centaur's RL-10 engines. The US Air Force had already built the first large-quantity liquid hydrogen production facility for the deep black Suntan reconnaissance program. In 1962, with the hydrogen propulsion technology being vital to the success of the Apollo program, Centaur management was transferred to NASA's Lewis Research Center. Lewis had fired their first experimental Lox/LH2 engine of 5,000 pounds thrust in 1953. The Centaur project was given the highest DX priority, but suffered delays due to management problems at both NASA and Convair. The first successful flight of Centaur atop Atlas occurred in November 1963. However thereafter von Braun's Saturn S-IV stage, using six of the RL-10 motors, leapfrogged the Centaur program . By the time of the first operational Centaur mission in May 1966, the S-IV had already completed its test series of six orbital flights. Yet thirty years later, the Saturn was long gone, and the Centaur continued, having been launched or planned for launch from Atlas, Titan, Delta, and Shuttle vehicles. Production continued into the 21st century, and no replacement for the RL-10 engine, the ultimate engine using the ultimate propellants, was ever put into production. Manufacturer: Convair. Launches: 585. Failures: 120. Success Rate: 79.49%. First Launch Date: 1948-07-14. Last Launch Date: 2004-08-31. Launch data is: complete. Development Cost $: 2,230.000 million. in: 1965 average dollars. Recurring Price $: 8.309 million. Flyaway Unit Cost $: 1.800 million. in: 1965 unit dollars. Cost comments: Development cost and flyaway cost total for Atlas A through F (ICBM's).
Version: MX-774.
Project MX-774 inaugurated by AAF with Consolidated-Vultee to study rocket capabilities with an ICBM as a final objective. Limited funds permitted a few test launches. These rockets demonstrated technologies that woud later be applied to the Atlas. The Air Force contracted for ten MX-774 vehicles, in three phases. Stage A, the Teetotaler, was a sub-sonic, self-guided cruise missile. Stage B, the Old Fashioned, was a test missile using V-2 technology but incorporating new concepts planned for the next phase. Stage C, the Manhattan, was to be an ICBM. The MX-774 was cancelled by the Air Force in 1947 due to budget restrictions and continued Air Force scepticism. Using residual contract and corporate funds, Bossart was able to launch three stage B test vehicles from White Sands after the cancellation. While none of the launches were completely successful, they did demonstrate Bossart’s innovative design concepts including pressurized monocoque propellant tanks. Despite the heavy investment of company funds, the Air Force later directed Bossart to sell the MX-774 development package to TRW for a song. TRW in turn delivered it, in total, to Douglas and Martin to assist them in design of their competing Thor and Titan missiles. There were many hard feelings at Convair about that. Launches: 3. Failures: 3. First Launch Date: 1948-07-14. Last Launch Date: 1948-12-02. Apogee: 50 km (31 mi). Liftoff Thrust: 35.000 kN (7,868 lbf). Total Mass: 1,300 kg (2,800 lb). Core Diameter: 0.76 m (2.49 ft). Total Length: 9.60 m (31.40 ft).
Concept ICBM. Status: Concept 1951. The January 1951 design for the Atlas used seven main engines plus two vernier engines to hurl the 3600 kg nuclear warhead over a 9300 km range. CEP was optimistically estimated as 460 m.
Core Diameter: 3.66 m (12.00 ft). Total Length: 43.00 m (141.00 ft). Standard warhead mass: 3,600 kg (7,900 lb). Maximum range: 9,300 km (5,700 mi). Standard warhead CEP: 0.46 km (0.28 mi).
Version: MX-1593.
The September 1951 design for the Atlas used seven main engines to hurl the 3600 kg nuclear warhead over a 9300 km range. CEP was 1850 m.
Core Diameter: 3.66 m (12.00 ft). Total Length: 37.00 m (121.00 ft). Standard warhead mass: 3,600 kg (7,900 lb). Maximum range: 9,300 km (5,700 mi). Standard warhead CEP: 1.85 km (1.14 mi).
Version: Proposed Atlas.
The April 1953 design for the Atlas at the time of Convair's proposal used five main engines to power a 200 metric tone rocket able to send a 1400 kg nuclear warhead over a 10,200 km range. CEP was 1850 m.
Total Mass: 200,000 kg (440,000 lb). Core Diameter: 3.66 m (12.00 ft). Total Length: 34.00 m (111.00 ft). Standard warhead mass: 1,360 kg (2,990 lb). Maximum range: 10,200 km (6,300 mi). Standard warhead CEP: 0.46 km (0.28 mi).
Version: Contracted Atlas.
The 1954 design for the Atlas as contracted for by the Air Force used three main engines to power a 110 metric ton rocket able to send a 1400 kg nuclear warhead over a 10,200 km range. CEP was 3700 m. The missile actually delivered six years later would have the same dimensions and launch mass, but 63% more range and four times better accuracy.
Total Mass: 109,000 kg (240,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 23.00 m (75.00 ft). Standard warhead mass: 1,360 kg (2,990 lb). Maximum range: 10,200 km (6,300 mi). Standard warhead CEP: 3.70 km (2.20 mi).
Version: Atlas A.
First test model of Atlas ICBM. Two booster engines, no sustainer, dummy warhead. 50% reliability in 8 flight tests. Historical Essay © Andreas Parsch Convair B-65/SM-65/CGM-16/HGM-16 Atlas The Atlas was the first Intercontinental Ballistic Missile (ICBM) deployed by the USA. Its descendents are still in use today as civilian and military space launch vehicles. The Atlas development can be traced back to the days immediately after World War II, when captured German rocket and missile technology supported many new missile research studies. In April 1946, Consolidated-Vultee (later Convair) began project MX-774 to study long-range ballistic missiles. The studies led to a test rocket, designated RTV-A-2 Hiroc, which was to pioneer several new design techniques which would later be used in the Atlas. The Hiroc featured a gimballed rocket nozzle to steer the vehicle by thrust-vectoring instead of weight- and drag-increasing control fins, and had a separable nose cone for the payload. The most radical feature of the RTV-A-2 was its internal pressure stabilized flight structure. The missile's skin was very thin, and was inflated by internal pressure like a balloon. This significantly reduced the empty weight of the vehicle. However, it also made the missile rather fragile, because a single hole in the skin would lead to the collapse of the whole structure, just like a limp balloon. Because limited funding allowed only to pursue the most promising missile projects, and long-range ballistic missiles were deemed to be too far in the future, MX-774 was cancelled in June 1947. However, Convair was allowed to complete three Hiroc vehicles, and the first of these flew in July 1948. All three flights were only partially successful but helped a lot to validate the new design concepts. After the cancellation of MX-774, Convair continued low-key internal studies on ballistic missiles, developing the idea of the "one and one half" stage rocket. In this type of design, both booster and sustainer engine(s) would ignite at lift-off, and the boosters would be dropped later in the flight. This circumvented the difficulty of having to ignite the sustainer at high altitude, which was then considered a potential problem. When military funding sharply increased after outbreak of the Korean War, Convair was awarded a contract for the long-range ballistic missile project MX-1593 in January 1951. Later in 1951, the USAF decided to assign aircraft-like designations to its guided missiles, and the designation B-65 was assigned to the MX-1593 missile (named Atlas by this time). In 1953 Convair had completed the initial design studies. The Atlas was to be a huge 27 m (90 ft) long, 3.6 m (12 ft) wide rocket, with five engines producting 2700+ kN (600000+ lb) of total thrust. The size was deemed necessary to launch the expected very heavy (65 ton) thermonuclear warhead to intercontinental range. Because of the limited accuracy of then available intercontinental guidance systems, a megaton-class thermonuclear warhead was necessary for the Atlas to be effective against hardened targets. A ten-year development program was approved, with an initial operational deployment planned for 1963. To minimize risk, it was decided to develop a single-engine test vehicle first, designated X-11, followed by a three-engine X-12 test vehicle and an XB-65 five-engine strategic missile prototype. In 1954, the H-bomb tests in the Pacific showed that the warhead for the Atlas could be made significantly smaller and lighter than expected. Therefore, the five-engine XB-65 design was cancelled and replaced by a much smaller three-engine design. The booster engines were North American (Rocketdyne) LR89, and the sustainer engine was a Rocketdyne LR105 enigne, both fueled with RP-1 (kerosene) and liquid oxygen. Two small Rocketdyne LR101 vernier engines were used for fine-tuning thrust and directional control. The whole Atlas propulsion system was known as MA-2. In 1955, in the light of discovering Russian ICBM activities, the Atlas development was accelerated, and it was approved to flight test preliminary prototype models which lacked some feartures of the planned production missile. The XB-65A Atlas A had only booster engines, and a dummy warhead. In August 1955, the USAF dropped all aircraft-like designations for guided missiles, and the Atlas became the SM-65. On 11 June 1957 the first attempt to fly an XSM-65A was made, but due to a booster malfunction the missile had to be destroyed a few seconds after lift-off. The first successful Atlas A flight to the full range of 1100 km (600 nm) was the third one, on 17 December 1957. Atlas A testing was completed in June 1958. Launches: 8. Failures: 5. First Launch Date: 1957-06-11. Last Launch Date: 1958-06-03. Apogee: 120 km (70 mi). Liftoff Thrust: 1,334.500 kN (300,008 lbf). Total Mass: 81,647 kg (180,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 28.00 m (91.00 ft). Maximum range: 900 km (550 mi).
Atlas B.
First all-up test version of the Atlas ICBM, with jettisonable booster engines and a single engine sustainer on core - a '1 1/2' stage launch vehicle.
Launches: 10. Failures: 3. First Launch Date: 1958-07-19. Last Launch Date: 1959-02-04. LEO Payload: 70 kg (154 lb). to: 185 km Orbit. at: 32.00 degrees. Apogee: 900 km (550 mi). Associated Spacecraft: Score. Liftoff Thrust: 1,587.200 kN (356,817 lbf). Total Mass: 110,740 kg (244,130 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 26.00 m (85.00 ft). Maximum range: 6,000 km (3,700 mi). Flyaway Unit Cost $: 14.210 million. in: 1985 unit dollars.
Atlas C.
Last development version of Atlas. Never deployed operationally or used for space launches. Historical Essay © Andreas Parsch The XSM-65C Atlas C, flown between December 1958 and August 1959, tested the thin-skinned fuel tanks and the radio-command guidance in production configuration. Launches: 6. Failures: 2. First Launch Date: 1958-12-24. Last Launch Date: 1959-08-24. LEO Payload: 70 kg (154 lb). to: 185 km Orbit. at: 32.00 degrees. Apogee: 900 km (550 mi). Liftoff Thrust: 1,587.200 kN (356,817 lbf). Total Mass: 110,740 kg (244,130 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 25.15 m (82.51 ft). Span: 4.88 m (16.01 ft). Maximum range: 8,000 km (4,900 mi). Number Standard Warheads: 1. Standard RV: Mk. 2/3. Standard warhead: W49. Standard warhead yield: 1,440 KT. Standard warhead CEP: 3.23 km (2.00 mi). Boost Propulsion: Liquid rocket, Lox/Kerosene. Guidance: Inertial. Maximum speed: 29,030 kph (18,030 mph). Ceiling: 1,287,800 m (4,225,000 ft). Total Number Built: 381. Total Development Built: 18. Total Production Built: 343.
World Series.
In May 1956 the Air Force proposed mating an Atlas A with an Aerobee-Hi upper stage in order to launch a satellite during the International Geophysical Year (1957-1958). The Eisenhower administration selected the Vanguard instead. After Sputnik, an Atlas B with no upper stage orbited the Score satellite as a reply to the Soviet's Sputnik 3. Beginning in 1954 the Army and Navy began advocating using modifications of their short-range rockets equipped with multiple upper stages to launch the first satellite into space during the 1957 International Geophysical Year. However a more reasonable and capable alternative would be to use the planned Atlas ICBM for the mission. The Air Force's General Bernard Schriever was in charge of the crash program to develop the Atlas ICBM, and was reluctant to lose a single month of schedule in order to pursue the peripheral scientific mission. The Eisenhower administration appointed the Stewart Committee on 26 May 1955 to select the best course of action. Goaded by interservice rivalry, the Air Force proposed its "World Series" launcher for the task in June 1955. This consisted of the Atlas A two-engined prototype of the missile topped with an Aerobee-Hi sounding rocket as a second stage. It was capable of putting a nominal payload (around 50 kg) into low earth orbit. During the Committee's evaluation process, they visited Schriever's Western Development Division and received briefings on the status of the Atlas program. The Air Force took pains to point out the likelihood of delays in the highest-priority Atlas ICBM program if they were tasked to launch a scientific satellite as well. They seem not to have even mentioned the Atlas-boosted but deep black Corona spy satellite program. Evidently outside knowledge or interference in this was not desirable. In August 1955 the Stewart Committee, having taken on the Pentagon's desire for the IGY effort not to affect either the Air Force Atlas ICBM or Army Jupiter IRBM programs, selected the Navy's Vanguard as the IGY satellite booster. Convair, however, saw a bright future for their Atlas rocket as a space launch vehicle. They made an unsolicited proposal before the Stewart Committee decision to the Air Force to use the three-engined Atlas C as an Orbital Research and Test Vehicle. This would boost a 230 kg satellite into orbit without the need for an upper stage. Nothing came of this proposal immediately. In January 1956 the Air Force would begin study of a scientific version of the Corona reconnaissance satellite, boosted by an Atlas Agena two-stage booster. This could provide a US capability for launching a 1600 kg scientific satellite into orbit, as a follow-on to Vanguard. It also would provide cover for launches under the secret Corona program. This was shelved at the time but would become reality as the "Discoverer" program, a cover for early the Corona satellites. On 1 February 1957 Air Force headquarters asked Schriever to provide a plan to fly a back-up scientific satellite for during the International Geophysical Year, in case Vanguard failed. The reply came a week later. $91 million would be required. But Atlas development was such that no launchings could be guaranteed before mid-1959. It was however possible, best case, that one or two launchings could be managed before the end of the IGY in 1958. The Air Force declined to spend the money. The Soviet launch of Sputnik 1 in October 1957 had a political impact far beyond the loss of a few months in the Atlas operational date. Vanguard did indeed fail, and another Vanguard competitor, the Army's Redstone, managed to orbit a tiny satellite in January 1958. The Soviets launched the massive 1327-kg Sputnik 3 in May 1957, again humbling the Americans. The Convair Orbital Research and Test Vehicle concept was resurrected as Project Score, and Schriever was given funds to launch a satellite using an Atlas as soon as possible. A three-engined Atlas B launched the Score satellite into orbit in December 1958, doing something to restore US prestige. It remained attached to the Atlas, allowing the Americans to claim they had orbited a 4 metric ton satellite, although all but 70 kg of that was the Atlas itself. LEO Payload: 50 kg (110 lb). to: 300 km Orbit. at: 28.00 degrees. Liftoff Thrust: 1,334.500 kN (300,008 lbf). Total Mass: 82,500 kg (181,800 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 35.00 m (114.00 ft).
Version: Atlas D.
Rocket used both as a space launcher and ICBM. Historical Essay © Andreas Parsch In July 1959, the XSM-65D prototype of the initial production variant, the Atlas D, first flew. On 31 October 1959, the first U.S. Air Force ICBM squadron went on Combat Alert at Vandenberg AFB, with 3 SM-65D missiles on unprotected open launch pads. To give the Atlas at least some sort of protection, the follow-on bases were equipped with "coffins" to store the missiles. This coffin was a blast-protected building in which the Atlas was stored horizontally. Following the launch order, the roof of the coffin would slide away, the missile raised to the vertical, ready for fueling and launching. The Atlas ICBM had several significant operational shortcomings. It had to be fueled immediately before launch, leading to a high reaction time (about 15 minutes) after launch order. The fueling was also a very dangerous process which lead to several heavy explosions during operational tests. The radio-command/inertial guidance system of the Atlas D was susceptible to jamming and restricted the launch frequency of an Atlas D squadron to one missile every 5 minutes. The SM-65D used either Mk.2 or Mk.3 blunt reentry vehicles. There was also an unarmed training version of the SM-65D, designated USM-65D. Launches: 135. Failures: 32. Success Rate: 76.30%. First Launch Date: 1959-04-14. Last Launch Date: 1967-11-07. LEO Payload: 1,400 kg (3,000 lb). to: 300 km Orbit. at: 28.00 degrees. Associated Spacecraft: Mercury, OV1, Project 7969, Outpost, McDonnell Project 7969, Project Mer, FIRE. Liftoff Thrust: 1,629.000 kN (366,213 lbf). Total Mass: 119,000 kg (262,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 25.15 m (82.51 ft). Span: 4.88 m (16.01 ft).
LV-3B. Status: Out of production. Department of Defence Designation: LV-3B. First operational version of Atlas ICBM and used as launch vehicle for Project Mercury.
LEO Payload: 1,360 kg (2,990 lb). to: 185 km Orbit. at: 28.00 degrees. Apogee: 1,855 km (1,152 mi). Liftoff Thrust: 1,587.200 kN (356,817 lbf). Total Mass: 117,730 kg (259,550 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 25.00 m (82.00 ft). Maximum range: 13,000 km (8,000 mi). Flyaway Unit Cost $: 14.210 million. in: 1985 unit dollars.
Version: Atlas LV-3B / Mercury.
Atlas D modified for use in Project Mercury.
LEO Payload: 1,360 kg (2,990 lb). to: 185 km Orbit. at: 28.00 degrees. Associated Spacecraft: Mercury. Liftoff Thrust: 1,587.190 kN (356,815 lbf). Total Mass: 116,100 kg (255,900 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 25.00 m (82.00 ft).
Atlas E.
Initial fully operational version of Atlas ICBM. Differed in guidance system from Atlas F. Deployed as missiles from 1960 to 1966. After retirement, the ICBM's were refurbished and used over twenty years as space launch vehicles. Historical Essay © Andreas Parsch The SM-65E Atlas E was an improved SM-65D. It used a more accurate Mk.4 reentry vehicle, had an improved propulsion system (designated MA-3), and used an all-inertial guidance system developed by Bosch Arma, which was originally planned for the HGM-25A Titan I. With this navigation system, located in the distinctive large bulge on the side of the missile, the Atlas E could reach an accuracy of about 600 m (2000 ft) CEP. Component testing on modified Atlas D missiles began in March 1960, and in February 1961 the first full Atlas E flight occurred. The SM-65E became operational in September 1961. Because the all-inertial guidance system did away with the necessity to launch the missile close to the launch control center of the base, the Atlas E was deployed in widely dispersed patterns. Adding also new semi-buried coffins, the Atlas E was significantly better (but still not satisfactorily) protected against a preemptive strike than the D model. The USM-65E was the unarmed training version of the Atlas E. The vehicles converted for space launch use and launched from Vandenberg AFB used a radio guidance system that was based on a modification of the General Electric Radio Tracking System (GERTS), originally employed on the Atlas D. In fact, the GERTS guidance used for space launch employed one of the original radar stations used for the Atlas D and even used some actual Atlas D components in its Pulse Beacon Decoder, the vehicle's X-band radio transponder. Newer solid state computers were used to run the guidance software and were interfaced with the radar; eventually they were made redundant, although with a human operator charged with detecting failure. The large Bosch-Arma pod on the side of the Atlas E and F space boosters launched from Vandenberg AFB from the mid-70's to the mid-90's was in fact empty. It was not removed and replaced with a more streamlined fairing since that would have cost money and gained no significant performance. So, the Atlas E and F space boosters used Atlas E and F ICBM airframes and engines with the tanks modified with a new payload interface section, a mixture of Atlas E and F components (selected based on which designs were most suitable for the space launch mission) and a modified Atlas D radio guidance system. GERTS was a complex, glitch-prone system, its only saving graces being that it was both the cheapest guidance system around and the most reliable, operating for almost 30 years without one flight failure and at a per-flight cost an order of magnitude below that of an inertial guidance system. Prior to Apollo-Saturn, all U.S. manned orbital flights used GERTS, both on the Mercury-Atlas D and the Gemini-Titan II missions. The proper way to refer to the space booster Atlas E's and F's was "Atlas E/F Space Booster," because of the mix of configuration features. Of course, individually the boosters were referred to by their "Tail Numbers" such as 19F, 76E, 68E, etc. The total launched cost of an Atlas E/F space booster was about $15M - or less than 1/3 the cost of a Titan II space booster, and less than 1/20th what was finally admitted as the cost of a single Space Shuttle mission. About 35 unmodified Atlas E/F missiles in storage at Norton AFB were scrapped in the early 1970's. The Space Shuttle was coming and it was assumed that they were not needed. The cost of maintaining them in storage was "horrendous" - about $2000 each per year. At least a half billion dollars worth of perfectly usable, incredibly cheap space boosters (equivalent to a couple of billon dollars in replacement costs) were run over with a bulldozer in order to save perhaps one million dollars in storage costs overtwenty years . The Air Force officer who recommended this travesty of planning received a medal for his farsightedness. Launches: 48. Failures: 15. Success Rate: 68.75%. First Launch Date: 1960-10-11. Last Launch Date: 1995-03-24. LEO Payload: 820 kg (1,800 lb). to: 185 km Orbit. at: 90.00 degrees. Associated Spacecraft: Advanced Tiros N, DMSP Block 5D-2, Geosat, GPS Block 1, LIPS, NOSS, POGS, Tiros N. Liftoff Thrust: 1,713.800 kN (385,278 lbf). Total Mass: 121,000 kg (266,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 28.10 m (92.10 ft). Launch Price $: 50.000 million. in: 1994 price dollars. Flyaway Unit Cost $: 11.000 million. in: 1985 unit dollars.
CGM-16E. Intercontinental ballistic missile. IOC: 1960. Department of Defence Designation: CGM-16E. Popular Name: Atlas E. Alternate Designation: SM-65E. ICBM version
Total Mass: 120,000 kg (260,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 25.15 m (82.51 ft). Span: 4.88 m (16.01 ft). Standard warhead mass: 2,500 kg (5,500 lb). Maximum range: 12,100 km (7,500 mi). Number Standard Warheads: 1. Standard RV: Mk. 4. Standard warhead: W38. Standard warhead yield: 3,750 KT. Standard warhead CEP: 3.23 km (2.00 mi). Boost Propulsion: Liquid rocket, Lox/Kerosene. Guidance: Inertial. Maximum speed: 29,030 kph (18,030 mph). Ceiling: 1,287,800 m (4,225,000 ft). Total Number Built: 381. Total Development Built: 18. Total Production Built: 343.
Atlas Burner 2. Atlas SLV-3 + 1 x Star 37B upper stage.
Launches: 1. Failures: 1. First Launch Date: 1968-08-16. Last Launch Date: 1968-08-16. Apogee: 800 km (490 mi). Liftoff Thrust: 1,700.000 kN (382,100 lbf). Total Mass: 130,000 kg (280,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 28.90 m (94.80 ft).
Atlas Burner 2A. Atlas F + 1 x Star 37B + 1 x Star 26B upper stages.
Launches: 1. First Launch Date: 1972-10-02. Last Launch Date: 1972-10-02. Apogee: 800 km (490 mi). Liftoff Thrust: 1,700.000 kN (382,100 lbf). Total Mass: 130,000 kg (280,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 30.00 m (98.00 ft).
Atlas E/Trident. Atlas E + 1 x Trident upper stage.
Launches: 2. First Launch Date: 1968-03-06. Last Launch Date: 1968-04-27. Apogee: 1,500 km (900 mi). Liftoff Thrust: 1,731.000 kN (389,144 lbf). Total Mass: 130,000 kg (280,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 25.00 m (82.00 ft).
Atlas E/MSD. Atlas E + 1 x MSD upper stage.
Launches: 1. Failures: 1. First Launch Date: 1980-12-09. Last Launch Date: 1980-12-09. Apogee: 1,100 km (600 mi). Liftoff Thrust: 1,731.000 kN (389,144 lbf). Total Mass: 122,000 kg (268,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 27.30 m (89.50 ft).
Atlas E/SVS. Atlas E + 1 x Star 37E + 1 x Star 37E upper stages.
Launches: 1. Failures: 1. First Launch Date: 1981-12-19. Last Launch Date: 1981-12-19. Apogee: 20,000 km (12,000 mi). Liftoff Thrust: 1,731.000 kN (389,144 lbf). Total Mass: 125,000 kg (275,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 29.20 m (95.80 ft).
Atlas E/SGS-2. Atlas E + 1 x Star 48 + 1 x Star 48 upper stages.
Launches: 4. First Launch Date: 1983-07-14. Last Launch Date: 1985-10-09. Apogee: 20,000 km (12,000 mi). Liftoff Thrust: 1,731.000 kN (389,144 lbf). Total Mass: 125,000 kg (275,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 32.10 m (105.30 ft).
Atlas E/OIS. Atlas E + 1 x OIS upper stage.
Launches: 1. First Launch Date: 1985-03-13. Last Launch Date: 1985-03-13. Apogee: 800 km (490 mi). Liftoff Thrust: 1,731.000 kN (389,144 lbf). Total Mass: 120,000 kg (260,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 28.70 m (94.10 ft).
Atlas E Altair. Atlas E + 1 x Star 20 upper stage.
Launches: 1. First Launch Date: 1990-04-11. Last Launch Date: 1990-04-11. Apogee: 1,000 km (600 mi). Liftoff Thrust: 1,731.000 kN (389,144 lbf). Total Mass: 125,000 kg (275,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 27.30 m (89.50 ft).
Atlas F.
Final operational version of Atlas ICBM. Differed in guidance systems. Deployed as missiles from 1961 to 1966. After retirement, the ICBM's were refurbished and used for over thirty years as space launch vehicles. Historical Essay © Andreas Parsch Because even the dispersed storage and semi-buried coffins of the Atlas E offered insufficient protection, the USAF decided already in 1959 to deploy Atlas missiles in underground silos, just like the HGM-25A Titan I. This resulted in the SM-65F Atlas F missile, which was essentially an SM-65E with a modified fueling system to accomodate the new silo launcher. The first silo-stored Atlas F squadron became operational in November 1962. Because the SM-65F could be fueled while still in the silo, launch survivability was much improved. After fueling, it took only two minutes to raise and launch the missile. In a crisis, it was even possible to store the SM-65F fully fueled in the silo for some length of time, which lead to a reaction time of only five minutes. However, fueling in the silo was even more dangerous than in the open, and four Atlas Fs violently exploded during this operation, destroying their silos. In June 1963, the existing Atlas missiles were redesignated in the xGM-16 series as follows:
There are also sources which claim that the SM-65Ds based on unprotected pads at Vandenberg AFB were redesignated as PGM-16D. While this would be logical, the PGM-16D designation was apparently never officially allocated. Also, reports claiming that XPGM-16A, XPGM-16B, and XPGM-16C were the new designations for XSM-65A, XSM-65B, and XSM-65C, respectively, are in error, because all three development models had long been expended by 1963. While the 1963 redesignations did include some "paper" designations of retired or cancelled missiles, this was not true for the Atlas series. After the LGM-30 Minuteman had become operational in early 1963, the Atlas became rapidly obsolete. By October 1964, all Atlas D missiles had been phased out, followed by the Atlas E/F in April 1965. About 350 Atlas ICBMs of all versions were built, with a peak deployment level of 129 (30 D, 27 E, 72 F). The Atlas was used as a space launch vehicle since the very beginning of the program, and Atlas developments are still used in this role in the 21st century. Converted ICBMs and early purpose-built space launchers, usually with additional upper stages, were used by the USAF under the basic SLV-3 designator. In 1990, the Atlas E, Atlas II and Atlas IIA/AS vehicles received the official military designations SB-1A, SB-2A and SB-2B, respectively. Current prime contractor for all Atlas rockets is Lockheed-Martin. SpecificationsNote: Data given by several sources show slight variations. Figures given below may therefore be inaccurate! Data for CGM-16D/E and HGM-16F:
[1] James N. Gibson: "Nuclear Weapons of the United States", Schiffer Publishing Ltd, 1996 The vehicles converted for space launch use and launched from Vandenberg AFB used a radio guidance system that was based on a modification of the General Electric Radio Tracking System (GERTS), originally employed on the Atlas D. In fact, the GERTS guidance used for space launch employed one of the original radar stations used for the Atlas D and even used some actual Atlas D components in its Pulse Beacon Decoder, the vehicle's X-band radio transponder. Newer solid state computers were used to run the guidance software and were interfaced with the radar; eventually they were made redundant, although with a human operator charged with detecting failure. The large Bosch-Arma pod on the side of the Atlas E and F space boosters launched from Vandenberg AFB from the mid-70's to the mid-90's was in fact empty. It was not removed and replaced with a more streamlined fairing since that would have cost money and gained no significant performance. So, the Atlas E and F space boosters used Atlas E and F ICBM airframes and engines with the tanks modified with a new payload interface section, a mixture of Atlas E and F components (selected based on which designs were most suitable for the space launch mission) and a modified Atlas D radio guidance system. GERTS was a complex, glitch-prone system, its only saving graces being that it was both the cheapest guidance system around and the most reliable, operating for almost 30 years without one flight failure and at a per-flight cost an order of magnitude below that of an inertial guidance system. Prior to Apollo-Saturn, all U.S. manned orbital flights used GERTS, both on the Mercury-Atlas D and the Gemini-Titan II missions. The proper way to refer to the space booster Atlas E's and F's was "Atlas E/F Space Booster," because of the mix of configuration features. Of course, individually the boosters were referred to by their "Tail Numbers" such as 19F, 76E, 68E, etc. The total launched cost of an Atlas E/F space booster was about $15M - or less than 1/3 the cost of a Titan II space booster, and less than 1/20th what was finally admitted as the cost of a single Space Shuttle mission. About 35 unmodified Atlas E/F missiles in storage at Norton AFB were scrapped in the early 1970's. The Space Shuttle was coming and it was assumed that they were not needed. The cost of maintaining them in storage was "horrendous" - about $2000 each per year. At least a half billion dollars worth of perfectly usable, incredibly cheap space boosters (equivalent to a couple of billon dollars in replacement costs) were run over with a bulldozer in order to save perhaps one million dollars in storage costs overtwenty years . The Air Force officer who recommended this travesty of planning received a medal for his farsightedness. Launches: 70. Failures: 17. Success Rate: 75.71%. First Launch Date: 1961-08-09. Last Launch Date: 1981-06-23. LEO Payload: 820 kg (1,800 lb). to: 185 km Orbit. at: 90.00 degrees. Associated Spacecraft: Calsphere, Cannonball, GPS Block 1, Gridsphere, LCS, Musketball, Mylar, NOSS, NOSS-Subsat, NTS, Orbiscal, OV1, OV5, P 72, RADCAT, Radsat, Rigidsphere, RM, Seasat, Solwind, Tiros N, Boost Glide Re-entry Vehicle. Liftoff Thrust: 1,713.800 kN (385,278 lbf). Total Mass: 121,980 kg (268,910 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 24.00 m (78.00 ft). Launch Price $: 50.000 million. in: 1994 price dollars. Flyaway Unit Cost $: 11.000 million. in: 1985 unit dollars.
HGM-16F. Intercontinental ballistic missile. IOC: 1960. Department of Defence Designation: CGM-16F. Popular Name: Atlas F. Alternate Designation: SM-65F. ICBM version. Also CGM-16F
Total Mass: 120,000 kg (260,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 25.15 m (82.51 ft). Span: 4.88 m (16.01 ft). Standard warhead mass: 2,500 kg (5,500 lb). Maximum range: 12,100 km (7,500 mi). Number Standard Warheads: 1. Standard RV: Mk. 4. Standard warhead: W38. Standard warhead yield: 3,750 KT. Standard warhead CEP: 3.23 km (2.00 mi). Boost Propulsion: Liquid rocket, Lox/Kerosene. Guidance: Inertial. Maximum speed: 29,030 kph (18,030 mph). Ceiling: 1,287,800 m (4,225,000 ft). Total Number Built: 381. Total Development Built: 18. Total Production Built: 343.
Atlas F/Trident. Atlas F + 1 x Trident upper stage.
Launches: 17. Failures: 3. First Launch Date: 1967-06-09. Last Launch Date: 1971-06-29. Apogee: 1,500 km (900 mi). Liftoff Thrust: 1,731.000 kN (389,144 lbf). Total Mass: 130,000 kg (280,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 25.00 m (82.00 ft).
Atlas F/PTS. Atlas F + 1 x Star 37E upper stage.
Launches: 1. First Launch Date: 1974-07-14. Last Launch Date: 1974-07-14. LEO Payload: 295 kg (650 lb). Payload: 295 kg (650 lb). to a: geosynchronous transfer orbit trajectory. Liftoff Thrust: 1,731.000 kN (389,144 lbf). Total Mass: 125,000 kg (275,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 29.20 m (95.80 ft).
Atlas F/MSD. Atlas F + 1 x MSD upper stage.
Launches: 3. First Launch Date: 1976-04-30. Last Launch Date: 1980-03-03. Apogee: 1,100 km (600 mi). Liftoff Thrust: 1,731.000 kN (389,144 lbf). Total Mass: 122,000 kg (268,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 27.30 m (89.50 ft).
Atlas F/SVS. Atlas F + 1 x Star 37E + 1 x Star 37E upper stages.
Launches: 6. First Launch Date: 1978-02-22. Last Launch Date: 1980-04-26. Apogee: 20,000 km (12,000 mi). Liftoff Thrust: 1,731.000 kN (389,144 lbf). Total Mass: 125,000 kg (275,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 29.20 m (95.80 ft).
Atlas F/OIS. Atlas F + 1 x OIS upper stage.
Launches: 1. First Launch Date: 1979-02-24. Last Launch Date: 1979-02-24. Apogee: 550 km (340 mi). Liftoff Thrust: 1,731.000 kN (389,144 lbf). Total Mass: 120,000 kg (260,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 32.10 m (105.30 ft).
Atlas C Able. Version with Atlas C first stage, Able AJ10-101A second stage, Altair solid third stage.
Launches: 1. Failures: 1. First Launch Date: 1959-09-24. Last Launch Date: 1959-09-24. Apogee: 400,000 km (240,000 mi). Liftoff Thrust: 1,615.000 kN (363,066 lbf). Total Mass: 120,000 kg (260,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 28.00 m (91.00 ft).
Atlas Able.
Atlas with upper stage based on Vanguard second stage. Six additional Able stages were delivered in parallel with the first production contract for the Thor-Able, and these were modified for use on Atlas, but this was not a good match, and only five were flown. There were problems with the main missile structure while passing through the regime of maximum dynamic pressure, and damage to the second stage during separation. Launches: 4. Failures: 4. First Launch Date: 1959-11-26. Last Launch Date: 1960-12-15. Payload: 170 kg (370 lb). to a: translunar trajectory. Associated Spacecraft: Pioneer P 3. Liftoff Thrust: 1,587.200 kN (356,817 lbf). Total Mass: 120,051 kg (264,667 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 35.00 m (114.00 ft). Flyaway Unit Cost $: 18.810 million. in: 1985 unit dollars.
Atlas D Able. Version with Atlas D first stage, Able AJ10-101A second stage, Altair solid third stage.
Atlas SLV-3.
Standardized Atlas booster with no or small solid upper stage.
Launches: 4. First Launch Date: 1966-06-01. Last Launch Date: 1967-04-20. LEO Payload: 800 kg (1,760 lb). to: 300 km Orbit. at: 28.00 degrees. Apogee: 1,500 km (900 mi). Associated Spacecraft: Atlas Target Docking Adapter. Liftoff Thrust: 1,650.000 kN (370,930 lbf). Total Mass: 120,000 kg (260,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 21.00 m (68.00 ft).
Atlas Agena A.
Atlas D + 1 x Agena A upper stage. Agena originally called 'Hustler', based on engine for cancelled rocket-propelled nuclear warhead pod for B-58 Hustler bomber.
Launches: 4. Failures: 2. First Launch Date: 1960-02-26. Last Launch Date: 1961-01-31. Payload: 800 kg (1,760 lb). to a: Geosynchronous transfer trajectory. Apogee: 600 km (370 mi). Associated Spacecraft: Midas, Samos, Aeronutronics Project 7969, Lockheed Project 7969, Convair Project 7969. Liftoff Thrust: 1,587.190 kN (356,815 lbf). Total Mass: 123,990 kg (273,350 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 30.00 m (98.00 ft).
Atlas Agena B.
Atlas D with improved, enlarged Agena upper stage.
Launches: 28. Failures: 8. First Launch Date: 1961-07-12. Last Launch Date: 1965-03-21. Payload: 850 kg (1,870 lb). to a: Geosynchronous transfer trajectory. Apogee: 400,000 km (240,000 mi). Associated Spacecraft: Dash, ERS, Mariner 1-2, Midas, OGO, Ranger 1-2, Ranger 3-4-5, Ranger 6-7-8-9, Samos, TRS, WestFord Needles, Mariner R. Liftoff Thrust: 1,721.100 kN (386,919 lbf). Total Mass: 127,367 kg (280,796 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 33.00 m (108.00 ft).
SLV-3 Agena B. Department of Defence Designation: SLV-3. Standardized Atlas booster with Agena B upper stage.
Launches: 1. First Launch Date: 1966-06-07. Last Launch Date: 1966-06-07. Payload: 600 kg (1,320 lb). to a: 19,500 x 103,000 km orbit at 77.5 deg inclination trajectory. Apogee: 400,000 km (240,000 mi). Associated Spacecraft: OGO. Liftoff Thrust: 1,629.000 kN (366,213 lbf). Total Mass: 140,000 kg (300,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 32.10 m (105.30 ft).
Atlas Agena D.
Atlas D with further improved and lightened Agena upper stage.
Launches: 15. Failures: 1. First Launch Date: 1963-07-12. Last Launch Date: 1965-07-20. LEO Payload: 800 kg (1,760 lb). Payload: 1,000 kg (2,200 lb). to a: Geosynchronous transfer trajectory. Apogee: 400,000 km (240,000 mi). Associated Spacecraft: ERS, KH-7, Mariner 3-4, SSF, TRS, Vela, SAINT. Liftoff Thrust: 1,939.290 kN (435,970 lbf). Total Mass: 153,365 kg (338,111 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 35.00 m (114.00 ft).
SLV-3 Agena D.
Standardized Atlas booster with Agena D upper stage.
Launches: 48. Failures: 5. Success Rate: 89.58%. First Launch Date: 1964-08-14. Last Launch Date: 1967-11-05. LEO Payload: 2,000 kg (4,400 lb). to: 180 km Orbit. at: 108.00 degrees. Payload: 850 kg (1,870 lb). to a: geosynchronous transfer orbit trajectory. Apogee: 400,000 km (240,000 mi). Associated Spacecraft: ATS-1, ATS-2, ATS-3, Bluebell, ERS, Gemini Agena Target Vehicle, KH-7, Lunar Orbiter, Mariner 5, Midas, OAO, SECOR, Snapshot, SSF. Liftoff Thrust: 1,629.000 kN (366,213 lbf). Total Mass: 140,000 kg (300,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 32.10 m (105.30 ft).
SLV-3A Agena D.
Uprated Atlas booster with Agena D upper stage.
Launches: 12. Failures: 1. First Launch Date: 1968-03-04. Last Launch Date: 1978-04-07. LEO Payload: 1,000 kg (2,200 lb). Payload: 700 kg (1,540 lb). to a: Geosynchronous orbit trajectory. Associated Spacecraft: Canyon, OGO, Rhyolite. Liftoff Thrust: 1,700.000 kN (382,100 lbf). Total Mass: 155,000 kg (341,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 36.00 m (118.00 ft).
Atlas F/Agena D. Atlas F + 1 x Agena D upper stage.
Launches: 1. First Launch Date: 1978-06-27. Last Launch Date: 1978-06-27. Apogee: 1,000 km (600 mi). Liftoff Thrust: 1,731.000 kN (389,144 lbf). Total Mass: 130,000 kg (280,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 34.60 m (113.50 ft).
Atlas Vega.
Atlas-Vega consisted of an Atlas booster with a storable propellant upper stage. It was planned by NASA at its inception for deep space and planetary missions before the Atlas Centaur was available. Work had already begun when NASA discovered that the CIA and the US Air Force had an essentially identical launch vehicle (Atlas-Hustler, later called Atlas-Agena) in development for the highly classified Corona reconnaisance satellite program. Atlas-Vega was accordingly cancelled.
First test version of Atlas with Centaur upper stage.
Launches: 5. Failures: 3. First Launch Date: 1962-05-08. Last Launch Date: 1965-03-02. LEO Payload: 1,700 kg (3,700 lb). Payload: 1,800 kg (3,900 lb). to a: Geosynchronous transfer trajectory. Associated Spacecraft: Surveyor. Liftoff Thrust: 1,704.820 kN (383,259 lbf). Total Mass: 136,124 kg (300,102 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 33.00 m (108.00 ft).
Atlas Centaur LV-3C. Version with basic Centaur upper stage.
Payload: 1,700 kg (3,700 lb). to a: geosynchronous transfer orbit trajectory.
Atlas Centaur D. Version with Centaur D upper stage.
Launches: 7. Failures: 1. First Launch Date: 1965-08-11. Last Launch Date: 1967-07-14. LEO Payload: 1,700 kg (3,700 lb). Payload: 1,700 kg (3,700 lb). to a: geosynchronous transfer orbit trajectory. Total Mass: 136,100 kg (300,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 33.00 m (108.00 ft).
SLV-3C Centaur.
Standardised SLV-3C Atlas booster with Centaur D upper stage.
Launches: 17. Failures: 3. First Launch Date: 1967-09-08. Last Launch Date: 1972-08-21. LEO Payload: 1,800 kg (3,900 lb). Payload: 1,800 kg (3,900 lb). to a: Geosynchronous transfer trajectory. Apogee: 400,000 km (240,000 mi). Associated Spacecraft: ATS-4, ATS-5, Intelsat 4, Mariner 6-7, Mariner 8-9, OAO, Pioneer 10-11, Surveyor, Surveyor Lunar Rover, Surveyor Orbiter, Surveyor Block II. Liftoff Thrust: 1,939.290 kN (435,970 lbf). Total Mass: 148,404 kg (327,174 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 38.00 m (124.00 ft).
SLV-3D Centaur.
Fully developed version of Atlas with Centaur D-1A upper stage.
Launches: 32. Failures: 3. Success Rate: 90.63%. First Launch Date: 1973-04-06. Last Launch Date: 1983-05-19. LEO Payload: 1,900 kg (4,100 lb). Payload: 1,900 kg (4,100 lb). to a: Geosynchronous transfer trajectory. Apogee: 400,000 km (240,000 mi). Associated Spacecraft: Fltsatcom, HEAO, Intelsat 4, Intelsat 4A, Intelsat 5, Mariner 10, Pioneer 10-11, Pioneer 12, Pioneer 13. Liftoff Thrust: 1,939.290 kN (435,970 lbf). Total Mass: 148,404 kg (327,174 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 38.00 m (124.00 ft).
Atlas G Centaur.
Atlas-Centaur launch vehicles using stretched, uprated Atlas core.
Launches: 7. Failures: 2. First Launch Date: 1984-06-09. Last Launch Date: 1989-09-25. LEO Payload: 3,630 kg (8,000 lb). to: 185 km Orbit. Payload: 2,255 kg (4,971 lb). to a: Geosynchronous transfer trajectory. Apogee: 40,000 km (24,000 mi). Associated Spacecraft: Fltsatcom, Intelsat 5, Intelsat 5A. Liftoff Thrust: 1,939.300 kN (435,972 lbf). Total Mass: 166,140 kg (366,270 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 38.00 m (124.00 ft). Launch Price $: 75.000 million. in: 1994 price dollars. Flyaway Unit Cost $: 70.300 million. in: 1985 unit dollars.
Atlas H.
Atlas H used the Atlas first stage developed for the Atlas G vehicle. It was flown without the Centaur upper stage. The Atlas H vehicles launched from Vandenberg AFB used a radio guidance system that was based on a modification of the General Electric Radio Tracking System (GERTS), originally employed on the Atlas D. In fact, the GERTS guidance used for space launch employed one of the original radar stations used for the Atlas D and even used some actual Atlas D components in its Pulse Beacon Decoder, the vehicle's X-band radio transponder. Newer solid state computers were used to run the guidance software and were interfaced with the radar; eventually they were made redundant, although with a human operator charged with detecting failure. GERTS was a complex, glitch-prone system, its only saving graces being that it was both the cheapest guidance system around and the most reliable, operating for almost 30 years without one flight failure and at a per-flight cost an order of magnitude below that of an inertial guidance system. Launches: 5. First Launch Date: 1983-02-09. Last Launch Date: 1987-05-15. LEO Payload: 3,630 kg (8,000 lb). to: 185 km Orbit. Payload: 2,255 kg (4,971 lb). to a: Geosynchronous transfer trajectory. Apogee: 1,100 km (600 mi). Associated Spacecraft: LIPS, NOSS, NOSS-Subsat. Liftoff Thrust: 1,939.300 kN (435,972 lbf). Total Mass: 150,540 kg (331,880 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 27.00 m (88.00 ft). Launch Price $: 50.000 million. in: 1994 price dollars. Flyaway Unit Cost $: 50.000 million. in: 1985 unit dollars.
Atlas I.
The Atlas I launch vehicle was derived from the Atlas G, and included the same basic vehicle components (Atlas booster and Centaur upper stage). Significant improvements in the guidance and control system were made with an emphasis on replacing analog flight control components with digital units interconnected with a digital data bus. The first flight of an Atlas I was on July 25, 1990. Originally, 18 Atlas I vehicles were planned for manufacture. With the award by the USAF to General Dynamics of the MLV-II vehicle development contract for the Atlas II launch vehicle, the Atlas program rescoped Atlas I production commitments to 11 vehicles and converted the remaining commitments to the Atlas II/IIA/IIAS production effort.
Launches: 11. Failures: 3. First Launch Date: 1990-07-25. Last Launch Date: 1997-04-25. LEO Payload: 3,630 kg (8,000 lb). to: 185 km Orbit. Payload: 2,255 kg (4,971 lb). to a: Geosynchronous transfer trajectory. Apogee: 400,000 km (240,000 mi). Associated Spacecraft: AS 3000, CRRES, GOES-Next, HS 376, HS 601, SAX. Liftoff Thrust: 1,939.300 kN (435,972 lbf). Total Mass: 164,300 kg (362,200 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 43.90 m (144.00 ft). Development Cost $: 400.000 million. in: 1987 average dollars. Launch Price $: 75.000 million. in: 1994 price dollars. Flyaway Unit Cost $: 70.300 million. in: 1985 unit dollars. Cost comments: 1989, 61 sets of motors cost $ 650 mn.
Atlas II.
The Atlas II booster was 2.7-meters longer than an Atlas I and included uprated Rocketdyne MA-5A engines. The Atlas I vernier engines were replaced with a hydrazine roll control system. The Centaur stage was stretched 0.9-meters compared to the Centaur I stage. Fixed foam insulation replaced Atlas I's jettisonable insulation panels. The original Atlas II model was developed to support the United States Air Force Medium Launch Vehicle II program. Its Centaur used RL10A-3-3A engines operating at an increased mixture ratio. The first Atlas II flew on 7 December 1991, successfully delivering AC-102/Eutelsat II F3 to orbit.
Launches: 10. First Launch Date: 1991-12-07. Last Launch Date: 1998-03-16. LEO Payload: 6,580 kg (14,500 lb). to: 185 km Orbit. at: 28.50 degrees. Payload: 2,810 kg (6,190 lb). to a: Geosynchronous transfer trajectory. Apogee: 40,000 km (24,000 mi). Associated Spacecraft: DSCS III, HS 601, Spacebus 100. Liftoff Thrust: 2,110.600 kN (474,482 lbf). Total Mass: 187,600 kg (413,500 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 47.50 m (155.80 ft). Launch Price $: 85.000 million. in: 1994 price dollars.
Atlas IIA.
The Atlas II booster was 2.7-meters longer than an Atlas I and included uprated Rocketdyne MA-5A engines. The Atlas I vernier engines were replaced with a hydrazine roll control system. The Centaur stage was stretched 0.9-meters compared to the Centaur I stage. Fixed foam insulation replaced Atlas I's jettisonable insulation panels. Atlas IIA was a commercial derivative of the Atlas II developed for the US Air Force. Higher performance RL10A-4 (or RL10A-4-1) engines replaced Atlas II's RL10A-3-3A engines. RL10A-4 and RL10A-4-1 engines were offered with or without extendable nozzles (Extendible nozzles increased the engines specific impulse, providing additional performance if required). AC-105 / INTELSAT-K, launched 9 June 1992, inaugurated Atlas IIA series flights.
Launches: 23. First Launch Date: 1992-06-10. Last Launch Date: 2002-12-05. LEO Payload: 7,280 kg (16,040 lb). to: 185 km Orbit. at: 28.50 degrees. Payload: 3,039 kg (6,699 lb). to a: Geosynchronous transfer trajectory. Apogee: 100,000 km (60,000 mi). Associated Spacecraft: AS 2100, AS 4000, AS 5000, CAPRICORN, DSCS III, Eurostar 2000, Falcon Gold, FS-1300, HS 601. Liftoff Thrust: 2,110.600 kN (474,482 lbf). Total Mass: 187,700 kg (413,800 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 47.50 m (155.80 ft). Launch Price $: 90.000 million. in: 1994 price dollars.
Atlas IIAS.
The Atlas II booster was 2.7-meters longer than the Atlas I and included uprated Rocketdyne MA-5A engines. The Atlas I vernier engines were replaced with a hydrazine roll control system. The Centaur stage was stretched 0.9-meters compared to the Centaur I stage. Fixed foam insulation replaced Atlas I's jettisonable insulation panels. Higher performance RL10A-4 or RL10A-4-1 engines replaced Atlas II's RL10A-3-3A. The Atlas IIAS model added four Thiokol Castor IVA solid rocket boosters (SRBs) to the core Atlas stage to augment thrust for the first two minutes of flight. The RL10A-4 and RL10A-4-1 engines were offered with or without extendable nozzles (which increased engine specific impulse, providing additional performance if required). The Atlas IIAS' first SRB pair was ignited at liftoff and burned for 54 seconds. The second pair was ignited in flight when vehicle loading constraints were satisfied. Both pairs were jettisoned shortly after their respective burnouts. The first Atlas IIAS successfully launched AC-108 / Telstar 401 on 15 December 1993. Launches: 30. Success Rate: 100.00%. First Launch Date: 1993-12-16. Last Launch Date: 2004-08-31. LEO Payload: 8,610 kg (18,980 lb). to: 185 km Orbit. at: 28.50 degrees. Payload: 3,630 kg (8,000 lb). to a: Geosynchronous transfer trajectory. Apogee: 400,000 km (240,000 mi). Associated Spacecraft: AS 2100, AS 7000, FS-1300, HS 601, NOSS-3, SDS-2, SOHO, Spacebus 3000, Terra. Liftoff Thrust: 3,546.300 kN (797,240 lbf). Total Mass: 234,000 kg (515,000 lb). Core Diameter: 4.90 m (16.00 ft). Total Length: 47.50 m (155.80 ft). Launch Price $: 105.000 million. in: 1994 price dollars.
Atlas Chronology 1945 October 31 - US Strategic Missile Programs Begin Request For Proposals were issued to 17 contractors by the US Army Air Force for studies of a 10-year R&D; program of four missile types. The missiles were to be air-, rail-, road-, or ship- transportable, and fit in three range categories: 280 to 800 km; 800 to 2400 km; and 2400 to 8000 km. Minimum speed was 970 kph, requiring turbojet, ramjet, or rocket propulsion. 1946 January 11 - Strategic Missile Proposals Bids were received in response to the USAAF request for proposal of the previous October. Vultee submitted proposals for two types (glide and ballistic) of 8000-km range missiles. North American proposed a three-year development program for a supersonic 800-km range missile, culminating in a production run of 50 missiles. March to April 1946 - Army Air Force awards nine one-year missile study contracts. The MX-770 contract for an 800-km range boost-glide missile derived from the German A9 concept went to North American; this would evolve into the Navaho triple-sonic intercontinental cruise missile. Martin received a contract for development of the MX-771, a subsonic ground-launched cruise missile with an 800-km range; it would evolve into the Matador and Mace missiles. Curtiss-Wright and Republic received contracts for the MX-772 and MX-773 surface-to-surface missiles; they never advanced beyond the initial study stage. Convair received the contract for long-range rocket-powered missiles; this evolved into the Atlas ICBM. Northrtop received the MX-775 contract for a 5000-km range cruise missile; this eventually flew as the Snark. Bell receives a contract to develop the MX-776, a 160-km range rocket-powered supersonic missile to be launched from B-29 bombers. This would evolve into the Rascal. McDonnell received a study contract for the MX-777 air-to-surface missile; this evolved into the anti-submarine 'hydrobomb' concept and was eventually transferred to the Navy. Goodyear received contracts for the MX-778 and MX-779 air-to-surface missiles; these never advanced beyond the preliminary study stage. Concurrently, the USAAF had the GARPA surface-to-air missile project underway, which would evolve into Bomarc; the USA Army the Corporal and Hermes (later Redstone) surface-to-surface missiles and the Nike and Hermes A1 surface-to-air missiles; and the Navy a range of missile technology development projects (Regulus, Bat, Kingfisher, Little Joe, Lark, Bumblebee, Gorgon, Dove). 1946 April 2 - MX-774 strategic missile study contract awarded Convair received contract W33-038-AC-14168 for a $1.4 million, one-year study of two missile designs. 1946 December - MX-774 Azusa tracking Study report submitted to Air Force on proposed Azusa tracking/guidance system. MX-774 funding cut back. Early 1947 - MX-774 Azusa tracking tests Tracking tests started with experimental Azusa equipment 1947 July 1 - MX-774 cancelled. Contract with Convair for the MX-774 "Upper Air Test Vehicle," predecessor of the Atlas ICBM, was cancelled by the AAF. However the service approves Convair use of unexpended MX-774 funds to launch the MX-774 test vehicles already built. The decision made to move Vultee operations to San Diego. 1947 September 15 - US Army Air Corps assigned control of surface-to-surface strategic missiles 1947 September 18 - U.S. Army Air Corps becomes U.S. Air Force The Air Force was now a separate service from the US Army. The agreement was made that the Air Force would only handle missiles with ranges over 1600 km. So the range requirement for the MX-770 (later the Navaho) was increased to 1600 km, while carrying a 1350-kg payload with an 800 m CEP, and it became an Air Force missile. The 800-km MX-771 (later Matador) became an Army missile. The MX-775 Snark already had an intercontinental range requirement, and became an Air Force missile. 1947 October - First complete MX-774 moved to Pt. Loma for test 1947 November 20 - First static firing of MX-774 Unsuccessful, small fire. 1948 January - Second MX-774 static firing Successful, at Point Loma. 1948 May 6 - MX-774 static firing tests at Pt Loma completed. 1948 June - First MX-774 arrives at White Sands Proving Ground 1948 July 14 - 01:05 GMT - White Sands LC33. FAILURE: Cutoff after half of the propellants were used. MX-774 Flight 1 Agency: USAF. Apogee: 1.00 km (0.60 mi). First Convair MX-774 (RTV-A-2) test rocket was successfully launched, first demonstrating use of gimballed engines and design features later incorporated in the Atlas ICBM. This was the first of three Convair-sponsored test flights. 1948 August - Spaatz calls for American ICBM. General Spaatz (Tooey Spaatz) calls for US development of missile with 10,200 km range 1948 September 27 - White Sands LC33. FAILURE: Cutoff at 16 km altitude. MX-774 Flight 2 Agency: USAF. Apogee: 47 km (29 mi). Second Corvair MX-774 test rocket fired. Shut down at 15 km; reached 65 km before malfunction of unknown origin caused self-destruction. 1948 December 2 - 22:01 GMT - White Sands LC33. FAILURE: Vibration closed valve early. MX-774 Flight 3 Agency: USAF. Apogee: 50 km (31 mi). Third (last) MX-774 launched, WSPG; shut down at 51 seconds attaining an altitude of 48 km. Self-destructed at high altitude. 1949 February - All MX-774 work shut off by Air Force During 1949 - MX-774 unexpended funds run out in 1950. Convair allocated R&D; funds to ICBM studies and marketing, running into 1950 1950 October 1 - RAND studies ICBM's. Rand Corp. completed missile feasibility studies begun in 1949, which confirmed the military practicability of long-range rocket weapons. 1951 - Atlas tracking system. Azusa tracking system reaching advanced stage of development 1951 January 16 - Project MX-1593 (Project Atlas) begins. Air Force established Project MX-1593 (Project Atlas), study phase for an intercontinental missile. Requirements included 8000-pound warhead, 5000 nautical mile range, to hit within 1500 ft. CEP. $1.5 million study contract was awarded to Consolidated-Vultee Aircraft on January 23. This was the follow-on to Project MX-774 terminated in 1947. Several test vehicles had been fired using residual funds in 1948 and 1949, after which the Convair MX-774 (Atlas) missile project had been shelved. The company, however, had continued to fund a research program. 1951 August - Atlas XB-65 configuration. MX-1593 named "Project Atlas" as XB-65; 120 feet long, 12-foot diameter, 7 engines, 8000-pound warhead, CEP 1 nautical mile 1951 August - Atlas to be accelerated. AF Gen. John Sessums proposes Atlas acceleration 1951 September 1 - Atlas project to concentrate on ballistic missile. MX-1593 glide missile cancelled. USAF directed all work in Project MX-1593 (Atlas) be for development of a rocket-powered ballistic missile. Late 1951/early 1952 - Reports of large Russian rocket engines During 1952 - Reduced thermonuclear warhead size will allow American ICBM's to be smaller. Atlas 3000-pound warhead anticipated, 1500-foot CEP 1952 March - Gen. Joseph McNarney joins Convair 1953 January - Millikan Committee Report Millikan Committee report issued, saying Atlas could be operational by 1963 Spring 1953 - Atlas size reduced. Atlas 12-foot diameter, 110 feet long, 440,000 pounds, 3000-pound warhead, 5500 nautical mile range, 1500-foot CEP 1953 June - Defense Secretary Wilson institutes reviews of guided missiles' status 1953 July - J.R. Dempsey joins Convair 1953 September - Von Neumann's "Teapot Committee" established 1953 October - Teapot Committee's first output ICBM could use smaller warhead 1953 December 3 - Convair leases test facility. A five-year Pt. Loma lease was approved. 1954 February 10 - Teapot Report The ICBM design feasible, as was acceleration of the program; Rand Corporation Report: Atlas ICBM could be operational by 1960-62 and should have crash project status 1954 March 1 - Atlas propulsion system work begins. Work on MA-2 propulsion system for Atlas by Rocketdyne was begun, drawing upon the experience in developing the regeneratively cooled chamber developed for the Navaho. 1954 March - Operation Castle thermonuclear tests confirm feasibility of small warheads 1954 March - First Atlas hardware. 12-foot diameter Atlas tank completed by Solar 1954 March 8 - First public indication that Project Atlas exists May 1954 - Atlas receives high priority. Highest AF development priority (and accelerated schedule) assigned Atlas 1954 May 17 - Ramo-Woolridge to manage Atlas. Ramo-Wooldridge given letter contract as Technical Director and Systems Integrator for Atlas program 1954 June 21 - Schriever named head of Atlas program. Brigadier-General Bernard A. Schriever, ARDC, assigned to head Atlas program 1954 July 1 - Western Development Division (WDD) established by USAF Western Development Division (WDD) established by AF under ARDC to manage Atlas development; Rocketdyne put on contract for propulsion system 1954 July 1 - Rocketdyne put on contract for Atlas engines. Western Development Division (WDD) established by AF under ARDC to manage Atlas development; 1954 July - Scientific Advisory Board recommendations rejected. Scientific Advisory Board recommendations differing from Teapot Committee rejected 1954 August - First USAF WDD Facility Inglewood "Schoolhouse" WDD facility established Late 1954 - Atlas further reduced in size Atlas size reduced from 12-foot to 10-foot diameter, with 3 large engines 1954 December - Atlas full-scale development First major Atlas WS107A1 development and construction contract awarded Convair; CEP 2-3 NM, IOC by 1960-62 1954 December 16 - Atlas publicly announced. USAF announced Atlas ICBM under construction by Convair. Early 1955 - Atlas fabrication begins 1955 March 6 - Atlas given top development priority. USAF Chief of Staff, Nathan F. Twining, reported that ICBM's were receiving priority in the AF program because of known Soviet progress. Navaho, Snark, and Atlas programs accelerated. 1955 April - New WDD complex New WDD complex activated on Arbor Vitae Blvd. in Los Angeles Late 1955 - Atlas program assigned top priority in the nation Atlas program assigned top priority in the nation (was highest priority only for AF) 1956 May - Atlas production plant at Kearney Mesa New Astronautics plant announced—$20 million funding by General Dynamics, with the Air Force to match, for tooling and special equipment 1956 May 3 - Convair announced as the prime contractorfor the Atlas The Air Force disclosed that a $41 million guided missile production facility would be built at Sorrento, California, for the Atlas launch vehicle. Convair was announced as the prime contractor. 1956 May 28 - RAND lunar instrument carrier based on the Atlas booster The RAND Corporation issued the first of a series of reports on the feasibility of a lunar instrument carrier, based on the use of an Atlas booster. A braking rocket would decelerate the vehicle before lunar landing, and a penetration spike on the forward point of the instrument package would help to absorb the 500 feet per second impact velocity. Instruments would then transmit information on the lunar surface to earth. 1956 June 21 - Edwards -. Atlas ICBM first test firing First captive Atlas first test firing. The 'battleship' missile was installed at test stand 1-4, Edwards Air Force Base. The test was a failure due to inadvertant closure of the fuel prevalve, leading to duct collapse, and a turbine overspeed cutoff. No damage was sustained and the first successful firing came the next day. Atlas, First successful captive test firing, June 22, 1956, Edwards Rocket Base, duration - 4 seconds. Successful. 1956 June 22 - Edwards -. Atlas ICBM first successful test firing First successful captive test firing of the Atlas ICBM at Edwards Air Force Base, duration - 4 seconds. 1956 June 23 - First Atlas battleship tests First system engine tests on ERB 1-4 battleship setup 1956 September - Atlas 1A Missile 1A delivered to Sycamore for captive tests 1956 November 16 - Vandenberg -. Vandenberg selected as first ICBM base. Department of Defense transferred northern portion of Camp Cooke, Calif. (now Vandenberg AFB), to the Air Force to be used as first ICBM base. The Secretary of Defense directed the United States Army to transfer 64,000 acres of Camp Cooke's 86,000 acres to the Air Force. 1956 December - Scheduled design complete (95%) for Atlas A-series missiles 1956 December - First Atlas firing, stand S-l, Sycamore 1956 December 21 - Atlas 1A destroyed in test. Missile 1A burned on second run at S-l with stand damage Spring 1957 - First flight Atlas missile, 4A, delivered, and shipped to AMR 1957 March - Atlas 4A erected on AMR LC-14 1957 June - WDD renamed Ballistic Missiles Division (BMD) 1957 June 11 - 19:37 GMT - Cape Canaveral LC14. Atlas A 4A FAILURE: Failure in the booster fuel system. Research and development test Agency: USAF. Apogee: 3.00 km (1.80 mi). First test flight of prototype WS-107A Atlas was detonated by command signal at 10,000 feet following a failure in the booster fuel system. The 23-second flight was considered a partial success. 1957 July 1 - Vandenberg -. First Atlas wing activated at Cooke AFB. Air Research and Development Command activated the 704th Strategic Missile Wing (Atlas) at Cooke AFB. 1957 August 1 - Atlas IOC delayed. Estimated operational capability date for Atlas changed from March 1959 to June 1959. 1957 September - Scheduled design complete (95%) for Atlas B-series missiles 1957 September 25 - 19:57 GMT - Cape Canaveral LC14. Atlas A 6A FAILURE: Failure in the booster fuel system. Research and development test Agency: USAF. Apogee: 4.00 km (2.40 mi). Atlas was again destroyed by command signal at three minutes into flight following a failure in the booster fuel system. The 50-second active flight was considered a partial success. 1957 December 17 - 17:39 GMT - Cape Canaveral LC14. Atlas A 12A Research and development test Agency: USAF. Apogee: 120 km (70 mi). First successful test firing of USAF Atlas ICBM, the missile landing in the target area after a flight of 600 miles. 1958 - During the year - Outpost four-man space station. Spacecraft: Outpost. In 1958, the year after Sputnik 1, Krafft Ehricke, then with General Dynamics' Convair Division, designed a four-man space station known as Outpost. Ehricke proposed that the Atlas ICBM being developed by Convair could be adapted as the station's basic structure. The Atlas, 3 m in diameter and 22.8 m long, was America's largest rocket at the time. During 1958 - NASA sketches two-crew Mercury follow-on spacecraft Spacecraft: Gemini. In 1958 H. Kurt Strass and Caldwell C. Johnson of NASA's Space Task Group at Langley Field, Virginia.sketched a spacecraft design concept for a two-man orbiting laboratory to be launched by an Atlas-Vega booster. This was one of the earliest sketches of a two-crew Mercury follow-on. The Vega stage was dropped in favour of the Agena a year later, and a similar one-crew Mercury-Agena space station was proposed by McDonnell some years later. 1958 January - Scheduled design complete (95%) for Atlas C-series missiles 1958 January 10 - 15:48 GMT - Cape Canaveral LC12. Atlas A 10A Research and development test Agency: USAF. Apogee: 120 km (70 mi). A successful limited flight was made by the fourth Atlas fired from Cape Canaveral. 1958 February 7 - 19:37 GMT - Cape Canaveral LC14. Atlas A 13A FAILURE: Failure. Research and development launch Agency: USAF. Apogee: 120 km (70 mi). 1958 February 20 - 17:46 GMT - Cape Canaveral LC12. Atlas A 11A FAILURE: Failure. Research and development launch Agency: USAF. 1958 April 5 - 17:01 GMT - Cape Canaveral LC14. Atlas A 15A FAILURE: Failure. Research and development test Agency: USAF. Apogee: 100 km (60 mi). USAF Atlas A ICBM was successfully flown from Cape Canaveral, Fla., to the impact area some 600 miles away. 1958 May 28 - Atlas production facility opens. Open house, new Astronautics facility on Kearny Mesa 1958 June 3 - 21:28 GMT - Cape Canaveral LC12. Atlas A 16A Research and development test Agency: USAF. Apogee: 120 km (70 mi). Last Atlas A flight, considered fully successful. Four of the eight flights were considered successful. 1958 July - Atlas ICBM soft pad design complete. Design of vertical initial operational capability ground support equipment 1958 July 19 - 17:36 GMT - Cape Canaveral LC11. Atlas B 3B FAILURE: Flight Control Failure. Research and development test Agency: USAF. Apogee: 10 km (6 mi). First full-powered flight of USAF Atlas B ICBM using both the sustainer and booster engines. 'Marginally successful'. 1958 August - Scheduled design complete (95%) for Atlas D-series missiles 1958 August 2 - 22:16 GMT - Cape Canaveral LC13. Atlas B 4B Research and development test Agency: USAF. Apogee: 900 km (550 mi). Second full-powered flight of USAF Atlas ICBM traveled 2,500 miles with radio-inertial guidance, fully successful. 1958 August 29 - 04:30 GMT - Cape Canaveral LC11. Atlas B 5B Research and development / AFSWC-1 test Agency: USAF. Apogee: 900 km (550 mi). 1958 September 14 - 05:24 GMT - Cape Canaveral LC14. Atlas B 8B Research and development / AFSWC-2 test Agency: USAF. Apogee: 900 km (550 mi). 1958 September 18 - 21:27 GMT - Cape Canaveral LC13. Atlas B 6B FAILURE: Failure. Research and development launch Agency: USAF. Apogee: 100 km (60 mi). 1958 October 1 - Centaur engine contract awarded. Air Force awarded contract Pratt & Whitney for Centaur vehicle with hydrogen-burning chamber based on research of Lewis Research Center between 1953 and 1957. Centaur project later transferred to NASA. 1958 October 17-18 - Negotiations for Mercury Atlas launch vehicles Langley Research Center personnel visited the Air Force Ballistic Missile Division, Inglewood, California, to open negotiations for procuring Atlas launch vehicles for the manned satellite project. 1958 November 18 - 04:00 GMT - Cape Canaveral LC11. Atlas B 9B Research and development launch Agency: USAF. Apogee: 800 km (490 mi). 1958 November 24 - Space Task Group orders first Mercury Atlas missile. The Space Task Group placed an order for one Atlas launch vehicle with the Air Force Missile Division, Inglewood, California, as part of a preliminary research program leading to manned space flight. The National Aeronautics and Space Administration Headquarters requested that the Air Force construct and launch one Atlas C launch vehicle to check the aerodynamics of the spacecraft. It was the intention to launch this missile about May 1959 in a ballistic trajectory. This was to be the launch vehicle for the Big Joe reentry test shot, but plans were later changed and an Atlas Model D launch vehicle was used instead. 1958 November 29 - 02:27 GMT - Cape Canaveral LC14. Atlas B 12B Research and development / AFSWC-3 test Agency: USAF. Apogee: 900 km (550 mi). Less than 18 months after the first flight, a USAF Atlas made its first successful full-range operational test flight in a 6,325 statute-mile flight, landed close to its target. 1958 December 8 - Nine Atlas launch vehicles required for Project Mercury The Space Task Group indicated that nine Atlas launch vehicles were required in support of the Project Mercury manned and unmanned flights and these were ordered from the Air Force Ballistic Missile Division. 1958 December 18 - 23:02 GMT - Cape Canaveral LC11. Atlas B 10B Score Mass: 70 kg (154 lb). Spacecraft: Score. Agency: DARPA. Perigee: 185 km (114 mi). Apogee: 1,484 km (922 mi). Inclination: 32.30 deg. Period: 101.50 min. Signal Communication by Orbiting Relay Equipment; first commsat; transmitted taped messages for 13 days. 1958 December 24 - 04:45 GMT - Cape Canaveral LC12. Atlas C 3C Research and development test Agency: USAF. Apogee: 900 km (550 mi). First Atlas C flight (3C), successful. 1959 January - Strategic Air Command takes over Atlas ICBM facilities. VAFB SMS 576A facilities turned over to SAC 1959 January 15 - Centaur first contract. Centaur project (Atlas upper stage) contracted for $7 million in its first year 1959 January 16 - 04:00 GMT - Cape Canaveral LC14. Atlas B 13B FAILURE: Failure. Research and development launch Agency: USAF. Apogee: 100 km (60 mi). 1959 January 27 - NASA National Space Vehicle Program After consultation and discussion with DOD, NASA formulated a national space vehicle program. The central idea of the program was that a single launch vehicle should be developed for use in each series of future space missions. The launch vehicle would thus achieve a high degree of reliability, while the guidance and payload could be varied according to purpose of the mission. Four general-purpose launch vehicles were described: Vega, Centaur, Saturn, and Nova. The Nova booster stage would be powered by a cluster of four F-1 engines, the second stage by a single F-1, and the third stage would be the size of an intercontinental ballistic missile but would use liquid hydrogen as a fuel. This launch vehicle would be the first in a series that could transport a man to the lunar surface and return him safely to earth in a direct ascent mission. Four additional stages would be required in such a mission. 1959 January 27 - 23:34 GMT - Cape Canaveral LC12. Atlas C 4C Mod II re-entry vehicle research and development mission Agency: USAF. Apogee: 990 km (610 mi). 1959 February - NASA/USAF responsibilities for the first two Mercury Atlas firings. During a meeting between personnel of the Space Task Group and the Air Force Ballistic Missile Division, the responsibilities of the two organizations were outlined for the first two Atlas firings. Space Technology Laboratories, under Air Force Ballistic Missile Division direction, would select the design trajectories according to the specifications set forth by the Space Task Group. These specifications were to match a point in the trajectory at about 450,000 feet, corresponding to a normal reentry condition for the manned spacecraft after firing of the retrorockets at an altitude of 120 nautical miles. Space Technology Laboratories would also provide impact dispersion data, data for range safety purposes, and the necessary reprograming of the guidance computers. The spacecraft for the suborbital Atlas flights would be manufactured under the deriction of the Lewis Research Center, based on Space Task Group designs. Space Task Group was developing the spacecraft instrumentation, with a contingent of personnel at the Lewis Research Center. The attitude control system was being developed by Lewis. 1959 February - Atlas ICBM coffin launcher design completed. Design of horizontal operational ground support equipment (coffin configuration) completed 1959 February 4 - 08:01 GMT - Cape Canaveral LC11. Atlas B 11B Research and development / AFSWC-4? test Agency: USAF. Apogee: 990 km (610 mi). Last Atlas B flight, fully successful 1959 February 12-13 - Atlas launch vehicles in Project Mercury. Discussions were held at Langley Field between the Space Task Group and the Air Force Ballistic Missile Division covering aspects of the use of Atlas launch vehicles in Project Mercury. Specifically discussed were technical details of the first Atlas test flight (Big Joe), the abort sensing capability for later flights, and overall program objectives. 1959 February 15 - NASA Booster Development Plan for 60's NASA issues plan for development in next decade of Vega (later cancelled as too similar to Agena), Centaur, Saturn, and Nova launch vehicles. Juno V renamed Saturn I. 1959 February 20 - 05:38 GMT - Cape Canaveral LC12. Atlas C 5C FAILURE: Failure. Research and development launch Agency: USAF. Apogee: 100 km (60 mi). 1959 March - Atlas C 6C Atlas 6C blows up. Missile 6C blows up, destroying ERB Stand 1-A. 1959 March 19 - 00:59 GMT - Cape Canaveral LC12. Atlas C 7C FAILURE: Failure. RVX-2 re-entry vehicle research and development mission Agency: USAF. Apogee: 200 km (120 mi). 1959 April - Scheduled design complete (95%) for Atlas E-series missiles 1959 April 14 - 21:46 GMT - Cape Canaveral LC13. Atlas D 3D FAILURE: Failure. Research and development launch Agency: USAF. Apogee: 1.00 km (0.60 mi). 1959 May 9 - High-resolution photographs of the moon using Vega rocket Spacecraft: Lunar Orbiter. Milton W. Rosen of NASA Headquarters proposed a plan for obtaining high-resolution photographs of the moon. A three-stage Vega would place the payload within a 500-mile diameter circle on the lunar surface. A stabilized retrorocket fired at 500 miles above the moon would slow the instrument package sufficiently to permit 20 photographs to be transmitted at a rate of one picture per minute. Additional Details: High-resolution photographs of the moon using Vega rocket. 1959 May 19 - 04:30 GMT - Cape Canaveral LC14. Atlas D 7D FAILURE: Failure. Research and development launch Agency: USAF. Apogee: 1.00 km (0.60 mi). 1959 June - Atlas D 2D Atlas 2D blows up. Missile 2D blows up on Sycamore stand S-2, after a total of 1486 seconds running time 1959 June 5 - Flight instrumentation necessary to support the Mercury-Atlas program. Space Technology Laboratories and Convair completed an analysis of flight instrumentation necessary to support the Mercury-Atlas program. The primary objective of the study was to select a light-weight telemetry system. A system weighing 270 pounds was recommended, and the National Aeronautics and Space Administration concurred with the proposal. 1959 June 6 - 17:39 GMT - Cape Canaveral LC13. Atlas D 5D FAILURE: Failure. Research and development launch Agency: USAF. 1959 July 12 - Instrumentation to measure noise level during the Mercury Big Joe-Atlas launching. An agreement was made with the Air Force for Space Task Group to place microphone pickups on the skin of the Atlas launch vehicle as a part of the instrumentation to measure noise level during the Big Joe-Atlas launching. Distribution of the microphones was as follows: one inside the Mercury spacecraft, three externally about midway of the launch vehicle, and one on the Atlas skirt. 1959 July 21 - 05:22 GMT - Cape Canaveral LC12. Atlas C 8C Research and development / AFSWC-5 test / particles mission Agency: USAF. Apogee: 900 km (550 mi). A full-scale USAF Atlas ICBM nose cone recovered for the first time after flight down the AMR. 1959 July 29 - 04:10 GMT - Cape Canaveral LC11. Atlas D 11D Research and development test Agency: USAF. Apogee: 1,800 km (1,100 mi). First Atlas successful D missile flight. 1959 August 11 - 18:01 GMT - Cape Canaveral LC13. Atlas D 14D Research and development launch Agency: USAF. Apogee: 1,800 km (1,100 mi). 1959 August 24 - 15:53 GMT - Cape Canaveral LC12. Atlas C 11C Research and development / AFSWC-6 test Agency: USAF. Apogee: 1,400 km (800 mi). Last successful Atlas C flight (11C); 9C exploded one month later during the Able static firing. 1959 August 28 - Additional Atlas launch vehicles in support of Project Mercury. NASA Headquarters authorized the Space Task Group to enter into negotiations with the Air Force Ballistic Missile Division for the procurement of additional Atlas launch vehicles in support of Project Mercury. The authorization was to be incorporated into Contract No. HS-36. 1959 September 1 - Vandenberg -. Atlas D ICBM operational. USAF Atlas ICBM officially declared operational and taken over by the Strategic Air Command, at Vandenberg AFB. 1959 September 9 - 08:19 GMT - Cape Canaveral LC14. Atlas D 10D FAILURE: Failure. Mercury BJ-1 Agency: USAF. Apogee: 153 km (95 mi). NASA boilerplate model of Mercury capsule successfully launched on an Atlas (Big Joe) missile from AMR and recovered in South Atlantic after surviving reentry heat of more than 10,000°F. 1959 September 9 - 17:50 GMT - Vandenberg 576A2. Atlas D 12D Initial operational capability demonstration launch Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). First SAC operational (IOC) launch, 576th SMS, successful: impacted within one mile of target near Wake Island, a 4,480 nautical mile flight. Afterwards, General Thomas S. Power, Commander in Chief of Strategic Air Command, declared the Atlas system to be operational. 1959 September 17 - 02:09 GMT - Cape Canaveral LC13. Atlas D 17D FAILURE: Failure. Research and development launch Agency: USAF. Apogee: 1,000 km (600 mi). 1959 September 24 - Cape Canaveral LC12. Atlas C Able 9C / Able-5 FAILURE: Vehicle exploded on pad. Atlas C Able explodes on pad during static test. Agency: USAF. A participant remembers: I live near the Cape on Merritt Island and have been here for about 41 years. I worked for the ARMA Corp that developed the Atlas Inertial Guidance System. I was in the Blockhouse at Complex 11 while a static test was performed on an Atlas Able on Complex 12. It did explode. Did it ever! After a couple of hours the six of us were allowed out of the blockhouse and saw all the damage to our complex...I had a tiny piece of that missile for a long time that somehow wound up on my person...labeled 9C. The next Atlas Able would not fly until over a year later, using the Atlas D as the booster stage. 1959 October 6 - 05:55 GMT - Cape Canaveral LC11. Atlas D 18D Mk 3 Mod 1 re-entry vehicle research and development mission Agency: USAF. Apogee: 1,800 km (1,100 mi). 1959 October 10 - 03:10 GMT - Cape Canaveral LC13. Atlas D 22D Research and development launch Agency: USAF. Apogee: 1,800 km (1,100 mi). 1959 October 29 - 07:20 GMT - Cape Canaveral LC11. Atlas D 26D Research and development test Agency: USAF. Apogee: 1,800 km (1,100 mi). USAF Atlas successfully launched from Cape Canaveral carrying a nose-cone camera which took a series of photographs of the earth's cloud cover from a 300-mile altitude. 1959 November 4 - 21:37 GMT - Cape Canaveral LC13. Atlas D 28D Research and development launch Agency: USAF. Apogee: 1,800 km (1,100 mi). 1959 November 24 - 19:48 GMT - Cape Canaveral LC13. Atlas D 15D Research and development launch Agency: USAF. Apogee: 1,800 km (1,100 mi). 1959 November 26 - 07:26 GMT - Cape Canaveral LC14. Atlas Able 20D / Able-5 FAILURE: Payload shroud failed after 45 sec, broke away prematurely. Pioneer (P 3) Mass: 168 kg (370 lb). Spacecraft: Pioneer P 3. Agency: NASA. Apogee: 1,000 km (600 mi). An intended lunar probe launched from the Atlantic Missile Range by an Atlas-Able booster disintegrated about 45 seconds later when the protective sheath covering the payload detached prematurely. The probe was sponsored by NASA, developed by the Jet Propulsion Laboratory, and launched by the Air Force Ballistic Missile Division. 1959 December 9 - 00:10 GMT - Cape Canaveral LC13. Atlas D 31D Research and development launch Agency: USAF. Apogee: 1,800 km (1,100 mi). 1959 December 19 - 00:48 GMT - Cape Canaveral LC13. Atlas D 40D Research and development test Agency: USAF. Apogee: 1,800 km (1,100 mi). Atlas ICBM made second successful 6,325-mile flight at AMR. 1960 January 7 - 01:40 GMT - Cape Canaveral LC13. Atlas D 43D Research and development test Agency: USAF. Apogee: 1,800 km (1,100 mi). 43D achieved a 6300 NM (7200 SM) flight from AMR with enough residual fuel for an additional 2000 miles 1960 January 18 - Mercury-Atlas flight test working group to become a standing coordination body. A proposal was made by Walter C. Williams, Associate Director of Project Mercury Operations, that the Mercury-Atlas flight test working group become an official and standing coordination body. This group brought together representation from the Space Task Group, Air Force Ballistic Missile Division, Convair Astronautics, McDonnell Aircraft Corporation, and the Atlantic Missile Range. Personnel from these organizations had met informally in the past on several occasions. 1960 January 21 - 15 Atlas launch vehicles and 26 Mercury spacecraft purchased. Spacecraft: Mercury. At a meeting to draft fiscal year 1962 funding estimates, the total purchase of Atlas launch vehicles was listed as 15, and the total purchase of Mercury spacecraft was listed as 26. 1960 January 26 - 23:43 GMT - Vandenberg 576A3. Atlas D 6D FAILURE: Failure. Initial operational capability demonstration launch Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). Two Atlas ICBMs launched within two hours - one by SAC at VAFB, one by GD/A at AMR; both successful. 1960 January 27 - 01:31 GMT - Cape Canaveral LC13. Atlas D 44D Research and development launch Agency: USAF. Apogee: 1,800 km (1,100 mi). 1960 January 31 - Six chimpanzees ready for Mercury missions. Six chimpanzees were rated as being trained and ready to support Mercury-Redstone or Mercury-Atlas missions. Other chimpanzees were being shipped from Africa to enter the animal training program. 1960 February 12 - 04:11 GMT - Cape Canaveral LC13. Atlas D 49D Research and development launch Agency: USAF. Apogee: 1,800 km (1,100 mi). 1960 February 15 - Cape Canaveral LC13. LV Model: Atlas Able . Atlas D / Able-5 FAILURE: Vehicle exploded in static firing. Pioneer (P 31) Spacecraft: Pioneer P 3. 1960 February 26 - 17:25 GMT - Cape Canaveral LC14. Atlas Agena A 29D / Agena A 1008 FAILURE: Second stage failed to separate. Midas 1 Mass: 2,025 kg (4,464 lb). Spacecraft: Midas. Agency: U.S. Air Force. Missile Defense Alarm System. 1960 March-April - Mercury-Atlas working panels The Mercury-Atlas working panels were reorganized into four groups: coordination, flight test, trajectory analysis, and change control. Each panel was composed of at least one representative from NASA (Space Task Group), McDonnell, Air Force Ballistic Missile Division, Space Technology Laboratory, and Convair-Astronautics. 1960 March 8 - 13:10 GMT - Cape Canaveral LC11. Atlas D 42D Research and development test Agency: USAF. Apogee: 1,800 km (1,100 mi). First USAF Atlas R&D; flight using all-inertial guidance system. 1960 March 11 - 00:36 GMT - Cape Canaveral LC13. Atlas D 51D FAILURE: Failure. Research and development launch Agency: USAF. 1960 March 16 - The Space Task Group published recovery requirements for the Mercury-Atlas 1 (MA-1) flight test. Spacecraft: Mercury. 1960 April 8 - 02:06 GMT - Cape Canaveral LC11. Atlas D 48D FAILURE: Failure. Research and development launch Agency: USAF. Apogee: 1.00 km (0.60 mi). 1960 April 22 - 19:39 GMT - Vandenberg 576B2. Atlas D 25D Initial operational capability operational readiness test launch Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). 1960 May 6 - 16:47 GMT - Vandenberg 576B2. Atlas D 23D FAILURE: Failure. Initial operational capability operational readiness test launch Agency: USAF SAC. Apogee: 2.00 km (1.20 mi). 1960 May 20 - 15:00 GMT - Cape Canaveral LC12. Atlas D 56D Research and development test Agency: USAF. Apogee: 1,800 km (1,100 mi). Atlas ICBM fired 9,040 statute miles from AMR to Indian Ocean, with operational weight nose cone plus instrumentation, longest known flight of an ICBM to date. Missile attained an apogee of about 1,000 miles. 1960 May 24 - 17:36 GMT - Cape Canaveral LC14. Atlas Agena A 45D / Agena A 1007 Midas 2 Mass: 2,300 kg (5,000 lb). Spacecraft: Midas. Agency: U.S. Air Force. Perigee: 473 km (293 mi). Apogee: 494 km (306 mi). Inclination: 33.00 deg. Period: 94.30 min. Missile Defense Alarm System. Test launch with W-17 sensor. 1960 June 11 - 06:30 GMT - Cape Canaveral LC11. Atlas D 54D Research and development launch Agency: USAF. Apogee: 1,800 km (1,100 mi). 1960 June 18 - Atlas launch vehicle 50-D was delivered for the first Mercury-Atlas mission (MA-1). 1960 June 22 - 14:49 GMT - Cape Canaveral LC14. Atlas D 62D FAILURE: Electrical Failure. Research and development test Agency: USAF. Apogee: 1,800 km (1,100 mi). 50th Atlas to be flown at AMR, successful 1960 June 28 - 02:30 GMT - Cape Canaveral LC12. Atlas D 27D Research and development / ionosphere mission Agency: USAF. Apogee: 1,800 km (1,100 mi). 1960 July 2 - 06:58 GMT - Cape Canaveral LC11. Atlas D 60D Research and development launch Agency: USAF. Apogee: 1,800 km (1,100 mi). 1960 July 7 - Reporting plan for Mercury-Atlas and Mercury-Redstone missions A reporting plan for Mercury-Atlas and Mercury-Redstone missions was issued. This document was amended on February 17, 1961, and April 10, 1961. 1960 July 11 - Atlas operational plans given high priority M. Gen. Tom Gerrity appointed head of new BMC for operational site selection through turnover 1960 July 22 - 23:46 GMT - Vandenberg 576B1. Atlas D 74D FAILURE: Failure. Initial operational capability operational readiness test launch Agency: USAF SAC. Apogee: 20 km (12 mi). 1960 July 29 - 13:13 GMT - Cape Canaveral LC14. Atlas D 50D FAILURE: Structural failure of Atlas. Mercury MA-1 Agency: USAF. Apogee: 13 km (8 mi). Mercury-Atlas 1 (MA-1) was launched from the Atlantic Missile Range in a test of spacecraft structural integrity under maximum heating conditions. After 58.5 seconds of flight, MA-1 exploded and the spacecraft was destroyed upon impact off-shore. None of the primary capsule test objectives were met. The mission objectives were to check the integrity of the spacecraft structure and afterbody shingles for a reentry associated with a critical abort and to evaluate the open-loop performance of the Atlas abort-sensing instrumentation system. The spacecraft contained no escape system and no test subject. Standard posigrade rockets were used to separate the spacecraft from the Atlas, but the retrorockets were dummies. The flight was terminated because of a launch vehicle and adapter structural failure. The spacecraft was destroyed upon impact with the water because the recovery system was not designed to actuate under the imposed flight conditions. Later most of the spacecraft, the booster engines, and the liquid oxygen vent valve were recovered from the ocean floor. Since none of the primary flight objectives was achieved, Mercury-Atlas 2 (MA-2) was planned to fulfill the mission. 1961 August 1960 to February - Exhaustive review of Mercury-Atlas after dual Atlas failures. Because of the failure of the Big Joe Atlas test flight and the Mercury-Atlas 1 (MA-1) flight to attain all its mission objectives, the overall Mercury-Atlas program underwent an exhaustive review. Additional Details: Exhaustive review of Mercury-Atlas after dual Atlas failures.. 1960 August 9 - 18:09 GMT - Cape Canaveral LC12. Atlas D 32D Research and development / aeronomy mission Agency: USAF. Apogee: 1,800 km (1,100 mi). 1960 August 11 - Mercury-Atlas 1 (MA-1) mission malfunction discussed. Representatives of NASA, McDonnell, Ballistic Missile Division, Space Technology Laboratories, and Convair met at Cape Canaveral and later at Convair Astronautics (Aug. 30, 1960) to discuss the Mercury-Atlas 1 (MA-1) mission malfunction. Additional Details: Mercury-Atlas 1 (MA-1) mission malfunction discussed.. 1960 August 12 - 13:00 GMT - Cape Canaveral LC11. Atlas D 66D Research and development launch Agency: USAF. Apogee: 1,800 km (1,100 mi). 1960 September 2 - Warren AFB -. Atlas SMS 564 operational. Warren -1 AFB SMS 564 operational 1960 September 12 - 20:38 GMT - Vandenberg 576B3. Atlas D 47D FAILURE: Failure. Initial operational capability demonstration and shakedown operations launch Agency: USAF SAC. Apogee: 1,000 km (600 mi). 1960 September 17 - 00:50 GMT - Cape Canaveral LC11. Atlas D 76D Research and development launch Agency: USAF. Apogee: 1,800 km (1,100 mi). 1960 September 19 - 18:31 GMT - Cape Canaveral LC14. Atlas D 79D Research and development test Agency: USAF. Apogee: 1,800 km (1,100 mi). Atlas ICBM fired 9030 statute miles, from Cape Canaveral to the Indian Ocean off the Cape of Good Hope in 50 minutes, the second record distance flight. 1960 September 20 - Mercury Atlas launch vehicle 67-D delivered to Cape Canaveral The Atlas launch vehicle 67-D was delivered to Cape Canaveral for the Mercury-Atlas 2 (MA-2) reentry test mission. 1960 September 25 - 15:13 GMT - Cape Canaveral LC12. Atlas Able 80D / Able-5 FAILURE: Second stage exploded. Pioneer (P 30) Mass: 175 kg (385 lb). Spacecraft: Pioneer P 3. Agency: NASA. Apogee: 1,290 km (800 mi). An attempt to launch a Pioneer satellite into lunar orbit failed when one of the upper stages of the Atlas- Able rocket malfunctioned. 1960 September 26 - Roll-out inspection of Mercury Atlas launch vehicle 77-D The roll-out inspection of Mercury Atlas launch vehicle 77-D was conducted at Convair-Astronautics. This launch vehicle was allocated for the Mercury-Atlas 3 (MA-3) mission, but was later canceled and Atlas booster 100-D was used instead. 1960 September 29 - 20:31 GMT - Vandenberg 576B2. Atlas D 33D FAILURE: Failure. Initial operational capability demonstration and shakedown operations launch Agency: USAF SAC. Apogee: 500 km (310 mi). 1960 October 11 - 19:15 GMT - Cape Canaveral LC13. Atlas E 3E FAILURE: Failure. Research and development test Agency: USAF. Apogee: 1,000 km (600 mi). First E missile flown with MA-3 engine, unsuccessful 1960 October 11 - 20:33 GMT - Vandenberg SLC3W. Atlas Agena A 57D / Agena A 2101 FAILURE: Second stage failure. Samos 1 Mass: 1,845 kg (4,067 lb). Spacecraft: Samos. Agency: U.S. Air Force. First generation photo surveillance; radio relay of images; Satellite and Missile Observation Satellite. 1960 October 13 - 04:53 GMT - Vandenberg 576B3. Atlas D 81D FAILURE: Failure. Initial operational capability demonstration and shakedown operations launch Agency: USAF SAC. Apogee: 20 km (12 mi). 1960 October 13 - 09:34 GMT - Cape Canaveral LC11. Atlas D 71D Research and development test Agency: USAF. Apogee: 1,800 km (1,100 mi). USAF Atlas launched at AMR placed nose cone containing three black mice 650 miles up and 5,000 miles downrange at 17,000 mph. Nose cone was recovered in target area near Ascension Island, the three mice surviving the flight in "good condition." 1960 October 22 - 05:13 GMT - Cape Canaveral LC14. Atlas D 55D Research and development launch Agency: USAF. Apogee: 1,800 km (1,100 mi). 1960 November 1 - Centaur tracking network test. Under arrangements of the AACB (Aeronautics and Astronautics Coordinating Board), NASA will utilize existing NASA tracking stations for initial Centaur development vehicles and switch to the Advent network (which is to be planned, funded, and constructed by DOD) when Centaur is operational, perhaps as early as the fourth of 10 development launchings of Centaur. November 1960-August 1961 - Crash program instigated to get Atlas sites operational. Golden Ram program accomplished at SMS 576-B2 & B3 1960 November 15 - Atlas D/AIG (All Inertial Guidance) scheduled design 95 % complete 1960 November 15 - 05:54 GMT - Cape Canaveral LC12. Atlas D 83D Research and development launch Agency: USAF. Apogee: 1,800 km (1,100 mi). 1960 November 18 - Mercury Spacecraft No. 8 delivered to Cape Canaveral Spacecraft: Mercury. Spacecraft No. 8 was delivered to Cape Canaveral for the Mercury-Atlas 3 (MA-3) unmanned orbital mission. 1960 November 30 - 01:12 GMT - Cape Canaveral LC13. Atlas E 4E FAILURE: Failure. Research and development launch Agency: USAF. Apogee: 1,000 km (600 mi). 1960 December 15 - 09:10 GMT - Cape Canaveral LC12. Atlas Able 91D / Able-5 FAILURE: Atlas exploded 70 seconds after liftoff. Pioneer (P 31) Mass: 175 kg (385 lb). Spacecraft: Pioneer P 3. Agency: NASA. Apogee: 13 km (8 mi). The final launch in the Pioneer lunar probe program was unsuccessful; the Atlas-Able booster rocket went out of control and exploded at an altitude of 12,200 m off Cape Canaveral. 1960 December 16 - 20:35 GMT - Vandenberg 576B3. Atlas D 99D Research and development launch Agency: USAF. Apogee: 1,800 km (1,100 mi). 1961 January 23 - 21:02 GMT - Cape Canaveral LC12. Atlas D 90D Research and development test Agency: USAF. Apogee: 1,800 km (1,100 mi). Final test flight of USAF Atlas D traveled 5,000 miles to target down Atlantic Missile Range, representing 35 successes, 8 partials, and 6 failures in 49 test launchings for D model. 75th Atlas launched at AMR, successful 1961 January 24 - 21:55 GMT - Cape Canaveral LC13. Atlas E 8E FAILURE: Failure. Research and development launch Agency: USAF. Apogee: 500 km (310 mi). 1961 January 31 - 20:21 GMT - Vandenberg SLC3W. Atlas Agena A 70D / Agena A 2102 Samos 2 Mass: 1,900 kg (4,100 lb). Spacecraft: Samos. Agency: U.S. Air Force. Perigee: 474 km (294 mi). Apogee: 557 km (346 mi). Inclination: 97.40 deg. Period: 95.00 min. First generation photo surveillance; radio relay of images; micrometeoroid impact data. Poor results. 1961 February 6 - Wallops Island -. Liquid hydrogen tests. NASA Aerobee-Hi successfully reached 96 miles above Wallops Station in test of behavior of liquid hydrogen in zero gravity for Lewis Research Center hydrogen propulsion development. 1961 February 7 - Centaur development milestones set. Meeting of NASA and contractor personnel held at NASA headquarters to review Centaur development program. 1961 February 17-20 - Rules for the Mercury MA-2 Spacecraft: Mercury. Spacecraft, mission, and launch vehicle flight safety rules for the Mercury-Atlas 2 (MA-2) mission were reviewed by Space Task Group personnel. 1961 February 17 - Space Task Group selected severe flight trajectory for Mercury-Atlas 2 Spacecraft: Mercury. Information was released by NASA Headquarters that Space Task Group engineers directing Project Mercury had selected the flight trajectory for the Mercury-Atlas 2 (MA-2) mission. Additional Details: Space Task Group selected severe flight trajectory for Mercury-Atlas 2. 1961 February 21 - 14:12 GMT - Cape Canaveral LC14. Atlas D 67D Mercury MA-2 Agency: USAF. Apogee: 182 km (113 mi). Mercury-Atlas 2 (MA-2) was launched from Cape Canaveral in a test to check maximum heating and its effects during the worst reentry design conditions. The flight closely matched the desired trajectory and attained a maximum altitude of 114.04 statute miles and a range of 1,431.6 statute miles. Inspection of the spacecraft aboard the recovery ship some 55 minutes after launch (actual flight time was 17.56 minutes) indicated that test objectives were met, since the structure and heat protection elements appeared to be in excellent condition. The flight control team obtained satisfactory data; and the complete launch computing and display system, operating for the first time in a flight, performed satisfactorily. 1961 February 24 - Mercury spacecraft No. 9 was delivered to Cape Canaveral Spacecraft: Mercury. Spacecraft No. 9 was delivered to Cape Canaveral for the Mercury-Atlas 5 (MA-5) orbital primate (Enos) mission. 1961 February 24 - 18:29 GMT - Cape Canaveral LC13. Atlas E 9E Research and development test Agency: USAF. Apogee: 1,500 km (900 mi). First successful Atlas E flight. 1961 March 3 - Mercury Atlas launch vehicle No. 100-D rolled out. Factory roll-out inspection of Atlas launch vehicle No. 100-D was conducted at Convair-Astronautics. This launch vehicle was allocated for the Mercury-Atlas 3 (MA-3) mission. 1961 March 7 - Warren AFB -. Atlas SMS 565 operational. Warren-2 AFB SMS 565 operational 1961 March 14 - Mercury Atlas launch vehicle 100-D delivered to Cape Canaveral Atlas launch vehicle 100-D was delivered to Cape Canaveral for the Mercury-Atlas 3 (MA-3) mission. 1961 March 14 - 04:17 GMT - Cape Canaveral LC13. Atlas E 13E FAILURE: Failure. Research and development launch Agency: USAF. Apogee: 500 km (310 mi). 1961 March 21 - The Mercury-Atlas Missile Range Projects Office designated as a staff function The Mercury-Atlas Missile Range Projects Office, headed by Elmer H. Buller, was designated as a staff function of the Space Task Group Director's office. 1961 March 25 - 01:49 GMT - Cape Canaveral LC13. Atlas E 16E FAILURE: Failure. Research and development launch Agency: USAF. Apogee: 1,000 km (600 mi). 1961 March 30 - Offutt AFB -. Atlas SMS 566 operational. Offutt AFB SMS 566 operational 1961 April 25 - 16:15 GMT - Cape Canaveral LC14. Atlas D 100D FAILURE: Destroyed by range safety. Mercury MA-3 Spacecraft: Mercury. Agency: NASA. Mercury-Atlas 3 (MA-3) was launched from Cape Canaveral in an attempt to orbit the spacecraft with a 'mechanical astronaut' aboard. After lift-off, the launch vehicle failed to roll to a 70 degree heading and to pitch over into the proper trajectory. The abort-sensing system activated the escape rockets prior to the launch vehicle's destruction by the range safety officer after approximately 40 seconds of flight that had attained an altitude of 16,400 feet. The spacecraft then coasted up to 24,000 feet, deployed its parachutes, and landed in the Atlantic Ocean 2,000 yards north of the launch pad. The spacecraft was recovered and was found to have incurred only superficial damage; it was then shipped to McDonnell for refitting. 1961 May 11 - Mercury spacecraft 8A delivered to Cape Canaveral Spacecraft: Mercury. Mercury spacecraft 8A was delivered to Cape Canaveral for the Mercury-Atlas 4 (MA-4) orbital unmanned (mechanical astronaut) mission. 1961 May 13 - 02:00 GMT - Cape Canaveral LC11. Atlas E 12E Research and development launch Agency: USAF. Apogee: 1,500 km (900 mi). 1961 May 17 - Mercury MA-3 investigation board An Atlas investigation board was convened to study the cause of the Mercury-Atlas 3 (MA-3) mission launch vehicle failure. Several possible areas were considered, and three were isolated as probable causes based on a review of test data. 1961 May 24 - 21:50 GMT - Vandenberg 576B2. Atlas D 95D Research and development launch Agency: USAF. Apogee: 1,800 km (1,100 mi). 1961 May 26 - 02:26 GMT - Cape Canaveral LC13. Atlas E 18E Research and development launch Agency: USAF. Apogee: 1,500 km (900 mi). 1961 May 29 - Ranger booster erected. Spacecraft: Ranger 1-2. Atlas booster 111-D, to be used for Ranger I, was erected on the launch pad at Cape Canaveral. 1961 May 29 - Centrifuge training for Mercury-Atlas orbital missions. A 30 day centrifuge training program was conducted at the Aviation Medical Acceleration Laboratory directed entirely toward training the astronauts for the Mercury-Atlas orbital missions. 1961 June 1 - Prelaunch mission rules for Mercury-Atlas 4 (MA-4) were published. 1961 June 7 - 21:37 GMT - Vandenberg OSTF1. Atlas E 27E FAILURE: Failure. Research and development Category II test Agency: USAF. First E launched at SMS 576 from OSTF-1, unsuccessful 1961 June 8 - Mercury-Atlas 4 (MA-4) recovery requirements were published. 1961 June 23 - 03:00 GMT - Cape Canaveral LC11. Atlas E 17E FAILURE: Failure. Research and development launch Agency: USAF. Apogee: 10 km (6 mi). 1961 June 29-30 - Mercury Atlas vehicle 88-D roll-out Factory roll-out inspection of Atlas launch vehicle 88-D, designated for the Mercury-Atlas 4 (MA-4) mission, was conducted at Convair. 1961 July 7 - McDonnell studies of the redesigned Mercury spacecraft. Spacecraft: Gemini. Walter F. Burke of McDonnell summarized the company's studies of the redesigned Mercury spacecraft for Space Task Group's senior staff. McDonnell had considered three configurations: (1) the minimum-change capsule, modified only to improve accessibility and handling, with an adapter added to carry such items as extra batteries; (2) a reconfigured capsule with an ejection seat installed and most of the equipment exterior to the pressure vessel on highly accessible pallets; and (3) a two-man capsule, similar to the reconfigured capsule except for the modification required for two rather than one-man operation. The capsule would be brought down on two Mercury-type main parachutes, the ejection seat serving as a redundant system. In evaluating the trajectory of the two-man capsule, McDonnell used Atlas Centaur booster performance data. 1961 July 7 - 04:51 GMT - Cape Canaveral LC13. Atlas E 22E Research and development test Agency: USAF. Apogee: 1,500 km (900 mi). Successful Atlas E flight, 9054 miles, from AMR to Indian Ocean (with GE Mark 3 nose cone) 1961 July 12 - 15:11 GMT - Vandenberg SLC3E. Atlas Agena B 97D / Agena B 1201 Midas 3 Mass: 1,600 kg (3,500 lb). Spacecraft: Midas. Agency: U.S. Air Force. Perigee: 3,343 km (2,077 mi). Apogee: 3,540 km (2,190 mi). Inclination: 91.20 deg. Period: 161.40 min. Missile Defense Alarm System. 1961 July 15 - Mercury Atlas launch vehicle 88-D delivered to Cape Canaveral Atlas launch vehicle 88-D was delivered to Cape Canaveral for the Mercury-Atlas 4 (MA-4) mission. 1961 July 31 - 21:32 GMT - Cape Canaveral LC11. Atlas E 21E Research and development launch Agency: USAF. Apogee: 1,500 km (900 mi). 1961 August 1 - Centaur operational contracts initiated. NASA directed Marshall Space Flight Center to enter contract negotiations with contractors for procurement of five operational Atlas-Centaur vehicles. These launchings were planned to begin in second quarter of 1964. 1961 August 9 - Retrofire-from-orbit mission rules for Mercury MA-4 Spacecraft: Mercury. Retrofire-from-orbit mission rules were published for the unmanned Mercury-Atlas 4 (MA-4) orbital flight. 1961 August 9 - Key personnel operational assignments for the Mercury MA-4 Key personnel operational assignments for the Mercury-Atlas 4 (MA-4) unmanned orbital mission were made by the Space Task Group. 1961 August 9 - 04:31 GMT - Cape Canaveral LC13. Atlas F 2F Research and development test Agency: USAF. Apogee: 1,400 km (800 mi). First F flight, at AMR), successful 1961 August 23 - 01:16 GMT - Vandenberg 576B3. Atlas D 101D Research and development launch Agency: USAF. Apogee: 1,800 km (1,100 mi). 1961 August 23 - 10:04 GMT - Cape Canaveral LC12. Atlas Agena B 111D (AA1) / Agena B 6001 (AA1) FAILURE: Agena B second stage failure. Ranger 1 Mass: 306 kg (674 lb). Spacecraft: Ranger 1-2. Agency: NASA. Perigee: 179 km (111 mi). Apogee: 446 km (277 mi). Inclination: 32.90 deg. Period: 90.60 min. Lunar probe; failed to leave Earth orbit. Ranger 1, a test version of the spacecraft which would attempt an unmanned crash landing on the moon, was launched from the Atlantic Missile Range by an Atlas-Agena B booster. The 306 kg spacecraft did not attain the scheduled extremely elongated orbit because of the misfiring of the Agena B rocket. Although the spacecraft systems were tested successfully, only part of the eight project experiments could be carried out. Ranger 1 reentered on August 29 after 111 orbits. Ranger 1's primary mission was to test the performance of those functions and parts that are necessary for carrying out subsequent lunar and planetary missions using essentially the same spacecraft design. 1961 August 24 - Mercury-Atlas 4 (MA-4) unmanned orbital flight was postponed. 1961 September 9 - 01:42 GMT - Cape Canaveral LC13. Atlas E 26E FAILURE: Failure. Research and development launch Agency: USAF. Apogee: 1,000 km (600 mi). 1961 September 9 - 19:28 GMT - Vandenberg SLC3W. Atlas Agena B 106D / Agena B 2120 FAILURE: Exploded on launch pad. Samos 3 Mass: 1,890 kg (4,160 lb). Spacecraft: Samos. Agency: U.S. Air Force. First generation photo surveillance; radio relay of images. 1961 September 13 - 14:04 GMT - Cape Canaveral LC14. Atlas D 88D Mercury MA-4 Mass: 1,200 kg (2,600 lb). Spacecraft: Mercury. Agency: NASA. Perigee: 156 km (96 mi). Apogee: 248 km (154 mi). Inclination: 32.80 deg. Period: 88.40 min. Mercury-Atlas 4 (MA-4) was launched from Cape Canaveral with special vibration and noise instrumentation and a mechanical crewman simulator aboard in addition to the normal spacecraft equipment. This was the first Mercury spacecraft to attain an earth orbit. The orbital apogee was 123 nautical miles and the perigee was 86 nautical miles. After one orbit, the spacecraft's orbital timing device triggered the retrograde rockets, and the spacecraft splashed in the Atlantic Ocean 161 miles east of Bermuda. Recovery was made by the USS Decatur. During the flight, only three slight deviations were noted - a small leak in the oxygen system; loss of voice contact over Australia; and the failure of an inverter in the environmental control system. Overall, the flight was highly successful: the Atlas booster performed well and demonstrated that it was ready for the manned flight, the spacecraft systems operated well, and the Mercury global tracking network and telemetry operated in an excellent manner and was ready to support manned orbital flight. 1961 September 18 - Mission rules for the Mercury-Atlas 5 (MA-5) orbital flight. Mission rules for the Mercury-Atlas 5 (MA-5) orbital flight were published. Revisions were issued on October 16 and 25, 1961, and November 11, 1961. 1961 September 28 - Mariner moved to Atlas-Agena due to Centaur delay. Spacecraft: Mariner 1-2. NASA announced that instrumented Venus probe to be launched next year would be launched by an Atlas-Agena B rather than a Centaur rocket as originally planned. 1961 September 28 - Fairchild AFB -. Atlas SMS 567 operational. Fairchild AFB SMS 567 operational 1961 October 1 - Factory roll-out inspection of Mercury Atlas booster No. 93-D Factory roll-out inspection of Atlas booster No. 93-D was conducted at Convair. This booster was designated for the Mercury-Atlas 5 (MA-5) mission. 1961 October 2 - 18:23 GMT - Cape Canaveral LC11. Atlas E 25E Research and development / Pod 7 test Agency: USAF. Apogee: 1,500 km (900 mi). 1961 October 5 - 13:42 GMT - Cape Canaveral LC13. Atlas E 30E Research and development test Agency: USAF. Apogee: 1,500 km (900 mi). USAF Atlas fired 9,000 miles for Atlantic Missile Range into Indian Ocean, carrying dummy nuclear warhead and a data capsule which was recovered. 1961 October 9 - Mercury Atlas booster No. 93-D delivered to Cape Canaveral Atlas booster No. 93-D was delivered to Cape Canaveral for the Mercury-Atlas 5 (MA-5) orbital flight mission. 1961 October 10 - Forbes AFB -. Atlas SMS 548 operational. Forbes AFB SMS 548 operational 1961 October 20 - STG discussed development of automatic checkout system for the entire NASA launch vehicle program The MSFC-STG Advanced Program Coordination Board met at STG and discussed the question of the development of an automatic checkout system which would include the entire launch vehicle program from the Saturn C-1 through the Nova. It agreed that the Apollo contractor should be instructed to make the spacecraft electrical subsystems compatible with the Saturn complex. In further discussion, Paul J. DeFries of Marshall Space Flight Center MSFC presented a list of proposed guidelines for use in studying early manned lunar landing missions:
1961 October 21 - 13:53 GMT - Vandenberg SLC3E. Atlas Agena B 105D Midas 4 Mass: 1,800 kg (3,900 lb). Spacecraft: Midas. Agency: U.S. Air Force. Perigee: 3,482 km (2,163 mi). Apogee: 3,763 km (2,338 mi). Inclination: 95.90 deg. Period: 165.90 min. Missile Defense Alarm System. Deployed subsatellites. 1961 October 27 - Program of manned spaceflight for 1963-1965. Spacecraft: Gemini. Space Task Group (STG), assisted by George M. Low, NASA Assistant Director for Space Flight Operations, and Warren J. North of Low's office, prepared a project summary presenting a program of manned spaceflight for 1963-1965. This was the final version of the Project Development Plan, work on which had been initiated August 14. Additional Details: Program of manned spaceflight for 1963-1965.. 1961 November 10 - 14:55 GMT - Cape Canaveral LC13. Atlas E 32E FAILURE: Sustainer engine failed 15 seconds after launch. Research and development test / Pod 13 chemical release Agency: USAF. Apogee: 10 km (6 mi). USAF Atlas with capsule containing squirrel monkey destroyed by range safety officer at Atlantic Missile Range when main sustainer engine failed 15 seconds after launch. 1961 November 12 - Mercury 5 launch postponed Spacecraft: Mercury. Mercury-Atlas 5, scheduled for launch no earlier than November 14, ran into technical difficulties, postponing launch for several days. 1961 November 18 - 08:12 GMT - Cape Canaveral LC12. Atlas Agena B 117D (AA2) / Agena B 6002 (AA2) FAILURE: Agena B Second Stage failed to restart. Ranger 2 Mass: 304 kg (670 lb). Spacecraft: Ranger 1-2. Agency: NASA. Perigee: 150 km (90 mi). Apogee: 242 km (150 mi). Inclination: 33.30 deg. Period: 88.30 min. This was a flight test of the Ranger spacecraft system designed for future lunar and interplanetary missions. The spacecraft was launched into a low earth parking orbit, but an inoperative roll gyro prevented Agena restart resulting in Ranger 2 being stranded in low earth orbit. The orbit decayed and the spacecraft reentered Earth's atmosphere on 20 November 1961. 1961 November 19 - RL-10 flight rating complete. NASA announced the completion of the preliminary flight rating test of the Nation's first liquid-hydrogen rocket engine. The engine, the RL-10, was designed and developed by Pratt and Whitney, of United Aircraft, for the Marshall Space Flight Center, and 20 captive firings were competed within 5 days under simulated space conditions, consistently producing 15,000 pounds of thrust. RL-10, previously known as XLR-115, was initiated in October 1958 and over 700 firings were conducted in its development. 1961 November 20 - Warren AFB -. Atlas SMS 549 operational. Warren-3 AFB SMS 549 operational 1961 November 22 - 20:45 GMT - Vandenberg SLC3W. Atlas Agena B 108D / Agena B 2202 FAILURE: Failure. Samos 4 Mass: 1,860 kg (4,100 lb). Spacecraft: Samos. Agency: U.S. Air Force. Apogee: 200 km (120 mi). First generation photo surveillance; return of camera and film by capsule; SAMOS type satellite. 1961 November 22 - 21:04 GMT - Cape Canaveral LC11. Atlas F 4F Research and development / Pod 3, 22 test / ionosphere / aeronomy mission Agency: USAF RS. Apogee: 1,400 km (800 mi). 1961 November 29 - 15:07 GMT - Cape Canaveral LC14. Atlas D 93D Mercury MA-5 Mass: 1,300 kg (2,800 lb). Spacecraft: Mercury. Agency: NASA. Perigee: 158 km (98 mi). Apogee: 237 km (147 mi). Inclination: 32.60 deg. Period: 88.30 min. Mercury-Atlas 5 (MA-5), the second and final orbital qualification of the spacecraft prior to manned flight was launched from Cape Canaveral with Enos, a 37.5 pound chimpanzee, aboard. Scheduled for three orbits, the spacecraft was returned to earth after two orbits due to the failure of a roll reaction jet and to the overheating of an inverter in the electrical system. Both of these difficulties could have been corrected had an astronaut been aboard. The spacecraft was recovered 255 miles southeast of Bermuda by the USS Stormes. During the flight, the chimpanzee performed psychomotor duties and upon recovery was found to be in excellent physical condition. The flight was termed highly successful and the Mercury spacecraft well qualified to support manned orbital flight. 1961 November 29 - 23:01 GMT - Vandenberg 576B2. Atlas D 53D Operational missile test Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). 1961 November 30 - Mercury Atlas launch vehicle 109-D delivered to Cape Canaveral Atlas launch vehicle 109-D was delivered to Cape Canaveral for the Mercury-Atlas 6 (MA-6) first manned orbital mission. 1961 December 1 - 20:40 GMT - Cape Canaveral LC13. Atlas E 35E Research and development / Pod 23 test Agency: USAF. Apogee: 1,600 km (900 mi). 1961 December 7 - NASA announced plans to develop a two-man Mercury capsule. Spacecraft: Gemini. In Houston, Director Robert R. Gilruth of Manned Spacecraft Center announced plans to develop a two-man Mercury capsule. Built by McDonnell, it would be similar in shape to the Mercury capsule but slightly larger and from two to three times heavier. Its booster would be a modified Titan II. A major program objective would be orbital rendezvous. The two-man spacecraft would be launched into orbit and would attempt to rendezvous with an Agena stage put into orbit by an Atlas. Total cost of 12 capsules plus boosters and other equipment was estimated at $500 million. The two-man flight program would begin in the 1963-1964 period with several unmanned ballistic flights to test overall booster-spacecraft compatibility and system engineering. Several manned orbital flights would follow. Besides rendezvous flybys of the target vehicle, actual docking missions would be attempted in final flights. The spacecraft would be capable of missions of a week or more to train pilots for future long-duration circumlunar and lunar landing flights. The Mercury astronauts would serve as pilots for the program, but additional crew members might be phased in during the latter portions of the program. 1961 December 7 - Recommendations to Secretary of Defense Robert S. McNamara on the division of effort between NASA and DOD in the Mark II program. Spacecraft: Gemini. NASA Associate Administrator Robert C. Seamans, Jr., and John H. Rubel, Department of Defense (DOD) Deputy Director for Defense Research and Engineering, offered recommendations to Secretary of Defense Robert S. McNamara on the division of effort between NASA and DOD in the Mark II program. They stressed NASA's primary responsibility for managing and directing the program, although attaining the program objectives would be facilitated by using DOD (especially Air Force) resources in a contractor relation to NASA. In addition, DOD personnel would aquire useful experience in manned spaceflight design, development, and operations. Space Systems Division of Air Force Systems Command became NASA's contractor for developing, procuring, and launching Titan II and Atlas-Agena vehicles for the Mark II program. 1961 December 7 - 21:18 GMT - Vandenberg 576B3. Atlas D 82D Operational missile test Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). 1961 December 12 - 20:16 GMT - Cape Canaveral LC11. Atlas F 5F FAILURE: Failure. Research and development / Pod 24 test Agency: USAF. Apogee: 1,000 km (600 mi). 1961 December 20 - 03:32 GMT - Cape Canaveral LC13. Atlas E 36E Research and development/Pod Test/Chemical release mission Agency: USAF. Apogee: 1,800 km (1,100 mi). 1961 December 21 - 03:35 GMT - Cape Canaveral LC11. Atlas F 6F FAILURE: Failure. Research and development test / Pod 15, 25 chemical release / ionosphere / meteorite mission Agency: USAF. Apogee: 500 km (310 mi). 1961 December 22 - 19:12 GMT - Vandenberg SLC3E. Atlas Agena B 114D / Agena B 2203 Samos 5 Mass: 1,860 kg (4,100 lb). Spacecraft: Samos. Agency: U.S. Air Force. Perigee: 187 km (116 mi). Apogee: 310 km (190 mi). Inclination: 89.60 deg. Period: 89.40 min. First generation photo surveillance; return of camera and film by capsule; SAMOS type satellite. Reached orbit but failed to deorbit and be recovered. In his memoirs Sergei Khrushchev recounts recovery of what he believed to be a recoverable Samos, except the date given is the winter before tests of this configuration actually started. He relates that a second American capsule was recovered in the spring of 1961. It was equipped with a 30 cm lens and 100’s of metres of 10 cm wide film. Also recovered were a pear-shaped module made of fibreglass, and an inertial orientation system powered by electric motors. It may have been a SAMOS prototype. The capsule was found by tractor drivers, who disassembled it and used the film to wrap around the frame of their outhouse to provide some privacy in the treeless area. Unfortunately this ruined the film, preventing the Russians from developing it and discovering the technical capabilities of the system. 1961 December 29 - NASA issued the Gemini Operational and Management Plan, which outlined the roles and responsibilities of NASA and Department of Defense in the Gemini (Mercury Mark II) program. Spacecraft: Gemini. NASA would be responsible for overall program planning, direction, systems engineering, and operation-including Gemini spacecraft development; Gemini/Agena rendezvous and docking equipment development; Titan II/Gemini spacecraft systems integration; launch, flight, and recovery operations; command, tracking, and telemetry during orbital operations; and reciprocal support of Department of Defense space projects and programs within the scope of the Gemini program. Department of Defense would be responsible for: Titan II development and procurement, Atlas procurement, Agena procurement, Atlas-Agena systems integration, launch of Titan II and Atlas-Agena vehicles, range support, and recovery support. A slightly revised version of the plan was signed in approval on March 27 by General Bernard A. Schriever, Commander, Air Force Systems Command, for the Air Force, and D. Brainerd Holmes, Director of Manned Space Flight, for NASA. 1962 January 15-17 - Recovery swimmers trained for Mercury MA-6. Recovery area swimmers were trained at the Pensacola Naval Air Station, Florida, for use in the Mercury-Atlas 6 (MA-6) manned orbital mission. Instruction included films, briefings, auxiliary flotation collar deployment, and jumps from a helicopter. 1962 January 16 - Mercury spacecraft 16 delivered to Cape Canaveral Spacecraft: Mercury. Spacecraft 16 was delivered to Cape Canaveral for the third manned (Schirra) orbital flight, Mercury-Atlas 8 (MA-8). 1962 January 17 - 21:02 GMT - Vandenberg 576B2. Atlas D 123D Operational missile test Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). 1962 January 23 - 21:28 GMT - Vandenberg 576B3. Atlas D 132D Operational missile test Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). 1962 January 26 - 20:30 GMT - Cape Canaveral LC12. Atlas Agena B 121D (AA3) / Agena B 6003 (AA3) FAILURE: Agena B second stage guidance system failure. Ranger 3 Mass: 327 kg (720 lb). Spacecraft: Ranger 3-4-5. Agency: NASA. Lunar impact probe; missed the moon by 36,874 km and went into solar orbit. A malfunction in the booster guidance system resulted in excessive spacecraft speed. Reversed command signals caused the telemetry antenna to lose earth acquisition, and mid-course correction was not possible. Some useful data were obtained from the flight. Of four scientific experiments only one was partially completed: gamma-ray readings of the lunar surface. Attempts to relay television pictures of the moon and to bounce radar signals off the moon at close range were unsuccessful. 1962 January 27 - Mercury MA-6 postponed at T-minus 29 minutes The Mercury-Atlas 6 (MA-6) manned orbital flight was postponed at T-minus 29 minutes due to weather conditions. 1962 January 30 - Mercury MA-6 postponed The Mercury-Atlas 6 (MA-6) mission was postponed because of technical difficulties with the launch vehicle. 1962 February 13 - 20:55 GMT - Cape Canaveral LC13. Atlas E 40E Research and development test Agency: USAF. Apogee: 1,600 km (900 mi). Last Atlas E R&D; flight. 1962 February 14 - Mercury MA-6 postponed. Unfavorable weather conditions caused the Mercury-Atlas 6 (MA-6) manned orbital mission to be postponed. 1962 February 16 - 23:04 GMT - Vandenberg 576B2. Atlas D 137D Operational missile test Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). 1962 February 18 - NASA announced Project Fire Spacecraft: FIRE. NASA announced Project Fire, a high-speed reentry heat research program to obtain data on materials, heating rates, and radio signal attenuation on spacecraft reentering the atmosphere at speeds of about 24,500 miles per hour. Information from the program would support technology for manned and unmanned reentry from lunar missions. Under the management of the Langley Research Center, Project Fire would use Atlas D boosters and the reentry package would be powered by an Antares solid-fuel motor (third stage of the Scout). 1962 February 20 - 14:47 GMT - Cape Canaveral LC14. Atlas D 109D Mercury MA-6 Mass: 1,355 kg (2,987 lb). Spacecraft: Mercury. Agency: NASA. Perigee: 159 km (98 mi). Apogee: 265 km (164 mi). Inclination: 32.50 deg. Period: 88.60 min. Crew: Glenn. Flight: Mercury MA-6. First US manned orbital mission. John Glenn finally puts America in orbit. False landing bag deploy light led to reentry being started with retropack left in place on heat shield. It turned out that indicator light was false and a spectacular reentry ensued, with glowing chunks of the retropack whizzing by the window. After four hours and 43 minutes the spacecraft reentered the atmosphere and landed at 2:43 pm EST in the planned recovery area NE of the Island of Puerto Rico. All flight objectives were achieved. Glenn was reported to be in excellent condition. Beause of failure of one of the automatic systems, the astronaut took over manual control of the spacecraft during part of the flight. With this flight, the basic objectives of Project Mercury had been achieved. 1962 February 21 - 22:30 GMT - Vandenberg 576B3. Atlas D 52D FAILURE: Failure. Operational missile test Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). 1962 February 25 - Factory roll-out inspection of Mercury Atlas launch vehicle 107-D. Flight: Mercury MA-7. Factory roll-out inspection of Atlas launch vehicle 107-D, designated for the Mercury-Atlas 7 (MA-7) manned orbital mission, was conducted at Convair. 1962 March 1 - 00:14 GMT - Vandenberg OSTF1. Atlas E 66E Research and development Category II test Agency: USAF. Apogee: 1,600 km (900 mi). 1962 March 5 - Westinghouse Electric Corporation, Baltimore, Maryland, received a $6.8 million subcontract from McDonnell to provide the rendezvous radar and transponder system for the Gemini spacecraft. Spacecraft: Gemini. Purpose of the rendezvous radar, sited in the recovery section of the spacecraft, was to locate and track the target vehicle during rendezvous maneuvers. The transponder, a combined receiver and transmitter designed to transmit signals automatically when triggered by an interrogating signal, was located in the Agena target vehicle. 1962 March 6 - Mercury Atlas launch vehicle 107-D delivered to Cape Canaveral Atlas launch vehicle 107-D was delivered to Cape Canaveral for the Mercury-Atlas 7 (MA-7) mission. 1962 March 7 - 22:10 GMT - Vandenberg SLC3E. Atlas Agena B 112D / Agena B 2204 Samos 6 Mass: 1,860 kg (4,100 lb). Spacecraft: Samos. Agency: U.S. Air Force. Perigee: 236 km (146 mi). Apogee: 686 km (426 mi). Inclination: 90.90 deg. Period: 93.90 min. First generation photo surveillance; return of camera and film by capsule; SAMOS type satellite. Failed to return camera and film. Samos film return project cancelled; remaining 4 cameras placed in warehouse and later used on KH-6 Lanyard. 1962 March 15 - Carpenter replaces Slayton on Mercury-Atlas 7 (MA-7) Flight: Mercury MA-7. NASA Headquarters publicly announced that Scott Carpenter would pilot the Mercury-Atlas 7 (MA-7) manned orbital mission replacing Donald Slayton. The latter, formerly scheduled for the flight, was disqualified because of a minor erratic heart rate. 1962 March 24 - 00:39 GMT - Vandenberg 576B2. Atlas D 134D Demonstration and shakedown operations launch Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). President John F. Kennedy visited Vandenberg AFB and witnessed the launch of Atlas 134D. 1962 April - Crash program completed to clear Atlas configuration problems. Golden Ram follow-on completed at all Atlas D operational bases 1962 April - Atlas F training facility activated. VAFB Atlas F training facility turned over to SAC 1962 April 6 - Symposium on the results of Mercury MA-6 NASA sponsored a 1-day symposium in Washington on the results of the Mercury-Atlas 6 (MA-6) three-orbit flight of John Glenn. One of the items of particular interest was Glenn's 'fire-flies,' or luminous particles, and their possible origin. 1962 April 9 - 15:04 GMT - Vandenberg SLC3E. Atlas Agena B 110D Midas 5 Mass: 1,860 kg (4,100 lb). Spacecraft: Midas. Agency: U.S. Air Force. Perigee: 2,784 km (1,729 mi). Apogee: 3,405 km (2,115 mi). Inclination: 86.70 deg. Period: 152.90 min. Missile Defense Alarm System. 1962 April 9 - 20:50 GMT - Cape Canaveral LC11. Atlas F 11F FAILURE: Failure. Research and development launch Agency: USAF. 1962 April 12 - 01:57 GMT - Vandenberg 576B2. Atlas D 129D Demonstration and shakedown operations launch Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). 1962 April 23 - 20:50 GMT - Cape Canaveral LC12. Atlas Agena B 133D (AA4) / Agena B 6004 (AA4) Ranger 4 Mass: 328 kg (723 lb). Spacecraft: Ranger 3-4-5. Agency: NASA. Ranger IV was launched by an Atlas-Agena B booster from the Atlantic Missile Range, attained a parking orbit, and was fired into the proper lunar trajectory by the restart of the Agena B engine. Failure of a timer in the spacecraft payload caused loss of both internal and ground control over the vehicle. The Goldstone Tracking Station maintained contact with the spacecraft until it passed behind the left edge of the moon on April 26. It impacted at a speed of 9,617 km per hour, the first American spacecraft to land on the lunar surface. The Agena B second stage passed to the right of the moon and later went into orbit around the sun. Lunar photography objectives were not achieved. 1962 April 26 - 18:56 GMT - Vandenberg SLC3W. Atlas Agena B 118D / Agena B SPS 2401 Samos 7 Mass: 1,588 kg (3,500 lb). Spacecraft: Samos. Agency: U.S. Air Force. Second generation photo surveillance; radio relay of images; Satellite and Missile Observation Satellite. Poor results. 1962 April 27 - 23:24 GMT - Vandenberg 576B2. Atlas D 140D Demonstration and shakedown operations launch Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). 1962 April 30 - Swimmer training for Mercury MA-7 Swimmer training was started for the Mercury-Atlas 7 (MA-7) manned orbital mission recovery area. Instruction consisted of films, briefings, exercises in deploying the auxiliary flotation collar, and jumps from a helicopter. 1962 May 1 - Small working group to discuss the feasibility of making the Gemini telemetry system a full PCM system. Following a Lockheed briefing on pulse-code-modulation (PCM) instrumentation systems, representatives of Goddard Space Flight Center and Manned Spacecraft Center (MSC) formed a small working group to discuss the feasibility of making the Gemini telemetry system a full PCM system. PCM was a digital telemetry system which could provide more channels of information, faster data rates, improved accuracy, and less weight of equipment per data channel. Goddard had already reviewed several PCM ground station proposals and had concluded that such a system could handle future NASA programs. All who attended the meeting agreed that a full PCM telemetry system, airborne and ground, could be implemented in time to support the Gemini program. Gemini Project Office approved the formation of an MSC-Gemini PCM Instrumentation Working Group to be responsible for the implementation and compatibility of the airborne and ground PCM system for Gemini. On June 27, Walter C. Williams, MSC Associated Director, notified Goddard of NASA's decision 'to utilize a PCM telemetry system for Gemini and Agena real time data.' Ten sites were selected for the installation of PCM equipment; each of these also received dual acquisition equipment, dual digital command system, and pulse coders for distinguishing between the manned Gemini spacecraft and the Agena target when both were in orbit. 1962 May 8 - 19:49 GMT - Cape Canaveral LC36A. Atlas Centaur F-1 FAILURE: Vehicle exploded due to insulation problems on the Atlas. Research and development test Agency: NASA. Apogee: 6.00 km (3.70 mi). First Centaur flight (unsuccessful). 1962 May 12 - Project Gemini cost estimates had tripled from the original estimate of $250 million. Spacecraft: Gemini. James E. Webb, NASA's new Administrator, reviewed the Gemini program. Project Gemini cost estimates at this point ($744.3 million) had increased substantially over the original estimate of $250 million. Estimated spacecraft cost had risen from $240.5 to $391.6 million; Titan II cost, from $113.0 to $161.8 million; Atlas-Agena, from $88.0 to $106.3 million; and supporting development (including the paraglider program), from $29.0 to $36.8 million. Estimated operations costs had declined from $59.0 to $47.8 million. 1962 May 12 - 00:31 GMT - Vandenberg 576B3. Atlas D 127D Demonstration and shakedown operations launch Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). 1962 May 24 - 12:45 GMT - Cape Canaveral LC14. Atlas D 107D Mercury MA-7 Mass: 1,349 kg (2,974 lb). Spacecraft: Mercury. Agency: NASA. Perigee: 154 km (95 mi). Apogee: 260 km (160 mi). Inclination: 32.50 deg. Period: 88.50 min. Crew: Carpenter. Flight: Mercury MA-7. Scott Carpenter in Aurora 7 is enthralled by his environment but uses too much orientation fuel. Yaw error and late retrofire caused the landing impact point to be over 300 km beyond the intended area and beyond radio range of the recovery forces. Landing occurred 4 hours and 56 minutes after liftoff. Astronaut Carpenter was later picked up safely by a helicopter after a long wait in the ocean and fears for his safety. NASA was not impressed and Carpenter left the agency soon thereafter to become an aquanaut. 1962 June 17 - 18:14 GMT - Vandenberg SLC3W. Atlas Agena B 115D / Agena B SPS 2402 Samos 8 Mass: 1,860 kg (4,100 lb). Spacecraft: Samos. Agency: U.S. Air Force. Perigee: 198 km (123 mi). Apogee: 198 km (123 mi). Inclination: 96.20 deg. Period: 88.40 min. First generation photo surveillance; radio relay of images; Satellite and Missile Observation Satellite. Poor results. 1962 June 26 - 10:57 GMT - Vandenberg 576B3. Atlas D 21D NTMP K-1 Target mission Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). First launch of an Atlas from Vandenberg AFB as a target for an Army Nike-Zeus from Kwajalein. 1962 July 12 - 16:57 GMT - Vandenberg 576B2. Atlas D 141D NTMP K-2 Target mission Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). 1962 July 13 - 21:11 GMT - Vandenberg OSTF1. Atlas E 67E FAILURE: Failure. Research and development Category II test Agency: USAF. Apogee: 1,800 km (1,100 mi). 1962 July 18 - 20:51 GMT - Vandenberg SLC3W. Atlas Agena B 120D Samos 9 Mass: 1,860 kg (4,100 lb). Spacecraft: Samos. Agency: U.S. Air Force. Perigee: 184 km (114 mi). Apogee: 234 km (145 mi). Inclination: 96.00 deg. Period: 88.60 min. First generation photo surveillance; radio relay of images; Satellite and Missile Observation Satellite. Poor results. 1962 July 19 - 11:05 GMT - Vandenberg 576B1. Atlas D 13D Demonstration and shakedown operations launch Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). 1962 July 22 - 09:21 GMT - Cape Canaveral LC12. Atlas Agena B 145D (AA5) / Agena B 6901 (AA5) FAILURE: Destroyed by range safety. Mariner 1 Mass: 200 kg (440 lb). Spacecraft: Mariner 1-2. Agency: NASA. Venus probe. 1962 July 27 - Mercury Atlas launch vehicle No. 113-D accepted Atlas launch vehicle No. 113-D was inspected at Convair and accepted for the Mercury-Atlas 8 (MA-8) manned orbital mission. 1962 August 1 - 21:07 GMT - Vandenberg 576E. Atlas F 15F Research and development test Agency: USAF. Apogee: 1,400 km (800 mi). First successful Atlas F flight at operational site, SMS 576E (15F) 1962 August 5 - 17:58 GMT - Vandenberg SLC3W. Atlas Agena B 124D / Agena B SPS 2404 FTV 2404 Spacecraft: Samos. Agency: USAF. 1962 August 8 - Mercury Atlas launch vehicle 113-D delivered to Cape Canaveral Atlas launch vehicle 113-D was delivered to Cape Canaveral for the Mercury-Atlas 8 (MA-8) manned orbital mission. 1962 August 9 - 22:51 GMT - Vandenberg 576B3. Atlas D 8D Demonstration and shakedown operations launch Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). 1962 August 9 - 23:05 GMT - Vandenberg 576B2. Atlas D 87D Demonstration and shakedown operations launch Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). 1962 August 10 - 21:11 GMT - Vandenberg OSTF2. Atlas F 57F FAILURE: Failure. Research and development launch Agency: USAF. Apogee: 10 km (6 mi). 1962 August 13 - 22:00 GMT - Cape Canaveral LC11. Atlas F 7F Research and development / Pod 16 test Agency: USAF. Apogee: 1,400 km (800 mi). 1962 August 27 - 06:53 GMT - Cape Canaveral LC12. Atlas Agena B 179D (AA6) / Agena B 6902 (AA6) Mariner 2 Mass: 201 kg (443 lb). Spacecraft: Mariner 1-2. Agency: NASA. Mariner 2 was the first spacecraft to successfully flyby another planet. It was a backup for the Mariner 1 mission which failed shortly after launch to Venus. After launch and termination of the Agena first burn, the Agena-Mariner was in a 118 km altitude Earth parking orbit. The Agena second burn injected the Mariner 2 spacecraft into a geocentric escape hyperbola at 26 minutes 3 seconds after lift-off. Solar panel extension was completed about 44 minutes after launch. On 29 August 1962 cruise science experiments were turned on. A midcourse maneuver was initiated at 22:49:00 GMT on 4 September and completed at 2:45:25 GMT 5 September. On 8 September at 17:50 GMT the spacecraft suddenly lost its attitude control, which was restored by the gyroscopes 3 minutes later. The cause was unknown but may have been a collision with a small object. On October 31 the output from one solar panel deteriorated abruptly, and the science cruise instruments were turned off. A week later the panel resumed normal function and instruments were turned back on. The panel permanently failed on 15 November, but Mariner 2 was close enough to the Sun that one panel could supply adequate power. On December 14 the radiometers were turned on. Mariner 2 approached Venus from 30 degrees above the dark side of the planet, and passed below the planet at its closest distance of 34,773 km at 19:59:28 GMT 14 December 1962. After encounter, cruise mode resumed. Spacecraft perihelion occurred on 27 December at a distance of 105,464,560 km. The last transmission from Mariner 2 was received on 3 January 1963 at 07:00 GMT. Mariner 2 remains in heliocentric orbit. Scientific discoveries made by Mariner 2 included a slow retrograde rotation rate for Venus, hot surface temperatures and high surface pressures, a predominantly carbon dioxide atmosphere, continuous cloud cover with a top altitude of about 60 km, and no detectable magnetic field. It was also shown that in interplanetary space the solar wind streams continuously and the cosmic dust density is much lower than the near-Earth region. Improved estimates of Venus' mass and the value of the astronomical unit were made. 1962 September - Schilling AFB -. Atlas SMS 560 operational. Schilling AFB SMS 550 operational 1962 September 8 - Mercury Atlas vehicle 113-D static-fired Atlas launch vehicle 113-D for the Mercury-Atlas 8 (MA-8) manned orbital mission was static-fired at Cape Canaveral. This test was conducted to check modifications that had been made to the booster for the purpose of smoother engine combustion. 1962 September 15 - Lincoln AFB -. Atlas SMS 551 operational. Lincoln AFB SMS 551 operational 1962 September 19 - 19:30 GMT - Cape Canaveral LC11. Atlas F 8F Research and development / Pod 17 test Agency: USAF. Apogee: 1,400 km (800 mi). 1962 September 25 - A preliminary design criteria review conference for complex 14, held in Los Angeles, resulted in ground rules for all contractors. Target dates established were (1) stand availability, July 1, 1963; (2) estimated beneficial occupancy date, November 1, 1963; and (3) vehicle on-stand date, February 1, 1964. Complex 14 would be used for launching the Gemini-Agena target vehicle and Mariner spacecraft, but basic modifications would be primarily for the Gemini program. On November 15, 1962, Air Force Space Systems Division reviewed the criteria summary report for complex 14 modifications and suggested only minor engineering changes. 1962 October 2 - 11:46 GMT - Vandenberg 576B2. Atlas D 4D FAILURE: Failure. NTMP K-3 Target mission Agency: USAF SAC. Apogee: 500 km (310 mi). 1962 October 3 - 12:15 GMT - Cape Canaveral LC14. Atlas D 113D Mercury MA-8 Mass: 1,374 kg (3,029 lb). Spacecraft: Mercury. Agency: NASA. Perigee: 153 km (95 mi). Apogee: 285 km (177 mi). Inclination: 32.50 deg. Period: 88.80 min. Crew: Schirra. Flight: Mercury MA-8. The Sigma 7 spacecraft with Astronaut Walter M. Schirra, Jr., as pilot was launched into orbit by a Mercury-Atlas vehicle from Atlantic Missile Range. In the most successful American manned space flight to date, Schirra traveled nearly six orbits, returning to earth at a predetermined point in the Pacific Ocean 9 hours, 13 minutes after liftoff. Within 40 minutes after landing, he and his spacecraft were safely aboard the aircraft carrier U.S.S. Kearsarge. Schirra attempted and achieved a nearly perfect mission by sticking rigorously to mission plan. 1962 October 7 - The Mercury-Atlas 8 (MA-8) press conference was held at the Rice University, Houston, Texas. Astronaut Schirra expressed his belief that the spacecraft was ready for the 1-day mission, that he experienced absolutely no difficulties with his better than 9 hours of weightlessness, and that the flight was of the 'textbook' variety. 1962 October 9 - Mercury spacecraft 20 delivered to Cape Canaveral Spacecraft: Mercury. Flight: Mercury MA-9. Spacecraft 20 was delivered to Cape Canaveral for the Mercury-Atlas 9 (MA-9) 1-day mission flight. 1962 October 9 - Altus AFB -. Atlas SMS 577 operational. Altus AFB SMS 577 operational 1962 October 18 - 16:59 GMT - Cape Canaveral LC12. Atlas Agena B 215D (AA7) / Agena B 6005 (AA7) Ranger 5 Mass: 340 kg (740 lb). Spacecraft: Ranger 3-4-5. Agency: NASA. The Ranger V lunar probe was launched from Atlantic Missile Range by an Atlas-Agena B launch vehicle. The Agena B stage attained parking orbit and 25 minutes later reignited to send Ranger V toward the moon. A malfunction in the Agena B guidance system resulted in excessive spacecraft velocity. The spacecraft's solar cells did not provide power and reversed command signals caused the telemetry antenna to lose earth acquisition. This made reception of the flight-path correction signal impossible and rendering its television cameras useless. Reversed command signals caused the telemetry antenna to lose earth acquisition, and mid-course correction was not possible. The spacecraft missed the Moon by 725 km and went into solar orbit. Gamma-ray data were collected for 4 hours prior to the loss of power. Ranger V was to have relayed television pictures of the lunar surface and rough-landed an instrumented capsule containing a seismometer. The spacecraft was tracked for 8 hours, 44 minutes, before its small reserve battery went dead. Additional Details: Ranger 5. 1962 October 19 - NASA Headquarters' recent decision to cut the MSC budget for fiscal year 1963 from $687 million to $660 million. Spacecraft: Gemini. Wesley L. Hjornevik, Manned Spacecraft Center (MSC) Assistant Director for Administration, described to members of MSC's senior staff the implications of NASA Headquarters' recent decision to cut the MSC budget for fiscal year 1963 from $687 million to $660 million, the entire reduction to be borne by the Gemini program. Hjornevik feared that the Gemini budget, already tight, could absorb so large a cut only by dropping the paraglider, Agena, and all rendezvous equipment from the program. Gemini Project Office (GPO) reported that funding limitations had already forced Martin and McDonnell to reduce their level of activity. The first Gemini flight (unmanned) was rescheduled for December 1963, with the second (manned) to follow three months later, and subsequent flights at two-month intervals, with the first Agena (fifth mission) in August or September 1964. This four-month delay imposed by budget limitations required a large-scale reprogramming of Gemini development work, reflected chiefly in drastic reduction in the scale of planned test programs. Details of the necessary reprogramming had been worked out by December 20, when GPO Manager James A. Chamberlin reported that December 1963 was a realistic date for the first Gemini flight. Gemini funding for fiscal year 1963 totaled $232.8 million. 1962 October 19 - 18:15 GMT - Cape Canaveral LC11. Atlas F 14F Research and development launch Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1962 October 25 - Manned Spacecraft Center informed Lockheed that Gemini program budget readjustments required reprogramming the Gemini-Agena program. Subsequent meetings on November 2 and November 20 worked out the changes necessary to implement the Agena program at minimum cost. The overall test program for the Agena and its propulsion systems was significantly reduced, but in general neither the scope nor the requirements of the Agena program were altered. The major result of the reprogramming was a four-month slip in the scheduled launch date of the first Agena (to September 1964); this delay was about a month and a half less than had been anticipated when reprogramming began. In addition, Lockheed was to continue its program at a reduced level through the rest of 1962, a period of about six weeks, and to resume its normal level of activity on January 1, 1963. 1962 October 26 - 10:59 GMT - Vandenberg 576A1. Atlas D 159D NTMP K-5 / Pod 20 Target Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi). 1962 November 7 - 19:43 GMT - Cape Canaveral LC11. Atlas F 16F Research and development launch Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1962 November 11 - 20:17 GMT - Vandenberg SLC3W. Atlas Agena B 128D / Agena B SPS 2405 Samos 11 Mass: 1,860 kg (4,100 lb). Spacecraft: Samos. Agency: U.S. Air Force. Perigee: 128 km (79 mi). Apogee: 292 km (181 mi). Inclination: 96.00 deg. Period: 88.70 min. Second generation photo surveillance; radio relay of images; Satellite and Missile Observation Satellite. Poor results. SAMOS project cancelled. 1962 November 13 - Cooper named for Mercury MA-9 1-day orbital mission Flight: Mercury MA-9. Gordon Cooper was named as the pilot for Mercury-Atlas 9 (MA-9) 1-day orbital mission slated for April 1963. Alan Shepard, pilot of Mercury-Redstone 3 (MR-3) was designated as backup pilot. 1962 November 14 - 22:36 GMT - Vandenberg OSTF2. Atlas F 13F FAILURE: Failure. Research and development launch Agency: USAF AFSC. Apogee: 300 km (180 mi). 1962 November 15 - Dyess AFB -. Atlas SMS 578 operational. Dyess AFB SMS 578 operational 1962 November 16 - "T-back" pod proposed as the Gemini rendezvous target instead of the Agena. Andre J. Meyer, Jr., of Gemini Project Office reported that Space Technology Laboratories was conducting a study for NASA Headquarters on a 'T-back' pod to be used in the spacecraft adapter as the rendezvous target instead of the Agena. The pod would be stabilized but would have no translation capabilities. Although it would be almost as expensive as the Agena, it would avoid separate launch problems. 1962 November 16 - Mercury spacecraft 15A delivered to Cape Canaveral Spacecraft: Mercury. Flight: Mercury MA-10. Mercury spacecraft 15A was delivered to Cape Canaveral for the Mercury-Atlas 10 (MA-10) orbital manned 1-day mission. 1962 November 28 - Retrofire initiated 2 seconds late during Mercury MA-8 Retrofire was reported to have initiated 2 seconds late during the Mercury-Atlas 8 (MA-8) mission. Because of this, the mechanics and tolerances of the Mercury orbital timing device were reviewed for the benefit of operational personnel, and the procedural sequence for Mercury retrofire initiation was outlined. 1962 November 28 - Mercury Simulator 2 modified to the 1-day configuration. Spacecraft: Mercury. Flight: Mercury MA-9. Mercury Simulator 2 was modified to the 1-day Mercury orbital configuration in preparation for the Mercury-Atlas 9 (MA-9) flight. 1962 November 30 - Walker AFB -. Atlas SMS 579 operational. Walker AFB SMS 579 operational By the end of 1962 - Atlas D Mercury s/n 77D Mercury MA-9A (cancelled) Spacecraft: Mercury. Crew: Cooper. Flight: Mercury MA-9A. NASA’s Mercury orbital operations plan of July 19, 1961 had four spacecraft equipped for three-orbit flights. However by Schirra’s flight the seven-astronaut corps was down to four. So even thought the flight-ready SC19 had been delivered to Cape Canaveral on March 20, 1962, the decision was taken to cancel the remaining short-duration mission and move directly to an 18 orbit mission. 1962 December 5 - 21:25 GMT - Cape Canaveral LC11. Atlas F 21F Research and development test Agency: USAF AFSC. Apogee: 1,400 km (800 mi). Last Atlas F R&D; flight. 1962 December 12 - 11:38 GMT - Vandenberg 576A3. Atlas D 161D NTMP K-6 Target mission Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi). 1962 December 17 - 20:36 GMT - Vandenberg SLC3E. Atlas Agena B 131D / Agena B 1205 FAILURE: Failure. Midas 6 Mass: 2,000 kg (4,400 lb). Spacecraft: Midas. Agency: U.S. Air Force. Missile Defense Alarm System. Carried ERS-3, ERS-4 subsatellites. 1962 December 18 - 17:26 GMT - Vandenberg OSTF1. Atlas E 64E FAILURE: Failure. NTMP K-4 ABM test Agency: USAF AFSC. Apogee: 10 km (6 mi). 1962 December 20 - Plattsburgh AFB -. Atlas SMS 556 - last Atlas squadron - operational. Plattsburgh AFB SMS 556 (last Atlas squadron) operational 1962 December 22 - 09:29 GMT - Vandenberg 576A1. Atlas D 160D NTMP K-7 / Pod 4 ABM sensor test / plume characterization mission Agency: USAF SAC. Apogee: 2,259 km (1,403 mi). 1963 January 3 - Mercury MA-9 flight to go 22 orbits. Tentative plans were made by NASA to extend the Mercury-Atlas 9 (MA-9) flight from 18 to 22 orbits. 1963 January 9 - Flight Operations Division outlined detailed requirements for the remote stations of the worldwide tracking network. Each station would need five consoles: Gemini system, Agena system, command, aeromedical, and maintenance and operations. The Gemini and Agena consoles would have 42 analog display meters and 40 on/off indicators. 1963 January 14 - MSC assumed complete responsibility for the Gemini target vehicle program. Manned Spacecraft Center (MSC) assumed complete responsibility for the Gemini target vehicle program from Marshall Space Flight Center following a meeting between MSC and Marshall on January 11 establishing procedures for the transfer. Marshall was to continue to participate actively in an advisory capacity until March 1 and thereafter as technical consultant to MSC upon request. All other NASA Atlas-Agena programs were transferred to Lewis Research Center in a move aimed at freeing Marshall to concentrate on Saturn launch vehicle development and consolidating Atlas launch vehicle technology at Lewis. NASA Headquarters had decided to effect the transfer on October 12, 1962. 1963 January 21 - James E Webb, Administrator of NASA, and Robert S McNamara, Secretary of Defense, concluded a major policy agreement defining the roles of NASA and Department of Defense (DOD) in Project Gemini. The agreement provided for the establishment of a joint NASA-DOD Gemini Program Planning Board. The board would plan experiments, conduct flight tests, and analyze and disseminate results. NASA would continue to manage Project Gemini, while DOD would take part in Gemini development, pilot training, preflight checkout, launch, and flight operations, and would be specifically responsible for the Titan II launch vehicle and the Atlas-Agena target vehicle. DOD would also contribute funds toward the attainment of Gemini objectives. 1963 January 25 - 10:44 GMT - Vandenberg 576B2. Atlas D 39D FAILURE: Failure. NTMP K-9/OT ABM test Agency: USAF SAC. Apogee: 100 km (60 mi). 1963 January 31 - 08:51 GMT - Vandenberg 576A3. Atlas D 176D NTMP K-12 ABM test Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). 1963 February 5-6 - Gemini Rendezvous and Reentry Panel meeting. At a Gemini Rendezvous and Reentry Panel meeting, it was reported that attempts to obtain information on flight controller procedures to command the Agena in orbit had been delayed by the Air Force Agena security program. 1963 February 12 - Objectives of the Mercury-Atlas 9 (MA-9) manned 1-day mission were published. Flight: Mercury MA-9. This was the ninth flight of a production Mercury spacecraft to be boosted by an Atlas launch vehicle and the sixth manned United States space flight. Additional Details: Objectives of the Mercury-Atlas 9 (MA-9) manned 1-day mission were published.. 1963 February 12 - The Manned Spacecraft Center announced a mid-May flight for Mercury-Atlas 9 (MA-9). Flight: Mercury MA-9. Originally scheduled for April, the launch date was delayed by a decision to rewire the Mercury-Atlas flight control system, as a result of the launch vehicle checkout at the plant inspection meeting. 1963 February 13 - 11:55 GMT - Vandenberg 576A1. Atlas D 182D NTMP K-8 / NC20.133 ABM test Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). 1963 February 15 - Agena target vehicle checkout plans were presented at a meeting of the Gemini Management Panel. Spacecraft: Gemini. Upon receipt at Cape Canaveral, the target vehicle would be inspected and certified. After this action, mechanical mate and interface checks with the target docking adapter would be accomplished. Agena-Gemini spacecraft compatibilty tests would then be conducted, and the Agena would undergo validation and weight checks. Subsequently, a joint checkout of the spacecraft and Agena would be conducted with tests on the Merritt Island radar tower. 1963 February 28 - 09:02 GMT - Vandenberg 576A3. Atlas D 188D NTMP K-10 ABM test Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). 1963 March 1 - 21:00 GMT - Cape Canaveral LC11. Atlas F 134F ABRES REX-I / Pod 1 Re-entry vehicle test Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi). 1963 March 5 - Gemini Project Office discussed with contractors the establishment of a philosophy for the final phase of the rendezvous mission. Spacecraft: Gemini. They agreed on the following general rules: (1) when the launch was on time, the terminal maneuver would be initiated when the Agena came within range of the spacecraft's sensors, which would occur between spacecraft insertion and first apogee; (2) automatic and optical terminal guidance techniques would always back each other up, one method being selected as an objective for each mission and the other serving as a standby; (3) during early rendezvous missions, the terminal phase would be initiated by the third spacecraft apogee or delayed until the twelfth because of range radar tracking limitations; (4) for the same reason, no midcourse corrections should be made during orbits 4 through 11; (5) in case of extreme plane or phase errors, the Agena would be maneuvered to bring it within the spacecraft's maneuver capability; and (6) after such gross Agena maneuvers, the Agena orbit would be recircularized and two orbits of spacecraft catchup would precede the initiation of terminal rendezvous plan. 1963 March 10 - 02:42 GMT - Vandenberg 576B3. Atlas D 102D FAILURE: Failure. Operational missile test Agency: USAF SAC. Apogee: 0 km ( mi). 1963 March 12 - 05:21 GMT - Vandenberg 576B2. Atlas D 64D Operational missile test Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). 1963 March 15 - 11:38 GMT - Vandenberg 576B1. Atlas D 46D FAILURE: Failure. TALL TREE 1 operational test launch Agency: USAF SAC. Apogee: 300 km (180 mi). 1963 March 16 - 02:05 GMT - Vandenberg 576D. Atlas F 63F OT TALL TREE 5 operational test launch Agency: USAF SAC. Apogee: 1,400 km (800 mi). 1963 March 16 - 08:32 GMT - Vandenberg 576A1. Atlas D 193D FAILURE: Failure. NTMP K-14/NC20.145 Target/Aeronomy mission Agency: USAF SAC. Apogee: 300 km (180 mi). 1963 March 21 - 21:10 GMT - Vandenberg OSTF2. Atlas F 83F Research and development launch Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1963 March 24 - 00:29 GMT - Vandenberg 576E. Atlas F 52F FAILURE: Failure. OT TALL TREE 4 operational test launch Agency: USAF SAC. Apogee: 10 km (6 mi). 1963 April - Bell Aerosystems successfully completed initial firing of the Gemini Agena Model 8247 engine at its Buffalo plant early in the month. The Model 8247 engine for the Gemini Agena's primary propulsion system was developed from the Model 8096 currently being flown in satellite and probe programs for NASA and the Air Force. Unlike the operational engine, the new engine was capable of being restarted several times in orbit, a Gemini program requirement. The principle change in the new engine was the substitution of liquid propellants for solid pyrotechnic 'starter cans' to start the gas generator. The unit tested was the development engine that had been assembled in March. In mid-April, the test engine was shipped to Arnold Engineering Development Center (AEDC), Tullahoma, Tennessee, for further development tests. At AEDC, test cell arrangements were completed April 12, with testing scheduled to begin in May. 1963 April 22 - Representatives of Air Force Space Systems Division (SSD), Manned Spacecraft Center, and Lockheed met in Sunnyvale for the first management review of the Gemini Agena target vehicle (GATV). Patterned after similar meetings regularly held between SSD, Lewis Research Center, and Lockheed on medium space vehicle satellite and probe programs, the Gemini Target Management Review Meetings encompassed a comprehensive monthly review of the status of the GATV program. 1963 April 22 - Mercury Spacecraft 20 mated to Atlas launch vehicle Spacecraft: Mercury. Flight: Mercury MA-9. Spacecraft 20 was moved from Hanger S at Cape Canaveral to Complex 14 and mated to Atlas launch vehicle 130-D in preparation for the Mercury-Atlas 9 (MA-9) mission. The first simulated flight test was begun immediately. 1963 April 24 - 20:59 GMT - Vandenberg OSTF1. Atlas E 65E Research and development test Agency: USAF AFSC. Apogee: 1,600 km (900 mi). First successful E missile from OSTF-1, SMS 576 1963 April 27 - 02:03 GMT - Cape Canaveral LC11. Atlas F 135F ABRES REX-II re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1963 April 29 - NASA Headquarters approved rescheduling of the Gemini flight program as proposed by Gemini Project Office (GPO). Spacecraft: Gemini. Late delivery of the spacecraft systems coupled with the unexpectedly small number of Mercury systems incorporated in the Gemini spacecraft had forced GPO to review the flight program critically. In the revised program, the first flight was still set for December 1963 and was still to be unmanned, but it was now to be orbital rather than suborbital to flight-qualify launch vehicle subsystems and demonstrate the compatibility of the launch vehicle and spacecraft; no separation or recovery was planned. The second mission, originally a manned orbital flight, now became an unmanned suborbital ballistic flight schedule for July 1964. Its primary objection was to test spacecraft reentry under maximum heating-rate reentry conditions; it would also qualify the launch vehicle and all spacecraft systems required for manned orbital flight. The third flight, formerly planned as a manned orbital rendezvous mission, became the first manned flight, a short-duration (probably three-orbit) systems evaluation flight scheduled for October 1964. Subsequent flights were to follow at three-month intervals, ending in January 1967. Rendezvous terminal maneuvers were planned for missions 3 (if flight duration permitted) and 4, a seven-day mission using a rendezvous pod. The sixth flight was to be a 14-day long-duration mission identical to 4 except that no rendezvous maneuver missions with the Atlas-launched Agena D target vehicle. Water landing by parachute was planned for the first six flights and land landing by paraglider from flight 7 on. 1963 April 30 - Improvements to the Mercury pressure suit for Mercury MA-9 Spacecraft: Mercury Space Suit. Flight: Mercury MA-9. A number of improvements had been made to the Mercury pressure suit for the Mercury-Atlas 9 (MA-9) flight. Additional Details: Improvements to the Mercury pressure suit for Mercury MA-9. 1963 May 2 - Charles W Mathews, new Acting Manager of Project Gemini, reviewed the current status of the spacecraft, launch vehicles, and ground facilities for the Gemini Management Panel. Modifications of launch complexes 19 and 14, of the tracking network, and of Atlantic Missile Range checkout facilities were all on schedule, although no margin remained for complex 19 work. The Atlas and Agena presented no problems, but the Gemini launch vehicle schedule was tight; technical problems, notably stage I longitudinal oscillations and stage II engine instability, were compounded by funding difficulties. The Gemini spacecraft, suffering from late deliveries by subcontractors, was being reprogrammed. 1963 May 9 - 20:06 GMT - Vandenberg SLC3E. Atlas Agena B 119D / Agena B S01 1206 Midas 7 Mass: 2,000 kg (4,400 lb). Spacecraft: Midas. Agency: USAF. Perigee: 3,609 km (2,242 mi). Apogee: 3,680 km (2,280 mi). Inclination: 87.30 deg. Period: 166.40 min. MIDAS 7 was the first operational MIDAS mission and the first equipped with the W-37 sensor. During its six weeks of operation, MIDAS 7 recorded nine US ICBM launches, including the first missile launch ever detected from space. 1963 May 15 - 13:04 GMT - Cape Canaveral LC14. Atlas D 130D Mercury MA-9 Mass: 1,376 kg (3,033 lb). Spacecraft: Mercury. Agency: NASA MSC. Perigee: 163 km (101 mi). Apogee: 265 km (164 mi). Inclination: 32.50 deg. Period: 88.70 min. Crew: Cooper. Flight: Mercury MA-9. Final Mercury mission, Faith 7, was piloted by Astronaut L. Gordon Cooper, Jr. 1963 June 1 - Atlas F propellant loading accident. Exploded during propellant loading (Walker AFB 1) 1963 June 2 - 00:26 GMT - Walker AFB Missile Site 579. Atlas F 77F Error mission Agency: USAF. Apogee: 0 km ( mi). 1963 June 4 - 20:12 GMT - Vandenberg OSTF1. Atlas E 62E Research and development launch Agency: USAF AFSC. Apogee: 1,600 km (900 mi). 1963 June 8 - Mercury MA-10 environmental control system changes Spacecraft: Mercury. Flight: Mercury MA-10. In preparation for the Mercury-Atlas 10 (MA-10) mission, should the flight be approved by NASA Headquarters, several environmental control system changes were made in spacecraft 15B. Particularly involved were improvements in the hardware and flexibility of the urine and condensate systems. With regard to the condensate portion, Gordon Cooper, in his press conference, indicated that the system was not easy to operate during the flight of Faith 7 (MA-9). 1963 June 12 - Vandenberg SLC3E. Atlas Agena B 139D / Agena B SPS 1204 FAILURE: Failure. Midas 8 Mass: 2,000 kg (4,400 lb). Spacecraft: Midas. Agency: U.S. Air Force. Missile Defense Alarm System. Carried ERS-7, ERS-8 subsatellites. 1963 June 12 - 09:03 GMT - Vandenberg 576A3. Atlas D 198D NTMP Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). 1963 June 19 - The Cape Gemini/Agena Test Integration Working Group met to define "Plan X" test procedures and responsibilities. Spacecraft: Gemini. The purpose of Plan X was to verify the Gemini spacecraft's ability to command the Agena target vehicle both by radio and hardline; to exercise all command, data, and communication links between the spacecraft, target vehicle, and mission control in all practical combinations, first with the two vehicles about six feet apart, then with the vehicles docked and latched but not rigidized; and to familiarize the astronauts with operating the spacecraft/target vehicle combination in a simulated rendezvous mission. Site of the test was to be the Merritt Island Launch Area Radar Range Boresight Tower ('Timber Tower'), a 65 x 25 x 50-foot wooden structure. 1963 July 3 - 21:13 GMT - Vandenberg 576C. Atlas E 69E Demonstration and shakedown operations launch Agency: USAF SAC. Apogee: 1,600 km (900 mi). 1963 July 12 - 20:45 GMT - Vandenberg SLC4W. Atlas Agena D 201D / Agena D S01A 4702 KH 7-01 (Gambit) Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 173 km (107 mi). Apogee: 212 km (131 mi). Inclination: 95.30 deg. Period: 88.30 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1963 July 15 - Development tests of the Agena 8247 engine ended in an emergency shutdown. Development tests of the Agena Model 8247 main engine at Arnold Engineering Development Center ended when the latch-type gas generator valve failed in testing, making an emergency shutdown of the engine necessary. The wrong choice of emergency shutdown procedures caused turbine overspeed and total failure of the engine's turbine pump assembly. As a result of this failure, the valve was redesigned. Because success of the new design was doubtful, a parallel program was initiated to design and develop an alternative valve configuration, solenoid-operated rather than latch-type. Intensive development testing followed; and in a meeting at Bell Aerosystems on November 15, the solenoid type was selected for use in the first flight system of the Agena target vehicle. The new valve allowed significant reductions in engine complexity and increased reliability, but the development effort imposed a serious delay in Preliminary Flight Rating Tests, which had been scheduled to begin in September 1963. 1963 July 19 - 03:51 GMT - Vandenberg SLC3E. Atlas Agena B 75D / Agena B S01 1207 Midas 9 Mass: 2,000 kg (4,400 lb). Spacecraft: Midas. Agency: USAF. Perigee: 3,676 km (2,284 mi). Apogee: 3,726 km (2,315 mi). Inclination: 88.40 deg. Period: 167.90 min. Missile Defense Alarm System. Did not eject ERS 10 subsatellite. 1963 July 26 - 19:19 GMT - Vandenberg OSTF1. Atlas E 24E FAILURE: Failure. Demonstration and shakedown operations launch Agency: USAF SAC. Apogee: 300 km (180 mi). 1963 July 30 - 18:36 GMT - Vandenberg 576C. Atlas E 70E Demonstration and shakedown operations launch Agency: USAF SAC. Apogee: 1,600 km (900 mi). 1963 July 31 - 20:52 GMT - Vandenberg 576B1. Atlas D 143D ST COOL WATER I test Agency: USAF SAC. Apogee: 1,000 km (600 mi). 1963 August 24 - 09:50 GMT - Vandenberg OSTF1. Atlas E 72E NTMP/OT DASO test Agency: USAF SAC. Apogee: 1,600 km (900 mi). 1963 August 28 - 23:10 GMT - Vandenberg 576B3. Atlas D 142D ST COOL WATER II test Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). 1963 September 5 - Lockheed's contract for the Gemini Agena target vehicle (GATV) was amended. As a result of the seven-and-one-half-month relaxation of the required launch date for the first GATV, Lockheed was directed to use the improved version of the standard Agena, the AD-62 block of vehicles, instead of AD-13. The AD-62 block originally included the multistart engine, subsequently slipped to the AD-71 block. Lockheed accordingly was directed in January 1964 to substitute the AD-71 for AD-62. The combined effect of these changes was to use up much of the seven-and-one-half-month leeway. The change to AD-62 caused a two-month slip, and changing to AD-71 added a five-week slip. With much of the contingency time gone, the Agena schedule was now tight, and further slippage threatened to cause launch delays. 1963 September 6 - 19:30 GMT - Vandenberg SLC4W. Atlas Agena D 212D / Agena D S01A 4701 KH 7-02 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 171 km (106 mi). Apogee: 243 km (150 mi). Inclination: 94.40 deg. Period: 88.70 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1963 September 6 - 21:59 GMT - Vandenberg 576B2. Atlas D 63D FAILURE: Failure. ST COOL WATER III test Agency: USAF SAC. Apogee: 200 km (120 mi). 1963 September 11 - 21:00 GMT - Vandenberg 576B1. Atlas D 84D FAILURE: Failure. ST COOL WATER IV test Agency: USAF SAC. Apogee: 1,700 km (1,000 mi). 1963 September 25 - 11:04 GMT - Vandenberg 576C. Atlas E 71E FAILURE: Failure. Demonstration and shakedown operations launch Agency: USAF SAC. Apogee: 100 km (60 mi). 1963 September 27 - Electro-Mechanical Research successfully tested the compatibility of airborne and ground station PCM (pulse code modulated) telemetry equipment. The tests demonstrated that Gemini spacecraft and Agena telemeter and recorder formats were compatible with NASA ground stations. 1963 October - Atlas D Mercury s/n 144D Mercury MA-10 (cancelled) Spacecraft: Mercury. Crew: Shepard. Flight: Mercury MA-10. Alan Shepard, and others pushed for a six day Mercury 10 endurance mission. This would give America the manned space endurance record for the first time and also cover the biological objectives of the first two Gemini missions. The Mercury 15B capsule had already been modified for long-duration flight and Shepard had the name 'Freedom 7 II' painted on the side. But the risk and work pending on Gemini persuaded NASA managers not to undertake another mission. 1963 October 4 - 05:17 GMT - Vandenberg OSTF2. Atlas F 45F FAILURE: Failure. Research and development launch Agency: USAF AFSC. 1963 October 7 - 21:31 GMT - Vandenberg 576B3. Atlas D 163D FAILURE: Failure. ST COOL WATER V test Agency: USAF SAC. Apogee: 10 km (6 mi). By the end of 1963 - Atlas D Mercury s/n 152D Mercury MA-11 (cancelled) Spacecraft: Mercury. Crew: Grissom. Flight: Mercury MA-11. From October 25, 1961 until April 1962 NASA’s Mercury program plan included four one-day flights in 1963. By October 1962 the decision had been quietly taken to limit the long-duration flights to only MA-9 and MA-10. MA-10 was fnally cancelled in turn after the successful MA-9 mission. 1963 October 17 - 02:37 GMT - Cape Canaveral LC13. Atlas Agena D 197D / Agena D 1801 Vela 2 Mass: 220 kg (480 lb). Spacecraft: Vela. Agency: USAF. Perigee: 101,081 km (62,808 mi). Apogee: 116,582 km (72,440 mi). Inclination: 38.70 deg. Period: 6,486.20 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1963 October 25 - 18:59 GMT - Vandenberg SLC4W. Atlas Agena D 224D / Agena D S01A 4703 KH 7-03 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 123 km (76 mi). Apogee: 312 km (193 mi). Inclination: 99.00 deg. Period: 88.80 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1963 October 28 - 03:15 GMT - Cape Canaveral LC11. Atlas F 136F FAILURE: Failure. ABRES WAC-1 / Pod 21 Reentry test / plume mission Agency: USAF AFSC. Apogee: 500 km (310 mi). 1963 November - Lockheed included a milestone schedule for the Gemini Agena target vehicle (GATV) in its monthly progress report for the first time since January 1963. The new schedule reflected the revised Gemini flight program of April 29 and the corresponding revision of the Agena program which followed. It displayed key events in the progress of the first GATV taking place between five and six months later than the January schedule. Engineering development was now scheduled to be completed by May 15, 1964, rather than by December 11, 1963. Completion of modification and final assembly was now planned for June 12 rather than January 10, 1964; preliminary vehicle systems testing was rescheduled from April 10 to September 11, 1964. Special tests, including a Radio frequency Interference Test in the later schedule in addition to the hot-firing scheduled earlier, were to end November 20 instead of May 22, 1964. Final Vehicle Systems Tests were to be completed December 18 instead of June 19, 1964, with shipment to follow on January 6, 1965, rather than June 30, 1964. Launch was now expected on April 15, 1965, seven and one-half months later than the September 1, 1964, date that had been planned in January 1963. 1963 November 4 - 09:34 GMT - Vandenberg 576A1. Atlas D 232D ABRES REX-III re-entry vehicle test flight Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). 1963 November 13 - 22:35 GMT - Vandenberg 576B2. Atlas D 158D FAILURE: Failure. ST COOL WATER VI test Agency: USAF SAC. Apogee: 100 km (60 mi). By the end of 1963 - Atlas D Mercury s/n 167D Mercury MA-12 (cancelled) Spacecraft: Mercury. Crew: Schirra. Flight: Mercury MA-12. From October 25, 1961 until April 1962 NASA’s Mercury program plan included four one-day flights in 1963. By October 1962 the decision had been quietly taken to limit the long-duration flights to only MA-9 and MA-10. MA-10 was fnally cancelled in turn after the successful MA-9 mission. 1963 November 17 - Douglas Aircraft Corporation, Tulsa, Oklahoma, began a series of tests to demonstrate the structural integrity of the Gemini target docking adapter (TDA) during shroud separation. The shroud, which protected the TDA during the launch and ascent of the Agena target vehicle, was tested under simulated altitude conditions to show proper operation of pyrotechnic devices and adequate clearance between shroud and TDA during separation. Successfully concluded on November 21, and tests demonstrated the compatibility of the TDA with the shroud system during operational performance, with no indication of damage or failure of the TDA structure. 1963 November 27 - 19:03 GMT - Cape Canaveral LC36A. Atlas Centaur AC-2 / Centaur D 126D Atlas Centaur 2 Mass: 4,620 kg (10,180 lb). Spacecraft: Surveyor. Agency: NASA LeR. Perigee: 469 km (291 mi). Apogee: 1,478 km (918 mi). Inclination: 30.40 deg. Period: 104.60 min. Launch vehicle test. Launch vehicle put dummy payload into geosynchronous transfer orbit. First successful Centaur (liquid hydrogen-fueled) flight. 1963 December 18 - 09:52 GMT - Vandenberg 576A1. Atlas D 233D ABRES LORV-8 re-entry vehicle test flight Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). 1963 December 18 - 21:45 GMT - Vandenberg SLC4W. Atlas Agena D 227D / Agena D S01A 4802 KH 7-04 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 122 km (75 mi). Apogee: 266 km (165 mi). Inclination: 97.90 deg. Period: 88.50 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1963 December 18 - 22:56 GMT - Vandenberg OSTF2. Atlas F 109F Research and development launch Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1964 January 1 - NASA Headquarters directed Gemini Project Office to take the radar and rendezvous evaluation pod out of Gemini-Titan (GT) missions 3 and 4. Spacecraft: Gemini. Flight: Gemini 4, Gemini 5. GT-4 would be a battery-powered long-duration flight. The pod would go on GT-5, and thus the first planned Agena flight would probably slip in the schedule. 1964 January 30 - 15:49 GMT - Cape Canaveral LC12. Atlas Agena B 199D (AA8) / Agena B 6008 (AA8) Ranger 6 Mass: 362 kg (798 lb). Spacecraft: Ranger 6-7-8-9. Agency: NASA/JPL. Impacted Moon but TV camera malfunctioned. A midcourse trajectory correction was accomplished early in the flight by ground control. On February 2, 1964, 65.5 hours after launch, Ranger 6 impacted the Moon on the eastern edge of Mare Tranquillitatis (Sea of Tranquility). No camera data were obtained, probably because of failure due to an arc-over in the TV power system when it inadvertently turned on during the period of booster-engine separation. 1964 February 5 - Bell Aerosystems began Preliminary Flight Rating Tests (PFRT) of the Agena primary propulsion system (PPS). Tests were expected to be completed April 24 but were not actually concluded until late June. Testing proceeded with only minor problems through the first week of April. But in the following week PPS testing encountered what proved to be a six-week delay when the test unit's fuel and oxidizer start tanks failed. The two start tanks, stainless steel canisters with an internal bellows arrangement, supplied the propellants required to initiate the main engine start sequence. Visible longitudinal cracks in the outer shell allowed the gas which forced the propellants out of the tank to escape. Investigation revealed that the cracks had resulted from intergranular corrosion of the stainless steel tanks. The defective tanks were replaced by start tanks with a new heat-treated shell (delivered April 24), and PFRT resumed early in May. 1964 February 12 - 19:59 GMT - Vandenberg OSTF1. Atlas E 48E FAILURE: Failure. ST Agency: USAF SAC. Apogee: 0 km ( mi). 1964 February 13 - 18:11 GMT - Walker AFB Missile Site 579. Atlas F 88F FAILURE: Exploded during propellant loading. Accident Agency: USAF. Apogee: 0 km ( mi). Operational ICBM test at Walker AFB. 1964 February 16 - Bell Aerosystems delivered the first Gemini Agena Model 8247 main engine to Lockheed. This engine was installed in the propulsion test vehicle assembly (PTVA), a unit to be used for a series of tests on the Agena primary and secondary propulsion systems at Lockheed's Santa Cruz Test Base. Bell delivered the two secondary propulsion system modules for the PTVA on March 6 and 14. Installation was completed and the PTVA delivered to Santa Cruz Test Base on March 26. 1964 February 17 - Bell Aerosystems began Preliminary Flight Rating Tests (PFRT) of the Agena secondary propulsion system (SPS). After proceeding through the acceleration and vibration test phases of PFRT without incident, the SPS began calibration firings early in April. The failure of a propellant valve in Unit I (the 16-pound thrust chamber fired prior to starting the main engine in order to orient propellant) of the SPS imposed a minor delay, but a more serious problem emerged late in April during high-temperature firings. The wall of the Unit II 200-pound thrust chamber burned through near the injector face after an accumulated PFRT firing time of 354 seconds, below the specification limit of 400 seconds although well in excess of the maximum orbital useful time of 200 seconds. The thrust chamber was replaced and testing continued, but PFRT, originally scheduled to end June 19, was first slipped to July 8, and finally completed in mid-August. To resolve the burn-through problem, Bell began a test program in September to determine the cause of failure. 1964 February 25 - 18:59 GMT - Vandenberg SLC4W. Atlas Agena D 285D / Agena D S01A 4803 KH 7-05 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 135 km (83 mi). Apogee: 135 km (83 mi). Inclination: 95.60 deg. Period: 87.20 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1964 February 25 - 20:22 GMT - Cape Canaveral LC11. Atlas E 5E ABRES WAC-3 / Pod 18 Re-entry vehicle test Agency: USAF AFSC. Apogee: 1,600 km (900 mi). 1964 February 28 - Gemini Project Manager Charles W. Mathews informed Manned Spacecraft Center senior staff of efforts to control Gemini spacecraft weight and configuration more tightly. Mathews had assigned Lewis R. Fisher of his office to head a Systems Integration Office within Gemini Project Office to oversee these efforts by keeping very precise accounts of spacecraft weight, interface actions between the spacecraft and launch vehicle, and interface actions between the spacecraft and the Agena target vehicle. 1964 March 9 - 21:54 GMT - Walker AFB Missile Site 579. Atlas F 90F FAILURE: Exploded during propellant loading. Accident Agency: USAF. Apogee: 0 km ( mi). Operational ICBM test at Walker AFB. 1964 March 11 - 20:14 GMT - Vandenberg SLC4W. Atlas Agena D 296D / Agena D S01A 4804 KH 7-06 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 163 km (101 mi). Apogee: 203 km (126 mi). Inclination: 95.70 deg. Period: 88.20 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1964 March 20 - Test program to increase confidence in critical components of the Gemini Agena target vehicle. Manned Spacecraft Center (MSC) approved Air Force Space Systems Division's (SSD) recommendations for a test program to increase confidence in 16 critical electronic and electrical components of the Gemini Agena target vehicle. The program included complete electromagnetic interference (EMI) testing of all components peculiar to the Gemini mission, as well as elevated stress tests and extended life tests. SSD had also recommended subsystem-level, as well as component-level, EMI testing, but this part of the program MSC disapproved. SSD directed Lockheed to proceed with the program on March 23. EMI tests were scheduled to be completed by July 1, stress and life tests by September 1, 1964. 1964 March 25 - Gemini mission plans for the first Agena rendezvous flight. Spacecraft: Gemini. At a meeting of the Gemini Project Office's Trajectories and Orbits Panel, members of Flight Operations Division described two mission plans currently under consideration for the first Agena rendezvous flight. One was based on the concept of tangential Agena and spacecraft orbits, as proposed by Howard W. Tindall, Jr., and James T. Rose when they were members of Space Task Group. The second plan, based on a proposal by Edwin E. Aldrin, Jr., then of Air Force Space Systems Division, involved orbits which were concentric rather than tangential. The most significant advantage of the second plan was that it provided the greatest utilization of onboard backup techniques; that is, it was specifically designed to make optimum use of remaining onboard systems in the event of failure in the inertial guidance system platform, computer, or radar. 1964 March 26 - The propulsion test vehicle assembly (PTVA) arrived at Santa Cruz Test Base. It consisted of a basic Agena structure with propellant pressurization, feed-and-load system, the primary propulsion system (PPS), and two secondary propulsion system (SPS) modules attached to the aft rack. The test program called for loading operations and hot firings of both propulsion systems to establish the adequacy of PPS and SPS propellant loading systems and associated ground equipment, to demonstrate proper overall system operation, and to provide engineering data on systems operation and the resulting environment. Start of testing was delayed by the PPS start tank problems which showed up during Preliminary Flight Rating Tests at Bell Aerosystems during April. Lockheed returned the PTVA main engine start tanks to Bell, where they were inspected and found to be defective. New tanks were ready by mid-May, but additional minor problems delayed the initiation of hot-firing until June 16. 1964 April 1 - 20:22 GMT - Cape Canaveral LC11. Atlas F 137F ABRES WAC-2 / Pod 2 Reentry test / plume mission Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1964 April 3 - 20:26 GMT - Vandenberg OSTF2. Atlas F 3F FAILURE: Failure. Demonstration and shakedown operations launch Agency: USAF SAC. Apogee: 0 km ( mi). 1964 April 13 - Air Force Space Systems Division (SSD) recommended a Gemini Agena launch on a nonrendezvous mission to improve confidence in target vehicle performance before undertaking a rendezvous mission. Flight: Gemini 12. Gemini Project Office (GPO) rejected this plan, regarding it as impractical within current schedule, launch sequence, and cost restraints. Additional Details: Air Force Space Systems Division (SSD) recommended a Gemini Agena launch on a nonrendezvous mission to improve confidence in target vehicle performance before undertaking a rendezvous mission.. 1964 April 14 - 21:42 GMT - Cape Canaveral LC12. Atlas D 263D FIRE 1 Agency: NASA?. Apogee: 837 km (520 mi). FIRE was a subscale model of the Apollo capsule used to verify the spacecraft's hypersonic flight and thermal characteristics. An Atlas D launch vehicle lifted a Project Fire spacecraft from Cape Kennedy in the first test of the heat that would be encountered by a spacecraft reentering the atmosphere at lunar-return velocity. During the spacecraft's fall toward earth, a solid-fuel Antares II rocket behind the payload fired for 30 seconds, increasing the descent speed to 40,501 kilometers (25,166 miles) per hour. Instruments in the spacecraft radioed temperature data to the ground. The spacecraft exterior reached an estimated temperature of 11,400 K (20,000 degrees F). About 32 minutes after launch, the spacecraft impacted into the Atlantic Ocean. The mission, sponsored by Langley Research Center, provided reentry heating measurements needed to evaluate heatshield materials and information on the communications blackout during reentry. 1964 April 23 - 16:19 GMT - Vandenberg SLC4W. Atlas Agena D 351D / Agena D S01A 4805 KH 7-07 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 150 km (90 mi). Apogee: 336 km (208 mi). Inclination: 103.60 deg. Period: 89.40 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1964 April 30 - First Agena D for the Gemini program. Spacecraft: Gemini. Flight: Gemini 12. Air Force Space Systems Division (SSD) accepted the first Agena D (AD-71) for the Gemini program. The Agena D was a production-line vehicle procured from Lockheed by SSD for NASA through routine procedures. Following minor retrofit operations, the vehicle, now designated Gemini Agena target vehicle 5001, entered the manufacturing final assembly area at the Lockheed plant on May 14. There began the conversion of the Agena D into a target vehicle for Gemini rendezvous missions. Major modifications were installation of a target docking adapter (supplied by McDonnell), an auxiliary equipment rack, external status displays, a secondary propulsion system, and an L-band tracking radar. 1964 May 11 - Sea trials of the tracking ship, Rose Knot, were begun on Chesapeake Bay to study the effects of shock vibrations on Gemini equipment. A few vibration problems with the pulse-code-modulation system were reported. Gemini-Agena systems were simulated by an instrumented Lockheed Super Constellation aircraft. 1964 May 13 - Flight Operations Division presented the Gemini Program Office's proposed mission plan No. 3 for the first Agena rendezvous flight to the Trajectories and Orbits Panel. Plan No. 3, as yet incomplete, provided for rendezvous at first apogee on a perfectly nominal mission. 1964 May 14 - Altus AFB 577-6. Atlas F 61F FAILURE: Exploded during propellant loading. Accident Agency: USAF. Apogee: 0 km ( mi). Operational missile test at Altus AFB. 1964 May 19 - 19:21 GMT - Vandenberg SLC4W. Atlas Agena D 350D / Agena D S01A 4806 KH 7-08 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 141 km (87 mi). Apogee: 380 km (230 mi). Inclination: 101.10 deg. Period: 89.70 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1964 June 3 - Lockheed inaugurated the Gemini Extra Care Program to reduce the incidence of equipment failures and discrepancies. In cooperation with Air Force and NASA, Lockheed inaugurated the Gemini Extra Care Program to reduce the incidence of equipment failures and discrepancies resulting from poor or careless workmanship during the modification and assembly of the Agena target vehicle. The program included increased inspection, exhortation, morale boosters, special awards, and other activities aimed at fostering and maintaining a strong team spirit at all levels. Results of the program were evidenced in a drastic decline in the number of FEDRs (Failed Equipment and Discrepancy Reports) recorded in the Gemini final manufacturing area on successive vehicles. 1964 June 16 - Lockheed began test-firing the propulsion test vehicle assembly at its Santa Cruz Test Base, after a delay caused primarily by problems with the Agena main engine start tanks. The program, undertaken because of extensive changes in the propulsion system required to adapt the standard Agena D for use in Gemini missions, comprised three series of static-firing tests. The first series, in addition to providing base line performance for both primary and secondary propulsion systems (PPS and SPS), also subjected one SPS module to the dynamic and acoustic environment created by 55 seconds of PPS firing. The second series, successfully completed July 16, simulated a possible Gemini mission profile, including multiple firings and various coast and burn times on both PPS and SPS units. The third series, which concluded the test program on August 7, involved a maximum number of starts and minimum-impulse firings on both PPS and SPS. All firings were successful, and review of test data revealed only minor anomalies. The entire test program comprised 27 PPS firings for a run time totaling 545 seconds, 30 SPS Unit I firings totaling 286 seconds, and 11 SPS Unit II firings totaling 268 seconds. Post-test disassembly revealed no physical damage to any equipment. 1964 June 18 - 14:56 GMT - Vandenberg 576A1. Atlas D 243D ABRES LORV-1 / Pod 31 Re-entry vehicle test Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). 1964 June 24 - Construction of Gemini-Agena facilities at complex 14 was completed. General Dynamics finished the installation and checkout of equipment in the Launch Operations Building on July 20. Lockheed equipment in the Launch Operations Building was installed and checked out by July 31. 1964 June 30 - 14:04 GMT - Cape Canaveral LC36A. Atlas Centaur AC-3 / Centaur D 135D FAILURE: Centaur hydraulics failure. Centaur AC-3 Mass: 4,815 kg (10,615 lb). Agency: NASA. Apogee: 500 km (310 mi). Centaur test. Launch vehicle was to have put payload into geosynchronous transfer orbit 1964 July 6 - 18:51 GMT - Vandenberg SLC4W. Atlas Agena D 352D / Agena D S01A 4807 KH 7-09 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 121 km (75 mi). Apogee: 345 km (214 mi). Inclination: 92.90 deg. Period: 89.10 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1964 July 17 - 08:22 GMT - Cape Canaveral LC13. Atlas Agena D 216D / Agena D 1802 Vela 3 Mass: 220 kg (480 lb). Spacecraft: Vela. Agency: USAF. Perigee: 102,500 km (63,600 mi). Apogee: 104,101 km (64,685 mi). Inclination: 39.10 deg. Period: 6,024.80 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1964 July 28 - 16:50 GMT - Cape Canaveral LC12. Atlas Agena B 250D (AA9) / Agena B 6009 (AA9) Ranger 7 Mass: 362 kg (798 lb). Spacecraft: Ranger 6-7-8-9. Agency: NASA/JPL. First successful Ranger; returned 4,308 photos before lunar impact. The Atlas- Agena B inserted the Agena and Ranger into a 192 km altitude Earth parking orbit. Half an hour after launch a second burn of the Agena engine injected the spacecraft into a lunar intercept trajectory. After separation from the Agena, the solar panels were deployed, attitude control activated, and spacecraft transmissions switched from the omniantenna to the high-gain antenna. The next day the planned mid-course maneuver was successfully initiated at 10:27 GMT. The only anomaly during flight was a brief loss of two-way lock on the spacecraft by the DSIF tracking station at Cape Kennedy following launch. Ranger 7 reached the Moon on 31 July. The F-channel began its one minute warm up 18 minutes before impact. The first image was taken at 13:08:45 GMT at an altitude of 2110 km. Transmission of 4,308 photographs of excellent quality occurred over the final 17 minutes of flight. The final image taken before impact had a resolution of 0.5 meters. The spacecraft encountered the lunar surface in direct motion along a hyperbolic trajectory, with an incoming asymptotic direction at an angle of -5.57 degrees from the lunar equator. The orbit plane was inclined 26.84 degrees to the lunar equator. After 68.6 hours of flight, Ranger 7 impacted in an area between Mare Nubium and Oceanus Procellarum (subsequently named Mare Cognitum) at approximately 10.35 S latitude, 339.42 E longitude. Impact occurred at 13:25:48.82 GMT at a velocity of 2.62 km/s. 1964 July 29 - 09:22 GMT - Vandenberg 576A3. Atlas D 248D NTMP KX-13 Target mission Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). 1964 August 7 - 20:12 GMT - Vandenberg 576E. Atlas F 110F Demonstration and shakedown operations launch Agency: USAF SAC. Apogee: 1,400 km (800 mi). 1964 August 14 - 22:00 GMT - Vandenberg SLC4E. SLV-3 Agena D 7101 / Agena D S01A 4808 KH 7-10 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 165 km (102 mi). Apogee: 300 km (180 mi). Inclination: 95.40 deg. Period: 89.10 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1964 August 27 - 09:54 GMT - Vandenberg OSTF1. Atlas E 57E ST/KX-48 Target mission Agency: USAF SAC. Apogee: 1,600 km (900 mi). 1964 August 31 - 15:46 GMT - Vandenberg 576D. Atlas F 36F Demonstration and shakedown operations launch Agency: USAF SAC. Apogee: 1,400 km (800 mi). 1964 September - Atlas SMS 564 deactivated. Warren-1 AFB SMS 564 deactivated 1964 September 5 - 01:23 GMT - Cape Canaveral LC12. Atlas Agena B 195D (AA10) / Agena B 6501 (AA10) OGO 1 Mass: 487 kg (1,073 lb). Spacecraft: OGO. Agency: NASA GSF. Perigee: 21,446 km (13,325 mi). Apogee: 127,394 km (79,158 mi). Inclination: 44.60 deg. Period: 3,809.50 min. Two experiment booms failed to properly deploy, with one of the booms obscuring a horizon scanner's view of earth. As a result, the spacecraft attitude could not be earth oriented and OGO 1 remained spin stabilized at 5 rpm. Nevertheless, data from all 20 experiments on board was received, although at a 'less than expected capacity' from some of them. Twelve of the experiemnts were particle studies and two were magnetic field studies. In addition, there was one experiment for each of the following types of studies: interplanetary dust, VLF, Lyman-alpha, Gegenschein, atmospheric mass, and radio astronomy. During September 1964, acceptable data were received over 70% of the orbital path. By June 1969, data acquisition was limited to 10% of the orbital path. Spacecraft operation was restricted to Spring and Fall due to power supply limitations. There were 11 such 3-month periods prior to the spacecraft being put into stand-by mode on 25 November 1969. By April 1970 the spacecraft perigee had increased to 46,000 km and the inclination had increased to 58.8 deg. All support was terminated November 1, 1971. 1964 September 15 - 15:27 GMT - Vandenberg 576A1. Atlas D 245D ABRES LORV-3 / Pod 26 Re-entry vehicle test Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). 1964 September 22 - 13:10 GMT - Vandenberg 576A3. Atlas D 247D NTMP KX-19 Target mission Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). 1964 September 23 - Manned Spacecraft Center announced at a Trajectories and Orbit Panel meeting that several changes in the ground rules had been made to the Gemini-Titan 6 mission plan. Flight: Gemini 6. One change concerned a previous assumption of a 20-day Agena lifetime; it was now established that the Agena would not be modified to provide this. As a result, greater emphasis had to be placed on ensuring spacecraft launch on the same day as the Agena, primarily by relieving the constraint of no Agena maneuvers. The restriction on using Agena maneuvers had been removed to increase the probability of achieving rendezvous within the few days that the Agena would remain an acceptable target. 1964 September 23 - 20:06 GMT - Vandenberg SLC4E. SLV-3 Agena D 7102 KH 7-11 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 143 km (88 mi). Apogee: 303 km (188 mi). Inclination: 92.90 deg. Period: 88.90 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1964 September 24 - Lockheed completed the modification and final assembly of Gemini Agena target vehicle 5001 and transferred it to systems test complex C-10 at the Lockheed plant. Flight: Gemini 12. Lockheed began the task of hooking the vehicle up for systems testing the next day, September 25. 1964 October 8 - Vandenberg SLC4E. SLV-3 Agena D 7103 FAILURE: Failure. KH-7 12 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: U.S. Air Force. KH-7 type satellite. 1964 October 23 - 18:30 GMT - Vandenberg SLC4W. Atlas Agena D 353D KH 7-13 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 140 km (80 mi). Apogee: 267 km (165 mi). Inclination: 95.50 deg. Period: 88.50 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1964 October 28 - Bell Aerosystems successfully fired the Agena secondary propulsion system (SPS) in a test of the system's ability to survive a launch hold. The SPS had first gone through a 20-day dry (unloaded) period, followed by a 20-day wet (loaded) period. The system reverted to hold condition and was successfully refired November 2. 1964 November 5 - 19:22 GMT - Cape Canaveral LC13. Atlas Agena D 289D (AA11) / Agena D 6931 (AA11) FAILURE: Launch fairing failure. Mariner 3 Mass: 260 kg (570 lb). Spacecraft: Mariner 3-4. Agency: NASA/JPL. Mars probe; launch fairing failure prevented Mars flyby. Solar Orbit (Heliocentric). Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). 1964 November 10 - Gemini Agena target vehicle (GATV) 5001 competed a simulated flight (ascent and orbit) at Lockheed test complex C-10. Flight: Gemini 12. Minor anomalies required portions of the test to be rerun. This concluded GATV 5001 systems tests in preparation for captive-firing tests to be conducted at Lockheed's Santa Cruz Test Base. The vehicle was shipped November 30. 1964 November 28 - 14:22 GMT - Cape Canaveral LC12. Atlas Agena D 288D (AA12) / Agena D 6932 (AA12) Mariner 4 Mass: 260 kg (570 lb). Spacecraft: Mariner 3-4. Agency: NASA/JPL. Mariner 4 provided the first up close pictures of Mars. The protective shroud covering Mariner 4 was jettisoned and the Agena D/Mariner 4 combination separated from the Atlas D booster at 14:27:23 GMT on 28 November 1964. The Agena D first burn from 14:28:14 to 14:30:38 put the spacecraft into an Earth parking orbit and the second burn from 15:02:53 to 15:04:28 injected the craft into a Mars transfer orbit. Mariner 4 separated from the Agena D at 15:07:09 and began cruise mode operations. The solar panels deployed and the scan platform was unlatched at 15:15:00 and Sun acquisition occurred 16 minutes later. A midcourse maneuver made on 5 December 1964. After a 228 day cruise, the spacecraft flew by Mars on July 14 and 15, 1965. Planetary science mode was turned on at 15:41:49 GMT on 14 July. The camera sequence started at 00:18:36 GMT on July 15 and 21 pictures plus 21 lines of a 22nd picture were taken. The images covered a discontinuous swath of Mars starting near 40 N, 170 E, down to about 35 S, 200 E, and then across to the terminator at 50 S, 255 E, representing about 1% of the planet's surface. The closest approach was 9,846 km from the Martian surface at 01:00:57 GMT 15 July 1965. The images taken during the flyby were stored in the onboard tape recorder. At 02:19:11 GMT Mariner 4 passed behind Mars as seen from Earth and the radio signal ceased. The signal was reacquired at 03:13:04 GMT when the spacecraft reappeared. Cruise mode was then re-established. Transmission of the taped images to Earth began about 8.5 hours after signal reacquisition and continued until 3 August. All images were transmitted twice to insure no data was missing or corrupt. The spacecraft performed all programmed activities successfully and returned useful data from launch until 22:05:07 GMT on 1 October 1965, when the distance from Earth (309.2 million km) and the antenna orientation temporarily halted signal acquisition. In 1967 Mariner 4 returned to the vicinity of Earth again and engineers decided to use the ageing craft for a series of operational and telemetry tests to improve their knowledge of the technologies that would be needed for future interplanetary spacecraft. The cosmic dust detector registered 17 hits in a 15 minute span on 15 September, part of an apparent micrometeoroid shower which temporarily changed the spacecraft attitude and probably slightly damaged the thermal shield. On 7 December the gas supply in the attitude control system was exhausted, and on December 10 and 11 a total of 83 micrometeoroid hits were recorded which caused perturbation of the attitude and degradation of the signal strength. On 21 December 1967 communications with Mariner 4 were terminated. Results The total data returned by the mission was 5.2 million bits. All experiments operated successfully with the exception of the ionization chamber/Geiger counter which failed in February, 1965 and the plasma probe, which had its performance degraded by a resistor failure on 6 December 1964. The images returned showed a Moon-like cratered terrain (which later missions showed was not typical for Mars, but only for the more ancient region imaged by Mariner 4). A surface atmospheric pressure of 4.1 to 7.0 mb was estimated and no magnetic field was detected. 1964 November 30 - Lockheed shipped Gemini Agena target vehicle (GATV) 5001 to its Santa Cruz Test Base for captive-firing tests. Flight: Gemini 12. Primary test objective was verifying the operational capabilities of the GATV during actual firing of the primary and secondary propulsion systems. Additional Details: Lockheed shipped Gemini Agena target vehicle (GATV) 5001 to its Santa Cruz Test Base for captive-firing tests.. 1964 December - Atlas SMS 565 deactivated. Warren-2 AFB SMS 565 deactivated 1964 December 1 - 08:45 GMT - Vandenberg 576A1. Atlas D 210D ABRES LORV-5 re-entry vehicle test flight Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). 1964 December 4 - 11:09 GMT - Vandenberg 576A3. Atlas D 300D NTMP RMV-303 Target mission Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). 1964 December 4 - 18:57 GMT - Vandenberg SLC4E. SLV-3 Agena D 7105 / Agena D 7105 KH 7-14 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 158 km (98 mi). Apogee: 357 km (221 mi). Inclination: 97.00 deg. Period: 89.70 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1964 December 11 - 14:25 GMT - Cape Canaveral LC36A. Atlas Centaur AC-4 / Centaur D 146D Surveyor SD-1 Mass: 2,944 kg (6,490 lb). Spacecraft: Surveyor. Agency: NASA/JPL. Perigee: 165 km (102 mi). Apogee: 178 km (110 mi). Inclination: 30.70 deg. Period: 87.80 min. Launch vehicle test. Centaur AC-4 put dummy Surveyor payload into geosynchronous transfer orbit 1964 December 12 - Gemini Program Office (GPO) reported that it had initiated contractual action to delete the eighth Agena from the Gemini Agena target vehicle program. On March 6, 1965, GPO reported its decision to eliminate the seventh Agena as well. 1964 December 15 - Atlas SMS 566 deactivated. Offutt AFB SMS 566 deactivated 1964 December 17 - Air Force Space Systems Division officially accepted Agena D (AD-82) for the Gemini program. Flight: Gemini 6. Lockheed then transferred it to the vehicle final assembly area for modification to Gemini Agena target vehicle 5002. Work was scheduled to begin in mid-January 1965. 1964 December 22 - 19:15 GMT - Vandenberg 576E. Atlas F 111F ST Agency: USAF SAC. Apogee: 1,400 km (800 mi). 1965 January 8 - 18:59 GMT - Vandenberg OSTF2. Atlas F 106F ST Agency: USAF SAC. Apogee: 1,400 km (800 mi). 1965 January 12 - 14:32 GMT - Vandenberg 576B1. Atlas D 166D NTMP RMV-302 Target mission Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). 1965 January 20 - Gemini Agena target vehicle 5001 underwent a successful hot-firing test at Lockheed's Santa Cruz Test Base. Flight: Gemini 12. The test simulated a full 20,000-second mission, including multiple firings of both the primary and secondary propulsion systems and transmission of operational data in real time to two PCM (pulse-code-modulated) telemetry ground stations, one at the test site and one in Sunnyvale. Major test anomaly was a series of command programmer time-accumulator jumps, seven of which totaled 77,899 seconds. The vehicle was removed from the test stand on February 1 and returned to Sunnyvale. 1965 January 21 - 21:34 GMT - Vandenberg 576B3. Atlas D 172D FAILURE: Failure. OV1-01 Mass: 85 kg (187 lb). Spacecraft: OV1. Agency: U.S. Air Force. Failure. 1965 January 23 - 20:09 GMT - Vandenberg SLC4W. SLV-3 Agena D 7106 / Agena D 7106 KH 7-15 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 146 km (90 mi). Apogee: 291 km (180 mi). Inclination: 102.50 deg. Period: 88.90 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1965 February - Lockheed initiated a "Ten-point Plan for C&C; Equipment." The Agena command and communication (C and C) system comprised the electronic systems for tracking the vehicle, for monitoring the performance of its various subsystems, and for verifying operating commands for orbital operations. Because of the unique requirements of the Gemini mission, in particular rendezvous and docking, Lockheed had had to design and develop a new C and C system for the Gemini target vehicle. Numerous failures and problems calling for rework during the initial manufacturing stages of the C and C system suggested the existence of mechanical and electronic design deficiencies. Aerospace, which had assumed technical surveillance functions for the Gemini Agena in the fall of 1964, was instrumental in bringing these problems to the attention of Air Force and Lockheed top management. Among the results of the 10-point plan were several redesigned programmer circuits and packaging changes, closer monitoring of vendor work, expedited failure analysis, and improved quality control. 1965 February 1 - Gemini Agena target vehicle (GATV) 5001 was removed from the test stand at Santa Cruz Test Base and returned to Sunnyvale. Flight: Gemini 12. After a brief stopover in systems test complex C-10, the vehicle was transferred to the anechoic chamber for elecromagnetic interference and radio-frequency-interference tests. Additional Details: Gemini Agena target vehicle (GATV) 5001 was removed from the test stand at Santa Cruz Test Base and returned to Sunnyvale.. 1965 February 17 - 17:05 GMT - Cape Canaveral LC12. Atlas Agena B 196D (AA13) / Agena B 6006 (AA13) Ranger 8 Mass: 366 kg (806 lb). Spacecraft: Ranger 6-7-8-9. Agency: NASA/JPL. Returned 7137 photos before lunar impact. The Atlas- Agena B booster injected the Agena and Ranger 8 into an Earth parking orbit at 185 km altitude 7 minutes after launch. Fourteen minutes later a 90 second burn of the Agena put the spacecraft into lunar transfer trajectory, and several minutes later the Ranger and Agena separated. The Ranger solar panels were deployed, attitude control activated, and spacecraft transmissions switched from the omni-directional antenna to the high-gain antenna by 21:30 GMT. On 18 February at a distance of 160,000 km from Earth the planned mid-course manoeuvre took place, involving reorientation and a 59 second rocket burn. During the 27 minute manoeuvre, spacecraft transmitter power dropped severely, so that lock was lost on all telemetry channels. This continued intermittently until the rocket burn, at which time power returned to normal. The telemetry dropout had no serious effects on the mission. A planned terminal sequence to point the cameras more in the direction of flight just before reaching the Moon was cancelled to allow the cameras to cover a greater area of the Moon's surface. Ranger 8 reached the Moon on 20 February 1965. The first image was taken at 9:34:32 GMT at an altitude of 2510 km. Transmission of 7,137 photographs of good quality occurred over the final 23 minutes of flight. The final image taken before impact has a resolution of 1.5 meters. The spacecraft encountered the lunar surface in a direct hyperbolic trajectory, with incoming asymptotic direction at an angle of -13.6 degrees from the lunar equator. The orbit plane was inclined 16.5 degrees to the lunar equator. After 64.9 hours of flight, impact occurred at 09:57:36.756 GMT on 20 February 1965 in Mare Tranquillitatis at approximately 2.67 degrees N, 24.65 degrees E. Impact velocity was slightly less than 2.68 km/s. 1965 February 27 - 11:11 GMT - Vandenberg 576A1. Atlas D 211D ABRES LORV-4 re-entry vehicle test flight Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). 1965 March 2 - 09:52 GMT - Vandenberg 576A3. Atlas D 301D NTMP RMV-301 Target mission Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). 1965 March 2 - 13:25 GMT - Cape Canaveral LC36A. Atlas Centaur AC-5 / Centaur D 156D FAILURE: Failure. Surveyor SD-1 Mass: 951 kg (2,096 lb). Spacecraft: Surveyor. Agency: NASA. Launch vehicle test. Launch vehicle was to have put payload into geosynchronous transfer orbit 1965 March 9 - Gemini Agena target vehicle 5001 completed electromagnetic compatibility tests in the anechoic chamber at Sunnyvale. Flight: Gemini 12. It remained in the chamber, however, until March 17 while Lockheed verified the corrective action that had been taken to eliminate programmer time-accumulator jumps and telemetry synchronization problems. The vehicle was then transferred to systems test complex C-10 for final Vehicle Systems Tests on March 18. 1965 March 10 - Air Force Space Systems Division repeated its position that on Gemini-Titan 6 the nominal plan should not call for use in orbit of the Agena primary propulsion system. Flight: Gemini 6. At a meeting of the Gemini Trajectory and Orbits Panel, Air Force Space Systems Division repeated its position that on Gemini-Titan 6 the nominal plan should not call for use in orbit of the Agena primary propulsion system, since it would not be qualified in actual flight before this mission. Additional Details: Air Force Space Systems Division repeated its position that on Gemini-Titan 6 the nominal plan should not call for use in orbit of the Agena primary propulsion system.. 1965 March 12 - 19:25 GMT - Vandenberg SLC4W. SLV-3 Agena D 7104 / Agena D 7104 KH 7-16 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 223 km (138 mi). Apogee: 358 km (222 mi). Inclination: 107.50 deg. Period: 90.30 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1965 March 12 - 23:21 GMT - Vandenberg 576B3. Atlas D 154D ABRES MTV-2 re-entry vehicle test flight Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). 1965 March 18 - Gemini Agena target vehicle (GATV) 5001 was transferred from the anechoic chamber to systems test complex C-10. Flight: Gemini 12. Six days were scheduled for vehicle modifications before beginning final systems tests. Additional Details: Gemini Agena target vehicle (GATV) 5001 was transferred from the anechoic chamber to systems test complex C-10.. 1965 March 21 - 21:37 GMT - Cape Canaveral LC12. Atlas Agena B 204D (AA14) / Agena B 6007 (AA14) Ranger 9 Mass: 366 kg (806 lb). Spacecraft: Ranger 6-7-8-9. Agency: NASA/JPL. Ranger 9, last of the series, returned 5814 images before lunar impact. The target was Alphonsus, a large crater about 12 degrees south of the lunar equator. The probe was timed to arrive when lighting conditions would be at their best. The Atlas- Agena B booster injected the Agena and Ranger 9 into an Earth parking orbit at 185 km altitude. A 90 second Agena 2nd burn put the spacecraft into lunar transfer trajectory. This was followed by the separation of the Agena and Ranger. The initial trajectory was highly accurate; uncorrected, the craft would have landed only 650 km north of Alphonsus. 70 minutes after launch the command was given to deploy solar panels, activate attitude control, and switch from the omni-directional antenna to the high-gain antenna. The accuracy of the initial trajectory enabled delay of the planned mid-course correction from 22 March to 23 March when the manoeuvre was initiated at 12:03 GMT. After orientation, a 31 second rocket burn at 12:30 GMT, and reorientation, the manoeuvre was completed at 13:30 GMT. Ranger 9 reached the Moon on 24 March 1965. At 13:31 GMT a terminal manoeuvre was executed to orient the spacecraft so the cameras were more in line with the flight direction to improve the resolution of the pictures. Twenty minutes before impact the one-minute camera system warm-up began. The first image was taken at 13:49:41 at an altitude of 2363 km. Transmission of 5,814 good contrast photographs was made during the final 19 minutes of flight. The final image taken before impact has a resolution of 0.3 meters. The spacecraft encountered the lunar surface with an incoming asymptotic direction at an angle of -5.6 degrees from the lunar equator. The orbit plane was inclined 15.6 degrees to the lunar equator. After 64.5 hours of flight, impact occurred at 14:08:19.994 GMT at approximately 12.83 S latitude, 357.63 E longitude in the crater Alphonsus. Impact velocity was 2.67 km/s. Millions of Americans followed the spacecraft's descent via real time television coverage provided to the three networks of many of the F-channel images (primarily camera B but also some camera A pictures) were provided for this flight. The pictures showed the rim and floor of the crater in fine detail: in those just prior to impact, objects less than a foot in size were discernible. A panel of scientists presented some preliminary conclusions from Ranger IX at a press conference that same afternoon. Crater rims and ridges inside the walls, they believed, were harder and smoother than the moon's dusty plains, and therefore were considered likely sites for future manned landings. Generally, the panel was dubious about landing on crater floors however. Apparently, the floors were solidified volcanic material incapable of supporting a spacecraft. Investigators believed several types of craters were seen that were of nonmeteoric origin. These findings reinforced arguments that the moon at one time had experienced volcanic activity. Later the images were shown to the press as a continuous-motion movie, leading astronaut Wally Schirra to yell ‘bail out you fool!’ just before the final frame. 1965 March 23-24 - Gemini Agena Target Vehicle (GATV) Management-Technical Review. Flight: Gemini 12, Gemini 3. Representatives of Air Force Space Systems Division (SSD), Aerospace, Lockheed, and Gemini Program Office met at Sunnyvale for the monthly Gemini Agena Target Vehicle (GATV) Management-Technical Review. Additional Details: Gemini Agena Target Vehicle (GATV) Management-Technical Review.. 1965 March 25 - Six Atlas squadrons deactivated. Forbes AFB SMS 548, Warren-3 AFB SMS 549, Altus AFB SMS 577, Dyess AFB SMS 578, Walker AFB SMS 579, and Plattsburgh AFB SMS 556 all deactivated 1965 March 26 - 09:01 GMT - Vandenberg 576A1. Atlas D 297D ABRES LORV-7 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi). 1965 April 3 - 21:24 GMT - Vandenberg SLC4E. SLV-3 Agena D 7401 Snapshot Mass: 440 kg (970 lb). Spacecraft: Snapshot. Agency: USAF/AEC. Perigee: 1,270 km (780 mi). Apogee: 1,314 km (816 mi). Inclination: 90.30 deg. Period: 111.40 min. Only nuclear reactor ever orbited by the United States. The SNAP-10A reactor provided electrical power for an 8.5 mN ion engine using cesium propellant. The engine was shut off after one hour of operation when high-voltage spikes created electromagnetic interference with the satellite's attitude control system sensors. The reactor continued in operation, generating 39 kWt and more than 500 watts of electrical power for 43 days before the spacecraft telemetry failed. 1965 April 6 - 13:34 GMT - Vandenberg 576B1. Atlas D 150D ABRES WAC-4 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi). 1965 April 28 - 20:17 GMT - Vandenberg SLC4E. SLV-3 Agena D 7107 / Agena D 7107 KH 7-17 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 180 km (110 mi). Apogee: 259 km (160 mi). Inclination: 95.60 deg. Period: 89.00 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1965 May 6 - Gemini Agena target vehicle (GATV) 5001 completed vehicle systems testing with a final simulated flight. Flight: Gemini 12. The vehicle was disconnected from the test complex on May 14, and data analysis was completed May 19. Meanwhile, the First Article Configuration Inspection on GATV 5001 began on May 10. 1965 May 10 - First Article Configuration Inspection (FACI) of Gemini Agena target vehicle (GATV) 5001 at Sunnyvale. Flight: Gemini 12, Gemini 6. A team of representatives from NASA, Air Force Space Systems Division, Aerospace, and Lockheed began the First Article Configuration Inspection (FACI) of Gemini Agena target vehicle (GATV) 5001 at Sunnyvale. Additional Details: First Article Configuration Inspection (FACI) of Gemini Agena target vehicle (GATV) 5001 at Sunnyvale.. 1965 May 18 - Gemini Agena target vehicle (GATV) 5002 completed final assembly and was transferred to systems test complex C-10 at Sunnyvale to begin Vehicle Systems Tests. Flight: Gemini 6. The transfer had been scheduled for May 5 but was delayed by parts shortages, engineering problems, and considerable work backlog. The major source of delay was correcting a gap between the forward auxiliary rack and the vehicle; machining and aligning the rack and refinishing the scraped surfaces proved time-consuming. GATV 5002 was still short several items of command equipment. Systems testing began May 21. 1965 May 22 - 21:55 GMT - Cape Canaveral LC12. Atlas D 264D FIRE 2 Agency: USAF. Apogee: 817 km (507 mi). Suborbital reentry heating experiment using the FIRE subscale Apollo capsule. An Atlas D booster propelled the instrumented probe, called a "flying thermometer," into a ballistic trajectory over 805 km (500 mi) high. After 26 minutes of flight, when the spacecraft began its descent, a solid-fueled Antares rocket accelerated its fall. The probe entered the atmosphere at a speed of 40,877 km (25,400 mph) and generated temperatures of about 11,206K (20,000 degrees F). Data on heating were transmitted to ground stations throughout the descent. Thirty-two minutes after the launch - and but six minutes after the Antares was fired - the device impacted in the Atlantic about 8,256 km (5,130 mi) southeast of the Cape. 1965 May 27 - 19:30 GMT - Vandenberg SLC4E. SLV-3 Agena D 7108 / Agena D 7108 KH 7-18 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 149 km (92 mi). Apogee: 267 km (165 mi). Inclination: 95.60 deg. Period: 88.70 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1965 May 28 - 02:54 GMT - Vandenberg 576B3. Atlas D 68D / OV-1 FAILURE: Failure. OV1-03 Spacecraft: OV1. Agency: USAF AFSC. 1965 May 29 - Gemini Agena target vehicle 5001 arrived at Cape Kennedy following its conditional acceptance by the Air Force on May 27. Flight: Gemini 6. It was moved to the Missile Assembly Building (Hanger E) for testing. The target vehicle was mated with target docking adapter No. 1 on June 18, and Combined Interface Tests began June 19. Testing was completed July 8 with secondary propulsion system (SPS) functional and static leak checks, SPS installation and postinstallation checks, and thermal control surface preparation. Target vehicle 5001 was then transferred to complex 14 to be mated to target launch vehicle 5301. 1965 June 3 - 10:38 GMT - Vandenberg 576B2. Atlas D 177D NTMP RMV-304 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi). 1965 June 8 - 15:17 GMT - Vandenberg 576A1. Atlas D 299D ABRES LORV-6 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi). 1965 June 10 - 12:26 GMT - Vandenberg 576A3. Atlas D 302D NTMP RMV-303 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi). 1965 June 25 - Three Atlas squadrons deactivated. Fairchild AFB SMS 567, Schilling AFB SMS 550, and Lincoln AFB SMS 551 all deactivated 1965 June 25 - 19:30 GMT - Vandenberg SLC4E. SLV-3 Agena D 7109 / Agena D 7109 OPS 6749 Mass: 60 kg (132 lb). Spacecraft: SSF. Agency: NRO/USAF. Perigee: 496 km (308 mi). Apogee: 510 km (310 mi). Inclination: 107.60 deg. Period: 94.70 min. Radar monitoring. 1965 June 30 - Gemini Agena target vehicle 5002 completed Vehicle Systems Tests at Sunnyvale, and the final acceptance test was conducted. Flight: Gemini 6. The vehicle was disconnected from the test complex on July 13, after NASA, Air Force Space Systems Division, Aerospace, and Lockheed representatives agreed that all data discrepancies from the final systems tests had been resolved. 1965 July 1 - 09:54 GMT - Vandenberg 576B1. Atlas D 59D NTMP KX-32 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi). 1965 July 12 - 19:00 GMT - Vandenberg SLC4E. SLV-3 Agena D 7112 FAILURE: Failure. KH-7-20 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: U.S. Air Force. KH-7 type satellite. 1965 July 20 - 08:27 GMT - Cape Canaveral LC13. Atlas Agena D 225D / Agena D 1803 Vela 5 Mass: 235 kg (518 lb). Spacecraft: Vela. Agency: USAF. Perigee: 106,367 km (66,093 mi). Apogee: 115,839 km (71,978 mi). Inclination: 35.20 deg. Period: 6,679.00 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1965 July 22 - Simultaneous Launch Demonstration (SLD) of Gemini Atlas-Agena target vehicle and Gemini-Titan (GT) 5. Flight: Gemini 5. A Simultaneous Launch Demonstration (SLD) was conducted between the Gemini Atlas-Agena target vehicle on complex 14 and Gemini-Titan (GT) 5 on complex 19, in conjunction with the Wet Mock Simulated Launch (WMSL) of GT-5. Additional Details: Simultaneous Launch Demonstration (SLD) of Gemini Atlas-Agena target vehicle and Gemini-Titan (GT) 5.. 1965 July 23 - Air Force Space Systems Division formally accepted delivery of Gemini Agena target vehicle (GATV) 5002 after the vehicle acceptance team inspection had been completed. Flight: Gemini 6. The vehicle was then shipped by air to Eastern Test Range on July 24, arriving July 25. Although GATV 5002 was accepted, several items of equipment remained in 'not qualified' status, including the shroud, secondary and primary propulsion systems, and components of both the electrical power and command systems. 1965 July 23 - Standard Agena D (AD-108), which had been completed in June and held in storage, was transferred to Building 104 at Sunnyvale for modifications and final assembly as Gemini Agena target vehicle 5003. Flight: Gemini 8. While in storage, several pieces of AD-108 equipment had been removed for modification to the Gemini configuration. Final assembly began August 8. 1965 August 3 - 19:12 GMT - Vandenberg SLC4E. SLV-3 Agena D 7111 / Agena D 7111 KH 7-21 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 278 km (172 mi). Apogee: 352 km (218 mi). Inclination: 107.40 deg. Period: 90.80 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1965 August 4 - 12:43 GMT - Vandenberg 576B1. Atlas D 183D ABRES WAC-5 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi). 1965 August 5 - 13:21 GMT - Vandenberg 576A2. Atlas F 147F ABRES LORV-2A re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1965 August 11 - 14:31 GMT - Cape Canaveral LC36B. Atlas Centaur D AC-6 / Centaur D 151D Surveyor; Atlas Centaur 6 Mass: 950 kg (2,090 lb). Spacecraft: Surveyor. Agency: NASA/JPL. Centaur AC-6 launched dummy Surveyor payload into a barycentric / translunar orbit. 1965 August 23 - Gemini Agena target vehicle 5002 completed preliminary systems testing at Hanger E. Flight: Gemini 6. Gemini Agena target vehicle 5002 completed preliminary systems testing at Hanger E and was transferred to Merritt Island Launch Area, where it was joined by spacecraft No. 6 for Plan X testing. After ground equipment checks, Plan X tests proceeded on August 25. No significant interference problems were found, and testing ended on August 31. 1965 August 26 - 11:20 GMT - Vandenberg 576B2. Atlas D 61D NTMP KX-41 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi). 1965 September 1 - Final troubleshooting on Gemini Agena target vehicle (GATV) 5002 after Plan X testing at Merritt Island Launch Area (MILA) was completed. Flight: Gemini 6. The next day GATV 5002 was returned to Hanger E from MILA, where it began a series of tests to verify the operational readiness of all vehicle systems prior to erection and mating with the launch vehicle. 1965 September 8 - Representatives of Air Force Space Systems Division, Aerospace, and Lockheed attended a technical review of the flight verification test program for the oxidizer gas generator solenoid valve. This was the last remaining component of the Agena primary propulsion system needing test qualification. Testing had been completed August 26; disassembly, inspection, and evaluation were concluded September 3. The consensus of those attending was that the successful test program had demonstrated flightworthiness of this configuration. This concluded qualification of all propulsion system components. 1965 September 29 - 10:40 GMT - Vandenberg 576B1. Atlas D 125D NTMP KX-45 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi). 1965 September 30 - 19:20 GMT - Vandenberg SLC4E. SLV-3 Agena D 7110 / Agena D 7110 KH 7-22 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 237 km (147 mi). Apogee: 361 km (224 mi). Inclination: 95.60 deg. Period: 90.50 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1965 October 1 - Gemini Agena target vehicle 5002 was transported to complex 14 and mated to target launch vehicle 5301. Flight: Gemini 6. Preliminary checks were followed, on October 4, by the Joint Flight Acceptance Composite Test (J-FACT). J-FACT was a combined check of all contractors, the range, the vehicles, and aerospace ground equipment in a simulated countdown and flight; propellants and high pressure gases were not loaded, nor was the gantry removed. Simultaneous Launch Demonstration was successfully completed October 7. 1965 October 5 - 09:07 GMT - Vandenberg 576B3. Atlas D 34D NB20.170 RS OV1-02 Mass: 86 kg (189 lb). Spacecraft: OV1. Agency: USAF OAR. Perigee: 408 km (253 mi). Apogee: 2,735 km (1,699 mi). Inclination: 144.20 deg. Period: 117.60 min. Radiation data. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1965 October 7 - The Wet Mock Simulated Launch (WMSL) of Gemini-Titan (GT) 6 and the Simultaneous Launch Demonstration with GT-6 and the Gemini Atlas-Agena target vehicle were conducted. Flight: Gemini 6. Following WMSL, the spacecraft and launch vehicle were demated to allow the spacecraft battery to be replaced. They were remated October 8-13. Spacecraft Systems Test was completed October 15. Prelaunch testing concluded October 20 with the Simulated Flight Test. 1965 October 14 - Gemini Agena target vehicle 5003 was transferred to Vehicle Systems Test after completing final assembly on October 9. Flight: Gemini 8. Testing began October 18. 1965 October 25 - 15:00 GMT - Cape Canaveral LC14. SLV-3 Agena D 5301 / Agena D 5002 FAILURE: Exploded 6 minutes after takeoff. Failure. Gemini 6 Agena Target Mass: 3,261 kg (7,189 lb). Spacecraft: Gemini Agena Target Vehicle. Agency: NASA. Flight: Gemini 6, Gemini 7. The Agena target vehicle failed to reach orbit. Gemini 6, awaiting launch, was cancelled. In the ashes of this setback, the idea of launching Gemini 6 to rendezvous with Gemini 7 was born. 1965 October 27 - Catastrophic anomaly of Gemini Agena target vehicle (GATV) 5002 on October 25 defined as a mission failure. Flight: Gemini 6. NASA Associate Administrator Robert C. Seamans, Jr., informed George E. Mueller, Associate Administrator for Manned Space Flight, that the catastrophic anomaly of Gemini Agena target vehicle (GATV) 5002 on October 25 had been defined as a mission failure. Additional Details: Catastrophic anomaly of Gemini Agena target vehicle (GATV) 5002 on October 25 defined as a mission failure.. 1965 October 28 - Discrepancies remaining on Gemini Agena target vehicle 5001 cleared. Flight: Gemini 12. The major portion of 819 discrepancies remaining from the First Article Configuration Inspection (FACI) of Gemini Agena target vehicle 5001 in June were cleared; 128 that had not been applied against the acceptance document (DD-250) remained. All subsystem FACI discrepancies were also closed out during October. 1965 November 1 - The subpanel for Gemini VI of the Agena Flight Safety Review Board met at Lockheed. Flight: Gemini 6. The subpanel, chaired by Colonel John B. Hudson, Deputy Commander for Launch Vehicles, Air Force Space Systems Division, reviewed Lockheed's flight safety analysis of the failure of Gemini Agena target vehicle (GATV) 5002 on October 25. Additional Details: The subpanel for Gemini VI of the Agena Flight Safety Review Board met at Lockheed.. 1965 November 3 - The Agena Flight Safety Review Board met at Lockheed to continue its investigation of the failure of Gemini Agena target vehicle 5002 on October 25. Flight: Gemini 6. The board, chaired by George E. Mueller, NASA Associate Administrator of Manned Space Flight, reviewed the findings of the subpanel for Gemini VI and reached the same conclusion: the failure resulted from a hard start probably caused by the fuel lead. Additional Details: The Agena Flight Safety Review Board met at Lockheed to continue its investigation of the failure of Gemini Agena target vehicle 5002 on October 25.. 1965 November 8 - 19:26 GMT - Vandenberg SLC4E. SLV-3 Agena D 7113 / Agena D 7113 KH 7-23 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 280 km (170 mi). Apogee: 352 km (218 mi). Inclination: 93.90 deg. Period: 90.80 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1965 November 11 - Gemini launch vehicle (GLV) 7 and spacecraft No. 7 were electrically mated at complex 19. Flight: Gemini 7. An electrical interface jumper cable connected the spacecraft, suspended about six feet above stage II, to the GLV. Additional Details: Gemini launch vehicle (GLV) 7 and spacecraft No. 7 were electrically mated at complex 19.. 1965 November 12-13 - A symposium on hypergolic rocket ignition at altitude was held at Lockheed. Flight: Gemini 6. Because too little diagnostic information had been obtained from the flight of Gemini Agena target vehicle (GATV) 5002 to determine the exact nature of the probable hard start, it was not certain that the proposed modification - a return to oxidizer lead - would definitely prevent a recurrence of the malfunctions. Additional Details: A symposium on hypergolic rocket ignition at altitude was held at Lockheed.. 1965 November 15 - Gemini Agena target vehicle (GATV) engine modification and test program. Lockheed presented its proposed Gemini Agena target vehicle (GATV) engine modification and test program to Colonel A. J. Gardner, Gemini Target Vehicle Program Director, Air Force Space Systems Division (SSD). The proposal was immediately turned over to a three-man team comprising B. A. Hohmann (Aerospace), Colonel J. B. Hudson (Deputy Commander for Launch Vehicles, SSD), and L. E. Root (Lockheed) for consideration. On November 18, the group decided on a final version of the proposal that called for: (1) modifying the Agena engine to provide oxidizer lead during the start sequence, (2) demonstrating sea-level engine flightworthiness in tests at Bell Aerosystems, and (3) conducting an altitude test program at Arnold Engineering Development Center. The final proposal was presented to the GATV Review Board at Manned Spacecraft Center on November 20. 1965 November 19 - Air Force Space Systems Division (SSD) directed Lockheed to return Gemini Agena target vehicle (GATV) 5001 to Sunnyvale. Flight: Gemini 12. The GATV was still being stored in Hanger E, Eastern Test Range, minus its main engine which SSD had directed Lockheed to ship to Bell Aerosystems on November 9 for modification. Additional Details: Air Force Space Systems Division (SSD) directed Lockheed to return Gemini Agena target vehicle (GATV) 5001 to Sunnyvale.. 1965 November 24 - Lockheed submitted an engineering change proposal to Air Force Space Systems Division (SSD) for Project Surefire. Flight: Gemini 8, Gemini 9. Surefire was the code name for the Gemini Agena Target Vehicle (GATV) Modification and Test Program designed to correct the malfunction which had caused the failure of GATV 5002 on October 25. Additional Details: Lockheed submitted an engineering change proposal to Air Force Space Systems Division (SSD) for Project Surefire.. 1965 November 26 - McDonnell proposed building a backup target vehicle for Gemini rendezvous missions. Spacecraft: Gemini. Flight: Gemini 8. The augmented target docking adapter (ATDA) would serve as an alternative to the Gemini Agena target vehicle (GATV) if efforts to remedy the GATV problem responsible for the October 25 mission abort did not meet the date scheduled for launching Gemini VIII. Additional Details: McDonnell proposed building a backup target vehicle for Gemini rendezvous missions.. 1965 November 29 - 14:30 GMT - Vandenberg 576A1. Atlas D 200D NTMP KX-33 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi). 1965 December 14 - Air Force Space Systems Division authorized Lockheed to begin the disassembly and inspection of Gemini Agena target vehicle 5001 to determine the extent of refurbishment needed. Flight: Gemini 12. The vehicle was stripped down to its major structural components to expose all areas of possible contamination. 1965 December 17 - The Air Force accepted the main rocket engine for Gemini Agena target vehicle (GATV) 5003 after Bell Aerosystems had completed Project Surefire modifications. Flight: Gemini 8. The engine was shipped immediately and arrived at Lockheed December 18. Lockheed completed reinstalling the engine on December 20. GATV 5003 systems retesting began December 27 after other equipment modifications had been installed. 1965 December 20 - 13:39 GMT - Vandenberg 576B2. Atlas D 85D NTMP KX-31 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi). 1966 January 8 - Gemini Agena target vehicle (GATV) 5003 completed its final acceptance tests at Sunnyvale, after an elusive command system problem had made it necessary to rerun the final systems test (January 4). Flight: Gemini 8. No vehicle discrepancy marred the rerun. Air Force Space Systems Division formally accepted GATV 5003 on January 18, after the vehicle acceptance team inspection. It was shipped to Eastern Test Range the same day, but bad weather delayed delivery until January 21. GATV 5003 was to be the target vehicle for Gemini VIII. 1966 January 16 - Project Surefire verification testing began at Bell Aerosystems. Flight: Gemini 8. Bell's part in the test program was to demonstrate the sea-level flightworthiness of the modified Agena main engine. Bell completed testing on March 4 with a full 180-second mission simulation firing. The successful completion of this phase of the test program gave the green light for the launch of Gemini Agena target vehicle 5003, scheduled for March 15. 1966 January 17 - Gemini Program Office review of possible future mission activities. Flight: Gemini 10, Gemini 8, Gemini 9. At a NASA-McDonnell Management Panel meeting, W. B. Evans of Gemini Program Office reviewed possible future mission activities. Gemini VIII would have three periods of extravehicular activity (EVA) - two in daylight, one in darkness - and would undock during EVA with the right hatch snubbed against the umbilical guide and the astronaut strapped into the adapter section. Additional Details: Gemini Program Office review of possible future mission activities.. 1966 January 19 - 20:10 GMT - Vandenberg SLC4E. SLV-3 Agena D 7114 / Agena D 7114 KH 7-24 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 138 km (85 mi). Apogee: 259 km (160 mi). Inclination: 93.80 deg. Period: 88.40 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1966 January 22 - Gemini Agena target vehicle (GATV) 5003 was mated to target docking adapter (TDA) 3. Flight: Gemini 8. McDonnell had delivered TDA-3 to Cape Kennedy on January 8. The GATV/TDA interface functional test was completed January 24, and the vehicle was transferred to Merritt Island Launch Area for integrated tests with spacecraft No. 8 and extravehicular equipment, which were completed January 28. 1966 January 26 - Gemini Agena target vehicle (GATV) 5004 was transferred to the vehicle systems test area at Sunnyvale. Flight: Gemini 9. Its modified main engine had been received on schedule from Bell Aerosystems January 12 and installed by January 20. Because of GATV 5003 priority, however, several main electronic assemblies, including the command system, had been removed from GATV 5004 and used in GATV 5003 final acceptance tests. As a result, GATV 5004 had fallen eight days behind its scheduled transfer date, January 18. 1966 January 28 - Gemini Agena target vehicle (GATV) 5003 was returned to Hanger E after completing Plan X tests at Merritt Island Launch Area. Flight: Gemini 8. Systems Verification and Combined Interface Tests were conducted through February 18, followed by functional checks of the primary and secondary propulsion systems. Hanger E testing ended February 28, and the GATV was transferred to complex 14. 1966 February 2 - A mission planning meeting for Gemini flights IX through XII, held at McDonnell, was attended by members of the Gemini Program Office and Flight Operations Division. The last item on the agenda was a reminder from McDonnell that the Gemini spacecraft was capable of flying to a relatively high elliptic orbit from which it could safely reenter under certain circumstances. The type of orbit McDonnell suggested had an apogee of 500-700 nautical miles. This would involve using the Agena primary propulsion system both to get into this orbit and to return to a 161-mile circular orbit for nominal reentry. 1966 February 2 - Agena D (AD-129) was accepted by the Air Force for delivery to the Gemini program. Flight: Gemini 10. It was transferred to the final assembly area at Sunnyvale for modification to Gemini Agena target vehicle 5005. 1966 February 4 - The augmented target docking adapter (ATDA) arrived at Cape Kennedy. Modifications, testing, and troubleshooting were completed March 4. Flight: Gemini 9. The ATDA, which was intended to back up the Gemini Agena target vehicle (GATV), was then placed in storage (March 8) where it remained until May 17, when the failure of target launch vehicle 5303 prevented GATV 5004 from achieving orbit. The ATDA became the target for Gemini IX-A. 1966 February 10 - 09:48 GMT - Vandenberg 576A1. Atlas D 305D NTMP KX-38 / Pod 32 Reentry test / plume mission Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi). 1966 February 11 - 13:04 GMT - Vandenberg 576B2. Atlas D 86D NTMP KX-51 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi). 1966 February 15 - 20:30 GMT - Vandenberg SLC4E. SLV-3 Agena D 7115 / Agena D 7115 KH 7-25 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 142 km (88 mi). Apogee: 290 km (180 mi). Inclination: 96.50 deg. Period: 88.90 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1966 February 19 - 09:56 GMT - Vandenberg 576B1. Atlas D 73D NTMP KX-47 Re-entry Vehicle test Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi). 1966 February 27 - Gemini Agena target vehicle (GATV) 5004 completed systems testing at Sunnyvale. Flight: Gemini 9. It was formally accepted by the Air Force on March 11, following the vehicle acceptance team inspection. The next day (March 12), GATV 5004 was shipped by air to Eastern Test Range, arriving March 14. 1966 March 4 - 12:29 GMT - Vandenberg 576A1. Atlas D 303D FAILURE: Failure. NTMP KX-35 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 500 km (310 mi). 1966 March 6 - Gemini launch vehicle 8 and spacecraft No. 8 were mated for flight at complex 19. Flight: Gemini 8. The Simultaneous Launch Demonstration with the Gemini Atlas-Agena target vehicle on complex 14 was completed March 9. The Final Simulated Flight Test concluded prelaunch tests on March 10. 1966 March 16 - Gemini Agena target vehicle 5003 systems exercised. Flight: Gemini 10, Gemini 8. Following the early termination of Gemini VIII, Gemini Agena target vehicle (GATV) 5003 remained in orbit, where its various systems were extensively exercised. The main engine was fired nine times, four more than required by contract, and 5000 commands were received and executed by the command and communications system, as against a contractural requirement of 1000. Additional Details: Gemini Agena target vehicle 5003 systems exercised.. 1966 March 16 - 15:00 GMT - Cape Canaveral LC14. SLV-3 Agena D 5302 / Agena D 5003 Gemini 8 Agena Target Mass: 3,175 kg (6,999 lb). Spacecraft: Gemini Agena Target Vehicle. Agency: NASA MSC. Perigee: 285 km (177 mi). Apogee: 299 km (185 mi). Inclination: 28.90 deg. Period: 90.40 min. Flight: Gemini 8. Target vehicle for Gemini 8. 1966 March 18 - 20:30 GMT - Vandenberg SLC4E. SLV-3 Agena D 7116 / Agena D 7116 KH 7-26 Mass: 60 kg (132 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 162 km (100 mi). Apogee: 308 km (191 mi). Inclination: 101.00 deg. Period: 89.30 min. Not identified as a subsatellite ferret by McDowell. 1966 March 19 - 12:30 GMT - Vandenberg 576A1. Atlas D 304D NTMP KX-43 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi). 1966 March 21 - Gemini Agena target vehicle 5004 and spacecraft No. 9 began Plan X compatibility tests at Merritt Island Launch Area Radar Range. Spacecraft: Gemini. Flight: Gemini 9. 1966 March 22 - Agena D (AD-130) was formally accepted by the Air Force for the Gemini program and moved to Building 104 at Sunnyvale for modification and final assembly as Gemini Agena target vehicle 5006. Flight: Gemini 11. 1966 March 24 - Project Surefire test program not to be curtailed. Flight: Gemini 8. Air Force Space Systems Division and Lockheed agreed not to curtail the Project Surefire test program despite the excellent performance of Gemini Agena target vehicle (GATV) 5003 during the Gemini VIII mission. Additional Details: Project Surefire test program not to be curtailed.. 1966 March 30 - 09:20 GMT - Vandenberg 576B3. Atlas D 72D NB20.152 RS OV1-04 Mass: 88 kg (194 lb). Spacecraft: OV1. Agency: USAF OAR. Perigee: 884 km (549 mi). Apogee: 1,008 km (626 mi). Inclination: 144.50 deg. Period: 104.00 min. Thermal control experiments. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1966 April - Final active Atlas squadron deactivated. VAFB SMS 576 deactivated 1966 April 8 - 01:00 GMT - Cape Canaveral LC36B. Atlas Centaur D AC-8 / Centaur D 184D FAILURE: Centaur propellant leak. Surveyor Model Mass: 784 kg (1,728 lb). Spacecraft: Surveyor. Agency: NASA/JPL. Perigee: 182 km (113 mi). Apogee: 336 km (208 mi). Inclination: 30.70 deg. Period: 89.70 min. Launch vehicle test. Payload was dummy Surveyor spacecraft. 1966 April 8 - 19:35 GMT - Cape Canaveral LC12. SLV-3 Agena D 5001 (AA15) / Agena D 6703 OAO 1 Mass: 1,774 kg (3,911 lb). Spacecraft: OAO. Agency: NASA GSF. Perigee: 783 km (486 mi). Apogee: 793 km (492 mi). Inclination: 35.00 deg. Period: 100.60 min. Orbiting Astronomical Observatory. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). 1966 April 12 - Gemini Agena target vehicle 5004 began the Combined Interface Test (CIT) at Hanger E, Eastern Test Range, after completing Plan X tests March 24. Flight: Gemini 9. CIT ended April 22 and engine functional tests of both the primary and secondary propulsion systems followed. Hanger E testing was completed May 1. 1966 April 15 - Evaluation of a Lockheed proposal to launch space probes from orbit using Agena rockets launched from AAP stations in space. Spacecraft: Orbital Workshop. Associate Administrator for Manned Space Fight George E. Mueller informed Deputy Administrator Robert C. Seamans, Jr., of the Saturn/Apollo Applications Program Office's evaluation of a Lockheed proposal to launch space probes from orbit using Agena rockets launched from AAP stations in space. The proposal was feasible, Mueller advised, but did not seem a desirable mission for inclusion in the AAP. Additional Details: Evaluation of a Lockheed proposal to launch space probes from orbit using Agena rockets launched from AAP stations in space.. 1966 April 19 - 19:12 GMT - Vandenberg SLC4E. SLV-3 Agena D 7117 / Agena D 7117 KH 7-27 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 139 km (86 mi). Apogee: 375 km (233 mi). Inclination: 116.90 deg. Period: 89.60 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1966 May 3 - Lockheed completed Combined Systems Acceptance Test on Gemini Agena target vehicle 5005 in test complex C-10 at Sunnyvale. Flight: Gemini 10. The vehicle was formally accepted by the Air Force on May 14 and delivered to Eastern Test Range on May 16. 1966 May 3 - 10:30 GMT - Vandenberg 576A1. Atlas D 208D FAILURE: Failure. NTMP KX-37 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 500 km (310 mi). 1966 May 8 - Lockheed established a task force to handle the refurbishing of Gemini Agena target vehicle (GATV) 5001 and announced a GATV 5001 Reassembly Plan. Flight: Gemini 12. The task force's function was to see that GATV 5001 reached a flightworthy condition on time and as economically as possible. The reassembly plan provided an operational base line as well as guidelines for reassembling the vehicle, which was completely disassembled down to the level of riveted or welded parts. GATV 5001 was scheduled for acceptance on September 20 and would be the target vehicle for Gemini XII. 1966 May 13 - 11:43 GMT - Vandenberg 576B1. Atlas D 98D ABRES WAC-5A re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi). 1966 May 14 - 18:30 GMT - Vandenberg SLC4E. SLV-3 Agena D 7118 / Agena D 7118 KH 7-28 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 130 km (80 mi). Apogee: 319 km (198 mi). Inclination: 110.50 deg. Period: 89.00 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1966 May 17 - Launch of Gemini IX was postponed when Agena target vehicle failed to achieve orbit. Flight: Gemini 9. The scheduled launch of Gemini IX was postponed when target launch vehicle 5303 malfunctioned and, as a result, Gemini Agena target vehicle 5004 failed to achieve orbit. Launch and flight were normal until about 120 seconds after liftoff, 10 seconds before booster engine cutoff. Additional Details: Launch of Gemini IX was postponed when Agena target vehicle failed to achieve orbit.. 1966 May 17 - 15:15 GMT - Cape Canaveral LC14. SLV-3 Agena D 5303 / Agena D 5004 FAILURE: Control system failure. Gemini 9 Agena Target Mass: 3,248 kg (7,160 lb). Spacecraft: Gemini Agena Target Vehicle. Agency: NASA. Flight: Gemini 9. 1966 May 25 - Gemini Agena target vehicle 5005 was mated to the target docking adapter (TDA) in Hanger E at Cape Kennedy. Flight: Gemini 10. McDonnell had delivered the TDA on May 4. After mating, interface functional tests were performed, May 25-27. Preparations then began for Plan X testing with spacecraft No. 10 at Merritt Island Launch Area. 1966 May 26 - 12:04 GMT - Vandenberg 576B2. Atlas D 41D NTMP KX-47 Re-entry Vehicle test Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi). 1966 May 30 - 14:41 GMT - Cape Canaveral LC36A. Atlas Centaur D AC-10 / Centaur D 290D Surveyor 1 Mass: 269 kg (593 lb). Spacecraft: Surveyor. Agency: NASA/JPL. Surveyor 1 soft landed on the moon in the Ocean of Storms and began transmitting the first of more than 11,150 clear, detailed television pictures to Jet Propulsion Laboratory's Deep Space Facility, Goldstone, Calif. The landing sequence began 3,200 kilometers above the moon with the spacecraft traveling at a speed of 9,700 kilometers per hour. The spacecraft was successfully slowed to 5.6 kilometers per hour by the time it reached 4-meter altitude and then free-fell to the surface at 13 kilometers per hour. The landing was so precise that the three footpads touched the surface within 19 milliseconds of each other, and it confirmed that the lunar surface could support the LM. It was the first U.S. attempt to soft land on the moon. 1966 June 1 - Gemini Agena target vehicle 5005 completed preliminary testing. Flight: Gemini 10, Gemini 9. Gemini Agena target vehicle 5005 completed preliminary testing at Hanger E, Eastern Test Range, and was moved to Merritt Island Launch Area for Plan X tests with spacecraft No. 10. Plan X tests had first been scheduled for May 23 but were rescheduled for June 2-3. Additional Details: Gemini Agena target vehicle 5005 completed preliminary testing.. 1966 June 1 - 15:00 GMT - Cape Canaveral LC14. Atlas SLV-3 5304 Gemini 9 ATDA Mass: 794 kg (1,750 lb). Spacecraft: Atlas Target Docking Adapter. Agency: NASA MSC. Perigee: 292 km (181 mi). Apogee: 296 km (183 mi). Inclination: 28.80 deg. Period: 90.40 min. Flight: Gemini 9. The ATDA achieved a near-circular orbit (apogee 161.5, perigee 158.5 nautical miles). One hour and 40 minutes later, the scheduled launch of Gemini IX-A was postponed by a ground equipment failure which prevented the transfer of updating information from Cape Kennedy mission control center to the spacecraft computer. The mission was recycled for launch on June 3, following a prepared 48-hour recycle plan. Anomalous telemetry indicated some sort of problem with the target, but it was not until Gemini IX rendezvoused with it in orbit that it was seen that fairing separation had failed. 1966 June 3 - 19:25 GMT - Vandenberg SLC4E. SLV-3 Agena D 7119 / Agena D 7119 KH 7-29 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 143 km (88 mi). Apogee: 288 km (178 mi). Inclination: 87.00 deg. Period: 88.90 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1966 June 6 - Gemini Agena target vehicle 5006 completed modification and final assembly and was transferred to Vehicle Systems Test (VST) at Sunnyvale. Flight: Gemini 11. Although the vehicle lacked the flight control electronics package and guidance module, testing began immediately. The guidance module was received June 7 and the flight control electronics package June 9. Preliminary VST was completed June 17. The Air Force Plant Representative Office at Sunnyvale authorized final acceptance test to begin on June 20. 1966 June 7 - 02:48 GMT - Cape Canaveral LC12. SLV-3 Agena B 5601 (AA16) / Agena B 6502 OGO 3 Mass: 634 kg (1,397 lb). Spacecraft: OGO. Agency: NASA GSF. Perigee: 19,519 km (12,128 mi). Apogee: 102,806 km (63,880 mi). Inclination: 77.60 deg. Period: 2,911.50 min. Orbiting Geophysical Observatory 3. All 21 experiments returned good data. At the time, this was the largest experimental complement ever put into orbit. There were 4 cosmic ray instruments (1 of which included a gamma-ray spectrometer), 4 plasma, 2 trapped radiation, 2 magnetic fields, 5 ionosphere, 3 radio/optical, and 1 micrometeoroid detectors. OGO 3 maintained 3-axis stabilization for 46 days. At that point, an attitude controller failed and the spacecraft was put into a spin on 23 July 1966. The spin period varied from 90-125 seconds. By June 1969, data acquisition was limited to 50% of the orbital path. Routine spacecraft operation was discontinued on December 1, 1969, after which only data from Heppner's experiment (Rubidium + Fluxgate magnetometer) was acquired. By March 1971 spacecraft perigee had increased to 16,400 km and the inclination had increased to 75.8 deg. All spacecraft support terminated on February 29, 1972. 1966 June 9 - 20:10 GMT - Vandenberg SLC3E. SLV-3 Agena D 7201 / Agena D 1351 Midas 10 Mass: 2,000 kg (4,400 lb). Spacecraft: Midas. Agency: USAF. Perigee: 154 km (95 mi). Apogee: 3,678 km (2,285 mi). Inclination: 90.00 deg. Period: 125.20 min. Missile Defense Alarm System. Left in transfer orbit. 1966 June 10 - 11:15 GMT - Vandenberg 576B1. Atlas D 96D NTMP KX-42 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi). 1966 June 13 - Combined Interface Tests(CIT) of Gemini Agena target vehicle (GATV) 5005 began. Flight: Gemini 10. CIT was completed June 22, with no significant anomalies detected. Primary and secondary propulsion system functional checks were completed June 30. The GATV was then moved to complex 14. 1966 June 19 - NASA announced that the Gemini X mission had been scheduled for no earlier than July 18, with John W. Young, command pilot, and Michael Collins, pilot, as the prime crew. Flight: Gemini 10, Gemini 8. Alan L. Bean, command pilot, and Clifton C. Williams, pilot, would be the backup crew. Mission plans would include rendezvous, docking, and extravehicular activity. The spacecraft was scheduled to rendezvous and dock with an Agena target vehicle which was to be launched the same day. If possible, Gemini X would also rendezvous with the Agena launched in the March 16 Gemini VIII mission. 1966 June 26 - 15:34 GMT - Vandenberg 576B2. Atlas D 147D NTMP KX-20 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi). 1966 June 27 - Final acceptance test of Gemini Agena target vehicle 5006 was completed at Sunnyvale. Flight: Gemini 11. The vehicle was disconnected from the test complex July 6 and formally accepted by the Air Force on July 13, two days ahead of schedule. Shipment of the vehicle to Eastern Test Range (ETR), planned for July 13, was delayed until July 14 by wind conditions. It arrived at ETR in the early morning of July 15. 1966 June 30 - 10:00 GMT - Vandenberg 576A1. Atlas D 298D NTMP KX-39 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi). 1966 July 1 - Gemini Agena target vehicle 5005 was transferred to complex 14 and mated to target launch vehicle 5305. Flight: Gemini 10. Joint Flight Acceptance Composite Test was completed July 8. Complex 14 systems tests were completed July 12 with the Simultaneous Launch Demonstration. 1966 July 12 - 17:57 GMT - Vandenberg SLC4E. SLV-3 Agena D 7120 / Agena D 7120 KH 7-30 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 150 km (90 mi). Apogee: 261 km (162 mi). Inclination: 95.50 deg. Period: 88.70 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1966 July 14 - 02:10 GMT - Vandenberg 576B3. Atlas D 58D FAILURE: Partial Failure. OV1-07 Mass: 10 kg (22 lb). Spacecraft: OV1. Agency: USAF OAR. Perigee: 985 km (612 mi). Apogee: 1,022 km (635 mi). Inclination: 144.20 deg. Period: 105.20 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1966 July 18 - Gemini Agena target vehicle (GATV) 5006 was mated to target docking adapter (TDA) 6. Flight: Gemini 10, Gemini 11, Gemini 8. McDonnell had delivered TDA-6 to Cape Kennedy July 7. The interface functional test was completed July 21. The next day GATV 5006 was moved to the Merritt Island Launch Area for integrated tests with spacecraft No. 11 and extravehicular equipment. 1966 July 18 - 20:39 GMT - Cape Canaveral LC14. SLV-3 Agena D 5305 / Agena D 5005 Gemini 10 Agena Target Mass: 3,175 kg (6,999 lb). Spacecraft: Gemini Agena Target Vehicle. Agency: NASA MSC. Perigee: 290 km (180 mi). Apogee: 296 km (183 mi). Inclination: 28.90 deg. Period: 90.40 min. Flight: Gemini 10. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1966 July 21 - Gemini Agena target vehicle made three orbital maneuvers under ground control. Flight: Gemini 10, Gemini 11. Following the reentry of spacecraft No. 10, Gemini Agena target vehicle (GATV) 5005 made three orbital maneuvers under ground control. Its primary propulsion system (PPS) fired to put the vehicle in a 750.5 by 208.6 nautical mile orbit in order to determine the temperature effects of such an orbit on the vehicle. Additional Details: Gemini Agena target vehicle made three orbital maneuvers under ground control.. 1966 July 21 - Gemini Agena target vehicle 5001 was transferred to systems test complex. Flight: Gemini 12. Gemini Agena target vehicle 5001 was transferred to systems test complex C-10 at Sunnyvale, after the long process of refurbishing it had been completed; however, it was still short several pieces of equipment. 1966 August 8 - 17:47 GMT - Vandenberg 576A2. Atlas F 149F FAILURE: Failure. ABRES MBRV-1 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 500 km (310 mi). 1966 August 10 - 19:26 GMT - Cape Canaveral LC13. SLV-3 Agena D 5801 (AA17) / Agena D 6630 Lunar Orbiter 1 Mass: 386 kg (850 lb). Spacecraft: Lunar Orbiter. Agency: NASA LaR. Lunar Orbiter I was launched from Cape Kennedy Launch Complex 13 at 3:26 p.m. EDT August 10 to photograph possible Apollo landing sites from lunar orbit. The Atlas-Agena D launch vehicle injected the spacecraft into its planned 90-hour trajectory to the moon. A midcourse correction maneuver was made at 8 p.m. the next day; a planned second midcourse maneuver was not necessary. A faultless deboost maneuver on August 14 achieved the desired initial elliptic orbit around the moon, and one week later the spacecraft was commanded to make a transfer maneuver to place it in a final close-in elliptic orbit of the moon. During the spacecraft's stay in the final close-in orbit, the gravitational fields of the earth and the moon were expected to influence the orbital elements. The influence was verified by spacecraft tracking data, which showed that the perilune altitude varied with time. From an initial perilune altitude of 58 kilometers, the perilune decreased to 49 kilometers. At this time an orbit adjustment maneuver began an increase in the altitude, which was expected to reach a maximum after three months and then begin to decrease again. The spacecraft was expected to impact on the lunar surface about six months after the orbit adjustment. During the photo-acquisition phase of the flight, August 18 to 29, Lunar Orbiter I photographed the 9 selected primary potential Apollo landing sites, including the one in which Surveyor I landed; 7 other potential Apollo landing sites; the east limb of the moon; and 11 areas on the far side of the moon. Lunar Orbiter I also took photos of the earth, giving man the first view of the earth from the vicinity of the moon (this particular view has been widely publicized). A total of 207 frames (sets of medium- and high-resolution pictures) were taken, 38 while the spacecraft was in initial orbit, the remainder while it was in the final close-in orbit. Lunar Orbiter I achieved its mission objectives, and, with the exception of the high-resolution camera, the performance of the photo subsystem and other spacecraft subsystems was outstanding. At the completion of the photo readouts, the spacecraft had responded to about 5,000 discrete commands from the earth and had made about 700 maneuvers. Photographs obtained during the mission were assessed and screened by representatives of the Lunar Orbiter Project Office, U.S. Geological Survey, DOD mapping agencies, MSC, and Jet Propulsion Laboratory. The spacecraft was deliberately crashed into moon after the mission was completed. 1966 August 16 - Gemini Agena target vehicle 5001 completed final acceptance testing. Flight: Gemini 12. Analysis of test data was completed by August 24 and the vehicle was disconnected from the test complex. 1966 August 16 - 18:30 GMT - Vandenberg SLC4E. SLV-3 Agena D 7121 / Agena D 7121 KH 7-31 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 143 km (88 mi). Apogee: 330 km (200 mi). Inclination: 93.20 deg. Period: 89.20 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1966 August 19 - 19:26 GMT - Vandenberg SLC3E. SLV-3 Agena D 7202 / Agena D 1352 Midas 11 Mass: 2,000 kg (4,400 lb). Spacecraft: Midas. Agency: USAF. Perigee: 3,658 km (2,272 mi). Apogee: 3,708 km (2,304 mi). Inclination: 89.70 deg. Period: 167.40 min. Missile Defense Alarm System. 1966 August 22 - Gemini Agena target vehicle 5006 was mated to target launch vehicle 5306. Flight: Gemini 11. Joint Flight Acceptance Composite Test was performed August 26, Simultaneous Launch Demonstration on August 31. 1966 September 2 - Gemini Agena target vehicle 5001 was formally accepted by the Air Force after vehicle acceptance team inspection. Flight: Gemini 12. It was shipped from Sunnyvale on September 3 and arrived at Eastern Test Range on September 4. 1966 September 12 - Gemini Agena target vehicle 5001 was mated to target docking adapter (TDA) 7A at Cape Kennedy. Flight: Gemini 12, Gemini 11. McDonnell had delivered TDA 7A to the Cape August 19. After functional verification tests (September 13-15), the vehicle was moved (September 19-20) to the Merritt Island Launch Area for Plan X integrated tests with spacecraft No. 12. 1966 September 12 - 13:05 GMT - Cape Canaveral LC14. SLV-3 Agena D 5306 / Agena D 5006 Gemini 11 Agena Target Mass: 3,175 kg (6,999 lb). Spacecraft: Gemini Agena Target Vehicle. Agency: NASA MSC. Perigee: 298 km (185 mi). Apogee: 298 km (185 mi). Inclination: 28.80 deg. Period: 90.40 min. Flight: Gemini 11. Docking target for Gemini 11. 1966 September 16 - 17:59 GMT - Vandenberg SLC4E. SLV-3 Agena D 7123 / Agena D 7123 KH 7-32 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 146 km (90 mi). Apogee: 328 km (203 mi). Inclination: 93.90 deg. Period: 89.20 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1966 September 20 - 12:32 GMT - Cape Canaveral LC36A. Atlas Centaur D AC-7 / Centaur D 194D Surveyor 2 Mass: 292 kg (643 lb). Spacecraft: Surveyor. Agency: NASA/JPL. Soft lunar landing attempt failed. Surveyor II was launched from Cape Kennedy at 8:32 a.m. EDT. The Atlas-Centaur launch vehicle placed the spacecraft on a nearly perfect lunar intercept trajectory that would have missed the aim point by about 130 kilometers. Following injection, the spacecraft successfully accomplished all required sequences up to the midcourse thrust phase. This phase was not successful because of the failure of one of the three vernier engines to ignite, causing eventual loss of the mission. Contact with the spacecraft was lost at 5:35 a.m. EDT, September 22, and impact on the lunar surface was predicted at 11:18 p.m. on that day. 1966 September 21 - Gemini Agena target vehicle (GATV) 5001 was returned to Hanger E and began systems test after completing Plan X tests at the Merritt Island Launch Area. Flight: Gemini 12. Systems testing was completed September 29. The Combined Interface Test (September 29-October 13) was followed by functional tests of the primary and secondary propulsion systems, completed October 22. GATV 5001 was then moved to complex 14. 1966 October 5 - 22:00 GMT - Vandenberg SLC3E. SLV-3 Agena D 7203 / Agena D 1353 Midas 12 Mass: 2,000 kg (4,400 lb). Spacecraft: Midas. Agency: USAF. Perigee: 3,657 km (2,272 mi). Apogee: 3,724 km (2,313 mi). Inclination: 89.80 deg. Period: 167.60 min. Missile Defense Alarm System. 1966 October 11 - 19:59 GMT - Vandenberg 576A2. Atlas F 115F FAILURE: Failure. ABRES SBGRV-1 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 50 km (31 mi). 1966 October 12 - 19:15 GMT - Vandenberg SLC4E. SLV-3 Agena D 7122 / Agena D 7122 KH 7-33 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 155 km (96 mi). Apogee: 287 km (178 mi). Inclination: 91.00 deg. Period: 89.00 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1966 October 23 - Gemini Agena target vehicle 5001 was mated to target launch vehicle 5307 on complex 14. Flight: Gemini 12. Joint Flight Acceptance Composite Test was completed October 28, Simultaneous Launch Demonstration on November 1. 1966 October 26 - 11:12 GMT - Cape Canaveral LC36B. Atlas Centaur D AC-9 / Centaur D 174D Surveyor SD-4 Mass: 951 kg (2,096 lb). Spacecraft: Surveyor. Agency: NASA/JPL. Perigee: 166 km (103 mi). Apogee: 406,200 km (252,400 mi). Inclination: 29.60 deg. Period: 15,912.00 min. Launch vehicle test. Centaur D AC-9 put Surveyor spacecraft payload into geosynchronous transfer orbit 1966 November 2 - 20:23 GMT - Vandenberg SLC4E. SLV-3 Agena D 7124 / Agena D 7124 KH 7-34 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 159 km (98 mi). Apogee: 305 km (189 mi). Inclination: 91.00 deg. Period: 89.20 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1966 November 6 - 23:21 GMT - Cape Canaveral LC13. SLV-3 Agena D 5802 (AA18) / Agena D 6631 Lunar Orbiter 2 Mass: 390 kg (850 lb). Spacecraft: Lunar Orbiter. Agency: NASA LaR. Lunar Orbiter II was launched at 6:21 p.m. EST from Launch Complex 13 at Cape Kennedy, to photograph possible landing sites on the moon for the Apollo program. The Atlas-Agena D booster placed the spacecraft in an earth-parking orbit and, after a 14-minute coast, injected it into its 94-hour trajectory toward the moon. A midcourse correction maneuver on November 8 increased the velocity from 3,051 to 3,133 kilometers per hour. At that time the spacecraft was 265,485 kilometers from the earth. The spacecraft executed a deboost maneuver at 3:26 p.m., November 10, while 352,370 kilometers from the earth and 1,260 kilometers from the moon and traveling at a speed of 5,028 kilometers per hour. The maneuver permitted the lunar gravitational field to pull the spacecraft into the planned initial orbit around the moon. On November 15, a micrometeoroid hit was detected by one of the 20 thin-walled pressurized sensors. The spacecraft was transferred into its final close-in orbit around the moon at 5:58 p.m. November 15 and the photo-acquisition phase of Lunar Orbiter II's mission began November 18. Thirteen selected primary potential landing sites and a number of secondary sites were to be photographed. By the morning of November 25, the spacecraft had taken 208 of the 211 photographs planned and pictures of all 13 selected potential landing sites. It also made 205 attitude change maneuvers and responded to 2,421 commands. The status report of the Lunar Orbiter II mission as of November 28 indicated that the first phase of the photographic mission was completed when the final photo was taken on the afternoon of November 25. On November 26, the developing web was cut with a hot wire in response to a command from the earth. Failure to achieve the cut would have prevented the final readout of all 211 photos. Readout began immediately after the cut was made. One day early, December 6, the readout terminated when a transmitter failed, and three medium-resolution and two high-resolution photos of primary site 1 were lost. Full low-resolution coverage of the site had been provided, however, and other data continued to be transmitted. Three meteoroid hits had been detected. 1966 November 11 - 19:07 GMT - Cape Canaveral LC14. SLV-3 Agena D 5307 / Agena D 5001R Gemini 12 Agena Target Mass: 3,175 kg (6,999 lb). Spacecraft: Gemini Agena Target Vehicle. Agency: NASA MSC. Perigee: 243 km (150 mi). Apogee: 310 km (190 mi). Inclination: 28.80 deg. Period: 89.90 min. Flight: Gemini 12. Docking target for Gemini 12. 1966 December 5 - 21:09 GMT - Vandenberg SLC4E. SLV-3 Agena D 7125 / Agena D 7125 KH 7-35 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 137 km (85 mi). Apogee: 341 km (211 mi). Inclination: 104.60 deg. Period: 89.20 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1966 December 7 - 02:12 GMT - Cape Canaveral LC12. SLV-3 Agena D 5101 (AA19) / Agena D 6151 ATS 1 Mass: 352 kg (776 lb). Spacecraft: ATS-1. Agency: NASA GSF. Perigee: 35,728 km (22,200 mi). Apogee: 35,783 km (22,234 mi). Inclination: 12.50 deg. Period: 1,434.50 min. Applications Technology Satellite; communications and meteorological experiments. Positioned in geosynchronous orbit over the Americas at 151 deg W in 1966-1968?; over the Americas at 149 deg W in 1968-1982; over the Pacific Ocean 170 deg E in 1982-1985 As of 3 September 2001 located at 167.30 deg E drifting at 0.065 deg E per day. As of 2007 Mar 9 located at 59.28W drifting at 0.332E degrees per day. 1966 December 11 - 21:09 GMT - Vandenberg 576B3. Atlas D 89D / OV-1 (2x) OV1-09 Mass: 230 kg (500 lb). Spacecraft: OV1. Agency: USAF OAR. Perigee: 475 km (295 mi). Apogee: 4,582 km (2,847 mi). Inclination: 99.10 deg. Period: 139.40 min. Radiation bio-hazard experiments. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1966 December 21 - 22:15 GMT - Vandenberg SLC3E. Atlas SLV-3 7001 Prime 1 Agency: USAF AFSC. Apogee: 1,500 km (900 mi). The first test of the X-23A SV-5D lifting body re-entry shape. It was a zero cross-range suborbital flight, with recovery 6935 km downrange. The ballute deployed at 30.440 m, followed by the main parachute at 13,700 m, and the vehicle was descending within 275 m of the target point. Nevertheless the air-snatch was unsuccessful, and the vehicle sank. However 90% of the planned telemetry was successfully transmitted by radio. 1967 January 18 - 01:34 GMT - Vandenberg 576A2. Atlas F 148F ABRES TVX-13 (21) re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1967 January 22 - 15:44 GMT - Vandenberg 576B2. Atlas D 35D ABRES Mk 12R PDV re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi). 1967 February 2 - 20:00 GMT - Vandenberg SLC4E. SLV-3 Agena D 7126 / Agena D 7126 KH 7-36 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 136 km (84 mi). Apogee: 357 km (221 mi). Inclination: 103.00 deg. Period: 89.50 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1967 February 5 - 01:17 GMT - Cape Canaveral LC13. SLV-3 Agena D 5803 (AA20) / Agena D 6632 Lunar Orbiter 3 Mass: 385 kg (848 lb). Spacecraft: Lunar Orbiter. Agency: NASA LaR. Crashed into Moon; returned 182 photos of lunar surface. Selenocentric orbit. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). 1967 February 13 - 22:05 GMT - Vandenberg 576A3. Atlas F 121F ABRES TX-22 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1967 March 5 - 23:05 GMT - Vandenberg SLC3E. Atlas SLV-3 7002 Prime 2 Agency: USAF AFSC. Apogee: 1,500 km (900 mi). The X-23A SV-5D lifting body vehicle demonstrated a 1055 km cross-range manoeuvre, but again air snatch failed. 1967 March 16 - 17:56 GMT - Vandenberg 576A2. Atlas F 151F ABRES MBRV-2 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1967 April 6 - 03:23 GMT - Cape Canaveral LC12. SLV-3 Agena D 5102 (AA21) / Agena D 6152 FAILURE: Partial Failure. ATS 2 Mass: 370 kg (810 lb). Spacecraft: ATS-2. Agency: NASA GSF. Perigee: 177 km (109 mi). Apogee: 11,119 km (6,909 mi). Inclination: 28.40 deg. Period: 218.80 min. Launch vehicle failure left in useless orbit; communications tests. 1967 April 7 - 11:19 GMT - Vandenberg 576B2. Atlas D 38D ABRES AX-1 / Pod 30 Reentry test / ionosphere mission Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi). 1967 April 17 - 07:05 GMT - Cape Canaveral LC36B. Atlas Centaur D AC-12 / Centaur D 292D Surveyor 3 Mass: 283 kg (623 lb). Spacecraft: Surveyor. Agency: NASA/JPL. Soft landed on Moon; perrformed soil sample tests and imaged lunar surface. 1967 April 20 - 01:35 GMT - Vandenberg SLC3E. Atlas SLV-3 7003 Prime 3 Agency: USAF AFSC. Apogee: 1,500 km (900 mi). The full design 1145 km cross range was demonstrated, and the X-23A SV-5D lifting body vehicle was successfully snatched at 3700 m altitude, 8 km from the target point. With this success the rest of the project was cancelled, and the two remaining unflown X-22A's were sent to the USAF Museum at Wright Patterson Air Force Base. 1967 May 4 - 22:25 GMT - Cape Canaveral LC13. SLV-3 Agena D 5804 (AA22) / Agena D 6633 Lunar Orbiter 4 Mass: 390 kg (850 lb). Spacecraft: Lunar Orbiter. Agency: NASA LaR. Returned 163 photos of lunar surface before impacting Moon. Selenocentric orbit. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). 1967 May 19 - 22:00 GMT - Vandenberg 576A1. Atlas F 119F ABRES SBGRV-2 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1967 May 22 - 18:30 GMT - Vandenberg SLC4E. SLV-3 Agena D 7127 / Agena D 7127 KH 7-37 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 135 km (83 mi). Apogee: 293 km (182 mi). Inclination: 91.50 deg. Period: 88.80 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1967 June 4 - 18:10 GMT - Vandenberg SLC4E. SLV-3 Agena D 7128 / Agena D SS-01B 4837 KH 7-38 Mass: 2,000 kg (4,400 lb). Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 149 km (92 mi). Apogee: 456 km (283 mi). Inclination: 104.90 deg. Period: 90.60 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1967 June 9 - 10:23 GMT - Vandenberg 576A3. Atlas F/Trident 122F ABRES SPDS (RMP-B-1) re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1967 June 14 - 06:01 GMT - Cape Canaveral LC12. SLV-3 Agena D 5401 (AA23) / Agena D 6933 Mariner 5 Mass: 244 kg (537 lb). Spacecraft: Mariner 5. Agency: NASA/JPL. Mariner 5 flew by Venus on October 19, 1967 at an altitude of 3,990 kilometres. With more sensitive instruments than its predecessor Mariner 2, Mariner 5 was able to shed new light on the hot, cloud-covered planet and on conditions in interplanetary space. Operations of Mariner 5 ended in November 1967. The spacecraft instruments measured both interplanetary and Venusian magnetic fields, charged particles, and plasmas, as well as the radio refractivity and UV emissions of the Venusian atmosphere. 1967 July 6 - Vandenberg 576B2. Atlas D 65D ABRES PDV re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi). 1967 July 14 - 11:53 GMT - Cape Canaveral LC36A. Atlas Centaur D AC-11 / Centaur D 291D Surveyor 4 Mass: 283 kg (623 lb). Spacecraft: Surveyor. Agency: NASA/JPL. Soft lunar landing attempt failed. 1967 July 22 - Vandenberg 576A3. Atlas F/Trident 114F RMP-B-2 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1967 July 27 - 19:00 GMT - Vandenberg 576B3. Atlas D 92D FAILURE: Partial Failure. OV1-08S Mass: 118 kg (260 lb). Spacecraft: OV1. Agency: USAF OAR. Perigee: 529 km (328 mi). Apogee: 557 km (346 mi). Inclination: 101.60 deg. Period: 95.50 min. Carried cosmic ray telescope. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1967 July 29 - 08:48 GMT - Vandenberg 576A2. Atlas F 150F ABRES MBRV-3 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1967 August 1 - 22:33 GMT - Cape Canaveral LC13. SLV-3 Agena D 5805 (AA24) / Agena D 6634 Lunar Orbiter 5 Mass: 389 kg (857 lb). Spacecraft: Lunar Orbiter. Agency: NASA LaR. Lunar Orbiter V was launched from the Eastern Test Range at 6:33 p.m. EDT August 1. The Deep Space Net Tracking Station at Woomera, Australia, acquired the spacecraft about 50 minutes after liftoff. Signals indicated that all systems were performing normally and that temperatures were within acceptable limits. At 12:48 p.m. EDT August 5, Lunar Orbiter V executed a deboost maneuver that placed it in orbit around the moon. The spacecraft took its first photograph of the moon at 7:22 a.m. EDT August 6. Before it landed on the lunar surface on January 31, 1968, Lunar Orbiter V had photographed 23 previously unphotographed areas of the moon's far side, the first photo of the full earth, 36 sites of scientific interest, and 5 Apollo sites for a total of 425 photos. 1967 September 8 - 07:57 GMT - Cape Canaveral LC36B. SLV-3C Centaur AC-13 / Centaur D-1A 5901C Surveyor 5 Mass: 279 kg (615 lb). Spacecraft: Surveyor. Agency: NASA/JPL. Soft lunar landing; returned 19,000 photos, soil data. 1967 October 11 - 11:30 GMT - Vandenberg 576B3. Atlas D 69D ABRES TVX-13 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi). 1967 October 14 - Vandenberg 576A2. Atlas F 118F ABRES MBRV-4 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1967 October 27 - Vandenberg 576A3. Atlas F/Trident 81F FAILURE: Failure. RMP-B-3 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1.00 km (0.60 mi). 1967 November 5 - 23:37 GMT - Cape Canaveral LC12. SLV-3 Agena D 5103 (AA25) / Agena D 6153 ATS 3 Mass: 365 kg (804 lb). Spacecraft: ATS-3. Agency: NASA GSF. Perigee: 35,736 km (22,205 mi). Apogee: 35,837 km (22,268 mi). Inclination: 14.50 deg. Period: 1,436.10 min. Communications tests. Positioned in geosynchronous orbit over the Atlantic Ocean at 45 deg W in-100 deg W in 1968-1970; over the Americas at 69 deg W in 1971-1976; over the Americas at 105 deg W in 1977-1998 As of 4 September 2001 located at 105.90 deg W drifting at 0.003 deg W per day. As of 2007 Mar 10 located at 105.23W drifting at 0.006W degrees per day. 1967 November 7 - 07:39 GMT - Cape Canaveral LC36B. SLV-3C Centaur AC-14 / Centaur D-1A 5902C Surveyor 6 Mass: 280 kg (610 lb). Spacecraft: Surveyor. Agency: NASA/JPL. Soft landed on lunar Moon; photographed lunar surface; sampled lunar soil; used propulsion system to briefly lift off of lunar surface. 1967 November 7 - 13:17 GMT - Vandenberg 576B2. Atlas D 94D ABRES Mk 11 AX-2 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi). Final launch of an Atlas D missile (first operational at Vandenberg on 9 September 1959). 1967 November 10 - 12:20 GMT - Vandenberg 576A1. Atlas F 113F ABRES BGRV-1 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1967 December 21 - Vandenberg 576A3. Atlas F/Trident 117F RMP-B-4 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1968 January 7 - 06:30 GMT - Cape Canaveral LC36A. SLV-3C Centaur AC-15 / Centaur D-1A 5903C Surveyor 7 Mass: 1,036 kg (2,283 lb). Spacecraft: Surveyor. Agency: NASA/JPL. Soft landed on lunar Moon; photographed lunar surface; sampled lunar soil. 1968 January 31 - Vandenberg 576A3. Atlas F/Trident 94F RMP-B-5 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1968 February 26 - Vandenberg 576A1. Atlas F 116F ABRES BGRV-2 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). The Boost Glide Re-entry Vehicle was launched from Vandenberg AFB, California to the area of Wake Island in the Pacific Ocean. It was launched from an Atlas missile booster and served to provide data on hypersonic manoeuvring flight characteristics. 1968 March 4 - 13:06 GMT - Cape Canaveral LC13. SLV-3A Agena D 5602A (AA26) / Agena D 6503 (AA26) OGO 5 Mass: 634 kg (1,397 lb). Spacecraft: OGO. Agency: NASA GSF. Perigee: 36,021 km (22,382 mi). Apogee: 111,034 km (68,993 mi). Inclination: 50.30 deg. Period: 3,746.50 min. OGO 5 carried 25 experiments, 17 of which were particle studies, and two were magnetic field studies. In addition, there was one each of the following types of experiments: radio astronomy, UV spectrum, Lyman-alpha, solar X ray, plasma waves, and electric field. By April 1971, spacecraft perigee had increased to 26,400 km and inclination had increased to 54 deg. The spacecraft attitude control failed on August 6, 1971, after 41 months of normal operation. The spacecraft was placed in a standby status on October 8, 1971. Four experiments (Meyer, Blamont, Thomas, and Simpson) were reactivated for the period from June 1 to July 13, 1972, after which all operational support terminated. Spacecraft orbit parameters changed significantly over the spacecraft life. 1968 March 6 - Vandenberg 576A3. Atlas E/Trident 74E RMP-B-6 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,600 km (900 mi). 1968 April 6 - 09:59 GMT - Vandenberg 576A2. Atlas F 107F / OV-1 (2x) OV1-13 Mass: 107 kg (235 lb). Spacecraft: OV1. Agency: USAF OAR. Perigee: 587 km (364 mi). Apogee: 9,214 km (5,725 mi). Inclination: 100.00 deg. Period: 198.70 min. Radiation, engineering experiments. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1968 April 18 - Vandenberg 576A1. Atlas E 77E ABRES RVTO-1A-1 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,600 km (900 mi). 1968 April 27 - Vandenberg 576A3. Atlas E/Trident 78E RMP-B-7 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,600 km (900 mi). 1968 May 3 - Vandenberg 576A2. Atlas F 95F FAILURE: Failure. ABRES Penaid TVX re-entry vehicle test flight Agency: USAF AFSC. Apogee: 100 km (60 mi). 1968 June 1 - Vandenberg 576A2. Atlas F 89F ABRES PDV re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1968 June 22 - Vandenberg 576A3. Atlas F/Trident 86F RMP-B-8 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1968 June 29 - Vandenberg 576A1. Atlas F 32F ABRES RVTO-1A-2 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1968 July 11 - 19:30 GMT - Vandenberg 576A2. Atlas F 75F / OV-1 (2x) OV1-15S Mass: 470 kg (1,030 lb). Spacecraft: OV1. Agency: USAF OAR. Perigee: 153 km (95 mi). Apogee: 1,800 km (1,100 mi). Inclination: 89.80 deg. Period: 104.60 min. Studied relationship between atmospheric density and solar radiation. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1968 August 6 - 11:16 GMT - Cape Canaveral LC13. SLV-3A Agena D 5501A / Agena D 2801 Canyon 1 Mass: 700 kg (1,540 lb). Spacecraft: Canyon. Agency: NRO/USAF. Perigee: 31,680 km (19,680 mi). Apogee: 39,860 km (24,760 mi). Inclination: 9.90 deg. Period: 1,436.00 min. First launch in a communications intelligence program operated by the USAF within the National Reconnaissance Office, on behalf of the National Security Agency. The first generation series, CANYON, was based on the Agena vehicle. The Agena D remained attached to the spacecraft. Positioned in geosynchronous orbit over the Indian Ocean. Last known longitude (30 December 1968) 98.50 deg W drifting at 0.166 deg E per day. 1968 August 10 - 22:33 GMT - Cape Canaveral LC36A. SLV-3C Centaur AC-17 / Centaur D-1A 5104C FAILURE: Centaur oxidizer leak. No restart. ATS 4 Mass: 391 kg (862 lb). Spacecraft: ATS-4. Agency: NASA GSF. Perigee: 220 km (130 mi). Apogee: 769 km (477 mi). Inclination: 29.10 deg. Period: 94.50 min. Applications Technology Satellite that was to have been put into a geosynchronous transfer orbit, instead was left in a nearly-useless LEO orbit. ATS-4 included two cesium contact ion engines. Flight test objectives were to measure thrust and to examine electromagnetic compatibility with other spacecraft subsystems. The 5 cm diameter thrusters were designed to operate at 0.02 kW and provide about 89 microN thrust at about 6700 s specific impulse. The thrusters had the capability to operate at 5 setpoints from 18 to 89 microN. Thrusters were configured so they could be used for East-West station-keeping. Prior to launch, a 5 cm cesium thruster was life tested for 2245 hours at the 67 microN thrust level. However the Centaur upper stage did not achieve a second burn and the spacecraft remained attached to the Centaur in a 218 km by 760 km orbit. It was estimated that the pressure at these altitudes was between 10^-6 and 10^-8 Torr. Each of the two engines was tested on at least two occasions each over the throttling range. Combined test time of the two engines was about 10 hours over a 55 day period. The spacecraft re-entered the atmosphere on October 17, 1968. TheATS-4 flight was the first successful orbital test of an ion engine. There was no evidence of IPS electromagnetic interference related to spacecraft subsystems. Measured values of neutralizer emission current were much less than the ion beam current, implying inadequate neutralization. The spacecraft potential was about -132V which was much different than the anticipated value of about -40V. 1968 August 16 - 20:57 GMT - Vandenberg SLC3E. LV Model: Atlas Burner 2 . Atlas / Burner 2 7004 FAILURE: Failure. LCS 3 Mass: 37 kg (81 lb). Spacecraft: Orbiscal. Agency: U.S. Air Force, U.S. Navy. First of two Atlas/Burner II space launches. 1 of 13 satellite launch attempts; investigate effects of ionosphere on radio signals. 1968 September 25 - Vandenberg 576A3. Atlas F/Trident 99F RMP-B-9 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1968 September 27 - Vandenberg 576A1. Atlas F 84F RVTO-1A-3 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1968 November 16 - Vandenberg 576A3. Atlas F/Trident 56F FAILURE: Failure. RMP-B-10 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 10 km (6 mi). 1968 November 24 - Vandenberg 576A1. Atlas F 60F RVTO-1A-4 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1968 December 7 - 08:40 GMT - Cape Canaveral LC36B. SLV-3C Centaur AC-16 / Centaur D-1A 5002C OAO 2 Mass: 2,012 kg (4,435 lb). Spacecraft: OAO. Agency: NASA GSF. Perigee: 749 km (465 mi). Apogee: 758 km (470 mi). Inclination: 35.00 deg. Period: 99.90 min. Orbiting Astronomical Observatory; carried 11 telescopes; performed X-ray, UV, IR observations of stars. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). Launch vehicle put payload into geosynchronous transfer orbit 1969 January 16 - Vandenberg 576A3. Atlas F/Trident 70F RMP-B-11 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1969 February 25 - 01:29 GMT - Cape Canaveral LC36B. SLV-3C Centaur AC-20 / Centaur D-1A 5403C Mariner 6 Mass: 412 kg (908 lb). Spacecraft: Mariner 6-7. Agency: NASA/JPL. Mars flyby 31 July 1969; returned 75 images of Martian surface. Ten days before the scheduled launch, a faulty switch opened the main valves on the Atlas stage. This released the pressure which supported the Atlas structure, and as the booster deflated it began to crumple. Two ground crewman started pressurizing pumps, saving the structure from further collapse. The two ground crewman, who had acted at risk of the 12-story rocket collapsing on them, were awarded Exceptional Bravery Medals from NASA. The Mariner 6 spacecraft was removed, put on another Atlas/Centaur, and launched on schedule. The main booster was jettisoned 4 min. 38 sec. after launch, followed by a 7.5 minute Centaur burn to inject the spacecraft into Mars direct trajectory. After Mariner 6 separated from the Centaur the solar panels were deployed. A midcourse correction involving a 5.35 second burn of the hydrazine rocket occurred on 1 March 1969. A few days later explosive valves were deployed to unlatch the scan platform. Some bright particles released during the explosion distracted the Canopus sensor, and attitude lock was lost temporarily. It was decided to place the spacecraft on inertial guidance for the Mars flyby to prevent a similar occurrence. On 29 July, 50 hours before closest approach, the scan platform was pointed to Mars and the scientific instruments turned on. Imaging of Mars began 2 hours later. For the next 41 hours, 49 approach images (plus a 50th fractional image) of Mars were taken through the narrow-angle camera. At 05:03 UT on 31 July the near-encounter phase began, including collection of 26 close-up images. Due to a cooling system failure, channel 1 of the IR spectrometer did not cool sufficiently to allow measurements from 6 to 14 micrometers so no infrared data were obtained over this range. Closest approach occurred at 05:19:07 UT at a distance of 3431 km from the martian surface. Eleven minutes later Mariner 6 passed behind Mars and reappeared after 25 minutes. X-band occultation data were taken during the entrance and exit phases. Science and imaging data were played back and transmitted over the next few days. The spacecraft was then returned to cruise mode which included engineering and communications tests, star photography TV tests, and UV scans of the Milky Way and an area containing comet 1969-B. Periodic tracking of the spacecraft in its heliocentric orbit was also done. Science Results Mariner 6 returned 49 far encounter and 26 near encounter images of Mars. Close-ups from the near encounter phases covered 20% of the surface. The spacecraft instruments measured UV and IR emissions and radio refractivity of the Martian atmosphere. Images showed the surface of Mars to be very different from that of the Moon, in some contrast to the results from Mariner 4. The south polar cap was identified as being composed predominantly of carbon dioxide. Atmospheric surface pressure was estimated at between 6 and 7 mb. Radio science refined estimates of the mass, radius and shape of Mars. 1969 March 18 - 07:40 GMT - Vandenberg 576A2. Atlas F 104F / OV-1 (3x) OV1-17S Mass: 142 kg (313 lb). Spacecraft: OV1. Agency: USAF OAR. Perigee: 400 km (240 mi). Apogee: 466 km (289 mi). Inclination: 99.10 deg. Period: 93.20 min. Solar radiation experiments. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1969 March 27 - 22:22 GMT - Cape Canaveral LC36A. SLV-3C Centaur AC-19 / Centaur D-1A 5105C Mariner 7 Mass: 412 kg (908 lb). Spacecraft: Mariner 6-7. Agency: NASA/JPL. Mars flyby 5 August 1969; returned 126 images of Martian surface. Mariner 7 was launched on a direct-ascent trajectory to Mars 31 days after Mariner 6. On 8 April 1969 a midcourse correction was made by firing the hydrazine moter for 7.6 seconds. On 8 May Mariner 7 was put on gyro control to avoid attitude control problems which were affecting Mariner 6. On 31 July telemetry from Mariner 7 was suddenly lost and the spacecraft was commanded to switch to the low-gain antenna. It was later successfully switched back to the high-gain antenna. It was thought that leaking gases, perhaps from the battery which later failed a few days before encounter, had caused the anomaly. At 09:32:33 GMT on 2 August 1969 Mariner 7 bagan the far-encounter sequence involving imaging of Mars with the narrow angle camera. Over the next 57 hours, ending about 5 hours before closest approach, 93 images of Mars were taken and transmitted. The spacecraft was reprogrammed as a result of analysis of Mariner 6 images. The new sequence called for the spacecraft to go further south than originally planned, take more near-encounter pictures, and collect more scientific data on the lighted side of Mars. Data from the dark side of Mars were to be transmitted directly back to Earth but there would be no room on the digital recorder for backup due to the added dayside data. At closest approach, 05:00:49 GMT on 5 August, Mariner 7 was 3430 km above the martian surface. Over this period, 33 near-encounter images were taken. About 19 minutes after the flyby, the spacecraft went behind Mars and emerged roughly 30 minutes later. X-band occultation data were taken during the entrance and exit phases. Science and imaging data were played back and transmitted over the next few days. The spacecraft was then returned to cruise mode which included engineering and communications tests, star photography TV tests, and UV scans of the Milky Way and an area containing comet 1969-B. Periodic tracking of the spacecraft in its heliocentric orbit was also done. Science Results The total data return for Mariners 6 and 7 was 800 million bits. Mariner 7 returned 93 far and 33 near encounter images. Close-ups from the near encounter phases covered 20% of the surface. The spacecraft instruments measured UV and IR emissions and radio refractivity of the Martian atmosphere. Images showed the surface of Mars to be very different from that of the Moon, in some contrast to the results from Mariner 4. The south polar cap was identified as being composed predominantly of carbon dioxide. Atmospheric surface pressure was estimated at between 6 and 7 mb. Radio science refined estimates of the mass, radius and shape of Mars. 1969 April 13 - 02:24 GMT - Cape Canaveral LC13. SLV-3A Agena D 5502A / Agena D 2802 Canyon 2 Mass: 700 kg (1,540 lb). Spacecraft: Canyon. Agency: USAF. Perigee: 32,670 km (20,300 mi). Apogee: 39,270 km (24,400 mi). Inclination: 9.90 deg. Period: 1,445.00 min. Positioned in geosynchronous orbit over the Indian Ocean. Last known longitude (31 December 1969) 99.24 deg W drifting at 2.246 deg W per day. 1969 August 12 - 11:01 GMT - Cape Canaveral LC36A. SLV-3C Centaur AC-18 / Centaur D-1A 5402C ATS 5 Mass: 821 kg (1,809 lb). Spacecraft: ATS-5. Agency: NASA GSF. Perigee: 35,992 km (22,364 mi). Apogee: 36,024 km (22,384 mi). Inclination: 14.50 deg. Period: 1,447.40 min. Applications Technology Satellite; communications tests. Launch vehicle successfully put the payload into a geosynchronous transfer orbit. The spacecraft maneuvered into geostationary orbit at 108 degrees W. The purpose of this flight was to demonstrate North-South Stationkeeping of a geosynchronous satellite. ATS-5 was equipped with an ion engine package identical to that on ATS-4. Once in geosynchronous orbit the spacecraft could not be despun as planned, and thus the spacecraft gravity gradient stabilization could not be implemented. The spacecraft spin rate was about 76 revolutions per minute, and this caused an effective 4g acceleration on the cesium feed system. The high g-loading on the cesium feed system caused flooding of the discharge chamber, and normal operation of the thruster with ion beam extraction could not be performed. The IPS was instead be operated as a neutral plasma source, without high-voltage ion extraction, along with the wire neutralizer to examine spacecraft charging effects. The neutralizer was also operated by itself to provide electron injection for the spacecraft charging experiments. Positioned in geosynchronous orbit over the Americas at 105 deg W in 1969-1977; over the Americas at 70 deg W in 1977-1983. As of 1 September 2001 located at 15.48 deg E drifting at 2.807 deg W per day. As of 2007 Mar 10 located at 111.70E drifting at 2.819W degrees per day. 1969 August 20 - Vandenberg 576A1. Atlas F 112F ABRES RVTO-1A-5 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1969 September 16 - Vandenberg 576A3. Atlas F/Trident 100F RMP-B-12 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1969 October 10 - Vandenberg 576A3. Atlas F/Trident 98F FAILURE: Failure. RMP-B-13 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 10 km (6 mi). 1969 December 3 - Vandenberg 576A1. Atlas F 44F ABRES RVTO-1A-6 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1969 December 12 - Vandenberg 576A3. Atlas F/Trident 93F RMP-B-14 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1970 February 8 - Vandenberg 576A3. Atlas F/Trident 96F RMP-B-15 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1970 March 13 - Vandenberg 576A3. Atlas F/Trident 28F RMP-B-16 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1970 May 30 - Vandenberg 576A3. Atlas F/Trident 91F RMP-B-17 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1970 June 9 - Vandenberg 576A1. Atlas F 92F ABRES RVTO-1A-7 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1970 June 19 - 11:37 GMT - Cape Canaveral LC13. SLV-3A Agena D 5201A / Agena D 1551 Rhyolite 1 Mass: 700 kg (1,540 lb). Spacecraft: Rhyolite. Agency: NRO/CIA. Perigee: 178 km (110 mi). Apogee: 33,685 km (20,930 mi). Inclination: 28.20 deg. Period: 588.90 min. First launch of Rhyolite geostationary ELINT satellite. Reportedly left in transfer orbit; other sources indicate a successful mission. Positioned in geosynchronous orbit over the Indian Ocean. 1970 September 1 - 01:00 GMT - Cape Canaveral LC13. SLV-3A Agena D 5203A / Agena D 2803 Canyon 3 Mass: 700 kg (1,540 lb). Spacecraft: Canyon. Agency: USAF. Perigee: 31,947 km (19,850 mi). Apogee: 39,855 km (24,764 mi). Inclination: 10.30 deg. Period: 1,441.90 min. Positioned in geosynchronous orbit over the Indian Ocean. Last known longitude (31 December 1970) 99.01 deg W drifting at 1.490 deg W per day. 1970 November 30 - 22:40 GMT - Cape Canaveral LC36B. SLV-3C Centaur AC-21 / Centaur D-1A 5003C FAILURE: Shroud failed to separate. OAO-B Mass: 2,121 kg (4,676 lb). Spacecraft: OAO. Agency: NASA. Orbiting Astronomical Observatory. Launch vehicle was to have put payload into geosynchronous transfer orbit 1970 December 22 - 08:38 GMT - Vandenberg 576A3. Atlas F/Trident 105F ABRES RVTO-2A-1 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1971 January 26 - 00:36 GMT - Cape Canaveral LC36A. SLV-3C Centaur AC-25 / Centaur D-1A 5005C Intelsat 4 F-2 Mass: 706 kg (1,556 lb). Spacecraft: Intelsat 4. Agency: Intelsat. Perigee: 36,151 km (22,463 mi). Apogee: 36,236 km (22,515 mi). Inclination: 15.30 deg. Period: 1,457.00 min. Launch vehicle put payload into geosynchronous transfer orbit; the satellite performed the apogee burn and positioned itself in geosynchronous orbit over the Atlantic Ocean at 24.5 deg W. Subsequently at 23 deg W in 1971-1975; over the Atlantic Ocean 1-6 deg W in 1976-1980; over the Atlantic Ocean 0-5 deg E in 1980-1983. As of 3 September 2001 at 31.91 deg E drifting at 5.168 deg W per day. As of 2006 Dec 18 located at 133.93E drifting at 5.166W degrees per day. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). 1971 April 5 - Vandenberg 576A1. Atlas F 85F ABRES LAR-1 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1971 May 9 - 01:11 GMT - Cape Canaveral LC36A. SLV-3C Centaur AC-24 / Centaur D-1A 5405C FAILURE: Inadvertent Centaur electronic signal shut down stage early. Mariner H Mass: 996 kg (2,195 lb). Spacecraft: Mariner 8-9. Agency: NASA. Intended Mars flyby. 1971 May 30 - 22:23 GMT - Cape Canaveral LC36B. SLV-3C Centaur AC-23 / Centaur D-1A 5404C Mariner 9 Mass: 974 kg (2,147 lb). Spacecraft: Mariner 8-9. Agency: NASA/JPL. The first spacecraft to orbit another planet. The Mariner Mars 71 mission was planned to consist of two spacecraft on complementary missions. Mariner 8 was to map 70 % of the Martian surface and Mariner 9 was to study temporal changes in the Martian atmosphere and on the Martian surface. The launch failure of Mariner 8 forced Mariner 9 to combine the mission objectives of both. For the survey portion of the mission, the planetary surface was to be mapped with the same resolution as planned for the original mission, although the resolution of pictures of the polar regions would be decreased due to the increased slant range. The variable features experiments were changed from studies of six given areas every 5 days to studies of smaller regions every 17 days. Mariner 9 was launched on a direct trajectory to Mars. Separation from the booster occurred at 22:36 GMT. The four solar panels were deployed at 22:40 GMT. The sensors locked onto the Sun at 23:16, shortly after the spacecraft left the Earth's shadow and Canopus acquisition was achieved at 02:26 GMT 31 May. A planned midcourse maneuver was executed on 5 June. Mariner 9 arrived at Mars on 14 November 1971 after a 167 day flight. A 15 minute 23 second rocket burn put the spacecraft into Mars orbit. The insertion orbit had a periapsis of 1398 km and a period of 12 hr, 34 min. Two days later a 6 second rocket burn changed the orbital period to just under 12 hours with a periapsis of 1387 km. A correction trim maneuver was made on 30 December on the 94th orbit which raised the periapsis to 1650 km and changed the orbital period to 11:59:28 so that synchronous data transmissions could be made to the Goldstone 64-m DSN antenna. Imaging of the surface of Mars by Mariner 9 was delayed by a dust storm which started on 22 September 1971 in the Noachis region. The storm quickly grew into one of the largest global storms ever observed on Mars. By the time the spacecraft arrived at Mars no surface details could be seen except the summits of Olympus Mons and the three Tharsis volcanoes. The storm abated through November and December and normal mapping operations began. The spacecraft gathered data on the atmospheric composition, density, pressure, and temperature and also the surface composition, temperature, gravity, and topography of Mars. A total of 54 billion bits of scientific data were returned, including 7329 images covering the entire planet. After depleting its supply of attitude control gas, the spacecraft was turned off on 27 October 1972. Mariner 9 was left in an orbit which should not decay for at least 50 years, after which the spacecraft will enter the Martian atmosphere. The Mariner 9 mission resulted in a global mapping of the surface of Mars, including the first detailed views of the martian volcanoes, Valles Marineris, the polar caps, and the satellites Phobos and Deimos. It also provided information on global dust storms, the gravity field as well as evidence for surface aeolian activity. 1971 June 29 - 13:10 GMT - Vandenberg 576A3. Atlas F/Trident 103F ABRES RVTO-2A-3 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1971 August 7 - 00:11 GMT - Vandenberg 576A2. Atlas F 76F / OV-1 (2x) OV1-20P Mass: 70 kg (154 lb). Spacecraft: OV1. Agency: USAF STP. Perigee: 136 km (84 mi). Apogee: 1,932 km (1,200 mi). Inclination: 92.00 deg. Period: 105.90 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1971 September 1 - Vandenberg 576A1. Atlas F 74F ABRES LAR-2 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1971 December 4 - 22:30 GMT - Cape Canaveral LC13. SLV-3A Agena D 5503A / Agena D 2804 FAILURE: First stage failure. AFP-827 / Canyon 4 Mass: 700 kg (1,540 lb). Spacecraft: Canyon. Agency: U.S. Air Force. 1971 December 20 - 01:10 GMT - Cape Canaveral LC36A. SLV-3C Centaur AC-26 / Centaur D-1A 5006C Intelsat 4 F-3 Mass: 1,410 kg (3,100 lb). Spacecraft: Intelsat 4. Agency: Intelsat. Perigee: 35,930 km (22,320 mi). Apogee: 36,009 km (22,374 mi). Inclination: 11.10 deg. Period: 1,445.50 min. Over Atlantic. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit over the Atlantic Ocean at 20-25 deg W in 1972-1976; over the Atlantic Ocean 34 deg W in 1976-1977; over the Atlantic Ocean 18-22 deg W in 1977-1980; over the Atlantic Ocean 53 deg W in 1981-1982; over the Atlantic Ocean 38-44 deg W in 1982-1983 As of 4 September 2001 located at 90.58 deg E drifting at 2.365 deg W per day. As of 2007 Mar 10 located at 54.69E drifting at 2.365W degrees per day. 1972 January 23 - 00:12 GMT - Cape Canaveral LC36B. SLV-3C Centaur AC-28 / Centaur D-1A 5008C Intelsat 4 F-4 Mass: 1,410 kg (3,100 lb). Spacecraft: Intelsat 4. Agency: Intelsat. Perigee: 35,905 km (22,310 mi). Apogee: 35,917 km (22,317 mi). Inclination: 10.50 deg. Period: 1,442.50 min. Over Pacific. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit over the Pacific Ocean at 174 deg E in 1972-1974; over the Pacific Ocean 179 deg E in 1975-1982; over the Atlantic Ocean 1 deg W in 1982-1983 As of 28 August 2001 located at 178.00 deg E drifting at 1.569 deg W per day. As of 2007 Mar 7 located at 155.84W drifting at 1.593W degrees per day. 1972 March 3 - 01:49 GMT - Cape Canaveral LC36A. SLV-3C Centaur AC-27 / Centaur D-1A 5007C Pioneer 10 Mass: 259 kg (570 lb). Spacecraft: Pioneer 10-11. Agency: NASA ARC. Jupiter flyby December 1973; first man-made object to leave solar system. The spacecraft achieved its closest approach to Jupiter on December 3, 1973, when it reached approximately 2.8 Jovian radii (about 200,000 km). As of Jan. 1, 1997 Pioneer 10 was at about 67 AU from the Sun near the ecliptic plane and heading outward from the Sun at 2.6 AU/year and downstream through the heliomagnetosphere towards the tail region and interstellar space. Additional Details: Pioneer 10. 1972 June 13 - 21:53 GMT - Cape Canaveral LC36B. SLV-3C Centaur AC-29 / Centaur D-1A 5009C Intelsat 4 F-5 Mass: 1,410 kg (3,100 lb). Spacecraft: Intelsat 4. Agency: Intelsat. Perigee: 35,811 km (22,251 mi). Apogee: 35,847 km (22,274 mi). Inclination: 11.30 deg. Period: 1,438.30 min. Over Indian Ocean. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit over the Indian Ocean at 61 deg E in 1972-1975; over the Indian Ocean 60 deg E in 1976-1980; over the Pacific Ocean 179 deg E in 1980-1981 As of 2 September 2001 located at 8.61 deg E drifting at 0.536 deg W per day. As of 2007 Mar 9 located at 73.10W drifting at 0.625W degrees per day. 1972 August 21 - 10:28 GMT - Cape Canaveral LC36B. SLV-3C Centaur AC-22 / Centaur D-1A 5004C OAO 3 Mass: 2,204 kg (4,858 lb). Spacecraft: OAO. Agency: NASA GSF. Perigee: 713 km (443 mi). Apogee: 724 km (449 mi). Inclination: 35.00 deg. Period: 99.20 min. UV observations of stellar objects. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). Launch vehicle put payload into geosynchronous transfer orbit 1972 October 2 - 20:09 GMT - Vandenberg 576A1. LV Model: Atlas Burner 2A . Atlas / Burner 2A 102F RADCAT Mass: 208 kg (458 lb). Spacecraft: RADCAT. Agency: USA. Perigee: 627 km (389 mi). Apogee: 638 km (396 mi). Inclination: 98.60 deg. Period: 97.40 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). 1972 December 20 - 22:20 GMT - Cape Canaveral LC13. SLV-3A Agena D 5204A / Agena D A 2805 Canyon 5 Mass: 700 kg (1,540 lb). Spacecraft: Canyon. Agency: NRO/USAF. Perigee: 31,012 km (19,269 mi). Apogee: 40,728 km (25,307 mi). Inclination: 9.70 deg. Period: 1,440.40 min. First launch of improved ELINT satellite. In comparison to earlier Canyon ELINT satellites, Improved Canyon had a similar but heavier payload which separated from the Agena D final stage. 1973 March 6 - 09:30 GMT - Cape Canaveral LC13. SLV-3A Agena D 5202A / Agena D A 1552 Rhyolite 2 Mass: 700 kg (1,540 lb). Spacecraft: Rhyolite. Agency: NRO/CIA. Perigee: 35,679 km (22,169 mi). Apogee: 35,855 km (22,279 mi). Inclination: 0.20 deg. Period: 1,435.10 min. Second launch of Rhyolite geostationary ELINT satellite. 1973 April 6 - 02:11 GMT - Cape Canaveral LC36B. SLV-3D Centaur AC-30 / Centaur D-1AR 5011D Pioneer 11 Mass: 259 kg (570 lb). Spacecraft: Pioneer 10-11. Agency: NASA ARC. Jupiter flyby December 1974; Saturn flyby September 1979. Solar system escape trajectory. Pioneer 11 was the second mission to investigate Jupiter and the outer solar system and the first to explore the planet Saturn and its main rings. Pioneer 11, like Pioneer 10, used Jupiter's gravitational field to alter its trajectory radically. It passed close to Saturn and then it followed an escape trajectory from the solar system. During its closest approach, December 4, 1974, Pioneer 11 passed to within 34,000 km of Jupiter's cloud tops. It passed by Saturn on September 1, 1979, at a distance of 21,000 km from Saturn's cloud tops. The spacecraft has operated on a backup transmitter since launch. Instrument power sharing began in February 1985 due to declining RTG power output. Science operations and daily telemetry ceased on September 30, 1995 when the RTG power level was insufficient to operate any experiments. As of the end of 1995 the spacecraft was located at 44.7 AU from the Sun at a nearly asymptotic latitude of 17.4 degrees above the solar equatorial plane and was heading outward at 2.5 AU/year. Routine tracking and project data processing operations were terminated on March 31, 1997 for budget reasons. 1973 August 23 - 22:57 GMT - Cape Canaveral LC36A. SLV-3D Centaur AC-31 / Centaur D-1AR 5010D Intelsat 4 F-7 Mass: 1,410 kg (3,100 lb). Spacecraft: Intelsat 4. Agency: Intelsat. Perigee: 36,080 km (22,410 mi). Apogee: 36,132 km (22,451 mi). Inclination: 10.40 deg. Period: 1,452.50 min. Over Atlantic Ocean. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit over the Atlantic Ocean at 30 deg W in 1973-1976 over the Atlantic Ocean 1 deg W in 1976-1980; over the Indian Ocean 56 deg E in 1980-1981; over the Pacific Ocean179 deg E in 1981-1982; over the Atlantic Ocean 53 deg W in 1982-1983 As of 31 August 2001 located at 74.52 deg W drifting at 4.067 deg W per day. As of 2007 Mar 10 located at 19.61E drifting at 4.058W degrees per day. 1973 August 29 - Vandenberg 576A3. Atlas F 78F BMRS RVTO-3A-2 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1973 September 30 - Vandenberg 576A1. Atlas F 108F BMRS ACE-1 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1973 November 3 - 05:45 GMT - Cape Canaveral LC36B. SLV-3D Centaur AC-34 / Centaur D-1AR 5014D Mariner 10 Mass: 526 kg (1,159 lb). Spacecraft: Mariner 10. Agency: NASA/JPL. Mariner 10 was the first spacecraft to reach Mercury. Mariner 10 was placed in a parking orbit for 25 minutes after launch, then accelerated to a trans-Venus escape trajectory. The television and ultraviolet experiments were trained on the comet Kohoutek while the spacecraft was en route to its destination. The vehicle's first planetary encounter was with Venus on February 5, 1974, at a distance of 4200 km. Mariner 10 took 4,000 photos of Venus, which revealed a nearly round planet enveloped in smooth cloud layers. The gravity of Venus bent the orbit of the spacecraft and sent it towards Mercury. It crossed the orbit of Mercury on March 29, 1974, at 20:46 GMT, at a distance of 704 km from the surface. Photographs taken during the pass revealed an intensely cratered, Moon-like surface and a faint atmosphere of mostly helium. After the first flyby, Mariner 10 entered solar orbit, which permitted two more rendezvous with Mercury. On September 21, 1974, the second Mercury rendezvous, at an altitude of about 47,000 km, provided another opportunity to photograph the sunlit side of the planet and the south polar region. The third and final Mercury encounter on March 16, 1975, at an altitude of 327 km, yielded 300 photographs and magnetic field measurements. The vehicle was turned off March 24, 1975 when the supply of attitude-control gas was depleted. 1974 March 6 - Vandenberg 576A1. Atlas F 73F BMRS SFT-1 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1974 March 23 - Vandenberg 576A3. Atlas F 97F BMRS ACE-2 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1974 May 1 - Vandenberg 576A1. Atlas F 54F BMRS SFT-2 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1974 June 28 - Vandenberg 576A1. Atlas F 82F BMRS SFT-3 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1974 July 14 - 05:17 GMT - Vandenberg SLC3W. Atlas F/PTS 69F NTS 1 Mass: 293 kg (645 lb). Spacecraft: NTS. Agency: USAF. Perigee: 13,446 km (8,354 mi). Apogee: 13,774 km (8,558 mi). Inclination: 125.20 deg. Period: 468.70 min. Demonstrated navigation technologies leading eventually to Navstar/GPS system. Operated for 5 years. 1974 September 8 - Vandenberg 576A1. Atlas F 80F BMRS ACE-3 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1974 October 14 - 04:46 GMT - Vandenberg 576A3. Atlas F 31F BMRS RVTO-3A-1 re-entry vehicle test flight Agency: USAF AFSC. Apogee: 1,400 km (800 mi). 1974 November 21 - 23:43 GMT - Cape Canaveral LC36B. SLV-3D Centaur AC-32 / Centaur D-1AR 5012D Intelsat 4 F-8 Mass: 1,410 kg (3,100 lb). Spacecraft: Intelsat 4. Agency: Intelsat. Perigee: 35,907 km (22,311 mi). Apogee: 35,944 km (22,334 mi). Inclination: 8.80 deg. Period: 1,443.20 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit over the Pacific Ocean at 174 deg E in 1974-1982; over the Pacific Ocean 179 deg E in 1982; over the Atlantic Ocean 1 deg W in 1983-1985 As of 1 September 2001 located at 139.80 deg W drifting at 1.762 deg W per day. As of 2007 Mar 9 located at 61.11W drifting at 1.754W degrees per day. 1975 February 20 - 23:35 GMT - Cape Canaveral LC36A. SLV-3D Centaur AC-33 / Centaur D-1AR 5015D FAILURE: Staging electrical disconnect. Intelsat 4 F-6 Mass: 1,410 kg (3,100 lb). Spacecraft: Intelsat 4. Agency: Intelsat. Staging electrical disconnect. Launch vehicle was to have put payload into geosynchronous transfer orbit 1975 April 13 - 00:51 GMT - Vandenberg SLC3W. Atlas F 71F / Star-17A FAILURE: First stage failure due to explosion in flame pit at lift-off. P 72-2 Spacecraft: P 72. Agency: U.S. Air Force. A lack of deluge water and collection in the flame bucket of a kerosene/liquid oxygen gel led to the explosion of the gel on lift-off, damaging one of the Atlas engines and leading to complete engine failure during the ascent. 1975 May 22 - 22:04 GMT - Cape Canaveral LC36A. SLV-3D Centaur AC-35 / Centaur D-1AR 5018D Intelsat 4 F-1 Mass: 727 kg (1,602 lb). Spacecraft: Intelsat 4. Agency: Intelsat. Perigee: 36,016 km (22,379 mi). Apogee: 36,128 km (22,448 mi). Inclination: 8.90 deg. Period: 1,450.70 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit over the Indian Ocean at 63 deg E in 1976-1978; over the Atlantic Ocean 17.0 deg W in 1978; over the Atlantic Ocean 18.5 deg W in 1979-1981; over the Pacific Ocean 174 deg E in 1982; over the Atlantic Ocean 53 deg W in 1983-1984; over the Atlantic Ocean 50 deg W in 1984-1987 As of 30 August 2001 located at 111.08 deg W drifting at 3.657 deg W per day. As of 2007 Mar 11 located at 95.13E drifting at 3.657W degrees per day. 1975 June 18 - 09:00 GMT - Cape Canaveral LC13. SLV-3A Agena D 5506A / Agena D A 2806 Canyon 6 Mass: 700 kg (1,540 lb). Spacecraft: Canyon. Agency: NRO/USAF. Perigee: 30,200 km (18,700 mi). Apogee: 40,800 km (25,300 mi). Inclination: 9.00 deg. Period: 1,422.00 min. 1975 September 26 - 00:17 GMT - Cape Canaveral LC36B. SLV-3D Centaur AC-36 / Centaur D-1AR 5016 Intelsat 4A F-1 Mass: 1,500 kg (3,300 lb). Spacecraft: Intelsat 4A. Agency: Intelsat. Perigee: 35,860 km (22,280 mi). Apogee: 35,910 km (22,310 mi). Inclination: 8.90 deg. Period: 1,441.10 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit over the Atlantic Ocean at 25 deg W in 1975-1981; over the Atlantic Ocean 18.5 deg W in 1982-1983; over the Atlantic Ocean 30 deg W in 1983-1986 As of 30 August 2001 located at 4.05 deg E drifting at 1.213 deg W per day. As of 2007 Mar 10 located at 28.51E drifting at 1.239W degrees per day. 1976 January 29 - 23:56 GMT - Cape Canaveral LC36B. SLV-3D Centaur AC-37 / Centaur D-1AR 501 Intelsat 4A F-2 Mass: 1,500 kg (3,300 lb). Spacecraft: Intelsat 4A. Agency: Intelsat. Perigee: 35,924 km (22,322 mi). Apogee: 35,981 km (22,357 mi). Inclination: 9.00 deg. Period: 1,444.60 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit over the Atlantic Ocean at 29.5 deg W in 1976-79; over the Atlantic Ocean 27.5 deg W in 1979-1980; over the Atlantic Ocean 21.5 deg W in 1980-1983; over the Indian Ocean 57 deg E in 1983-1984; over the Atlantic Ocean 2-4 deg W in 1984-1985 As of 3 September 2001 located at 151.88 deg E drifting at 2.088 deg W per day. As of 2007 Mar 10 located at 130.98W drifting at 2.123W degrees per day. 1976 April 30 - 19:12 GMT - Vandenberg SLC3W. Atlas F/MSD 59F NOSS 1 (Whitecloud 1) Spacecraft: NOSS. Agency: USN. Perigee: 1,092 km (678 mi). Apogee: 1,128 km (700 mi). Inclination: 63.50 deg. Period: 107.50 min. Ocean surveillance; aka White Cloud type spacecraft; Navy Ocean Surveillance Satellite; PARCAE. 1976 May 13 - 22:28 GMT - Cape Canaveral LC36A. SLV-3D Centaur AC-38 / Centaur D-1AR 5020 Comstar 1 Mass: 792 kg (1,746 lb). Spacecraft: Intelsat 4A. Agency: Comsat. Perigee: 35,903 km (22,309 mi). Apogee: 35,925 km (22,322 mi). Inclination: 12.70 deg. Period: 1,442.60 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit over the Americas at 128 deg W in 1976-1981 over the Americas at 95 deg W in 1981-1983 over the Atlantic Ocean 76 deg W in 1983-1984 As of 4 September 2001 located at 48.64 deg E drifting at 1.641 deg W per day. As of 2007 Mar 10 located at 31.21E drifting at 1.624W degrees per day. 1976 July 22 - 22:04 GMT - Cape Canaveral LC36B. SLV-3D Centaur AC-40 / Centaur D-1AR 5022 Comstar 2 Mass: 792 kg (1,746 lb). Spacecraft: Intelsat 4A. Agency: Comsat. Perigee: 35,855 km (22,279 mi). Apogee: 35,887 km (22,299 mi). Inclination: 12.60 deg. Period: 1,440.40 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit over the Americas at 95 deg W in 1976-1983 over the Americas at 76 deg W in 1983-1993 As of 28 August 2001 located at 172.63 deg W drifting at 1.031 deg W per day. As of 2007 Mar 10 located at 150.18W drifting at 1.064W degrees per day. 1977 May 23 - 18:13 GMT - Cape Canaveral LC13. SLV-3A Agena D 5507A / Agena D A 2807 Canyon 7 Mass: 700 kg (1,540 lb). Spacecraft: Canyon. Agency: NRO/USAF. Perigee: 35,679 km (22,169 mi). Apogee: 35,855 km (22,279 mi). Inclination: 0.20 deg. Period: 1,435.10 min. 1977 May 26 - 21:47 GMT - Cape Canaveral LC36A. SLV-3D Centaur AC-39 / Centaur D-1AR 5019 Intelsat 4A F-4 Mass: 1,500 kg (3,300 lb). Spacecraft: Intelsat 4A. Agency: Intelsat. Perigee: 35,969 km (22,350 mi). Apogee: 36,075 km (22,415 mi). Inclination: 7.80 deg. Period: 1,448.20 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit over the Atlantic Ocean at 34.5 deg W in 1977-1983 over the Atlantic Ocean 21.5 deg W in 1983-1989 As of 28 August 2001 located at 153.30 deg E drifting at 2.976 deg W per day. As of 2007 Mar 10 located at 121.69W drifting at 3.003W degrees per day. 1977 June 23 - 09:16 GMT - Vandenberg SLC3W. Atlas F 65F / SGS-1 NTS 2 Mass: 431 kg (950 lb). Spacecraft: NTS. Agency: USAF/USN. Perigee: 20,115 km (12,498 mi). Apogee: 20,256 km (12,586 mi). Inclination: 63.90 deg. Period: 718.10 min. Navigation Technical Satellite; GPS precursor. Operated 50% satisfactorily -- still operating 25 years later. 1977 August 12 - 06:29 GMT - Cape Canaveral LC36B. SLV-3D Centaur AC-45 / Centaur D-1AR 5025 HEAO 1 Mass: 2,720 kg (5,990 lb). Spacecraft: HEAO. Agency: NASA MSF. Perigee: 429 km (266 mi). Apogee: 447 km (277 mi). Inclination: 22.70 deg. Period: 93.40 min. High Energy Astronomical Observatory; surveyed sky in X-ray band. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). 1977 September 30 - 01:02 GMT - Cape Canaveral LC36A. SLV-3D Centaur AC-43 / Centaur D-1AR 5701 FAILURE: Atlas failure - gas generator hot gas leak. Intelsat IVA F-5 Mass: 1,500 kg (3,300 lb). Spacecraft: Intelsat 4A. Agency: Intelsat. 1977 December 8 - 17:45 GMT - Vandenberg SLC3W. Atlas F/MSD 50F NOSS 2 Spacecraft: NOSS. Agency: USN. Perigee: 1,054 km (654 mi). Apogee: 1,169 km (726 mi). Inclination: 63.40 deg. Period: 107.50 min. Ocean surveillance; aka White Cloud type spacecraft; Navy Ocean Surveillance Satellite; PARCAE. 1977 December 11 - 22:45 GMT - Cape Canaveral LC13. SLV-3A Agena D 5504A / Agena D A 1553 Rhyolite 3 Mass: 700 kg (1,540 lb). Spacecraft: Rhyolite. Agency: NRO/CIA. Perigee: 35,679 km (22,169 mi). Apogee: 35,855 km (22,279 mi). Inclination: 0.20 deg. Period: 1,435.10 min. Third launch of Rhyolite geostationary ELINT satellite. Code name changed to Aquacade after Rhyolite name came out in trial of spy Boyce. 1978 January 7 - 00:15 GMT - Cape Canaveral LC36B. SLV-3D Centaur AC-46 / Centaur-D1AR AC-46 Intelsat 4A F-3 Mass: 1,511 kg (3,331 lb). Spacecraft: Intelsat 4A. Agency: Intelsat. Perigee: 35,874 km (22,291 mi). Apogee: 35,909 km (22,312 mi). Inclination: 7.20 deg. Period: 1,441.50 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit over the Indian Ocean at 60 deg E in 1978-1982 over the Pacific Ocean 179 deg E in 1982-1986 over the Pacific Ocean 177 deg E in 1986-1988 As of 2 September 2001 located at 156.51 deg W drifting at 1.304 deg W per day. As of 2007 Feb 27 located at 107.90E drifting at 1.326W degrees per day. 1978 February 9 - 21:17 GMT - Cape Canaveral LC36A. SLV-3D Centaur AC-44 / Centaur D-1AR 5024 Fltsatcom 1 Mass: 1,884 kg (4,153 lb). Spacecraft: Fltsatcom. Agency: USN. Perigee: 36,119 km (22,443 mi). Apogee: 36,170 km (22,470 mi). Inclination: 14.60 deg. Period: 1,454.40 min. Fleet Satellite Communications. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit over the Americas at 100 deg W in 1978-1987; over the Pacific Ocean 177 deg W in 1987-1992; over the Atlantic Ocean 15 deg W in 1992-1996;over the Indian Ocean 72 deg E in 1996-2001. Last known longitude (26 July 1999) 71.17 deg E drifting at 0.004 deg W per day. 1978 February 22 - 23:44 GMT - Vandenberg SLC3E. Atlas F/SVS 64F Navstar 1 Mass: 759 kg (1,673 lb). Spacecraft: GPS Block 1. Agency: USAF. Perigee: 20,249 km (12,582 mi). Apogee: 20,560 km (12,770 mi). Inclination: 64.50 deg. Period: 727.00 min. Also known as Navigational Development Satellite 1. Technology prototype of Navstar satellite. 1978 March 31 - 23:36 GMT - Cape Canaveral LC36B. SLV-3D Centaur AC-48 / Centaur D-1AR 5028 Intelsat 4A F-6 Mass: 826 kg (1,821 lb). Spacecraft: Intelsat 4A. Agency: Intelsat. Perigee: 35,758 km (22,218 mi). Apogee: 35,823 km (22,259 mi). Inclination: 11.60 deg. Period: 1,436.30 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit over the Indian Ocean at 63 deg E in 1978-1982; over the Pacific Ocean 174 deg E in 1982-1986; over the Pacific Ocean 170 deg E in 1986 As of 26 August 2001 located at 92.43 deg E drifting at 0.407 deg E per day. As of 2007 Mar 11 located at 75.50E drifting at 0.437W degrees per day. 1978 April 7 - 00:45 GMT - Cape Canaveral LC13. SLV-3A Agena D 5505A / Agena D A 1554 Rhyolite 4 Mass: 700 kg (1,540 lb). Spacecraft: Rhyolite. Agency: NRO/CIA. Perigee: 35,679 km (22,169 mi). Apogee: 35,855 km (22,279 mi). Inclination: 0.20 deg. Period: 1,435.10 min. Fourth and final launch of Rhyolite geostationary ELINT satellite. Code name changed to Aquacade after Rhyolite name came out in trial of spy Boyce. 1978 May 13 - 10:34 GMT - Vandenberg SLC3E. Atlas F/SVS 49F Navstar 2 Mass: 759 kg (1,673 lb). Spacecraft: GPS Block 1. Agency: USAF. Perigee: 19,523 km (12,131 mi). Apogee: 20,653 km (12,833 mi). Inclination: 63.60 deg. Period: 714.20 min. Also known as Navigational Development Satellite 2. Technology prototype of Navstar satellite. 1978 May 20 - 13:13 GMT - Cape Canaveral LC36A. SLV-3D Centaur AC-50 / Centaur D-1AR 5030 Pioneer Venus Orbiter Mass: 582 kg (1,283 lb). Spacecraft: Pioneer 12. Agency: NASA ARC. The Pioneer Venus Orbiter was inserted into an elliptical orbit around Venus on December 4, 1978. After entering orbit around Venus in 1978, the spacecraft returned global maps of the planet's clouds, atmosphere and ionosphere, measurements of the atmosphere-solar wind interaction, and radar maps of 93 percent of the planet's surface. Additionally, the vehicle made use of several opportunities to make systematic UV observations of several comets. From Venus orbit insertion to July 1980, periapsis was held between 142 and 253 km (at 17 degrees north latitude) to facilitate radar and ionospheric measurements. The spacecraft was in a 24 hour orbit with an apoapsis of 66,900 km. Thereafter, the periapsis was allowed to rise (to 2290 km at maximum) and then fall, to conserve fuel. In 1991 the Radar Mapper was reactivated to investigate previously inaccessible southern portions of the planet. In May 1992 Pioneer Venus began the final phase of its mission, in which the periapsis was held between 150 and 250 km until the fuel ran out and atmospheric entry destroyed the spacecraft. With a planned primary mission duration of only eight months, the spacecraft remained in operation until October 8, 1992 when it finally burned up in Venus' atmosphere after running out of propellant. 1978 June 27 - 01:12 GMT - Vandenberg SLC3W. Atlas F/Agena D 23F Seasat 1 Mass: 2,300 kg (5,000 lb). Spacecraft: Seasat. Agency: NASA/JPL. Perigee: 761 km (472 mi). Apogee: 765 km (475 mi). Inclination: 108.00 deg. Period: 100.10 min. Oceanographic. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). 1978 June 29 - 22:24 GMT - Cape Canaveral LC36B. SLV-3D Centaur AC-41 / Centaur D-1AR 5021 Comstar 3 Mass: 1,520 kg (3,350 lb). Spacecraft: Intelsat 4A. Agency: Comsat. Perigee: 36,007 km (22,373 mi). Apogee: 36,172 km (22,476 mi). Inclination: 11.50 deg. Period: 1,451.60 min. US domestic telephone service. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit over the Americas at 87 deg W in 1978-1984 over the Americas at 76 deg W in 1984-1986 As of 1 September 2001 located at 101.79 deg W drifting at 3.884 deg W per day. As of 2007 Mar 4 located at 39.19E drifting at 3.878W degrees per day. 1978 August 8 - 07:33 GMT - Cape Canaveral LC36A. SLV-3D Centaur AC-51 / Centaur D-1AR 5031 Pioneer Venus 2 Mass: 904 kg (1,992 lb). Spacecraft: Pioneer 13. Agency: NASA ARC. The Pioneer Venus Multiprobe consisted of a bus which carried one large and three small `atmospheric probes. The large probe was released on November 16, 1978 and the three small probes on November 20. All four probes entered the Venus atmosphere on December 9, followed by the bus. The small probes were each targeted at different parts of the planet and were named accordingly. The North probe entered the atmosphere at about 60 degrees north latitude on the day side. The night probe entered on the night side. The day probe entered well into the day side, and was the only one of the four probes which continued to send radio signals back after impact, for over an hour. With no heat shield or parachute, the bus survived and made measurements only to about 110 km altitude before burning up. It afforded the only direct view of the upper Venus atmosphere, as the probes did not begin making direct measurements until they had decelerated lower in the atmosphere. 1978 October 7 - 00:28 GMT - Vandenberg SLC3E. Atlas F/SVS 47F Navstar 3 Mass: 759 kg (1,673 lb). Spacecraft: GPS Block 1. Agency: USAF. Perigee: 20,706 km (12,866 mi). Apogee: 20,941 km (13,012 mi). Inclination: 63.30 deg. Period: 744.20 min. Technology prototype of Navstar satellite. 1978 October 13 - 11:23 GMT - Vandenberg SLC3W. Atlas F 29F / Star-37S-ISS Tiros N Mass: 734 kg (1,618 lb). Spacecraft: Tiros N. Agency: NASA GSF. Perigee: 829 km (515 mi). Apogee: 845 km (525 mi). Inclination: 98.70 deg. Period: 101.70 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). 1978 November 13 - 05:24 GMT - Cape Canaveral LC36B. SLV-3D Centaur AC-52 / Centaur D-1AR 5032 HEAO 2 Mass: 3,150 kg (6,940 lb). Spacecraft: HEAO. Agency: NASA MSF. Perigee: 526 km (326 mi). Apogee: 548 km (340 mi). Inclination: 23.50 deg. Period: 95.40 min. High Energy Astronomy Observatory. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). 1978 December 11 - 03:59 GMT - Vandenberg SLC3E. Atlas F/SVS 39F Navstar 4 Mass: 770 kg (1,690 lb). Spacecraft: GPS Block 1. Agency: USAF. Perigee: 20,750 km (12,890 mi). Apogee: 21,012 km (13,056 mi). Inclination: 64.60 deg. Period: 746.50 min. Global Positioning System. First pre-opertional Navstar satellite. 1979 February 24 - 08:24 GMT - Vandenberg SLC3W. Atlas F/OIS 27F Solwind (P 78-1) Mass: 1,331 kg (2,934 lb). Spacecraft: Solwind. Agency: USN. Perigee: 310 km (190 mi). Apogee: 317 km (196 mi). Inclination: 97.80 deg. Period: 90.80 min. Ionosphere and magnetosphere studies; destroyed on 13 September 1985 (while still functioning) as part of an American ASAT test. 1979 May 4 - 18:56 GMT - Cape Canaveral LC36A. SLV-3D Centaur AC-47 / Centaur D-1AR 5027 Fltsatcom 2 Mass: 1,884 kg (4,153 lb). Spacecraft: Fltsatcom. Agency: USN. Perigee: 36,227 km (22,510 mi). Apogee: 36,331 km (22,574 mi). Inclination: 13.50 deg. Period: 1,461.30 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit at 23 deg W in 1979-1980; 72 deg E in 1980-1992 As of 5 September 2001 located at 90.48 deg W drifting at 6.234 deg W per day. As of 2007 Mar 9 located at 12.01W drifting at 6.223W degrees per day. 1979 June 27 - 15:51 GMT - Vandenberg SLC3W. Atlas F 25F / Star-37S-ISS NOAA 6 Mass: 723 kg (1,593 lb). Spacecraft: Tiros N. Agency: NOAA. Perigee: 785 km (487 mi). Apogee: 800 km (490 mi). Inclination: 98.60 deg. Period: 100.70 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). 1979 September 20 - 05:28 GMT - Cape Canaveral LC36B. SLV-3D Centaur AC-53 / Centaur D-1AR 5033 HEAO 3 Mass: 3,150 kg (6,940 lb). Spacecraft: HEAO. Agency: NASA. Perigee: 487 km (302 mi). Apogee: 503 km (312 mi). Inclination: 43.60 deg. Period: 94.50 min. High Energy Astronomy Observatory; cosmic, gamma ray measurements. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). 1980 January 18 - 01:26 GMT - Cape Canaveral LC36A. SLV-3D Centaur AC-49 / Centaur D-1AR 5029 Fltsatcom 3 Mass: 1,884 kg (4,153 lb). Spacecraft: Fltsatcom. Agency: USN. Perigee: 35,669 km (22,163 mi). Apogee: 35,851 km (22,276 mi). Inclination: 9.10 deg. Period: 1,434.80 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit at 22 deg W in 1980-1990 As of 28 August 2001 located at 174.83 deg W drifting at 0.082 deg W per day. As of 2007 Mar 10 located at 84.20W drifting at 0.376E degrees per day. 1980 February 9 - 23:08 GMT - Vandenberg SLC3E. Atlas F/SVS 35F Navstar 5 Mass: 770 kg (1,690 lb). Spacecraft: GPS Block 1. Agency: USAF. Perigee: 19,805 km (12,306 mi). Apogee: 20,560 km (12,770 mi). Inclination: 64.90 deg. Period: 718.00 min. Global Positioning System. 1980 March 3 - 09:27 GMT - Vandenberg SLC3W. Atlas F/MSD 67F NOSS 3 Spacecraft: NOSS. Agency: USN. Perigee: 1,035 km (643 mi). Apogee: 1,150 km (710 mi). Inclination: 63.00 deg. Period: 107.10 min. Ocean surveillance; aka White Cloud type spacecraft; Navy Ocean Surveillance Satellite; PARCAE. 1980 April 26 - 22:00 GMT - Vandenberg SLC3E. Atlas F/SVS 34F Navstar 6 Mass: 770 kg (1,690 lb). Spacecraft: GPS Block 1. Agency: USAF. Perigee: 19,387 km (12,046 mi). Apogee: 20,471 km (12,720 mi). Inclination: 62.80 deg. Period: 707.80 min. Global Positioning System. 1980 May 29 - 10:53 GMT - Vandenberg SLC3W. Atlas F 19F / Star-37S-ISS FAILURE: Atlas sustainer engine under-thrust resulted in 50 second extended burn time, and spacecraft attempted to separate and fired apogee kick motor while booster was still thrusting. NOAA B Mass: 1,405 kg (3,097 lb). Spacecraft: Tiros N. Agency: NOAA. Perigee: 264 km (164 mi). Apogee: 1,445 km (897 mi). Inclination: 92.20 deg. Period: 102.10 min. Unusable orbit; would have been NOAA 7. At engine start up, one of the booster engines suffered an internal fuel leak, causing it to run at about 80% thrust. As a result the booster was low on velocity and heavy on propellant over much of its flight and ran an incredible 50 seconds longer than the nominal burn. The NOAA Advanced TIROS payload was designed with no direct communication with the booster, and unaware of the booster problem, at 375 sec after liftoff attempted to separate with the booster still firing. The booster's continued thrusting defeated the payload's attempt to perform the required pitch maneuver. When the payload fired its apogee kick motor, it blew the top of the booster's liquid oxygen tank off. The spacecraft survived all this, but the resultant orbit was highly elliptical rather than the desired circular sun-synchronous. The mission was a total loss. Officially: Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).> 1980 October 31 - 03:54 GMT - Cape Canaveral LC36A. SLV-3D Centaur AC-57 / Centaur D-1AR 5037 Fltsatcom 4 Mass: 1,800 kg (3,900 lb). Spacecraft: Fltsatcom. Agency: USN. Perigee: 35,769 km (22,225 mi). Apogee: 35,803 km (22,246 mi). Inclination: 9.20 deg. Period: 1,436.10 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit at 171 deg E from 1981. Last known longitude (25 July 1999) 172.61 deg E drifting at 0.001 deg W per day. 1980 December 6 - 23:31 GMT - Cape Canaveral LC36B. SLV-3D Centaur AC-54 / Centaur D-1AR 5034 Intelsat 5 F-2 Mass: 2,000 kg (4,400 lb). Spacecraft: Intelsat 5. Agency: Intelsat. Perigee: 36,118 km (22,442 mi). Apogee: 36,242 km (22,519 mi). Inclination: 9.70 deg. Period: 1,456.20 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit at 21 deg W in 1981; 27 deg W in 1981-1983; 34 deg W in 1983-1985; 27 deg W in 1985; 1 deg W in 1985-1989; 21 deg W in 1989-1994; 40 deg W in 1994-1998 As of 2 September 2001 located at 103.82 deg W drifting at 5.004 deg W per day. As of 2007 Mar 10 located at 81.84W drifting at 5.000W degrees per day. 1980 December 9 - 07:18 GMT - Vandenberg SLC3W. Atlas E/MSD 68E FAILURE: Premature shut down of one of the Atlas booster engines turned the vehicle around, thereafter the sustainer thrust it back toward the earth. NOSS Spacecraft: NOSS. Agency: U.S. Navy. Ocean surveillance; aka White Cloud type spacecraft; Navy Ocean Surveillance Satellite; PARCAE. Other sources give the payload designation ABSAD. The failure was caused by a loss of lubricating oil to one of the booster engines, causing the engine to fail approx 200 milliseconds before it was to have shut down on guidance command. The asymmetric thrust pivoted the booster around approximately 180 degrees, where it stabilized in a retrofire attitude with the sustainer engine still firing. It descended back toward earth through its own exhaust flame and exploded a couple of minutes later. 1981 February 21 - 23:23 GMT - Cape Canaveral LC36A. SLV-3D Centaur AC-42 / Centaur D-1AR 5023 Comstar 4 Mass: 1,520 kg (3,350 lb). Spacecraft: Intelsat 4A. Agency: Comsat. Perigee: 35,783 km (22,234 mi). Apogee: 35,792 km (22,240 mi). Inclination: 7.20 deg. Period: 1,436.20 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit at 142 deg W in 1981; 127 deg W in 1981-1985; 76 deg W in 1985-on. As of 31 August 2001 located at 25.65 deg W drifting at 1.067 deg E per day. As of 2007 Mar 11 located at 78.95E drifting at 0.039W degrees per day. 1981 May 23 - 22:42 GMT - Cape Canaveral LC36B. SLV-3D Centaur AC-56 / Centaur D-1AR 5036 Intelsat 5 F-1 Mass: 1,928 kg (4,250 lb). Spacecraft: Intelsat 5. Agency: Intelsat. Perigee: 36,151 km (22,463 mi). Apogee: 36,224 km (22,508 mi). Inclination: 10.10 deg. Period: 1,456.60 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit at 24 deg W in 1981; 60 deg E in 1982-1984; 57 deg E in 1984-1986; 174 deg E in 1986-1988; 177 deg E in 1988-1990; 177 deg W in 1990-1992; 91 deg E in 1993-1996; 72 deg E in 1996-1997 As of 4 September 2001 located at 169.69 deg W drifting at 5.095 deg W per day. As of 2007 Mar 10 located at 13.28E drifting at 5.096W degrees per day. 1981 June 23 - 10:52 GMT - Vandenberg SLC3W. Atlas F 87F / Star-37S-ISS NOAA 7 Mass: 1,405 kg (3,097 lb). Spacecraft: Tiros N. Agency: NOAA. Perigee: 828 km (514 mi). Apogee: 847 km (526 mi). Inclination: 98.90 deg. Period: 101.70 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). 1981 August 6 - 08:16 GMT - Cape Canaveral LC36A. SLV-3D Centaur AC-59 / Centaur D-1AR 5039 FAILURE: Failure of the fiberglass fairing during ascent. Fltsatcom 5 Mass: 1,884 kg (4,153 lb). Spacecraft: Fltsatcom. Agency: USN. Perigee: 36,221 km (22,506 mi). Apogee: 36,300 km (22,500 mi). Inclination: 8.90 deg. Period: 1,460.40 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit. The Atlas G Centaur delivered a badly damaged but operating FLTSATCOM spacecraft to its correct orbit. Investigation showed that the most likely cause was failure of the fiberglass fairing during ascent. Positioned in geosynchronous orbit at 90 deg W in 1981; 90-114 deg W in 1982; 44 deg W in 1982-1986 As of 5 September 2001 located at 140.32 deg W drifting at 6.003 deg W per day. As of 2007 Mar 10 located at 31.85E drifting at 6.002W degrees per day. 1981 December 15 - 23:35 GMT - Cape Canaveral LC36B. SLV-3D Centaur AC-55 / Centaur D-1AR 5035 Intelsat 5 F-3 Mass: 1,870 kg (4,120 lb). Spacecraft: Intelsat 5. Agency: Intelsat. Perigee: 35,894 km (22,303 mi). Apogee: 36,129 km (22,449 mi). Inclination: 9.40 deg. Period: 1,447.60 min. Positioned in geosynchronous orbit at 24 deg W in 1982-1985; 27 deg W in 1985; 53 deg W in 1985-1988; 174 deg E in 1988-1990; 177 deg E in 1990-1992; 177 deg W in 1992-1995; 157 deg E in 1995-1998 As of 5 September 2001 located at 57.52 deg W drifting at 2.890 deg W per day. As of 2007 Mar 9 located at 101.94W drifting at 2.904W degrees per day. 1981 December 19 - 01:10 GMT - Vandenberg SLC3E. Atlas E/SVS 76E FAILURE: Failure. Navstar 7 Mass: 770 kg (1,690 lb). Spacecraft: GPS Block 1. Agency: U.S. Air Force. Global Positioning System. 1982 March 5 - 00:23 GMT - Cape Canaveral LC36A. SLV-3D Centaur AC-58 / Centaur D-1AR 5038 Intelsat 5 F-4 Mass: 1,928 kg (4,250 lb). Spacecraft: Intelsat 5. Agency: Intelsat. Perigee: 35,920 km (22,310 mi). Apogee: 36,243 km (22,520 mi). Inclination: 9.40 deg. Period: 1,451.20 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit at 32 deg E in 1982; 63 deg E in 1982; 27 deg W in 1983-1985; 34 deg W in 1985-1992; 40 deg W in 1992; 31 deg W in 1993-1995; 29 deg W in 1995 As of 1 September 2001 located at 4.64 deg W drifting at 3.747 deg W per day. As of 2007 Mar 7 located at 4.34W drifting at 3.748W degrees per day. 1982 September 28 - 23:17 GMT - Cape Canaveral LC36B. SLV-3D Centaur AC-60 / Centaur D-1AR 5040 Intelsat 5 F-5 Mass: 2,000 kg (4,400 lb). Spacecraft: Intelsat 5. Agency: Intelsat. Perigee: 36,228 km (22,510 mi). Apogee: 36,404 km (22,620 mi). Inclination: 9.00 deg. Period: 1,463.30 min. Positioned in geosynchronous orbit at 63 deg E in 1982-1990; 66 deg E in 1991-1996; 33 deg E in 1996; 72 deg E in 1997-on. As of 3 September 2001 located at 16.28 deg E drifting at 6.707 deg W per day. As of 2007 Mar 9 located at 163.88W drifting at 6.709W degrees per day. 1982 December 21 - 02:38 GMT - Vandenberg SLC3W. Atlas E 60E / Star-37S-ISS AMS 5 Mass: 750 kg (1,650 lb). Spacecraft: DMSP Block 5D-2. Agency: USAF. Perigee: 797 km (495 mi). Apogee: 810 km (500 mi). Inclination: 98.60 deg. Period: 100.90 min. Defense Meteorological Satellite Program. 1983 February 9 - 13:47 GMT - Vandenberg SLC3E. Atlas H 6001H NOSS 4 Spacecraft: NOSS. Agency: USN. Perigee: 1,063 km (660 mi). Apogee: 1,186 km (736 mi). Inclination: 63.40 deg. Period: 107.80 min. Ocean surveillance; aka White Cloud type spacecraft; Navy Ocean Surveillance Satellite; PARCAE. 1983 March 28 - 15:52 GMT - Vandenberg SLC3W. Atlas E 73E / Star-37S-ISS NOAA 8 Mass: 3,775 kg (8,322 lb). Spacecraft: Advanced Tiros N. Agency: NOAA. Perigee: 793 km (492 mi). Apogee: 817 km (507 mi). Inclination: 98.60 deg. Period: 101.00 min. Carried search and rescue package. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). 1983 May 19 - 22:26 GMT - Cape Canaveral LC36A. SLV-3D Centaur AC-61 / Centaur D-1AR 5041 Intelsat 5 F-6 Mass: 1,928 kg (4,250 lb). Spacecraft: Intelsat 5. Agency: Intelsat. Perigee: 36,076 km (22,416 mi). Apogee: 36,125 km (22,446 mi). Inclination: 8.30 deg. Period: 1,452.10 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit at 29 deg E in 1983; 18 deg W in 1983-1992; 34 deg W in 1992; 50 deg W in 1992-1995; 31 deg W in 1995-1998 As of 4 September 2001 located at 47.96 deg E drifting at 3.999 deg W per day. As of 2007 Mar 10 located at 62.15W drifting at 3.995W degrees per day. 1983 June 9 - 23:23 GMT - Vandenberg SLC3E. Atlas H 6002H / 6002H NOSS 5 Spacecraft: NOSS. Agency: USN. Perigee: 1,049 km (651 mi). Apogee: 1,167 km (725 mi). Inclination: 63.40 deg. Period: 107.40 min. Ocean surveillance; aka White Cloud type spacecraft; Navy Ocean Surveillance Satellite; PARCAE. 1983 July 14 - 10:21 GMT - Vandenberg SLC3W. Atlas E/SGS-2 75E Navstar 8 Mass: 770 kg (1,690 lb). Spacecraft: GPS Block 1. Agency: USAF. Perigee: 20,757 km (12,897 mi). Apogee: 21,229 km (13,191 mi). Inclination: 64.20 deg. Period: 751.10 min. Global Positioning System. 1983 November 18 - 06:32 GMT - Vandenberg SLC3W. Atlas E 58E / Star-37S-ISS DMSP B5D2-2 Mass: 750 kg (1,650 lb). Spacecraft: DMSP Block 5D-2. Agency: USAF. Perigee: 801 km (497 mi). Apogee: 818 km (508 mi). Inclination: 98.40 deg. Period: 101.10 min. Defense Meteorological Satellite Program. 1984 February 5 - 18:44 GMT - Vandenberg SLC3E. Atlas H 6003H / 6003H NOSS 6 Spacecraft: NOSS. Agency: USN. Perigee: 1,052 km (653 mi). Apogee: 1,172 km (728 mi). Inclination: 63.40 deg. Period: 107.00 min. Ocean surveillance; aka White Cloud type spacecraft; Navy Ocean Surveillance Satellite; PARCAE. 1984 June 9 - 23:03 GMT - Cape Canaveral LC36B. Atlas G Centaur AC-62 / Centaur D-1AR 5042G FAILURE: Centaur structural failure. Intelsat 5 F-9 Mass: 1,091 kg (2,405 lb). Spacecraft: Intelsat 5. Agency: Intelsat. Perigee: 180 km (110 mi). Apogee: 1,227 km (762 mi). Inclination: 29.20 deg. Period: 98.90 min. Failure of Centaur upper stage left stranded in useless orbit. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle was to have put payload into geosynchronous transfer orbit 1984 June 13 - 11:37 GMT - Vandenberg SLC3W. Atlas E/SGS-2 42E USA 1 Mass: 770 kg (1,690 lb). Spacecraft: GPS Block 1. Agency: USAF. Perigee: 20,681 km (12,850 mi). Apogee: 21,194 km (13,169 mi). Inclination: 64.20 deg. Period: 748.80 min. Global Positioning System. 1984 September 8 - 21:41 GMT - Vandenberg SLC3W. Atlas E/SGS-2 14E USA 5 Mass: 770 kg (1,690 lb). Spacecraft: GPS Block 1. Agency: USAF. Perigee: 20,612 km (12,807 mi). Apogee: 21,203 km (13,174 mi). Inclination: 61.90 deg. Period: 747.60 min. Global Positioning System. 1984 December 12 - 10:42 GMT - Vandenberg SLC3W. Atlas E 39E / Star-37S-ISS NOAA 9 Mass: 1,712 kg (3,774 lb). Spacecraft: Advanced Tiros N. Agency: NOAA. Perigee: 833 km (517 mi). Apogee: 855 km (531 mi). Inclination: 99.10 deg. Period: 101.80 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). 1985 February 6 - Vandenberg -. Atlas F USAF 1985 March 13 - 02:00 GMT - Vandenberg SLC3W. Atlas E/OIS 41E Geosat Mass: 635 kg (1,399 lb). Spacecraft: Geosat. Agency: USN. Perigee: 775 km (481 mi). Apogee: 779 km (484 mi). Inclination: 108.10 deg. Period: 100.40 min. Ocean sea height mapping. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). 1985 March 22 - 23:58 GMT - Cape Canaveral LC36B. Atlas G Centaur AC-63 / Centaur D-1AR 5043G Intelsat 5A F-10 Mass: 2,013 kg (4,437 lb). Spacecraft: Intelsat 5A. Agency: Intelsat. Perigee: 36,237 km (22,516 mi). Apogee: 36,468 km (22,660 mi). Inclination: 7.20 deg. Period: 1,465.10 min. Positioned in geosynchronous orbit at 24 deg W in 1985-1990; 174 deg E in 1990-1994; 66 deg E in 1994-1995; 57 deg E in 1995-1996; 33 deg E in 1996-1999 As of 5 September 2001 located at 135.23 deg W drifting at 7.152 deg W per day. As of 2007 Mar 9 located at 107.21W drifting at 7.157W degrees per day. 1985 June 30 - 00:44 GMT - Cape Canaveral LC36B. Atlas G Centaur AC-64 / Centaur D-1AR 5044G Intelsat 5A F-11 Mass: 1,098 kg (2,420 lb). Spacecraft: Intelsat 5A. Agency: Intelsat. Perigee: 35,773 km (22,228 mi). Apogee: 35,799 km (22,244 mi). Inclination: 0.70 deg. Period: 1,436.10 min. Positioned in geosynchronous orbit at 27 deg W in 1985-1990; 63 deg E in 1990-1992; 177 deg E in 1992-1994; 180 deg E in 1994-1997; 29 deg W in 1998-1999 As of 4 September 2001 located at 29.54 deg W drifting at 0.005 deg W per day. As of 2007 Mar 9 located at 113.07W drifting at 0.696W degrees per day. 1985 September 28 - 23:36 GMT - Cape Canaveral LC36B. Atlas G Centaur AC-65 / Centaur D-1AR 5045G Intelsat 5A F-12 Mass: 1,096 kg (2,416 lb). Spacecraft: Intelsat 5A. Agency: Intelsat. Perigee: 36,086 km (22,422 mi). Apogee: 36,140 km (22,450 mi). Inclination: 6.20 deg. Period: 1,452.80 min. Telephone communications; 31 deg E. Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit at 60 deg E in 1985-1989; 1 deg W in 1989-1994; 21 deg W in 1994-1996; 56 deg W in 1996-1998 As of 28 August 2001 located at 145.57 deg E drifting at 4.159 deg W per day. As of 2007 Mar 10 located at 19.14E drifting at 4.163W degrees per day. 1985 October 9 - 02:53 GMT - Vandenberg SLC3W. Atlas E/SGS-2 55E USA 10 Mass: 770 kg (1,690 lb). Spacecraft: GPS Block 1. Agency: USAF. Perigee: 20,765 km (12,902 mi). Apogee: 21,673 km (13,466 mi). Inclination: 65.00 deg. Period: 760.40 min. Global Positioning System. 1986 February 9 - 10:06 GMT - Vandenberg SLC3E. Atlas H 6004H / 6004H USA 15 Spacecraft: NOSS. Agency: USN. Perigee: 1,049 km (651 mi). Apogee: 1,166 km (724 mi). Inclination: 63.00 deg. Period: 107.40 min. Ocean surveillance; aka White Cloud type spacecraft; Navy Ocean Surveillance Satellite; PARCAE. 1986 September 17 - 15:52 GMT - Vandenberg SLC3W. Atlas E 52E / Star-37S-ISS NOAA 10 Mass: 1,700 kg (3,700 lb). Spacecraft: Advanced Tiros N. Agency: NOAA. Perigee: 795 km (493 mi). Apogee: 816 km (507 mi). Inclination: 98.50 deg. Period: 101.00 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). 1986 December 5 - 02:30 GMT - Cape Canaveral LC36B. Atlas G Centaur AC-66 / Centaur D-1AR 5046G USA 20 Mass: 2,310 kg (5,090 lb). Spacecraft: Fltsatcom. Agency: USN. Perigee: 35,740 km (22,200 mi). Apogee: 35,832 km (22,264 mi). Inclination: 0.90 deg. Period: 1,436.10 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit at 100 deg W in 1987-1999 Last known longitude (27 July 1999) 100.33 deg W drifting at 0.027 deg W per day. 1987 March 26 - 21:22 GMT - Cape Canaveral LC36B. Atlas G Centaur AC-67 / Centaur D-1AR 5048G FAILURE: Lightning strike zapped guidance at T+51 seconds. Fault was directly attributed to a random memory upset that forced rocket to veer off course. Destroyed by range safety. Fltsatcom 6 Mass: 2,300 kg (5,000 lb). Spacecraft: Fltsatcom. Agency: U.S. Navy. 1987 May 15 - 15:45 GMT - Vandenberg SLC3E. Atlas H 6005H USA 22 Spacecraft: NOSS. Agency: USN. Perigee: 1,045 km (649 mi). Apogee: 1,179 km (732 mi). Inclination: 62.90 deg. Period: 107.80 min. Ocean surveillance; aka White Cloud type spacecraft; Navy Ocean Surveillance Satellite; PARCAE. 1987 June 20 - 02:34 GMT - Vandenberg SLC3W. Atlas E 59E / Star-37S-ISS USA 26 Mass: 750 kg (1,650 lb). Spacecraft: DMSP Block 5D-2. Agency: USAF. Perigee: 828 km (514 mi). Apogee: 848 km (526 mi). Inclination: 98.80 deg. Period: 101.70 min. Defense Meteorological Satellite Program. 1988 February 3 - 05:53 GMT - Vandenberg SLC3W. Atlas E 54E / Star-37S-ISS USA 29 Mass: 750 kg (1,650 lb). Spacecraft: DMSP Block 5D-2. Agency: USAF. Perigee: 807 km (501 mi). Apogee: 817 km (507 mi). Inclination: 98.50 deg. Period: 101.10 min. Defense Meteorological Satellite Program. 1988 September 24 - 10:02 GMT - Vandenberg SLC3W. Atlas E 63E / Star-37S-ISS NOAA 11 Mass: 1,712 kg (3,774 lb). Spacecraft: Advanced Tiros N. Agency: NOAA. Perigee: 838 km (520 mi). Apogee: 854 km (530 mi). Inclination: 99.20 deg. Period: 101.90 min. Carried search & rescue package. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). 1989 September 25 - 08:41 GMT - Cape Canaveral LC36B. Atlas G Centaur AC-68 / Centaur D-1AR 5047G USA 46 Mass: 2,310 kg (5,090 lb). Spacecraft: Fltsatcom. Agency: USN. Perigee: 35,777 km (22,230 mi). Apogee: 35,797 km (22,243 mi). Inclination: 4.10 deg. Period: 1,436.10 min. Last in series of 8. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit at 23 deg W in 1989-1999. 1990 April 11 - 15:00 GMT - Vandenberg SLC3W. LV Model: Atlas E Altair . Atlas E / Altair 28E USA 56 Spacecraft: Stacksat P87-2. Agency: USAF. Perigee: 627 km (389 mi). Apogee: 745 km (462 mi). Inclination: 89.80 deg. Period: 98.48 min. Polar Orbiting Geomagnetic Survey satellite designed to measure the Earth's magnetic field vector as a function of position. Data from the experiment was used to improve Earth navigation systems, and was stored in an experimental solid state recorder. Six low cost ground stations were designed, built and located around the world to operate the spacecraft flown on this mission. 1990 July 25 - 19:21 GMT - Cape Canaveral LC36B. Atlas I AC-69 / Centaur I 5049 CRRES Mass: 1,629 kg (3,591 lb). Spacecraft: CRRES. Agency: USAF/NAS. Perigee: 335 km (208 mi). Apogee: 34,739 km (21,585 mi). Inclination: 18.00 deg. Period: 613.40 min. Combined Release and Radiation Effects Satellite. First launch of commercial Atlas-Centaur. Spacecraft engaged in research and exploration of the upper atmosphere or outer space. Elliptical orbit; MRS trajectory. 1990 December 1 - 15:57 GMT - Vandenberg SLC3W. Atlas E 61E / Star-37S-ISS FAILURE: Failure of the spacecraft's TEM-364-15 AKM nozzle due to a manufacturing defect led to the satellite being placed into lower than planned orbit. USA 68 Mass: 750 kg (1,650 lb). Spacecraft: DMSP Block 5D-2. Agency: USAF. Perigee: 724 km (449 mi). Apogee: 837 km (520 mi). Inclination: 98.70 deg. Period: 100.50 min. Defense Meteorological Satellite Program; broken nozzle prevented satellite from reaching desired orbit. 1991 April 18 - 23:30 GMT - Cape Canaveral LC36B. Atlas I AC-70 FAILURE: RL-10 Centaur engine turbopump failed at T+361 seconds; destroyed by range safety. Yuri 3H Mass: 600 kg (1,320 lb). Spacecraft: AS 3000. Agency: TSCJ. Apogee: 175 km (108 mi). 1991 May 14 - 15:52 GMT - Vandenberg SLC3W. Atlas E 50E / Star-37S-ISS NOAA 12 Mass: 1,416 kg (3,121 lb). Spacecraft: Tiros N. Agency: NOAA. Perigee: 805 km (500 mi). Apogee: 824 km (512 mi). Inclination: 98.60 deg. Period: 101.20 min. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). 1991 November 28 - 13:23 GMT - Vandenberg SLC3W. Atlas E 53E / Star-37S-ISS USA 73 Mass: 830 kg (1,820 lb). Spacecraft: DMSP Block 5D-2. Agency: USAF. Perigee: 835 km (518 mi). Apogee: 852 km (529 mi). Inclination: 99.00 deg. Period: 101.80 min. Defense Meteorological Satellite Program. 500th Atlas launch. 1991 December 7 - 22:47 GMT - Cape Canaveral LC36B. Atlas II AC-102 / Centaur II 8102 Eutelsat II F3 Mass: 1,874 kg (4,131 lb). Spacecraft: Spacebus 100. Agency: Eutelsat. Perigee: 35,769 km (22,225 mi). Apogee: 35,802 km (22,246 mi). Inclination: 2.00 deg. Period: 1,436.10 min. Stationed at 16 deg E. Telecommunications satellite. French registration 1991-8. Transfer orbit was 663 min, 200 x 36000 km x 7.0 deg. Registered by France in ST/SG/SER.E/249 until EUTELSAT can register the satellite. EUTELSAT is the European Telecommunications Satellite Organi zation. Launch vehicle put payload into supersynchronous earth orbit with IFR trajectory option. Positioned in geosynchronous orbit at 16 deg E in 1992-1998; 36 deg E in 1999. As of 1 September 2001 located at 21.51 deg E drifting at 0.017 deg E per day. As of 2007 Mar 11 located at 74.40E drifting at 3.531W degrees per day. 1992 February 11 - 00:41 GMT - Cape Canaveral LC36A. Atlas II AC-101 / Centaur II 8101 USA 78 Spacecraft: DSCS III. Agency: USAF. Perigee: 30,675 km (19,060 mi). Apogee: 35,503 km (22,060 mi). Inclination: 0.90 deg. Period: 1,300.50 min. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). Launch vehicle put payload into geosynchronous transfer orbit with GCS trajectory option. Positioned in geosynchronous orbit; at 135 deg W in 1995. 1992 March 14 - 00:00 GMT - Cape Canaveral LC36B. Atlas I AC-72 / Centaur I 5052 Galaxy 5 Mass: 1,412 kg (3,112 lb). Spacecraft: HS 376. Agency: HCI. Perigee: 35,782 km (22,233 mi). Apogee: 35,790 km (22,230 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Geostationary at 125 deg W. Launch vehicle put payload into geosynchronous transfer orbit with GCS trajectory option. Positioned in geosynchronous orbit at 125 deg W in 1992-2001. As of 2007 Mar 8 located at 7.46E drifting at 3.538W degrees per day. 1992 June 10 - 00:00 GMT - Cape Canaveral LC36B. Atlas IIA AC-105 / Centaur II 8105 Intelsat K Mass: 2,928 kg (6,455 lb). Spacecraft: AS 5000. Agency: Intelsat. Perigee: 35,781 km (22,233 mi). Apogee: 35,793 km (22,240 mi). Inclination: 0.10 deg. Period: 1,436.10 min. Stationed at 21.5 deg W. Intelsat K is a single spacecraft purchased to meet critical requirements for Ku-band capacity over the Atlantic region, driven primarily by international broadcasters. The satellite was purchased from GE Americom while under construction (as Satcom K4) and required extensive payload modifications. Spacecraft: Based on GE 5000 series bus.3-axis stabilised using magnetotorquers. Hydrazine propulsion system. Two large solar panels with 1-axis articulation provide 4800 W BOL.4 50 Ahr NiH batteries. Payload: 16 Ku-band transponders which can be configured into 32 high quality television channels. Permits access from ground antennas 1.2 meters dia. and smaller. Launch vehicle put payload into geosynchronous transfer orbit with GCS trajectory option. Positioned in geosynchronous orbit at 21 deg W in 1992-1999 As of 6 September 2001 located at 21.54 deg W drifting at 0.011 deg W per day. As of 2007 Mar 10 located at 160.51W drifting at 11.137W degrees per day. 1992 July 2 - 21:54 GMT - Cape Canaveral LC36A. Atlas II AC-103 / Centaur II 8103 USA 82 Spacecraft: DSCS III. Agency: USAF. Perigee: 35,775 km (22,229 mi). Apogee: 35,800 km (22,200 mi). Inclination: 0.20 deg. Period: 1,436.20 min. Launch vehicle put payload into geosynchronous transfer orbit with GCS trajectory option. Positioned in geosynchronous orbit at 12 deg W in 1995-1996. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). 1992 August 22 - 22:40 GMT - Cape Canaveral LC36B. Atlas I AC-71 / Centaur I 5051 FAILURE: Destroyed by range safety. Centaur engine turbopump did not start. Identical to the 18 April 1991 failure. Galaxy 1R Spacecraft: HS 376. Agency: Hughes Communications Inc. 1993 March 25 - 21:38 GMT - Cape Canaveral LC36B. Atlas I AC-74 / Centaur I 5054 FAILURE: Atlas engine failure. Loss of booster engine thrust resulted in a lower-than planned 1560 km x 1900 km orbit. UHF F1 Mass: 2,866 kg (6,318 lb). Spacecraft: HS 601. Agency: HCI. Perigee: 36,053 km (22,402 mi). Apogee: 36,098 km (22,430 mi). Inclination: 21.10 deg. Period: 1,450.90 min. US Navy communications; Ultra High Frequency Follow On; unusable orbit. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle was to have put payload into subsynchronous earth orbit with MRS trajectory option. As of 28 August 2001 located at 45.55 deg W drifting at 3.676 deg W per day. As of 2007 Mar 10 located at 95.89E drifting at 3.687W degrees per day. 1993 July 19 - 22:04 GMT - Cape Canaveral LC36A. Atlas II AC-104 / Centaur II 8104 USA 93 Mass: 2,615 kg (5,765 lb). Spacecraft: DSCS III. Agency: USAF. Perigee: 183 km (113 mi). Apogee: 35,764 km (22,222 mi). Inclination: 26.10 deg. Period: 625.80 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit with GCS trajectory option. Positioned in geosynchronous orbit at 175 deg E in 1995-1997. 1993 August 9 - 10:02 GMT - Vandenberg SLC3W. Atlas E 34E / Star-37S-ISS NOAA 13 Mass: 1,712 kg (3,774 lb). Spacecraft: Advanced Tiros N. Agency: NOAA. Perigee: 846 km (525 mi). Apogee: 860 km (530 mi). Inclination: 99.20 deg. Period: 102.00 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). 1993 September 3 - 11:17 GMT - Cape Canaveral LC36B. Atlas I AC-75 / Centaur I 5055 USA 95 Mass: 2,844 kg (6,269 lb). Spacecraft: HS 601. Agency: HCI. Perigee: 35,767 km (22,224 mi). Apogee: 35,805 km (22,248 mi). Inclination: 5.00 deg. Period: 1,436.10 min. US Navy communications. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into subsynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 72 deg E in 1993-1999. 1993 November 28 - 23:40 GMT - Cape Canaveral LC36A. Atlas II AC-106 / Centaur II 8106 USA 97 Mass: 2,615 kg (5,765 lb). Spacecraft: DSCS III. Agency: USAF. Perigee: 195 km (121 mi). Apogee: 35,501 km (22,059 mi). Inclination: 26.40 deg. Period: 625.40 min. Launch vehicle put payload into geosynchronous transfer orbit with GCS trajectory option. Positioned in geosynchronous orbit at 52 deg W in 1995; 60 deg E in 1997. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). 1993 December 16 - 00:38 GMT - Cape Canaveral LC36B. Atlas IIAS AC-108 / Centaur II 8201 Telstar 401 Mass: 3,375 kg (7,440 lb). Spacecraft: AS 7000. Agency: AT&T.; Perigee: 35,759 km (22,219 mi). Apogee: 35,821 km (22,258 mi). Inclination: 4.30 deg. Period: 1,436.30 min. Stationed at 97 deg W. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit with IFR trajectory option. Positioned in geosynchronous orbit at 97 deg W in 1994-1997 As of 5 September 2001 located at 100.42 deg W drifting at 0.039 deg E per day. As of 2007 Mar 10 located at 97.36W drifting at 0.024W degrees per day. 1994 April 13 - 06:04 GMT - Cape Canaveral LC36B. Atlas I AC-73 / Centaur I 5053 GOES 8 Mass: 2,105 kg (4,640 lb). Spacecraft: GOES-Next. Agency: NOAA. Perigee: 35,770 km (22,220 mi). Apogee: 35,807 km (22,249 mi). Inclination: 0.10 deg. Period: 1,436.20 min. Geostationary Environmental Satellite. Stationed at 75 deg W. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). Launch vehicle put payload into supersynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 90 deg W in 1994-1995; 75 deg W in 1995-1999 As of 5 September 2001 located at 74.78 deg W drifting at 0.019 deg E per day. NASA announced that GOES-8 was "de-orbited" (presumably moved to a sub-synchronous orbit) on May 5, 2004 after 10 years of service. As of 2007 Mar 11 located at 87.46E drifting at 4.935W degrees per day. 1994 June 24 - 13:50 GMT - Cape Canaveral LC36B. Atlas I AC-76 / Centaur I 5056 USA 104 Mass: 2,847 kg (6,276 lb). Spacecraft: HS 601. Agency: HCI. Perigee: 35,776 km (22,230 mi). Apogee: 35,795 km (22,241 mi). Inclination: 4.81 deg. Period: 1,436.05 min. US Navy communications . Stationed at 14.38 deg W 1995-1999. Launch vehicle put payload into subsynchronous earth orbit with MRS trajectory option. 1994 August 3 - 23:57 GMT - Cape Canaveral LC36A. Atlas IIA AC-107 / Centaur II 8107 DBS 2 Mass: 2,860 kg (6,300 lb). Spacecraft: HS 601. Agency: DirecTV. Perigee: 35,776 km (22,230 mi). Apogee: 35,797 km (22,243 mi). Inclination: 0.0100 deg. Period: 1,436.11 min. Commercial TV broadcast. Stationed at 100.79 deg W. Launch vehicle put payload into supersynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 101 deg W in 1994-1999 As of 5 September 2001 located at 100.81 deg W drifting at 0.010 deg W per day. As of 2007 Mar 11 located at 91.17W drifting at 0.006W degrees per day. 1994 August 29 - 17:38 GMT - Vandenberg SLC3W. Atlas E 20E / Star-37S-ISS USA 106 Mass: 830 kg (1,820 lb). Spacecraft: DMSP Block 5D-2. Agency: USAF. Perigee: 840 km (520 mi). Apogee: 860 km (530 mi). Inclination: 98.89 deg. Period: 101.94 min. Defense Meteorological Satellite Program. 1994 October 6 - 06:35 GMT - Cape Canaveral LC36B. Atlas IIAS AC-111 / Centaur II 8202 Intelsat 703 Mass: 3,656 kg (8,060 lb). Spacecraft: FS-1300. Agency: Intelsat. Perigee: 35,779 km (22,231 mi). Apogee: 35,792 km (22,240 mi). Inclination: 0.0400 deg. Period: 1,436.07 min. 38 C-band and 20 Ku-band transponders. Initially positioned in geosynchronous orbit at 177 deg E in 1994-1996. Then reassigned to Intelsat subsidiary New Skies, redesignated NSS 703, and moved to 57 deg E after 1996. At the crossroads of three continents, NSS-703 provided cross-connectivity for Europe, Africa and Asia. NSS-703 was used for video contribution from Europe to India and Africa, and was capable of bringing signals from London to India and Australia in one hop. NSS-703's coverage included a global beam, and two C-band hemispheric beams, which covered Africa and the triangle from Eastern Iran to Japan and Australia, including all of India and China. Three steerable Ku-band spot beams targeted Europe and Iran, Central Asia and Afghanistan-Pakistan-North India. Expected end of life March 2009. As of 2007 Mar 9 located at 56.96E drifting at 0.001E degrees per day. 1994 November 29 - 10:21 GMT - Cape Canaveral LC36A. Atlas IIA AC-110 / Centaur II 8109 Orion 1 Mass: 2,358 kg (5,198 lb). Spacecraft: Eurostar 2000. Agency: Orion. Perigee: 35,781 km (22,233 mi). Apogee: 35,792 km (22,240 mi). Inclination: 0.00 deg. Period: 1,436.10 min. 34 Ku-band transponders for TV. Stationed at 37.48 deg W. Launch vehicle put payload into supersynchronous earth orbit with IFR trajectory option. Positioned in geosynchronous orbit at 37 deg W in 1994-1999 As of 5 September 2001 located at 37.54 deg W drifting at 0.010 deg W per day. As of 2007 Mar 11 located at 37.60W drifting at 0.015W degrees per day. 1994 December 30 - 10:02 GMT - Vandenberg SLC3W. Atlas E 11E / Star-37S-ISS NOAA 14 Mass: 1,712 kg (3,774 lb). Spacecraft: Advanced Tiros N. Agency: NOAA. Perigee: 847 km (526 mi). Apogee: 861 km (534 mi). Inclination: 98.88 deg. Period: 102.02 min. 1995 January 10 - 06:18 GMT - Cape Canaveral LC36B. Atlas IIAS AC-113 / Centaur II 8203 Intelsat 704 Mass: 3,656 kg (8,060 lb). Spacecraft: FS-1300. Agency: Intelsat. Perigee: 35,776 km (22,230 mi). Apogee: 35,796 km (22,242 mi). Inclination: 0.10 deg. Stationed at 66.0 deg E. Launch vehicle put payload into supersynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 66 deg E in 1995-1999 As of 29 August 2001 located at 66.03 deg E drifting at 0.005 deg W per day. As of 2007 Mar 10 located at 66.03E drifting at 0.002W degrees per day. 1995 January 29 - 01:25 GMT - Cape Canaveral LC36A. Atlas II AC-112 / Centaur II 8110 USA 108 Mass: 3,023 kg (6,664 lb). Spacecraft: HS 601. Agency: HCI. Perigee: 35,775 km (22,229 mi). Apogee: 35,799 km (22,244 mi). Inclination: 2.20 deg. Period: 1,436.10 min. UHF Follow-On #4; US Navy communications . Stationed at 177.0 deg W. Launch vehicle put payload into subsynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 177 deg W in 1995-1999. 1995 March 22 - 06:18 GMT - Cape Canaveral LC36B. Atlas IIAS AC-115 Intelsat 705 Mass: 3,669 kg (8,088 lb). Spacecraft: FS-1300. Agency: Intelsat. Perigee: 35,776 km (22,230 mi). Apogee: 35,798 km (22,243 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Stationed at 50.1 deg W. Launch vehicle put payload into supersynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 50 deg W in 1995-1996; 18 deg W in 1996-1999 As of 5 September 2001 located at 17.97 deg W drifting at 0.006 deg W per day. As of 2007 Mar 11 located at 50.01W drifting at 0.007W degrees per day. 1995 March 24 - 14:05 GMT - Vandenberg SLC3W. Atlas E 45E / Star-37S-ISS USA 109 Mass: 750 kg (1,650 lb). Spacecraft: DMSP Block 5D-2. Agency: USAF. Perigee: 845 km (525 mi). Apogee: 854 km (530 mi). Inclination: 98.80 deg. Period: 101.90 min. Last successful Atlas E space launch. 1995 April 7 - 23:47 GMT - Cape Canaveral LC36A. Atlas IIA AC-114 AMSC-1 Mass: 2,700 kg (5,900 lb). Spacecraft: HS 601. Agency: AMSC. Perigee: 35,777 km (22,230 mi). Apogee: 35,796 km (22,242 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Mobile communicaitons. Stationed at 101.1 deg W. Launch vehicle put payload into supersynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 101 deg W in 1995-1999 As of 5 September 2001 located at 101.01 deg W drifting at 0.024 deg W per day. As of 2007 Mar 11 located at 100.99W drifting at 0.003W degrees per day. 1995 May 23 - 05:52 GMT - Cape Canaveral LC36B. Atlas I AC-77 / Centaur I 5057 GOES 9 Mass: 2,105 kg (4,640 lb). Spacecraft: GOES-Next. Agency: NOAA. Perigee: 35,809 km (22,250 mi). Apogee: 35,911 km (22,314 mi). Inclination: 0.20 deg. Period: 1,435.90 min. Stationed at 135 deg W. Launch vehicle put payload into supersynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 90 deg W in 1995; 135 deg W in 1996-1998; 98-105 deg W in 1998-1999 As of 5 September 2001 located at 103.62 deg W drifting at 0.009 deg W per day. As of 2007 Mar 10 located at 159.81E drifting at 0.002W degrees per day. 1995 May 31 - 15:27 GMT - Cape Canaveral LC36A. Atlas II AC-116 / Centaur II USA 111 Mass: 3,015 kg (6,646 lb). Spacecraft: HS 601. Agency: USN. Perigee: 35,774 km (22,228 mi). Apogee: 35,796 km (22,242 mi). Inclination: 4.80 deg. Period: 1,436.10 min. UHF Follow-On #5; US Navy communications . Stationed at 72.3 deg E. Launch vehicle put payload into subsynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 72 deg E in 1995-1999. 1995 June 16 - General Dynamics Space Division bought by Martin 1995 June 17 - Lockheed Aircraft Corporation merged with Martin to form Lockheed Martin Atlas assembly line moved from Kearney Mesa, California, to Littleton, Colorado 1995 July 31 - 23:30 GMT - Cape Canaveral LC36A. Atlas IIA AC-118 USA 113 Mass: 2,610 kg (5,750 lb). Spacecraft: DSCS III. Agency: USAF. Perigee: 35,787 km (22,236 mi). Apogee: 35,787 km (22,236 mi). Inclination: 0.00 deg. Positioned in geosynchronous orbit; located at 53 deg W in 1997. 1995 August 29 - 00:53 GMT - Cape Canaveral LC36B. Atlas IIAS AC-117 JCSAT 3 Mass: 1,841 kg (4,058 lb). Spacecraft: HS 601. Agency: JSAT. Perigee: 35,779 km (22,231 mi). Apogee: 35,794 km (22,241 mi). Inclination: 0.00 deg. Period: 1,436.20 min. 8 transponders for digital TV. Stationed at 128.1 deg E. Launch vehicle put payload into supersynchronous earth orbit with IFR/MRS trajectory option. Positioned in geosynchronous orbit at 128 deg E in 1995-1999 As of 5 September 2001 located at 128.05 deg E drifting at 0.005 deg E per day. As of 2007 Feb 20 located at 126.99E drifting at 0.144W degrees per day. 1995 September 27 - Final Atlas produced in California. Ceremony commemorating final Atlas (AC-126) produced at Kearny Mesa plant 1995 October 22 - 08:00 GMT - Cape Canaveral LC36A. Atlas II AC-119 / Centaur II USA 114 Mass: 3,015 kg (6,646 lb). Spacecraft: HS 601. Agency: USN. Perigee: 35,776 km (22,230 mi). Apogee: 35,797 km (22,243 mi). Inclination: 5.00 deg. Period: 1,436.10 min. UHF Follow-On #6; US Navy communications. Stationed at 105.3 deg W. Launch vehicle put payload into subsynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 105 deg W in 1995-1999. 1995 December 2 - 08:08 GMT - Cape Canaveral LC36B. Atlas IIAS AC-121 SOHO Mass: 1,850 kg (4,070 lb). Spacecraft: SOHO. Agency: ESA. Perigee: 8,973 km (5,575 mi). Apogee: 671,400 km (417,100 mi). Inclination: 29.60 deg. Period: 29,196.30 min. Solar and Heliospheric Observatory; orbiting at L1 Lagrange point; solar physics. En route Earth-Sun L1 point Earth-Sun L1 libration point transfer trajectory. Inertial trajectory option. 1995 December 15 - 00:23 GMT - Cape Canaveral LC36A. Atlas IIA AC-120 Galaxy 3R Mass: 2,980 kg (6,560 lb). Spacecraft: HS 601. Agency: HCG. Perigee: 35,774 km (22,228 mi). Apogee: 35,799 km (22,244 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Stationed at 95 deg W; 24 C-band, 24 Ku-band transponders; TV for Caribbean and Central America. Launch vehicle put payload into subsynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 95 deg W in 1996-1999 As of 3 September 2001 located at 95.05 deg W drifting at 0.008 deg W per day. As of 2007 Mar 9 located at 132.80W drifting at 0.084W degrees per day. 1996 February 1 - 01:15 GMT - Cape Canaveral LC36B. Atlas IIAS AC-126 Palapa C-1 Spacecraft: HS 601. Agency: Satelind. Perigee: 35,777 km (22,230 mi). Apogee: 35,798 km (22,243 mi). Inclination: 0.00 deg. Period: 1,436.10 min. 30 C-band, 6 Ku-band transponders. Geostationary at 150.4E. Launch vehicle put payload into supersynchronous earth orbit with IFR/MRS trajectory option. Positioned in geosynchronous orbit at 113 deg E in 1996; 150 deg E in 1996-1999 As of 5 September 2001 located at 50.03 deg E drifting at 0.006 deg E per day. As of 2007 Mar 11 located at 38.04E drifting at 0.007E degrees per day. 1996 April 3 - 23:01 GMT - Cape Canaveral LC36A. Atlas IIA AC-122 Inmarsat 3 F1 Mass: 2,068 kg (4,559 lb). Spacecraft: AS 4000. Agency: Inmarsat. Perigee: 35,767 km (22,224 mi). Apogee: 35,806 km (22,248 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Geostationary at 64.1E. Launch vehicle put payload into geosynchronous transfer orbit with RAAN Cntl trajectory option. Positioned in geosynchronous orbit at 64 deg E in 1996-1999 As of 5 September 2001 located at 63.98 deg E drifting at 0.003 deg E per day. As of 2007 Mar 10 located at 64.52E drifting at 0.006W degrees per day. 1996 April 30 - 04:31 GMT - Cape Canaveral LC36B. Atlas I AC-78 / Centaur I 5058 Beppo SAX Spacecraft: SAX. Agency: ASI. Perigee: 584 km (362 mi). Apogee: 601 km (373 mi). Inclination: 4.00 deg. Period: 96.50 min. LEO. Satellite per Astronomia a raggi X; X-ray celestial observatory Launch vehicle put payload into low earth orbit with IFR trajectory option. 100th Atlas-Centaur flight. 1996 July 25 - 12:42 GMT - Cape Canaveral LC36A. Atlas II AC-125 USA 127 Mass: 3,015 kg (6,646 lb). Spacecraft: HS 601. Agency: HCI. Perigee: 35,784 km (22,235 mi). Apogee: 35,791 km (22,239 mi). Inclination: 4.90 deg. Period: 1,436.20 min. Positioned in geosynchronous orbit at 170 deg W in 1996; 23 deg W in 1996-1999; 100 deg W in 1999. As of 29 July 1999) 99.21 deg W drifting at 0.011 deg W per day. As of 2007 Feb 22 located at 21.85W drifting at 0.014W degrees per day. 1996 September 8 - 21:49 GMT - Cape Canaveral LC36B. Atlas IIA AC-123 GE 1 Spacecraft: AS 2100. Agency: GE Americom. Perigee: 35,780 km (22,230 mi). Apogee: 35,793 km (22,240 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Geostationary at 103.0W. Launch vehicle put payload into supersynchronous earth orbit with IFR/MRS trajectory option. Positioned in geosynchronous orbit at 103 deg W in 1996-1999 As of 4 September 2001 located at 103.06 deg W drifting at 0.009 deg W per day. As of 2007 Mar 11 located at 103.03W drifting at 0.006W degrees per day. 1996 November 21 - 20:47 GMT - Cape Canaveral LC36A. Atlas IIA AC-124 Hot Bird 2 Spacecraft: Eurostar 2000. Agency: Eutelsat. Perigee: 35,768 km (22,225 mi). Apogee: 35,803 km (22,246 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Geostationary at 13.0E. Launch vehicle put payload into supersynchronous earth orbit with IFR/MRS trajectory option. Positioned in geosynchronous orbit at 13 deg E in 1997-1999 As of 3 September 2001 located at 12.95 deg E drifting at 0.024 deg E per day. As of 2007 Mar 4 located at 13.07E drifting at 0.011E degrees per day. 1996 December 18 - 01:57 GMT - Cape Canaveral LC36B. Atlas IIA AC-129 Inmarsat 3 F3 Mass: 1,021 kg (2,250 lb). Spacecraft: AS 4000. Agency: Inmarsat. Perigee: 35,764 km (22,222 mi). Apogee: 35,807 km (22,249 mi). Inclination: 0.00 deg. Period: 1,436.00 min. Geostationary at 157.6E. Launch vehicle put payload into geosynchronous transfer orbit with RAAN Cntl trajectory option. Positioned in geosynchronous orbit at 178 deg E in 1997-1999 As of 5 September 2001 located at 178.02 deg E drifting at 0.006 deg W per day. As of 2007 Mar 10 located at 178.19E drifting at 0.002E degrees per day. 1997 February 17 - 01:42 GMT - Cape Canaveral LC36B. Atlas IIAS AC-127 JCSAT 4 Spacecraft: HS 601. Agency: JSAT. Perigee: 35,780 km (22,230 mi). Apogee: 35,793 km (22,240 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Geosynchronous. Stationed over 150.0E Launch vehicle put payload into supersynchronous earth orbit with IFR/MRS trajectory option. Positioned in geosynchronous orbit at 150 deg E in 1997-1998; 124 deg E in 1998-1999; 127 deg E in 1999. As of 5 September 2001 located at 127.02 deg E drifting at 0.015 deg W per day. As of 2007 Mar 7 located at 150.01E drifting at 0.008W degrees per day. 1997 March 8 - 06:01 GMT - Cape Canaveral LC36A. Atlas IIA AC-128 Tempo 2 Spacecraft: FS-1300. Agency: TCI. Perigee: 35,781 km (22,233 mi). Apogee: 35,792 km (22,240 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Geosynchronous. Stationed over 118.7W Launch vehicle put payload into subsynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 119 deg W in 1997-1999 As of 5 September 2001 located at 118.82 deg W drifting at 0.001 deg W per day. As of 2007 Mar 10 located at 42.64E drifting at 4.479W degrees per day. 1997 April 25 - 05:49 GMT - Cape Canaveral LC36B. Atlas I AC-79 GOES 10 Spacecraft: GOES-Next. Agency: NOAA. Perigee: 35,780 km (22,230 mi). Apogee: 35,799 km (22,244 mi). Inclination: 0.40 deg. Period: 1,436.30 min. Geosynchronous. Stationed over 105.7W Launch vehicle put payload into supersynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 105 deg W in 1997-1998; 135 deg W in 1998-1999 As of 6 September 2001 located at 135.09 deg W drifting at 0.037 deg W per day. As of 2007 Mar 11 located at 59.64W drifting at 0.009W degrees per day. 1997 July 28 - 01:15 GMT - Cape Canaveral LC36B. Atlas IIAS AC-133 Superbird C Spacecraft: HS 601. Agency: SCC. Perigee: 35,780 km (22,230 mi). Apogee: 35,793 km (22,240 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Geosynchronous. Stationed over 144.0E Launch vehicle put payload into supersynchronous earth orbit with IFR/MRS trajectory option. Positioned in geosynchronous orbit at 144 deg E in 1997-1999 As of 5 September 2001 located at 144.00 deg E drifting at 0.014 deg W per day. As of 2007 Mar 9 located at 143.94E drifting at 0.009W degrees per day. 1997 September 4 - 12:03 GMT - Cape Canaveral LC36A. Atlas IIAS AC-146 GE 3 Spacecraft: AS 2100. Agency: GE Americom. Perigee: 35,779 km (22,231 mi). Apogee: 35,795 km (22,241 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Geosynchronous. Stationed over 87.1W Launch vehicle put payload into supersynchronous earth orbit with IFR/MRS trajectory option. Positioned in geosynchronous orbit at 87 deg W in 1997-1999 As of 3 September 2001 located at 87.12 deg W drifting at 0.002 deg W per day. As of 2007 Mar 11 located at 86.99W drifting at 0.010W degrees per day. 1997 October 5 - 21:01 GMT - Cape Canaveral LC36B. Atlas IIAS AC-135 Echostar 3 Spacecraft: AS 7000. Agency: Echostar. Perigee: 35,777 km (22,230 mi). Apogee: 35,794 km (22,241 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Geosynchronous. Stationed over 61.4W Launch vehicle put payload into supersynchronous earth orbit with IFR/MRS trajectory option. Positioned in geosynchronous orbit at 61 deg W in 1997-1999 As of 5 September 2001 located at 61.53 deg W drifting at 0.017 deg W per day. As of 2007 Mar 11 located at 61.50W drifting at 0.007W degrees per day. 1997 October 25 - 00:46 GMT - Cape Canaveral LC36A. Atlas IIA AC-131 USA 135 Spacecraft: DSCS III. Agency: USAF. Perigee: 35,770 km (22,220 mi). Apogee: 35,800 km (22,200 mi). Inclination: 0.00 deg. Geosynchronous. Launch vehicle put payload into geosynchronous transfer orbit with GCS trajectory option. 1997 December 8 - 23:52 GMT - Cape Canaveral LC36B. Atlas IIAS AC-149 Galaxy 8i Spacecraft: HS 601. Agency: Panamsat. Perigee: 35,781 km (22,233 mi). Apogee: 35,799 km (22,244 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Geosynchronous. Stationed over 79.2W Launch vehicle put payload into geosynchronous transfer orbit with MRS trajectory option. Used HS-601 XIPS ion engine for station keeping. Positioned in geosynchronous orbit at 95 deg W in 1998-1999 As of 3 September 2001 located at 94.92 deg W drifting at 0.000 deg W per day. As of 2007 Mar 10 located at 37.58W drifting at 2.053W degrees per day. 1998 January 29 - 18:37 GMT - Cape Canaveral LC36A. Atlas IIA AC-109 USA 137 Spacecraft: CAPRICORN. Agency: NRO. Perigee: 200 km (120 mi). Apogee: 39,500 km (24,500 mi). Inclination: 63.40 deg. Classified satellite for the National Reconnaissance Office. It was likely that it was a technology test satellite combining equipment for several future projects, including a prototype COBRA BRASS infrared early warning satellite sensor. The project seemed to have been several years behind schedule (based on the launch vehicle serial number. 1998 February 28 - 00:21 GMT - Cape Canaveral LC36B. Atlas IIAS AC-151 Intelsat 806 Spacecraft: AS 7000. Agency: Intelsat. Perigee: 35,775 km (22,229 mi). Apogee: 35,799 km (22,244 mi). Inclination: 0.10 deg. Period: 1,436.10 min. Initially positioned in geosynchronous orbit at 40 deg W in 1998-2001. 36 C-band and 6 Ku-band transponders. Later assigned to Intelsat spin-off New Skies, redesignated NSS-806, and moved to 319.5º East, giving it an optimum view of Latin American markets while also reaching the Iberian peninsula, the Canary Islands, Western Europe and much of Eastern Europe. Its tailored, high-powered hemispheric beam provided simultaneous coverage of both Europe and the Americas, with virtually complete coverage of North, Central and South America, therefore ensuring the maximum reach throughout Spanish and Portuguese speaking markets. Expected end of life July 2016. As of 2007 Mar 10 located at 40.47W drifting at 0.007W degrees per day. 1998 March 16 - 21:32 GMT - Cape Canaveral LC36A. Atlas II AC-132 USA 138 Spacecraft: HS 601. Agency: USN. Perigee: 35,771 km (22,227 mi). Apogee: 35,803 km (22,246 mi). Inclination: 3.30 deg. Period: 1,436.10 min. UHF Follow-On F8 was the first Block III UHF Follow-On satellite, replacing the old FLTSATCOM satellites. It carried UHF, EHF and Ka-band transponders, including a video broadcast payload. This was the last Atlas II launch; future Atlas launches would use the Atlas IIA, IIAS and III models. Positioned in geosynchronous orbit at 172 deg E in 1998-1999. 1998 June 18 - 22:48 GMT - Cape Canaveral LC36A. Atlas IIAS AC-153 Intelsat 805 Mass: 3,520 kg (7,760 lb). Spacecraft: AS 7000. Agency: Intelsat. Perigee: 35,775 km (22,229 mi). Apogee: 35,800 km (22,200 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Satellite had 28 C-band and 3 Ku-band transponders, and initially served the Atlantic Ocean region for INTELSAT. Launch vehicle put payload into geosynchronous transfer orbit with GCS trajectory option. Geostationary at 55.5 degrees W. Positioned in geosynchronous orbit at 55 deg W in 1998-1999 As of 5 September 2001 located at 55.52 deg W drifting at 0.009 deg W per day. As of 2007 Mar 11 located at 55.54W drifting at 0.012W degrees per day. 1998 October 9 - 22:50 GMT - Cape Canaveral LC36B. Atlas IIA AC-134 Hot Bird 5 Mass: 3,000 kg (6,600 lb). Spacecraft: Eurostar 2000. Agency: Eutelsat. Perigee: 35,766 km (22,223 mi). Apogee: 35,805 km (22,248 mi). Inclination: 0.00 deg. Geostationary at 10.0 degrees E. Positioned in geosynchronous orbit at 13 deg E in 1998-1999 As of 3 September 2001 located at 12.97 deg E drifting at 0.010 deg E per day. As of 2007 Mar 11 located at 25.56E drifting at 0.014W degrees per day. 1998 October 20 - 07:19 GMT - Cape Canaveral LC36A. Atlas IIA AC-130 USA 140 Mass: 3,200 kg (7,000 lb). Spacecraft: HS 601. Agency: USN. Perigee: 35,773 km (22,228 mi). Apogee: 35,806 km (22,248 mi). Inclination: 3.80 deg. Period: 1,436.20 min. The orbit at burnout of the Centaur was 286 km x 25866 km x 27.0 degree. Modification of the orbit to a geostationary 38,300 km circular x 0.0 degree inclination was accomplished by the Marquardt R-4D liquid propellant motor on the HS-601 spacecraft. The satellite carried UHF and EHF transponders for naval communications, and a Ka-band Global Broadcast Service video relay package. Launch mass of 3200 kg dropped to 1550 kg once geostationary orbit was reached. UHF F/O F9 was placed over the Atlantic Ocean in geosynchronous orbit at 174 deg W in 1998; 22 deg W in 1999. Additional Details: USA 140. 1999 February 16 - 01:45 GMT - Cape Canaveral LC36A. Atlas IIAS AC-152 JCSAT-6 Mass: 2,900 kg (6,300 lb). Spacecraft: HS 601. Agency: JSAT. Perigee: 35,784 km (22,235 mi). Apogee: 35,791 km (22,239 mi). Inclination: 0.00 deg. Period: 1,436.10 min. JCSAT-6 carried a Ku-band relay system. It was operated by Japan Satellite Systems, Inc., Tokyo, provided communications and data relay for Japan and the Pacific Rim. Two burns of the Centaur upper stage placed it into a supersynchronous transfer orbit of 258 km x 96736 km x 24.1 degrees. JCSAT-6's on-board R-4D engine would maneuver it into its final geostationary location. Dry mass of the spacecraft was 1230 kg. Stationed at 124 deg E Positioned in geosynchronous orbit at 123 deg E in 1999. As of 5 September 2001 located at 124.00 deg E drifting at 0.014 deg W per day. As of 2007 Mar 10 located at 124.01E drifting at 0.011W degrees per day. 1999 April 12 - 22:50 GMT - Cape Canaveral LC36A. Atlas IIAS AC-154 Eutelsat W3 Spacecraft: Spacebus 3000. Agency: Eutelsat. Perigee: 35,774 km (22,228 mi). Apogee: 35,797 km (22,243 mi). Inclination: 0.00 deg. Communications satellite is for the European Telecommunications Satellite Organization. The vehicle entered a 153 km x 385 km x 27.4 deg parking orbit nine minutes after launch. The second Centaur stage burn delivered the satellite to a 166 km x 46,076 km x 19.7 deg super-synchronous transfer orbit. The satellite was stationed at 7 deg E and carried 24 Ku-band transponders with a wide beam covering Europe, North Africa and Asia, and a spot beam for digital TV to Turkey. Positioned in geosynchronous orbit at 7 deg E in 1999. As of 26 August 2001 located at 7.01 deg E drifting at 0.004 deg W per day. As of 2007 Mar 7 located at 21.59E drifting at 0.003E degrees per day. 1999 September 23 - 06:02 GMT - Cape Canaveral LC36A. Atlas IIAS AC-155 Echostar 5 Spacecraft: FS-1300. Agency: Echostar. Perigee: 35,777 km (22,230 mi). Apogee: 35,795 km (22,241 mi). Inclination: 0.00 deg. Period: 1,436.10 min. The Centaur second stage put Echostar 5 into a supersynchronous transfer orbit of 131 km x 45526 km x 26.6 degrees. The satellite's own engine put it into the final geosynchronous orbit. Echostar 5 was a Ku-band satellite, part of the Dish Network. Stationed at 110 deg W. Positioned in geosynchronous orbit at 110 deg W in 1999. As of 5 September 2001 located at 110.01 deg W drifting at 0.003 deg W per day. As of 2007 Mar 11 located at 128.86W drifting at 0.001E degrees per day. 1999 November 23 - 04:06 GMT - Cape Canaveral LC36B. Atlas IIA AC-136 USA 146 Spacecraft: HS 601. Agency: USN. Perigee: 35,945 km (22,335 mi). Apogee: 36,626 km (22,758 mi). Inclination: 6.00 deg. UHF Follow-on satellite providing UHF and EHF communications, and Global Broadcast Service television for the US Navy. Positioned in geosynchronous orbit at 173 deg W in 1999; 72 deg E in 2000-2003. 1999 December 18 - 18:57 GMT - Vandenberg SLC3E. Atlas IIAS AC-141 Terra Mass: 4,854 kg (10,701 lb). Spacecraft: Terra. Agency: NASA GSF. Perigee: 702 km (436 mi). Apogee: 703 km (436 mi). Inclination: 98.20 deg. Period: 98.80 min. First launch in NASA's Earth Observing System program. Terra carried multispectral imagers, a radiation budget instrument, a detector to measure CO and methane pollution, and an instrument to study cloud top and vegetation properties. 2000 January 21 - 01:03 GMT - Cape Canaveral LC36A. Atlas IIA AC-138 USA 148 Mass: 1,232 kg (2,716 lb). Spacecraft: DSCS III. Agency: USAF. Perigee: 35,780 km (22,230 mi). Apogee: 35,790 km (22,230 mi). Inclination: 0.00 deg. Part of the US Air Force Defense Satellite Communications System. To be stationed in geosynchronous orbit over the Pacific Ocean. 2000 February 3 - 23:30 GMT - Cape Canaveral LC36B. Atlas IIAS AC-158 Hispasat 1C Mass: 3,112 kg (6,860 lb). Spacecraft: Spacebus 3000. Agency: Hispasat. Perigee: 35,778 km (22,231 mi). Apogee: 35,796 km (22,242 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Spanish domestic geosynchronous communications satellite. Stationed at 30 deg W. Positioned in geosynchronous orbit at 30 deg W in 2000. As of 3 September 2001 located at 30.14 deg W drifting at 0.013 deg W per day. As of 2007 Mar 9 located at 30.01W drifting at 0.005W degrees per day. 2000 May 3 - 07:07 GMT - Cape Canaveral LC36A. Atlas IIA AC-137 GOES 11 Mass: 2,217 kg (4,887 lb). Spacecraft: FS-1300. Agency: NOAA. Perigee: 35,786 km (22,236 mi). Apogee: 35,796 km (22,242 mi). Inclination: 0.40 deg. Period: 1,436.30 min. US civilian geostationary weather satellite in the Geostationary Operational Environmental Satellite series. It was the first GOES launch on the Atlas II launch vehicle (the Atlas I having been phased out). Built by SS/Loral, based on the FS-1300 bus. It was equipped with one solar panel array and a counter-boom with a solar sail. The satellite carried well as an imaging radiometer and an X-ray detector to monitor solar activity. Stationed at 106 deg W. Positioned in geosynchronous orbit at 104 deg W in 2000. As of 5 September 2001 located at 108.58 deg W drifting at 0.018 deg E per day. As of 2007 Mar 11 located at 135.52W drifting at 0.001E degrees per day. 2000 June 30 - 12:56 GMT - Cape Canaveral LC36A. Atlas IIA AC-139 TDRS 8 Mass: 3,180 kg (7,010 lb). Spacecraft: HS 601. Agency: NASA GSF. Perigee: 35,773 km (22,228 mi). Apogee: 35,800 km (22,200 mi). Inclination: 5.40 deg. Period: 1,436.10 min. Launch delayed from June 29. First Advanced Tracking and Data Relay Satellite, using a Hughes HS 601 satellite bus. It included an S-band phased array antenna and two Ku/Ka band reflectors 4.6 meters in diameter. The satellite was launched into a a 167 x 577 km x 28.3 deg parking orbit at 13:05 GMT. The Centaur upper stage made a second burn at 13:21 GMT, releasing the satellite into a subsynchronous transfer orbit of 237 x 27,666 km x 27.0 deg. The satellite's own Primex/Marquardt R4D liquid apogee engine would be used to maneuver the satellite into its final geosynchronous orbit. Stationed at 151 deg W. Positioned in geosynchronous orbit at 150 deg W in 2000. As of 5 September 2001 located at 149.99 deg W drifting at 0.014 deg E per day. As of 2007 Mar 11 located at 145.38E drifting at 3.007W degrees per day. 2000 July 14 - 05:21 GMT - Cape Canaveral LC36B. Atlas IIAS AC-161 Echostar 6 Mass: 3,700 kg (8,100 lb). Spacecraft: FS-1300. Agency: Echostar. Perigee: 35,779 km (22,231 mi). Apogee: 35,793 km (22,240 mi). Inclination: 0.00 deg. Communications satellite, positioned in geosynchronous orbit at 149 deg W. By 5 September 2001 located at 119.07 deg W drifting at 0.002 deg W per day. As of 2007 Mar 10 located at 110.39W drifting at 0.006W degrees per day. 2000 October 20 - Cape Canaveral LC36A. Atlas IIA AC-140 MLV-9 USA 153 Mass: 1,235 kg (2,722 lb). Spacecraft: DSCS III. Agency: USAF. Perigee: 35,780 km (22,230 mi). Apogee: 35,790 km (22,230 mi). Inclination: 0.00 deg. Military Communications satellite. Launch delayed from October 12 by spacecraft problem. The US Air Force Defense Satellite Communications System satellite was placed by the Centaur upper stage into a 148 km x 898 km x 29.3 deg parking orbit. A second burn put it into a 218 km x 35,232 km x 26.0 deg transfer orbit. The DSCS III B-11 IABS-8 apogee stage, with two Primex R4D liquid apogee engines, circularised the orbit at geostationary altitude on October 21 and then separated from the DSCS. 2000 December 6 - Cape Canaveral LC36A. Atlas IIAS AC-157 MLV-11 USA 155 Mass: 3,600 kg (7,900 lb). Spacecraft: SDS-3. Agency: NRO. Perigee: 35,780 km (22,230 mi). Apogee: 35,790 km (22,230 mi). Inclination: 0.00 deg. Classified satellite. Launch delayed 24 hours by RL10 engine problem in upper stage. USA 155 was a classified National Reconnaissance Office satellite. The Centaur placed the payload in a 176 x 831 km parking orbit and then in a 270 x 37490 km x 26.5 deg geostationary transfer orbit. The spacecraft was probably either a data relay satellite (to relay spy satellite imagery and data to the ground) and/or a signals intelligence satellite. 2001 June 19 - 04:41 GMT - Cape Canaveral LC36B. Atlas IIAS AC-156 ICO F-2 Mass: 2,750 kg (6,060 lb). Spacecraft: HS 601. Agency: ICO. Perigee: 10,385 km (6,452 mi). Apogee: 10,389 km (6,455 mi). Inclination: 45.00 deg. Period: 360.10 min. Launch delayed from June 5. The ICO-2 satellite was launched by British New ICO (formerly ICO Global Communications) to provide mobile communications and data/Internet services at S-band, supporting 4500 simultaneous calls. The Boeing BSS-601M satellite was similar to the standard geostationary 601 model except that it omitted the R-4D apogee engine and associated fuel, and had a larger payload section. Launch mass was 2700 kg; dry mass was around 2200-2400 kg with the remainder being station-keeping fuel. The AC-156 launch vehicle's Centaur stage reached a 167 x 10099 km x 44.6 deg transfer orbit 10 minutes after launch. A second burn 1.5 hours later put ICO-2 into a circular 10,100 km orbit. The first ICO satellite was launched in March 2000 but failed to reach orbit. ICO-2 was used for testing of the ICO system before the remaining satellites would be launched. Unlike the Iridium and Globalstar constellations, ICO proposed to use a small number of large satellites. The ICO fleet, anticipated to consist of 10 satellites, was to enable relay in S- and C-bands of voice and internet communications from/to land and ocean based mobile telephones. With a total power of 5 kW, ICO F2 was to enable a simultaneous capacity in 4,500 channels. 2001 July 23 - 07:23 GMT - Cape Canaveral LC36A. Atlas IIA AC-142 GOES 12 Mass: 2,105 kg (4,640 lb). Spacecraft: FS-1300. Agency: NOAA. Perigee: 35,769 km (22,225 mi). Apogee: 35,813 km (22,253 mi). Inclination: 0.00 deg. Period: 1,436.30 min. Launch delayed from July 12, 15 and 22. The GOES-M weather satellite was placed by the Atlas AC-142 Centaur stage into a 164 x 505 km parking orbit and then a super synchronous transfer orbit of 274 x 42275 km x 20 deg. GOES-M was a Loral 1300-series satellite with a single solar array and a solar attitude control sail. Launch mass was 2279 kg and dry mass 1042 kg. The Geostationary Operational Environmental Satellites were developed by NASA-Goddard and were transferred to the NOAA weather agency when operational. In addition to the usual weather imager/sounder, GOES-M carried a new solar soft X-ray imager. Earlier GOES satellites carried simple X-ray collimator detectors, but the new SXI was a full-fledged grazing incidence telescope similar to the SXT on Japan's Yohkoh satellite. The GOES-M satellite was redesignated GOES 12 once in orbit. GOES 12 was a 980 kg, 973 W spacecraft that carried an IR imager, a "sounder", and an X-ray imager. The IR imager was a Cassegrain telescope covering five wavelength channels, 0.55-0.75, 3.80-4.00, 6.50-7.00, 10.20-11.20, and 11.50-12.50 microns. It provided images covering 3,000 km x 3,000 km every 41 seconds, by scanning the area in 16 square kilometer sections. The "sounder" provided vertical distribution of temperature, moisture and ozone, by passive monitoring in 18 depth-dependent wavelengths. (Long wave IR: 14.71, 14.37, 14.06, 13.64, 13.37, 12.66, and 12.02 microns. Medium wave IR: 11.03, 9.71, 7.43, 7.02, and 6.51 microns. Short wave IR: 4.57, 4.52, 4.45, 4.13, 3.98, and 3.74 microns. There was also another band at visible wavelength 0.7 microns, to provide pictures of cloud tops.) The sounder covered an area of 3,000 km x 3,000 km in about 42 minutes. Another instrument package named SEM (Space Environment Monitor) monitored the energetic electrons and protons in the magnetosphere and the X-rays from the Sun. The above three had been carried on the earlier GOES missions, but GOES 12 carried also an X-ray imager providing an X-ray (about 0.1-1.0 nm wavelength) picture of the solar disk. For some months, the spacecraft was to be on standby, to be activated and moved to a desired longitude. As of 5 September 2001 located at 89.93 deg W drifting at 0.001 deg W per day. As of 2007 Mar 11 located at 74.73W drifting at 0.014E degrees per day. 2001 September 8 - 15:25 GMT - Vandenberg SLC3E. Atlas IIAS AC-160 MLV-10 USA 160 Mass: 5,000 kg (11,000 lb). Spacecraft: NOSS-3. Agency: National Reconnaissance Office (U.S.). Launch delayed from July 31. First of a new series of naval electronic intelligence satellites for the National Reconnaissance Office (NRO). The Lockheed Martin Atlas IIAS AC-160 put the vehicle in a transfer orbit. The phrasing of the launch commentary implied that the second burn left the payload in 'transfer orbit', but several observers saw the bright Centaur in the typical final deployment orbit of the earlier NOSS satellites. Therefore it seemed the first burn was to a transfer orbit of around 180 x 1100 km x 63 deg. The second burn at 1629 GMT put the Centaur and payload into an 1100 x 1100 km x 63 deg orbit. The design was apparently quite different from earlier generation NOSS satellites since only one companion satellite was deployed rather than two. Prime contractor for the new satellites was again believed to be Lockheed Martin Astronautics at Denver. The NRL probably continued to have a management and technical role in the program under overall NRO auspices. 2001 October 11 - 02:32 GMT - Cape Canaveral LC36B. Atlas IIAS AC-162 USA 162 Mass: 3,600 kg (7,900 lb). Spacecraft: SDS-3. Agency: U.S. Air Force (U.S.). The Atlas AC-162 Centaur entered a 176 x 907 km x 28.2 deg parking orbit at 0242 GMT and then made a second burn to deploy its payload in a 274 x 37538 km x 26.5 deg geostationary transfer orbit at 0301 GMT. USA 162 was rumoured to be a data relay satellite used to return data from imaging satellites similar to the one launched on October 5 2001. It was also possible that the satellite is a signals intelligence payload. The satellite is owned and operated by the National Reconnaissance Office (NRO). 2002 March 8 - 22:59 GMT - Cape Canaveral LC36A. Atlas IIA AC-143 TDRS 9 Mass: 3,192 kg (7,037 lb). Spacecraft: HS 601. Agency: NASA GSF. Perigee: 35,758 km (22,218 mi). Apogee: 35,811 km (22,251 mi). Inclination: 8.30 deg. Period: 1,436.00 min. Launch delayed from October 31, November 13 and 26, 2001 and February 6 due to contract dispute with Boeing over performance of earlier satellites of the series. The Centaur upper stage entered a 167 x 578 km parking orbit and then placed the payload into a 247 x 29135 km x 27.1 deg subsynchronous transfer orbit. NASA's TDRS-I (TDRS-9) data relay satellite used a Boeing BSS-601 bus and was to provide S, Ku and Ka band communications for the Shuttle and International Space Station. After launch a problem developed with the fuel supply from one of the satellite's four propellant tanks. The tanks were paired, so losing one tank cuts the propellant supply in half. A test burn of the General Dynamics R-4D apogee motor raised the orbit to 433 x 29146 km x 26.4 deg on March 11 and a larger perigee burn raised the apogee to geostationary altitude, 429 x 35800 km, on March 13. A further burn on March 19, raised the orbit to 3521 x 35789 km and lowered the inclination to 21.4 deg. A burn on March 25 raised the orbit further to 8383 x 35811 km and lowered inclination to 17.4 deg. As of 2007 Mar 11 located at 62.04W drifting at 0.008W degrees per day. 2002 September 18 - 22:04 GMT - Cape Canaveral LC36A. Atlas IIAS AC-159 Hispasat 1D Mass: 3,250 kg (7,160 lb). Spacecraft: Spacebus 3000. Agency: Hispasat. Perigee: 35,772 km (22,227 mi). Apogee: 35,802 km (22,246 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Launch delayed from May 28, August 14. Hispasat 1D was a Spanish geostationary communications spacecraft. The 3.3-ton, 7.0-kW satellite carried three antennae looking in different directions to provide video, data, and Internet services to Europe, North America, and North Africa via 28 Ku-band transponders after being parked over 30° W longitude alongside Hispasat 1A, 1B, and 1C. As of 2007 Mar 9 located at 29.97W drifting at 0.014W degrees per day. 2002 December 5 - 02:42 GMT - Cape Canaveral LC36A. Atlas IIA AC-144 TDRS 10 Mass: 3,190 kg (7,030 lb). Spacecraft: HS 601. Agency: NASA GSF. Perigee: 35,765 km (22,223 mi). Apogee: 35,804 km (22,247 mi). Inclination: 7.00 deg. Period: 1,436.00 min. Delayed from October 29, November 21 and 23. The third and final Advanced Tracking and Data Relay Satellite satellite separated from the Centaur upper stage 30 minutes after launch. This completed the $800 million, three satellite contract. Last launch of the Atlas 2A booster. Flight delayed from October 29, November 21 and 23. As of 2007 Mar 10 located at 40.92W drifting at 0.012E degrees per day. 2003 December 2 - 10:04 GMT - Vandenberg SLC3E. Atlas IIAS AC-164 / MLV-14 USA 173 Spacecraft: NOSS-3. Agency: NRO. Perigee: 1,010 km (620 mi). Apogee: 1,210 km (750 mi). Inclination: 63.40 deg. Second launch of new generation paired satellites used for tracking, characterisation, and intelligence on naval vessels and civilian shipping worldwide. 2004 February 5 - 23:46 GMT - Cape Canaveral LC36A. Atlas IIAS AC-165 AMC-10 (GE-10) Mass: 2,340 kg (5,150 lb). Spacecraft: AS 2100. Agency: SES Americom. Perigee: 361 km (224 mi). Apogee: 376 km (233 mi). Inclination: 51.60 deg. Period: 91.90 min. Americom 10 (AMC-10) was a replacement satellite for Satcom C3. It was to be located at 135 deg W. The C-band satellite, to be accompanied by AMC-11 later in 2004, were designed to support SES Americom's cable network in the United States, Canada, the Caribbean, and Mexico. The satellite had a design life of 15 years and carried 24 x 36 MHz C-band transponders. As of 2007 Mar 10 located at 134.97W drifting at 0.005E degrees per day. 2004 April 16 - 00:45 GMT - Cape Canaveral LC36A. Atlas IIAS AC-163 Superbird 6 Spacecraft: HS 601. Agency: Japanese Communications Corporation. Perigee: 35,775 km (22,229 mi). Apogee: 35,797 km (22,243 mi). Inclination: 0.00 deg. Period: 1,436.10 min. The satellite was to provide Ka and Ku band communications for Japan's Space Communications Corporation. 2004 May 19 - 22:22 GMT - Cape Canaveral LC36B. Atlas IIAS AC-166 AMC-11 (GE-11) Mass: 2,316 kg (5,105 lb). Spacecraft: AS 2100. Agency: SES Americom. Perigee: 35,778 km (22,231 mi). Apogee: 35,792 km (22,240 mi). Inclination: 0.00 deg. Period: 1,436.00 min. Delayed from May 17. As of 2007 Mar 11 located at 131.04W drifting at 0.000E degrees per day. 2004 August 31 - 23:17 GMT - Cape Canaveral LC36A. Atlas IIAS AC-167 USA 179 Mass: 3,600 kg (7,900 lb). Spacecraft: SDS-3. Agency: NRO. 63rd and last flight of Atlas IIAS. 576th and final launch of Rocketdyne-powered Atlas rockets. Final launch from LC36A after 42 years of use. Launch delayed from June 24 and 25, July 1 and 27, August 27, 28, 29 and 30. The payload was probably a communications satellite used to relay data from imaging spy satellites. Bibliography:
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