convert

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ehicLes

Russia

Japan

EuRopE

u.s.

soyuz sL-4

proton sL-12

H-ii

ariane 5

space shuttle

First launch

1957

1963 (Soyuz variant)

1965

1996

1981

Launch site(s)

Baikonur

Cosmodrome

Baikonur

Cosmodrome

Tanegashima

Space Center

Guiana

Space Center

Kennedy Space Center

Launch performance

payload capacity

7,150 kg

(15,750 lb)

20,000 kg

(44,000 lb)

16,500 kg

(36,400 lb)

18,000 kg

(39,700 lb)

18,600 kg

(41,000 lb)

105,000 kg (230,000 lb),

orbiter only

Return performance

payload capacity

N/A

18,600 kg

(41,000 lb)

105,000 kg (230,000 lb),

orbiter only

number of stages

2 + 4 strap-ons

4 + 6 strap-ons

2 + 2 strap-ons

1.5 + 2 strap-ons

Length

49.5 m

(162 ft)

57 m

(187 ft)

53 m

(173 ft)

51 m

(167 ft)

56.14 m

(18.2 ft)

37.24 m (122.17 ft),

orbiter only

Mass

310,000 kg

(683,400 lb)

690,000 kg

(1,521,200 lb)

570,000 kg

(1,256,600 lb)

746,000 kg

(1,644,600 lb)

2,040,000 kg

(4,497,400 lb)

Launch thrust

6,000 kN

(1,348,800 lbf)

9,000 kN

(2,023,200 lbf)

5,600 kN

(1,258,900 lbf)

11,400 kN

(2,562,820 lbf)

34,677 kN

(7,795,700 lbf)

payload

Examples

Soyuz

Progress

Pirs

Service Module

Functional

Cargo Block (FGB)

Research Module (RM)

Multipurpose Lab

Module (MLM)

H-II

Transfer Vehicle

(HTV)

Ariane Automated

Transfer Vehicle

(ATV)

Shuttle Orbiter

Nodes, U.S. Lab

Columbus, JEM,

Truss elements

Airlock, SSRMS

Soyuz

Proton

H-II

Ariane

Shuttle

Roscosmos

Russia

JAXA

Japan

ESA

Europe

NASA

United States

The largest U.S. and Russian launch vehicles are used to place elements of the ISS, crew, and cargo in orbit.

Eventually, Japanese and European launch vehicles will support cargo delivery. Currently, only the U.S. Space

Shuttle provides the capability to return significant payloads.

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oyuz

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oyuz

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rogress

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Kurs antenna

Booster attachment

structure

attitude Control

Engines

VHF Radio

antenna

primary

propulsion system

Environmental

Control Electronics

Bat-

teries

Crew

periscope

stowage

Reentry Module Hatch

Controls and Displays

solar array

Command

Radio antenna

Cargo Load

MaxiMuM

TypiCaL*

Dry cargo

such as bags

1,800 kg

(3,968 lb)

1,070 kg

(2,360 lb)

Water

420 kg

(925 lb)

300 kg

(660 lb)

air

50 kg

(110 lb)

47 kg

(103 lb)

Refueling

propellant

1,700 kg

(3,748 lb)

870 kg

(1,918 lb)

Reboost

propellant

250 kg

(550 lb)

250 kg

(550 lb)

Waste

capacity

2,000 kg

(4,409 lb)

2,000 kg

(4,409 lb)

Kurs

antenna

Booster

attachment

structure

attitude

Control

Engines

pressurized

instrumentation

section

Fluids storage

Tanks

probe and Drogue

Docking system

Kurs

antenna

Command

Radio antenna

primary

propulsion

system

stepped scan

array antenna

VHF Radio

antenna

solar array

fue

lin

g M

odu

rgo M

odu

Soyuz departs ISS.

Progress

approaches ISS.

* Measurements are

from the 21 P flight.

pressurized

section

orbital Module

Descent Module

instrumentation/

propulsion

Module

Progress prior to reentry.

Soyuz spacecraft have been in use since the mid-1960s and have been upgraded
periodically. Soyuz can support three suited crewmembers for up to 3 days. A nitrogen/
oxygen atmosphere at sea level pressure is provided. The vehicle has an automatic
docking system and may be piloted automatically or by a crewmember. The Soyuz
TMA used for the ISS includes changes to accommodate larger and smaller crewmem-
bers, an improved landing system, and digital electronic controls and displays.

Soyuz

S.P. Korolev Rocket and Space Corporation Energia

(RSC Energia)

Launch and aborts

Launch

abort using escape rocket

Escape rocket jettison, nose shroud

separation (160 seconds in full)

staging (186 seconds)

abort by separation of soyuz

orbital velocity (526 seconds)

Return

soyuz retrofire, orbital module separation,

reentry module separation

pilot parachute deploys

Drogue parachute deploys

Main parachute reefed

Main parachute fully deployed

Reentry heatshield jettison

Landing, retro rocket firing

Mission Sequence

Launch mass

6,441 kg (14,200 lb)

Descent module

2,630 kg (5,800 lb)

orbital module

1,179 kg (2,600 lb)

instrumentation/

propulsion module

2,360 kg (5,200 lb)

Delivered payload

(with three crewmembers)

30 kg (66 lb)

Returned payload

50 kg (110 lb)

Length

7 m (22.9 ft)

Maximum diameter

2.7 m (8.9 ft)

Diameter of habitable

modules

2.2 m (7.2 ft)

solar array span

10.7 m (35.1 ft)

Volume of orbital module

6.5 m

(229.5 ft

)

Volume of descent module

4 m

(141.3 ft

)

Descent G-loads

3–4 g

Final landing speed

2 m/s (6.6 ft/s)

Progress is a resupply vehicle used for cargo and propellant deliveries to the ISS. Once
docked to the ISS, Progress engines can boost the ISS to higher altitudes and control the
orientation of the ISS in space. Typically, three Progress vehicles bring supplies to the
ISS each year. Progress is based upon the Soyuz design, and it can either work
autonomously or can be flown remotely by crewmembers aboard the ISS. After a
Progress vehicle is filled with trash from the ISS, and after undocking and deorbit, it is
incinerated in Earth’s atmosphere at the end of its mission.

Progress

S.P. Korolev Rocket and Space Corporation Energia

(RSC Energia)

Length

7.4 m (24.3 ft)

Maximum diameter

2.7 m (8.9 ft)

span with solar arrays

10.6 m (34.8 ft)

Launch mass

7,150 kg

(15,800 lb)

Cargo upload capacity

2,230–3,200 kg

(4,915–7,055 lb)

pressurized habitable volume

6.6 m

(233 ft

)

Engine thrust

2,942 N

(661 lbf)

orbital life

6 mo

Progress cargo module interior.

Progress prelaunch processing.

Soyuz descent module interior.

Soyuz being prepared for launch.

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Pace

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uLti

-P

urPose

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Body Flap

Thermal Control

Radiators

Remote

Manipulator

Flight

Deck

Forward attitude

Control Engines

nose Landing

Gear

Middeck

Fuel Cells

Main Landing Gear

Rudder and

speed Brake

Main Engines

orbital

Maneuvering

Engines

aft attitude

Control

Engines

Body Flap

Elevon

Hydrazine and nitrogen

Tetroxide Tanks

Maneuvering

Engines

orbital and

attitude Maneuvering

system pod

payload Bay

Door Hinges

Main Landing

Gear Door

Crew

access Hatch

star

Tracker

Forward Reaction

Control primary

Engines

Vernier

Thrusters

air Data

probe

External Tank

umbilical Door

Reinforced Carbon-

Carbon Leading Edge

nose Cap

MPLM interior during cargo transfers.

Shuttle berthed at the U.S. Lab, PMA 2.

The Shuttle approaches the

ISS carrying the Multi-Purpose

Logistics Module (MPLM).

MPLM berthed at Node 1.

Stowage within MPLM.

aft Bulkhead

aileron/Elevon

Space Shuttle Orbiter/

Discovery, Atlantis,

Endeavour

NASA/Boeing/Rockwell

The U.S. Space Shuttle provides Earth-to-orbit and return capabilities and in-orbit
support. The diversity of its missions and customers is testimony to the adaptability of

its design. As of mid-2006, the Shuttle
had flown 115 times. The Shuttle’s

primary purpose during the remaining

4 years of operation will be to complete

the assembly of the ISS. By 2010, it will

be retired.

Length

37.2 m (122.2 ft)

Height

17.3 m (56.7 ft)

Wingspan

23.8 m (78 ft)

Typical mass

104,000 kg (230,000 lb)

Cargo capacity

16,000 kg (35,000 lb)

(typical launch and return to ISS)

pressurized

habitable volume

74 m

(2,625 ft

)

Mission length

7–16 days, typical

number of crew

7, typical

atmosphere

oxygen-nitrogen

Cargo Bay

Length

18.3 m (60 ft)

Diameter

4.6 m (15 ft)

The Italian-built Multi-Purpose Logistics Module (MPLM)
serves as the International Space Station’s “moving van”
by carrying laboratory racks filled with equipment,
experiments, and supplies to and from the Station
aboard the Space Shuttle.

Mounted in the Shuttle’s cargo bay for

launch and landing, the modules are transferred
to the Station using the Shuttle’s robotic arm
after the Shuttle has docked. While berthed to
the Station, racks of equipment and stowage
items are unloaded from the module, and racks
and equipment may be reloaded to be transported
back to Earth. The MPLM is then detached from
the Station and positioned in the Shuttle’s cargo bay
for the trip home.

Multi-Purpose Logistics

Module (MPLM)/Leonardo,

Raffaelo, Donatello

NASA/Alcatel Alenia Space

Length

6.6 m (21.7 ft)

Diameter

4.2 m (13.8 ft)

Mass (structure)

4,685 kg (10,329 lb)

Mass (payload)

9,400 kg (20,700 lb)

Racks

16, 5 active

pressurized habitable volume

31 m

(1,095 ft

)

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The HTV primary propulsion system

performs rendezvous maneuvers.

Interior view of

HTV pressurized

carrier.

The HTV is berthed onto JEM by the

Space Station RMS.

After rendezvous

with the ISS, the HTV

awaits grappling by

the SSRMS.

probe and Drogue

Docking system

integrated

Cargo Carrier

aTV

spacecraft

Bus

attitude Control

Engines (20)

primary

Maneuvering

Engines (4)

solar

array

Titanium Tanks,

(for carrying water,

propellant, and oxygen)

Environmental

Control system

ispRs (8)

aTV

spacec

raft

Bus

integrat

Cargo C

arrier

(based o

MpLM d

esign)

iss

service

Module

pres

suriz

unpr

essu

rized

avio

nics

prop

ulsio

Carr

ier

Carr

ier

Mod

ule

Mod

ule

primary

Engines

propellant

Tanks

Earth sensors

Lithium ion

Batteries

avionics

Exposed pallet

payload

international

standard payload

Racks (ispRs)

Forward attitude

Control Engines

Hatch and

Berthing Ring

(to iss node)

Cargo

Compartment

JAXA H-II Transfer Vehicle

(HTV)

Japan Aerospace Exploration Agency (JAXA)/

Mitsubishi Heavy Industries, Ltd.

The H-II Transfer Vehicle is an autonomous logistical resupply vehicle designed to
berth to the International Space Station using the Space Station Remote Manipulation
System (SSRMS). HTV offers the capability to carry logistics materials in both its internal
pressurized carrier as well as in an unpressurized carrier for exterior placement. It is
launched on the H-II unmanned launch vehicle and can carry dry cargo, gas and water, and
propellant. After fresh cargo is unloaded at the ISS, the HTV is loaded with trash and waste
products; after unberthing and deorbit, it is incinerated during reentry.

The ATV during manufacture.

Automated Transfer Vehicle

(ATV)

European Space Agency (ESA)/European Aeronautic

Defence and Space Co. (EADS)

The European Space Agency Automated Transfer Vehicle is an autonomous logistical
resupply vehicle designed to dock to the International Space Station and provide the crew
with dry cargo, atmospheric gas, water, and propellant. After the cargo is unloaded, the ATV
is reloaded with trash and waste products, undocks, and is incinerated during reentry.

Length

10.3 m (33.8 ft)

Maximum diameter

4.5 m (14.8 ft)

span across solar arrays

22.3 m (73.2 ft)

Launch mass

20,750 kg (45,746 lb)

Cargo upload capacity

7,667 kg (16,903 lb)

Engine thrust

1,960 N (441 lbf)

orbital life

6 mo

Cargo Load

Dry cargo such as bags

5,500 kg (12,125 lb)

Water

840 kg (1,852 lb)

air (o

, n

)

100 kg (220 lb)

Refueling propellant

860 kg (1,896 lb)

Reboost propellant

4,700 kg (10,360 lb)

Waste capacity

6,500 kg (14,330 lb)

Artist’s rendering shows the

ATV approaching the ISS.

Russian-built

probe and

drogue docking

system.

Length

9.2 m (30 ft)

Maximum diameter

4.4 m (14.4 ft)

Launch mass

16,500 kg (36,375 lb)

Cargo upload capacity

5,500 kg (12,125 lb)

pressurized habitable

volume

14 m

(495 ft

)

unpressurized volume

16 m

(565 ft

)

orbital life

6 mo