99-82839-pr

iii

Contents

Paragraphs

Page

Introduction

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1-10

Measurements of space debris . . . . . . . . . . . . . . . . . . .

11-60

Ground-based measurements . . . . . . . . . . . . . . . . .

11-31

Radar measurements . . . . . . . . . . . . . . . . . . . .

12-25

Optical measurements . . . . . . . . . . . . . . . . . . .

26-31

Space-based measurements . . . . . . . . . . . . . . . . . .

32-45

Retrieved surfaces and impact detectors . . . . .

32-40

Space-based debris measurements . . . . . . . . .

41-45

Summary of measurements . . . . . . . . . . . . . . . . . .

Cataloguing and databases . . . . . . . . . . . . . . . . . .

47-53

Effects of the space debris environment on the
operation of space systems . . . . . . . . . . . . . . . . . .

54-59

Effects of large debris objects on the
operation of space systems . . . . . . . . . . . . . . .

Effects of small debris objects on the
operation of space systems . . . . . . . . . . . . . . .

56-59

Other effects of space debris . . . . . . . . . . . . . . . . .

II.

Modelling of the space debris environment and risk
assessment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

61-94

Modelling of the space debris environment . . . . . .

61-78

Introduction and methodology . . . . . . . . . . . .

61-67

Short-term models . . . . . . . . . . . . . . . . . . . . . .

68-69

Long-term models . . . . . . . . . . . . . . . . . . . . . .

70-78

Space debris risk assessments . . . . . . . . . . . . . . . . .

79-94

Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . .

79-80

Collision risk assessments in low Earth orbit .

81-86

Collision risk assessments in geostationary
orbit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

87-89

Risk assessments for re-entering space debris

90-94

III.

Space debris mitigation measures . . . . . . . . . . . . . . . . .

95-130

Reduction of the debris increase in time . . . . . . . .

95-104

Avoidance of debris generated under normal
operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

95-97

Paragraphs

Page

Prevention of on-orbit break-ups . . . . . . . . . .

98-101

Deorbiting and reorbiting of space objects . . . 102-104

Protection strategies . . . . . . . . . . . . . . . . . . . . . . . . 105-119

Shielding . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 106-112

Collision avoidance . . . . . . . . . . . . . . . . . . . . . 113-119

Effectiveness of debris mitigation measures . . . . . . 120-130

Scenarios of mitigation measures . . . . . . . . . . 123-125

Cost or other impact of mitigation measures . 126-130

IV.

Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 131-136

Annex.

List of documents relevant to the subject “Space debris” . . . . . . .

Introduction

The item on space debris was included on the agenda of the Scientific and

Technical Subcommittee at its thirty-first session, in February 1994, in accordance
with General Assembly resolution 48/39 of 10 December 1993. The Subcommittee,
at its thirty-first session, expressed its satisfaction at having the subject of space
debris as a separate agenda item after many years of discussion in various inter-
national fora, including the Subcommittee and the Committee on the Peaceful Uses
of Outer Space. The Subcommittee agreed that consideration of space debris was
important and that international cooperation was needed to evolve appropriate and
affordable strategies to minimize the potential impact of space debris on future
space missions. At its subsequent sessions, the Subcommittee continued its consi-
deration of that agenda item on a priority basis.

The Subcommittee agreed that it was important to have a firm scientific and

technical basis for future action on the complex attributes of space debris and that
it should, inter alia, focus on understanding aspects of research related to space
debris, including: debris measurement techniques; mathematical modelling of
the debris environment, characterizing the space debris environment; and measures
to mitigate the risks of space debris, including spacecraft design measures to pro-
tect against space debris. In order to advance in its consideration of space debris,
the following work plan was adopted by the Subcommittee at its thirty-second
session:

1996: Measurements of space debris, understanding of data and effects of this
environment on space systems. Measurements of space debris comprise all pro-
cesses by which information on the near-Earth particulate environment is gained
through ground- and space-based sensors. The effect (impact of particles and
resulting damage) of this environment on space systems should be described;

1997: Modelling of space debris environment and risk assessment. A space
debris model is a mathematical description of the current and future distribution
in space of debris as a function of its size and other physical parameters.
Aspects to be addressed are: an analysis of fragmentation models; short-
and long-term evolution of the space debris population; and comparison of
models. The various methods for collision risk assessment should be critically
reviewed;

1998: Space debris mitigation measures. Mitigation comprises reduction of the
space debris population growth and protection against particulate impact. Meas-
ures for the reduction of space debris growth include methods for debris preven-
tion and removal. Protection against space debris includes physical protection
with shielding and protection through collision avoidance.

Each session was to review the current operational debris mitigation practices

and consider future mitigation methods with regard to cost-efficiency. The Sub-
committee agreed that the work plan should be implemented with flexibility and
that, notwithstanding the selection of a specific topic for the next session, delega-
tions wishing to address the Subcommittee at that time on other aspects of scien-
tific research related to space debris should be free to do so.

The Subcommittee noted that a certain amount of research on space debris had

already been undertaken in some countries, which had allowed for a better under-
standing of the sources of debris, the areas in near-Earth orbit that were reaching
high levels of space debris density, the probabilities and effects of collisions and
the necessity to minimize the creation of space debris. The Subcommittee agreed
that Member States should pay more attention to the problem of collision of space
objects, including those with nuclear power sources on board, with space debris
and to other aspects of space debris. It also agreed that national research on space
debris should continue and that Member States should make available to all inter-
ested parties the results of that research.

The Subcommittee encouraged Member States and relevant international or-

ganizations to provide information on practices that they had adopted and that had
proven effective in minimizing the creation of space debris. The information was
compiled by the Secretariat and made available as United Nations documents. A list
of the documents relevant to the subject “Space debris” is provided in the annex.

In order to have a common understanding of the term “space debris”, the

Subcommittee at its thirty-second session proposed a definition of the term that it
modified at its subsequent sessions to read as follows: “Space debris are all man-
made objects, including their fragments and parts, whether their owners can be
identified or not, in Earth orbit or re-entering the dense layers of the atmosphere
that are non-functional with no reasonable expectation of their being able to as-
sume or resume their intended functions or any other functions for which they are
or can be authorized.” However, there is still no consensus agreement on the
definition.

At its thirty-third session, the Subcommittee initiated the development of its

technical report on space debris in order to establish a common understanding that
could serve as the basis for further deliberations of the Committee on that impor-
tant matter. The technical report was structured according to the specific topics
addressed by the work plan during the period 1996-1998 and carried forward and
updated each year. The text was drafted during the sessions of the Subcommittee
by an unofficial group of experts provided by Member States. In drafting the
technical report, working papers prepared for the sessions and scientific and tech-
nical presentations made by leading space debris experts were evaluated.

Especially valuable contributions to all parts of the technical report, in particu-

lar graphical and numerical data, were made by the Inter-Agency Space Debris
Coordination Committee (IADC), which had been formally founded in 1993 to

enable space agencies to exchange information on space debris research activities,
to review the progress of ongoing cooperative activities, to facilitate opportunities
for cooperation in space debris research and to identify debris mitigation options.
The founding members of IADC were the European Space Agency (ESA), Japan,
the National Aeronautics and Space Administration (NASA) of the United States
of America and the Russian Space Agency (RSA). China joined in 1995; it was
followed by the British National Space Centre, the Centre nationale d’études
spatiales (CNES) of France and the Indian Space Research Organization (ISRO) in
1996, by the German Aerospace Centre (DLR) in 1997 and by the Italian Space
Agency (ASI) in 1998.

At its thirty-fifth session, the Subcommittee agreed that the final technical

report of the Subcommittee on space debris should be adopted at its thirty-sixth
session, in 1999, after final editing during the inter-sessional period and considera-
tion by relevant organizations (such as IADC and the International Academy of
Astronautics (IAA)). At its thirty-sixth session, the Subcommittee adopted the draft
technical report on space debris together with the changes proposed by the drafting
group (A/AC.105/719, para. 35).

10.

This document was generated following a multi-year review conducted under

the auspices of the Scientific and Technical Subcommittee of the Committee on the
Peaceful Uses of Outer Space. The aim of conducting such a review was to estab-
lish a common understanding of the nature of space debris that could serve as a
basis for further deliberations. The information presented in this report will be
updated, as both the environment it describes, and the knowledge of that environ-
ment, evolve with time. Although significant increases in the magnitude of the
space debris population are not anticipated in the short term, it is expected that
enhanced ability to monitor and model the future debris population could result in
greater understanding of the issues and methods to address them.

Measurements of space debris

Ground-based measurements

11.

Remote sensing of space debris from ground-based measurements generally

falls into two categories: radar measurements and optical measurements. Typically,
radar measurements have been used for space debris in low Earth orbit (LEO),
while optical measurements have been used for high Earth orbit (HEO). For pas-
sive optical measurements, the signal intensity return is inversely proportional to
the square of the distance or altitude of the object since the incident illumination
from the Sun is essentially independent of altitude. For radar measurements, the
signal intensity return is inversely proportional to the fourth power of distance
since radars must provide their own illumination. The result is that an optical
telescope of modest size can outperform most radars for detection of debris at high
altitudes. Some optical measurements of small debris in LEO have been done, but
in general radars outperform telescopes for measurements in LEO.

Radar measurements

12.

Ground-based radars are well suited to observe space objects because of their

all-weather and day-and-night performance. The radar power budget and operating
wavelength are limiting factors for detection of small objects at long ranges.

13.

Basically two types of radars are used for space object measurements:

(a)

Radars with mechanically controlled beam direction using parabolic

reflector antennas. Only objects in the actual field of view—given by the mechani-
cal direction of the parabolic reflector antenna—can be detected and measured;

(b)

Radars with electronically controlled beam direction using phased

array antennas. Multiple objects at different directions can be detected and
measured simultaneously.

14.

The first type of radar is used mainly for tracking and/or imaging satellites,

and the second type is used mainly for both tracking and search tasks.

15.

The following radar modes are used for observation of space debris: tracking

mode; beam-park mode; and mixed mode (sometimes called stare-and-chase).

16.

In the tracking mode the radar follows an object for a few minutes, gaining

data on angular direction, range, range rate, amplitude and phase of the radar
echoes. From the evaluation of direction and velocity (angular rate and range rate)
as a function of time, orbital elements can be derived.

17.

In the beam-park mode, the antenna is kept fixed in a given direction and

echoes are received from objects passing within its field of view. This gives sta-
tistical information on the number and size of the detected objects but less precise
data on their orbit.

18.

In the mixed mode, the radar would start in the beam-park mode and change

to the tracking mode when an object passes the beam, thereby gaining more precise
orbital data. Once the data are collected, the radar might return to the beam-park
mode.

19.

Radars have been used in both a monostatic (a single antenna for both trans-

mitter and receiver) and bistatic (transmitting from one antenna and receiving from
a second antenna) configuration. In the bistatic mode, an additional receiver an-
tenna, separate from the emitting antenna, is used. This allows a greater sensitivity,
which enables the detection of smaller objects, and flexibility for networking dif-
ferent kinds of antennas.

20.

From radar measurements principally, the following space object character-

istics can be derived (all of the following parameters will have some degree of
uncertainty):

(a)

Orbital elements, describing the motion of the object’s centre of mass

around Earth;

(b)

Attitude, describing the motion of the object around its centre of mass;

(c)

Size and shape of the object;

(d)

Orbital lifetime;

(e)

Ballistic coefficient, as defined in paragraph 48 (g) below, specifying

the rate at which the orbital semi-major axis decays;

(f)

Object mass;

(g)

Material properties.

21.

The deterministic data can go into a catalogue of space objects, as well as the

statistical information on numbers of detected objects of a given size in a given
region at a certain time.

22.

Both the Russian Federation and the United States (United States Space

Command) operate networks of radars (and optical telescopes) for detecting, track-
ing and cataloguing orbiting space objects. These catalogues date from the first
artificial satellite launch in 1957 and include space debris as small as 10-30 cm in
diameter.

23.

Radar measurements of space debris population statistics at sizes smaller than

30 cm (the nominal limit for the Russian and United States catalogues) have been
conducted by the United States using Haystack, Haystack Auxiliary (HAX) and
Goldstone radars, by the Russian Federation using some Russian radars and by
Germany using the Research Establishment for Applied Science of Wachtberg-
Werthhoven (FGAN) radar and the Effelsberg Radio Telescope. Haystack, HAX

Table 1.

Radar facilities for debris observation

Primary

Field

Wave-

Sensitivity

operation

length

(diameter)

Country

Organization

Facility

Type

mode

Configuration

view

(m)

Status

Germany

FGAN

TIRA

Dish

Mixed

Monostatic

0.5

0.23

0.02 at

Operational

1,000 km

Germany

MPIfR

Effelsberg

Dish

Stare

Bistatic

0.16

0.23

0.009 at

Experimental

with TIRA

1,000 km

Japan

Kyoto

MU radar

Phased

Stare

Monostatic

3.7

6.4

0.02 at

Operational

University

array

500 km

Japan

ISAS

Uchinoura

Dish

Mixed

Bistatic

0.4

0.13

0.02 at

Experimental

500 km

Japan

ISAS

Usuda

Dish

Mixed

Bistatic

0.13

0.02 at

Experimental

500 km

Ukraine/Russian

. .

Evpatoria

Dish

Stare

Bistatic

0.1

0.056

0.003 at

Developmental

Federation

1,000 km

United States

NASA/

Arecibo

Dish

Stare

Bistatic

0.13

0.004 at

One-time

NSF

575 km

experiment

United States

NASA/

Haystack

Dish

Stare

Monostatic

0.1

0.03

0.006 at

Operational

DoD

1,000 km

United States

NASA/

HAX

Dish

Stare

Monostatic

0.1

0.02

0.05 at

Operational

DoD

1,000 km

United States

NASA

Goldstone

Dish

Stare

Bistatic

0.035

0.002 at

Operational

500 km

United States

DoD

TRADEX

Dish

Mixed

Monostatic

0.61/

0.23/

0.03 at

Operational

0.30

0.10

500 km

and Goldstone radars have provided a statistical picture of LEO debris environment
at sizes down to 0.5 cm (with some data down to 0.2 cm). FGAN radar measure-
ments have not extended to quite such small sizes but in general agree with the
NASA results. The picture that emerges from these and other measurements is that
the debris population exceeds the natural meteoroid population for all sizes (except
between 30 and 500 µm).

24.

The MU radar of Kyoto University of Japan has observed the radar cross-

section variation of unknown objects for a period of 20 seconds. A bistatic radar
system of the Institute of Space and Astronautical Sciences (ISAS) of Japan has the
capability to detect objects as small as 2 cm at an altitude of 500 km.

25.

The existing and planned radar capabilities for observation of debris for sizes

smaller than 10-30 cm in diameter are given in table 1.

Optical measurements

26.

Debris can be detected by a telescope when the debris object is sunlit while

the sky background is dark. For objects in LEO, this period is limited to an hour
or two just after sunset or before sunrise. However, for objects in HEO, such as
those in geosynchronous orbit, observations can often be continued during the
entire night. The requirement of clear, dark skies is another limitation on optical
measurements.

27.

The United States Space Command employs aperture telescopes of 1 m fitted

with intensified vidicon detectors to track HEO objects. These measurements are
used to maintain the HEO part of the Space Command catalogue. The capability
of these telescopes is limited to detection of objects of 1 m at geosynchronous
altitudes, corresponding to a limiting stellar magnitude of 16. Charge-coupled
device (CCD) detectors are planned for these telescopes, which will improve their
performance. RSA has a similar telescope capability used to maintain the orbits of
HEO objects in its catalogue.

28.

In general, the United States Space Command and the Russian geostationary

orbit (GEO) catalogues are concerned with intact spacecraft and rocket bodies.
However, there are reasons to believe that small space debris resulting from explo-
sions also exist in the GEO region. A Russian Ekran satellite in GEO was observed
to explode in 1978. Many uncatalogued objects have been seen in high elliptical
orbits at an inclination of 7 degrees, possibly the result of Ariane geotransfer stage
break-ups. The United States Space Command telescope on Maui, in Hawaii, ac-
cidentally observed the break-up of a Titan transtage (1968-081E) in Febru-
ary 1992. There are other stages near GEO that may still have the potential to
explode. Some of these stages appear to be lost and may have exploded.

29.

An exceptional combination of sensitivity and field of view is required to

survey the GEO region for the small space debris that are suspected to exist there.

A limiting stellar magnitude of 17 or greater is needed to detect debris smaller than
1 m near geosynchronous altitude, and as wide a field of view as possible is needed
to allow the rapid surveying of large areas. Most astronomical telescopes that have
sufficient sensitivity have a small field of view. This is useful for accurate deter-
mination of satellite positions (once their approximate locations are known), but
not for surveying large areas of the sky.

30.

Some preliminary measurements have been done to survey the region near

GEO for debris objects smaller than 1 m. NASA used a small telescope capable of
detecting objects as faint as 17.1 stellar magnitude (equivalent to an object about
0.6 m in diameter at geosynchronous altitude), with a field of view of about 1.5
degrees. The results showed that there does exist an appreciable population of
debris near those altitudes. Further debris surveys are justified. IADC is currently
conducting an exploratory GEO space debris campaign.

31.

The existing and planned optical capabilities for optical observation of debris

are summarized in table 2.

Table 2.

Optical facilities for debris observation

Telescope

Field of

aperture

view

Detection

Limiting

Country

Organization

(m)

(degrees)

type

magnitude

Status

ESA

CCD

In development

France

French National

0.9

0.5

CCD

In development

Centre for
Scientific Research

Japan

JSF

/NAL

/NASDA

1.0

3.0

CCD

19.5

In development

Japan

JSF

/NAL

/NASDA

0.5

2.0

CCD

18.5

In development

Japan

Sundai

0.75

0.04

CCD

Operational

Japan

CRL

1.5

0.28

CCD

18.7

Operational

Russian

Federation

RAS

0.2

CCD

Operational

RAS

0.6

0.2

CCD

Operational

Russian

Federation

RSA

0.6

0.2

Operational

Switzerland

University of Berne

0.5

CCD

19.5

Operational

United Kingdom Royal Greenwich

0.4

0.6

CCD

Two telescopes

of Great

Observatory/MOD

operational,

Britain and

United Kingdom

Northern

and overseas

Ireland

United States

NASA

0.3

1.5

CCD

17.1

Operational

United States

NASA

0.3

CCD

21.5

Operational

Japan Space Forum.

National Aerospace Laboratory of Japan.

Russian Academy of Sciences.

Russian Space Agency.

Space-based measurements

Retrieved surfaces and impact detectors

32.

Information on submillimetre-sized particles can be gained with the analysis,

after return to Earth, of surfaces or spacecraft exposed to the space environment.
Similar information can also be obtained through dedicated debris and dust
detectors. Most of them contain, as a key element, a detection surface. Some of
them are designed to catch an impact particle for further analysis. For cost reasons,
surfaces are retrieved for later analysis only from LEO.

33.

Examples of retrieved spacecraft and surfaces are given in table 3.

Table 3.

Examples of retrieved spacecraft and surfaces

Name

Orbit

In orbit

Stabilization

Exposed area

Salyut 4 and 6

350 km

1974-1979

Various

~7 m

of sensors

51.6 degrees

and cassettes

STS-7 Window

295-320 km

June 1983

Various

~2.5 m

(NASA)

28.5 degrees

Solar Maximum

500-570 km

February 1980-

Sun-pointing

2.3 m

Mission (NASA)

28.5 degrees

April 1984

STS-52

350 km

October 1992

Various

1 m

(Canada/NASA)

28.4 degrees

LDEF (NASA)

340-470 km

April 1984-

Gravity-gradient

151 m

28.5 degrees

January 1990

EURECA (ESA)

520 km

July 1992-

Sun-pointing

35 m

of spacecraft

28.5 degrees

June 1993

plus 96 m

solar arrays

HST Solar Array

610 km

May 1990-

Sun-pointing

62 m

(NASA/ESA)

28.5 degrees

December 1993

Mir/EUROMIR 95

390 km

October 1995-

Gravity-gradient

20 x 30 cm

(RSA/ESA)

51.6 degrees

February 1996

(cassette)

Mir

390 km

1986-1998

Various

~15 m

of cassettes

51.6 degrees

and other elements

Mir

390 km

November 1997-

Various

1 m

(Canada/Ukraine)

51.6 degrees

February 1999

SFU (Japan)

480 km

March 1995-

Sun-pointing

50 m

28.5 degrees

January 1996

(except 1 month
IR telescope
operation)

Space Shuttle Orbiter

300-600 km

1992-present

Various

100 m

(NASA)

28.5-51.6 degrees

34.

After exposure to the space environment, spacecraft surfaces are covered

with a large number of impact craters caused by meteoroids and debris. The size
of individual impact craters and holes ranges from micrometres to several milli-
metres. A basic problem is to distinguish between impacts of meteoroids and
man-made debris. A proven method to determine their origin is chemical analysis.

However, there are some difficulties associated with this method. Because of the
high impact speed, little of the impacting material survives unaltered. The particle
vaporizes and then recondenses on the surrounding surfaces. In many cases, there-
fore, the origin of an impacting particle cannot be uniquely determined. In order
to relate the size of the impact feature with the size of the particle, ground-
calibration tests (hypervelocity impact tests) have been performed for different
materials.

35.

From impact statistics and calibration experiments, the flux for meteoroids

and debris can be determined as a function of particle size. An important issue to
be considered is that of secondary impacts. If these are not properly treated, the
derived flux figures will be overestimated.

36.

The Long-Duration Exposure Facility (LDEF) was covered by more than

30,000 craters visible to the naked eye, of which 5,000 had a diameter larger than
0.5 mm. The largest crater, 5 mm in diameter, was probably caused by a particle
of 1 mm. LDEF showed that some impacts were clustered in time, and it also
pointed to the existence of a submillimetre population in elliptical orbits.

37.

On the European Retrievable Carrier (EURECA), the largest impact crater

diameter was 6.4 mm. Among the retrieved surfaces, the returned solar array of the
Hubble Space Telescope (HST) had been the one with the highest orbit altitude. An
interesting finding was that the impact flux for HST was considerably higher
(factor of 2-8) than for EURECA for crater pit sizes larger than 200-300 µm.

38.

The Space Flyer Unit (SFU) launched by an H-II rocket in March 1995 was

retrieved by the Space Shuttle in January 1996. A post-flight analysis (PFA) is
under way.

39.

The cases discussed above give evidence of the effect of the particulate

environment on spacecraft in orbit. In all cases, no functional degradation of the
spacecraft was observed. Available information on the submillimetre population is
limited to altitudes below 600 km. In particular, no information is available in the
regions of highest density of space debris in LEO (at an altitude of about 800-1,000
km) as well as in geostationary orbit. In 1996, an ESA debris and dust detector was
placed in geostationary orbit on the Russian spacecraft Express-2. CNES will place
active and passive detectors on Mir in 1999. CNES plans to use the same detectors
on the French satellite STENTOR in geostationary orbit (1999) and in helio-
synchronous orbit on an Israeli satellite (1999).

40.

Since 1971, regular measurements of submillimetre-sized meteoroid and

debris particles have been carried out on the Russian space stations Salyut 1, 2, 3,
4, 6 and 7 and Mir. The measurements have been carried out by capacitive sensors
with an overall exposed area of about 3 m

, as well as by changeable returned

cassettes with an exposed area of about 0.1 m

each. In January 1998, during the

Space Shuttle mission, eight sections of solar panels from the space station Mir,
with an overall area of about 10 m

and an exposure time of about 10 years, were

returned to Earth for further investigation.

Space-based debris measurements

41.

Space-based measurements in general have the advantage of higher resolu-

tion because of the smaller distance between the observer and the object. Also,
there is no disturbing effect of the atmosphere (extinction and absorption of elec-
tromagnetic signals). The costs of space-based systems are in general higher than
the costs of ground-based systems, and careful cost-performance trade-offs are
needed.

42.

The infra-red astronomical satellite (IRAS), launched in 1983 to perform a

sky survey at wavelengths ranging from 8 to 120 µm, was operational during the
10 months in a Sun-synchronous orbit near an altitude of 900 km. The satellite was
pointing radially away from Earth and scanning the celestial sphere. The complete
set of unprocessed IRAS data has been analysed by the Space Research Organiza-
tion of the Netherlands (SRON), in Groningen, in order to characterize the infra-
red emission of debris objects and to extract a comprehensive set of debris
sightings. The method of identifying space debris signatures is based on the rec-
ognition of their track over the IRAS focal plane. The 200,000 potential debris
sightings are stored in a database. About 10,000 sightings are attributed to real
objects. From the debris sightings, it is not possible to compute the orbital elements
of a debris object in a unique manner.

43.

In 1996, the United States launched the MSX spacecraft into a 900 km orbit.

Its visible and infra-red sensors are being used to observe nearby small debris.

44.

In September 1996, the impact ionization detector Geostationary Orbit Im-

pact Detector (GORID) was placed into GEO on board the Russian telecommuni-
cation satellite Express 12. It is stationed at 80 degrees east longitude and measures
the submillimetre-sized meteoroid and space debris population.

45.

To measure the small-sized solid particle population in different orbits and

on a more regular basis, a low resource standard in situ detector called DEBIE is
under development. The first flight of DEBIE is planned on the small ESA tech-
nology satellite PROBA in polar orbit.

Summary of measurements

46.

Figure I presents a compilation of the results of many of the measurement

systems described in previous sections. It shows the cross-sectional flux (number
of objects per year per square metre) for objects of a given size and larger. The
figure summarizes measurements in LEO near 500 km altitude.

Cataloguing and databases

47.

A catalogue is a record of the characteristics of the orbital population that

have been derived from measurements or records. (For the purposes of the present

report, the term catalogue includes the collection of orbital elements.) The purposes
of a catalogue are to provide current orbital elements, which can be used to predict
orbital motion, and to provide correlation with observations of orbiting objects; to
act as a historical record of orbital activity for the purposes of environment moni-
toring; to serve as an input to modelling the behaviour of orbiting objects; and to
provide a basis for predicting future launch and operational activity.

48.

The following characteristics of orbiting objects may be recorded:

(a)

Regularly updated state vectors: the characteristics of the orbit of an

object derived at a particular instant in time and used for orbit propagation;

(b)

Mass: the launch mass, beginning of life mass and dry mass (end of

life);

(c)

Radar cross-section: the returned signature of an orbiting object, from

which shape, orientation and size can be derived (the radar cross-section is
dependent on the wavelength of the radar; therefore, the wavelength of the
measurement must also be recorded);

(d)

Albedo: a measure of the reflectivity of an object that characterizes the

optical visibility of an object;

1.0E+0

1.0E+2

1.0E+4

1.0E+6

1.0E2

1.0E4

1.0E6

1.0E8

Cross-sectional flux of a given size and larger

(number/m

-yr)

Meteoroids, 400 km
SSN catalog flux, 400 km

May 1997
Haystack flux, 350600 km
HAX flux, 450600 km
LDEF IDE, 300400 km
SMM impacts
LDEF craters (Humes)

HST impacts (Drolshagen), 500 km

Space Flyer Unit, 480 km
Goldstone radar, 300600 km
SMM holes
SMM craters, 500570 km
LDEF craters (Horz)
EURECA impacts (Drolshagen),

500 km

0.00001 0.0001

0.001

0.01

0.1

100

1 000

Diameter (cm)

Figure I.

Approximate measured debris flux in low Earth orbit,

by object size

(e)

Dimensions;

(f)

Orientations;

(g)

Ballistic coefficient: a measure of the aerodynamic and area-to-mass

characteristics of the object that will influence the orbital lifetime of an object until
its entry into the upper atmosphere;

(h)

Material composition: although not currently of importance, to effec-

tively represent shedding of micro-debris would require the definition of surface
characteristics;

(i)

Launch characteristics: this will include the launch vehicle, launch date

and launch site.

49.

There are two catalogues of space objects that are frequently updated by

observations: the United States Space Command catalogue and the space
object catalogue of the Russian Federation. Data are also archived in the
Database and Information System Characterizing Objects in Space (DISCOS) of
ESA based on those two catalogues. Figure II shows the growth of the number
of objects in the United States catalogue with time (limited to sizes larger than
10-30 cm).

50.

The National Space Development Agency (NASDA) of Japan is studying a

debris database that can provide data to the international common debris data-
base currently being discussed in IADC. NASDA is also studying a trajectory
prediction analysis for re-entering objects and collision avoidance analysis for new
launches.

51.

NASDA currently depends on the United States Space Command orbital

element data as the source of its debris database. NASDA will add the orbital data
of its own spacecraft acquired through observations conducted by the National
Astronomy Observatory.

52.

A catalogue record can be stored on a number of media. A hard-copy (paper)

format is not well suited to the dynamic nature of the orbital population. An
electronic format is well suited to the recording of such information, modification
and updating of characteristics, manipulation of data for the purposes of com-
parison and input to models, and access via networks by users for the purposes of
querying and contribution.

53.

Current catalogues contain information on satellites and debris as small as

10-30 cm in diameter. Some recent activities in the United States are aimed at
improving the sensitivity of the United States catalogue to provide detection of
5 cm objects at altitudes below 600 km. Some studies have looked at improvements
to provide detection of objects as small as 1 cm. However, improvements of
catalogues beyond 5 cm are not likely in the near future. Therefore, modellers
must continue to use statistical measurements for smaller sizes (see figures III
and IV).

Effects of the space debris environment on the operation

of space systems

54.

Four factors determine how the space debris environment affects space sys-

tems operations. These are time in orbit, projected area, orbital altitude and orbital
inclination. Of these, time in orbit, projected area and orbital altitude are the domi-
nant factors.

1960

1964

1968

1972

1976

1980

1984

1988

1992

1996

8 000

7 000

6 000

5 000

4 000

3 000

2 000

1 000

10 000

9 000

Number of objects in orbit

Year

Figure II.

Number of objects in the United States catalogue,

by type, 1959-1996

Note

: This figure does not take into account objects that have re-entered the

atmosphere.

A: Total number of objects, including objects not contained in the official catalogue
B: Total number of objects, based on the official catalogue
C: Fragmentation debris; fragments are counted since the year of event; fragmenta-

tion parents are counted as intacts until the date of event; since the event date

the parents are counted as fragments

D: Spacecraft
E: Rocket bodies
F:

Operational debris; operational debris related to a launch are counted since the

year of launch; Salyut 4, 5, 6, 7 and Mir operational debris are not counted since

the date of launch of the parent but since a more realistic date

Effects of large debris objects on the operation of space systems

55.

Large debris objects are typically defined as objects larger than 10 cm in size.

Such objects are capable of being tracked, and orbital elements are maintained.
During the course of shuttle missions, orbiters have executed collision avoidance
manoeuvres in order to avoid catastrophic collisions with these large debris objects.
Two unmanned satellites have also performed collision-avoidance manoeuvres to
avoid large debris: the European remote sensing satellite (ERS-1) in June 1997 and
March 1998; and Satellite pour l’observation de la Terre (SPOT-2) in July 1997.
Post processing of orbital data indicate that none of the predicted collisions would
have actually occurred; however, the agencies responsible for the spacecraft
wanted to increase the safety distances between objects because of positional

A = Solar Max

B = LDEF

C = EURECA

D = SFU

E = HST Solar Array

F = STS Windows

G = STS Surfaces

Diameter

(cm)

Figure III.

Coverage of ranges of debris diameter and period of exposure:

space-based data, 1980-1998

0.05

0.10

0.15

0.20

0.25

uncertainties, which will likely continue into the future. In 1996, the first recorded
natural collision occurred between two catalogued objects, the operational Cerise
satellite and a fragment from an exploded Ariane upper stage.

Effects of small debris objects on the operation of space systems

56.

Small debris objects (smaller than a few millimetres in diameter) have al-

ready caused some damage to operational space systems. These impacts have had
no known effect on mission success. This damage can be divided into two catego-
ries. The first category is damage to surfaces or subsystems. The second category
is the effect on operations.

A = Mir photo studies

B = Haystack

C = Haystack Auxiliary (HAX)

D = Liquid Mirror Telescope (LMT)

E = CCD Debris Telescope (CDT)

F = Space Surveillance Network (SSN)

(United States)

G = Goldstone

H = Ground Electro-Optical Deep Space

Surveillance System (GEODSS)

K = Arecibo

L = Research Establishment for Applied

Science (FGAN) Germany

Diameter

(cm)

Figure IV.

Coverage of ranges of debris diameter and period of exposure:

ground-based data, 1980-1998

(a)

Damage to surface or subsystems

57.

Examples of damage that affect the surface of operational systems are:

(a)

Damage to shuttle windows;

(b)

Damage to HST high gain antenna;

(c)

Severing of the Small Expendable Deployer System-2 (SEDS-2) tether;

(d)

Damage to other exposed shuttle surfaces.

In the damage described in subparagraphs (a), (b) and (d) above, there is clear
evidence of damage due to space debris. In subparagraph (c), it is unclear whether
the damage is caused by man-made debris or a micrometeoroid.

(b)

Effects of space debris on human space operations

58.

In order to protect crews from debris during flight, operational procedures

have been adopted. In the case of the Space Shuttle, the orbiter is often oriented
during flight, with the tail pointed in the direction of the velocity vector. This flight
orientation was adopted to protect the crew and sensitive orbiter systems from
damage caused by collisions with small debris.

59.

Operational restrictions have also been adopted for extravehicular activities

(EVAs). Whenever possible, EVAs are conducted in such a way as to ensure that
the EVA crew is shielded from debris by the orbiter.

Other effects of space debris

60.

Astronomers are observing during wide field imaging an increasing number

of trails per plate caused by space debris. These trails degrade the quality of the
observation. Space debris trailing will entirely negate a photometric observation
when debris cross the narrow photometric field.

II. Modelling of the space debris environment

and risk assessment

Modelling of the space debris environment

Introduction and methodology

61.

Space debris models provide a mathematical description of the distribution of

objects in space, the movement and flux of objects and the physical characteristics
of objects (e.g. size, mass, density, reflection properties and intrinsic motion).
These models can be deterministic in nature (i.e. each object is described individu-
ally by its orbital parameters and physical characteristics), statistical in type (i.e.
characterization of an ensemble by a sample number of objects) or a combination
(i.e. hybrid). These models can be applied to risk and damage assessments, predic-
tion of debris detection rates for ground-based sensors, prediction of avoidance
manoeuvres of operational spacecraft and long-term analysis of the effectiveness of
debris mitigation measures.

62.

Space debris models must consider the contribution to the population of

orbiting objects of the following source mechanisms:

(a)

Launches (including launch vehicle upper stages, payloads and mission-

related objects);

(b)

Manoeuvres (to account for solid rocket motor firings);

(c)

Break-ups (produced by explosions and collisions);

(d)

Material separation from surfaces (ageing effects, e.g. paint flakes);

(e)

Material due to leakage (e.g. nuclear power source (NPS) coolant).

63.

The following sink mechanisms must also be considered:

(a)

Orbital decay due to atmospheric drag or other perturbations;

(b)

Retrievals from orbit;

(c)

Deorbiting;

(d)

Fragmentation (leading to a loss of large objects).

A debris environment model must contain all or some of these elements.

64.

Space debris models make use of available data sources. These include:

(a)

Deterministic data on decimetre-sized and larger objects within the

United States Space Command Satellite catalogue and the Russian Space Surveil-
lance catalogue (see figure V for the related spatial density distribution);

(b)

Statistical data on centimetre-sized objects derived from dedicated radar

campaigns in LEO;

(c)

Statistical data on encountered submillimetre debris populations in-

ferred from analysis of retrieved surfaces and from in situ impact sensors;

(d)

Statistical data on decimetre and larger objects in LEO using ground-

based telescopes;

(e)

Ground-based simulations of hypervelocity collisions with satellite and

rocket bodies;

(f)

Ground-based simulations of explosive fragmentations.

-16

-15

-14

-13

-12

-11

-10

-9

-8

-7

-8

-9

-10

Spatial density (number/km

)

10 000

20 000

30 000

40 000

50 000

Altitude (km)

1 000

500

1 500 2 000

Figure V.

Spatial density of catalogued objects (as at 21 August 1997)

65.

These models are limited by the sparse amount of data available to validate

the derived relationships. The models must rely upon historical records of satellite
characteristics, launch activity and in-orbit break-ups; in addition, there are only
limited data on spacecraft material response to impact and exposure to the orbital
environment. Furthermore, major assumptions must be made in applying these
models to predict the future environment. In particular, future traffic scenarios and
the application of mitigation measures will have a major influence on the outcome
of model predictions. Space debris models must be continually updated and vali-
dated to reflect improvements in the detail and size of observational and experi-
mental data sets.

66.

Environment models may take two forms: as discrete models, which repre-

sent the debris population in a detailed format, or as an engineering approximation.
Furthermore, these models can be short term in nature (considering time-frames of
up to 10 years) or long term (considering time-frames of over 10 years). In the
preparation of all these models, the initial debris population is represented at a
particular starting epoch and propagated forward in time in a stepwise manner,
taking account of source and sink mechanisms and relevant orbit perturbations.
Neither the short-term nor the long-term models account for the periodic concen-
trations of debris that exist hours to months following a break-up; such “very short-
term” models are occasionally used to assess the hazard to specific space systems
but are not discussed below.

67.

The pertinent characteristics of the models are compared in table 4.

Table 4.

Debris environment models

Engineering

Evolutionary

model

Minimum

Orbital

Model name

Source

period

available

size

regime

CHAIN

NASA

Long term

1 cm

LEO

CHAINEE

ESA

Long term

1 cm

LEO

EVOLVE

NASA

Short and

1 mm

LEO

long term

IDES

DERA

Short and

0.01 mm

LEO

long term

LUCA

TUBS

Long term

1 mm

LEO/MEO

MASTER

ESA

Short term

Yes

0.1 mm

LEO/GEO

Nazarenko

RSA

Short and

0.6 mm

LEO

long term

ORDEM96

NASA

Short term

Yes

1 µm

LEO

SDM/STAT

ESA/

Short and

LEO/GEO

CNUCE

long term

Short-term models

68.

The following short-term models are available in the scientific and engineer-

ing community:

(a)

EVOLVE was developed by the NASA Johnson Space Center to provide

both short-term and long-term forecasts of the LEO environment with excessive
source terms and detailed traffic models, based on quasi-deterministic population
propagation techniques that are suitable for both LEO and GEO modelling;

(b)

ORDEM96 is a semi-empirical engineering model developed by the

NASA Johnson Space Center. It is based upon extensive remote and in situ obser-
vations and is used to support United States Space Shuttle and International Space
Station design and operations;

(c)

MASTER is an ESA semi-deterministic environment model based on

3-D discretization of spatial densities and transient velocities. The model is appli-
cable to altitudes from LEO to GEO, providing environment estimates in the short
term. A less detailed version of MASTER is available as an engineering format.
Both models were developed by the Technical University of Braunschweig under
ESA contract;

(d)

IDES is a semi-deterministic model of the environment using detailed

historical and future traffic models to provide short-term and long-term predictions
of the space debris environment and the collision flux it presents to specific
satellites. The model was developed by the Defence Evaluation and Research
Agency (DERA), Farnborough, United Kingdom;

(e)

Nazarenko, a model developed by the Centre for Programme Studies

(CPS) of RSA, is a semi-analytic, stochastic model for both short-term and long-
term prediction of the LEO debris environment, providing spatial density, velocity
distributions and particle fluxes. The model takes account, in average form, of
debris sources (except for the cascading effect) and of atmospheric drag; it has
been adjusted on the basis of Russian and American catalogue data and published
measurements of somewhat smaller fragments (more than 1 mm), while also taking
account of a priori information;

(f)

SDM is a semi-deterministic model to provide both short-term and long-

term predictions of the space debris environment. The code, developed at CNUCE,
makes use of a detailed traffic model, including satellite constellations, and con-
siders several source model options for explosions, collisions and RORSAT leaks.
SDM has been developed under ESA and ASI contracts.

69.

These models can be used to “predict” the current environment. Several

different models have been used to develop “envelopes of solution” for the current
environment, as shown in figure VI.

Long-term models

70.

The scope of the long-term modelling of the space debris environment is the

long-term (up to 100-year) prediction of the number of objects as a function of
time, of altitude, of inclination and of object size. These projections are important
for assessing the necessity and the effectiveness of debris mitigation techniques and
the impact of new space activity.

71.

In addition to the sources of space debris that are considered in the modelling

of the current debris population, it is necessary to take into account collisions
among larger objects (>10 cm). Currently, collisions among larger objects do not
play a significant role in the increase of the number of objects, since their prob-
abilities are low. However, in the future, the interactive risk for so-called destruc-
tive collisions, i.e. collisions that generate larger fragments, may increase. This
so-called interactive collision risk among all objects of the population is propor-
tional to the square of the number of objects. Hence, in the future, long-term
mitigation option evaluation should focus on the removal of mass and cross-section
from orbit.

72.

In order to assess the consequences of collisions among larger objects, it is

necessary to have reliable break-up models for collisions of this type. However, it
is very difficult to simulate on-orbit collisions without having test data for valida-
tion purposes available. Hence, a certain degree of uncertainty is introduced into
the models by the collision simulation.

73.

Other than the modelling of the present debris population, the long-term

modelling requires assumptions describing the future space flight activities, includ-
ing the debris generation mechanisms, in terms of, for example:

(a)

Future number of launches and related orbits;

(b)

Future number and size of payloads per launch;

-3

-4

-5

-6

-7

-8

-9

-10

200

400

600

800

1 000 1 200 1 400 1 600 1 800 2 000

Spatial density (number/km

)

Altitude (km)

욷

1 mm

욷

1 cm

욷

10 cm

Figure VI.

Model values for current spatial density

Sources:

NASA (ORDEM96); DERA (IDES); ESA (MASTER); CNUCE (SDM); and NAZARENKO

(c)

Future number of mission-related objects (fairing, bolts etc.);

(d)

Future number of explosions of spacecraft and upper stages;

(e)

New uses of space (e.g. commercial LEO communications satellite

constellations).

74.

All of these parameters are subject to variations with time due to technical/

scientific, financial and political aspects. Hence, some uncertainties are added to
those uncertainties that are due to the mathematical model itself (break-up models
etc.).

75.

A number of models have been developed for the purpose of long-term

modelling of the debris environment. They can be characterized briefly as
follows:

(a)

CHAIN and CHAINEE. CHAIN was developed by the Technical Uni-

versity of Braunschweig under contract. Since 1993, this model has been main-
tained and improved by NASA. CHAINEE, the European extension of CHAlN, is
used by ESA. The model, an analytical “particle-in-a-box” model, describes the
population and the collision fragments up to an altitude of 2,000 km using four
altitude bins in LEO and five mass classes. CHAIN and CHAINEE are extremely
fast computer codes. They enable the identification of relative trends associated
with specific mitigation policies. The resolution of CHAIN is limited due to the
binning used;

(b)

EVOLVE. The EVOLVE model has been developed by NASA. It is a

semi-deterministic model (SDM), i.e. debris objects are described individually by
a set of parameters. In addition to being capable of modelling the present debris
environment, it can be used to investigate future evolutionary characteristics under
various mitigation practices using Monte Carlo techniques. For this purpose mis-
sion model data are used;

(c)

IDES. The IDES model was developed at the Space Department of

DERA. Historical sources such as launches, break-ups and paint flakes are simu-
lated and evolved to generate the current debris environment. This is used as the
initial conditions, together with a detailed mission model, to simulate the future
evolution of the debris environment. IDES can be used to study the collision
interactions of multiple LEO satellite constellations and the effectiveness of debris
mitigation measures;

(d)

LUCA. For the detailed analysis of future scenarios, especially if a high

resolution concerning the orbital altitude and the declination is required, the semi-
deterministic computer code LUCA has been developed at the Technical Univer-
sity of Braunschweig. This code combines the advantages of a high spatial reso-
lution and of a tolerable computer time need. In order to calculate the
time-dependent collision risk, a special tool has been implemented. This tool re-
flects the increased collision risks at higher declinations (e.g. close to the polar
regions);

(e)

SDM/STAT. The semi-deterministic model (SDM) and the stochastic

approach (STAT) use the same initial population, as provided by a computer

model, and the same source and sink assumptions, including collisions. In SDM,
orbits of a representative subset of the population are used to map the population
forward in time; by means of parametric studies, effects of launch policies and
mitigation measures can be analysed. STAT is a computer time-efficient “particle-
in-a-box” alternative to SDM. It is based on a system of coupled differential
equations for the populations of 80,000 bins in mass, semi-major axis and eccen-
tricity. The two codes can be compared and given similar results;

(f)

Dual-size particle-in-a-box. These are two models with the ability to

handle LEO constellations;

(g)

Nazarenko. The Nazarenko model, developed by CPS (Russian Federa-

tion), is a semi-analytic, stochastic model for both short-term and long-term pre-
dictions of the LEO environment, providing spatial density, velocity distributions
and collision risk assessment. The model is based on Russian and United States
catalogue data and on published data on small space debris (>1 mm). The model
uses the same initial population, based on the satellite catalogues and an averaged
space debris source. Source characteristics are based on the historical analysis of
space debris contamination. Forecasting is performed by integrating the partial
differential equations for the space debris distribution as a function of altitude.
Atmospheric drag, distribution of ballistic coefficients and orbit eccentricity are
taken into account in the orbit propagation.

76.

Due to the assumptions and limitations of the models described above, the

findings do not fully agree with each other. However, the long-term debris model
trends can be summarized as follows:

(a)

The debris population may grow in an accelerated manner in the future

if space flight is performed as in the past. This is because of the collisions that will
occur given the increased mass on orbit;

(b)

Currently depending on size, fragments from explosions are the main

source of space debris. Without some mitigation, collision fragments may become
one of the main debris sources in the twenty-first century;

(c)

Collisional fragments may contribute to the number of subsequent col-

lisions. This means that, at some point in the future, which is difficult to predict,
the population could grow exponentially. Only by limiting the accumulation of
mass in LEO can this be prevented;

(d)

Suppressing explosions can reduce the increase in the number of objects

in orbit, but cannot prevent collisions, which are driven by the total mass in orbit
and the number of large objects.

77.

The results of the long-term debris models do not agree quantitatively

because of differences in assumptions and initial conditions. However, the basic
trends and tendencies obtained by the models agree qualitatively. The number of
major collisions predicted by several models (EVOLVE, CHAIN, CHAINEE and
IDES) are presented as envelopes of predictions in figure VII. The number of
fragments generated by future sources is less consistently predicted for small
fragments.

78.

The collision probabilities among the larger objects are initially low. Hence,

it is essential to analyse a number of single Monte Carlo runs or to use mean value
approaches in order to obtain reliable trends and tendencies. The above models
take care of that effect.

Space debris risk assessments

Introduction

79.

Risk assessments include the probability of an event, as well as its subse-

quent consequences. With the assistance of models of the space debris environ-
ment, the risk of collision among operational spacecraft and space debris can be
evaluated. Spacecraft in LEO are routinely bombarded by very small particles
(<100 µm) because of the large number of such debris, but the effects are normally
slight due to the small masses and energies involved. Because of the smaller popu-
lation of large debris objects, the likelihood of collision decreases rapidly as the
size of the debris increases. However, the severity of collisions between large
objects increases.

Note

: The results of the long-term debris models do not agree quantitatively because of differences in

assumptions and initial conditions. However, the basic trends and tendencies obtained by the models agree

qualitatively. With the continued implementation of debris mitigation measures, the business as usual

scenario could be avoided (see figure IX).

1995

2005

2015

2025

2035

2045

2055

2065

2075

2085 2095

Cumulative number of major collisions

Year

A = Business as usual

B = Business as usual for the next 20 years; then no more launches

C = No future launches

Figure VII.

Typical ranges for number of major collisions

for three scenarios, 1995-2095

80.

The principal risk factors are the spatial density and average relative

collisional velocity along the orbit (altitude and inclination) of the space object of
interest, the cross-sectional area of the space object and the duration of the flight.
The consequences of a collision will depend upon the respective masses and com-
positions of the objects involved. Whereas the collision risk between an orbiting
object and a meteoroid is essentially independent of altitude, the probability of
collision between orbital objects is strongly related to altitude, in general being an
order of magnitude higher in LEO than in GEO.

Collision risk assessments in low Earth orbit

(a)

Methodology

81.

Risk assessments have been routinely performed on LEO spacecraft since the

1960s. The Poisson model is used in cases where there is a large number of
independent events and each event has a small probability of occurring. Man-made
debris and micrometeoroids meet these criteria for independence, except in cases
of a recent break-up or a meteor storm.

82.

To compute the probability of an impact from space debris requires a

meteoroid/space debris (M/OD) environment model, a spacecraft configuration and
a mission profile. To compute the probability of a penetration and/or a failure
due to space debris requires detailed knowledge of the spacecraft configuration,
including:

(a)

The geometry of critical subsystems;

(b)

The penetration resistance or ballistic limit equation of each subsystem;

(c)

Data on the ability of each subsystem to tolerate damage.

83.

Based on this information, computer codes can calculate:

(a)

The probability of impacts for a particle of a given size;

(b)

The probability of impact damage to any given subsystem;

(c)

The split between damage from space debris and micrometeoroids.

(b)

Results of risk assessments

84.

Risk assessments in LEO are routinely utilized to enhance the safety of space

operation. In cases involving human space flight, risk assessments have proved
invaluable in ensuring the safety of shuttle operations. Shuttle missions are opera-
tionally reconfigured whenever a pre-flight risk assessment indicates that the risks
of space debris are at an unacceptable level.

85.

Risk assessments are being utilized to design the location and type of space

debris shielding that will protect the crew as well as the crucial subsystems on the
International Space Station.

86.

Risk assessments are also utilized in the design of unmanned spacecraft.

They aid in the placement and protective shielding design of critical subsystems
and components, as well as in the system design of large communication satellite
constellations. An example of risk assessment at LEO is given in table 5.

Table 5.

Mean time between impacts on a satellite with a cross-section area

of 10 square metres

Height of circular orbit

Objects 0.1-1.0 cm

Objects 1-10 cm

Objects >10 cm

500 km

10-100 years

3,500-7,000 years

150,000 years

1,000 km

3-30 years

700-1,400 years

20,000 years

1,500 km

7-70 years

1,000-2,000 years

30,000 years

Collision risk assessments in geostationary orbit

87.

Currently, the population of space objects in and near the GEO region (see

figure VIII) is well known for only spacecraft and upper stages. The limited
number of these objects, their wide spatial distribution and the lower average
relative velocities (500 m/sec) combine to produce a substantially lower probability
of collision in GEO. Moreover, as more spacecraft and upper stages are left
in orbits above or below GEO, the number of uncontrolled intact objects intersect-
ing the GEO region is increasing at a very slow rate. Special collision possibilities
exist in GEO because of the close proximity of operational spacecraft at selected
longitudes, but these collision hazards can be eliminated by spacecraft control pro-
cedures. The limited number of large objects near GEO also permits the prediction
of close approaches between operational spacecraft and tracked space debris in
sufficient time to conduct an evasive manoeuvre.

88.

The number of space debris of less than 1 m in diameter near GEO is not

well known. Two break-ups (one a spacecraft and one an upper stage) have been
identified, and some evidence suggests that additional break-ups may have oc-
curred. Such debris would be perturbed into new orbits, possibly reducing the
residence time in GEO but increasing the relative collision velocity, making the
flux contribution nearly constant with inclination change. In many cases debris
fragments would be widely dispersed in both altitude and inclination. Additional
space debris measurements in GEO are needed before more accurate risk assess-
ments can be performed. Also, new techniques to predict collision probability may
need to be developed to take into accounyt the non-random nature of close ap-
proaches in GEO.

89.

There is no natural removal mechanism for satellites in GEO. Therefore,

operational spacecraft are at risk of being damaged by uncontrolled spacecraft.
This annual collision probability for an average operational satellite with other
catalogued objects is currently estimated at 10

-5

Risk assessments for re-entering space debris

90.

The risk assessment discussed here is limited to uncontrolled re-entry from

Earth orbit.

91.

There have been more than 16,000 known re-entries of catalogued space

objects in almost 40 years. No significant damage or injury has been reported. In
large measure this can be attributed to the large expanse of ocean surface and the
sparse population density in many land regions. In the past five years, approxi-
mately once each week, an object with a cross-section of 1 m

or more has re-

entered Earth’s atmosphere and some fragments have been known to survive.

92.

The risk of re-entry is not only from mechanical impact, but also from chemi-

cal or radiological contamination to the environment. Mechanical damage will
be caused by objects surviving aerodynamic heating. This risk will depend on
the characteristics of the final orbit, the shape of the object and its material
properties.

Figure VIII.

Payloads and upper stages launched into geostationary orbit,

1963-1996

Number of objects

Launch year

1 1 1

6 6

Upper stages

Payloads

1963

1965

1967

1969

1971

1973

1975

1977

1979

1981

1983

1985

1987

1989

1991

1993

1995

III.

Space debris mitigation measures

Reduction of the debris increase in time

Avoidance of debris generated under normal operation

(a)

Mission-related objects

95.

Approximately 12 per cent of the present catalogued space debris population

consists of objects discarded during normal satellite deployment and operations.
Typical objects in this category are fasteners, yaw and yo-yo weights, nozzle cov-
ers, lens caps, multiple payload mechanisms and so forth. It is normally relatively
easy, both technically and economically, to take mitigation measures against these
objects. Many agencies are reported to have taken such action. For example, clamp
bands and sensor covers should be retained by parent bodies, and all fragments of
explosive bolts should be captured. However, there may be some parts that will be
released for unavoidable reasons, such as a structural element left in geostationary
transfer orbit (GTO) during a multiple payload mission. Every agency is encour-
aged to minimize these kinds of debris whenever possible using state-of-the-art
equipment or techniques.

(b)

Tethers

96.

Tethers may become space debris if they are discarded after use or if they are

severed by an impacting object (man-made debris or meteoroid). Tethers several
thousand metres in length and a few millimetres in diameter might not survive for
extended periods. New multi-strand tether designs can reduce the risk of being
severed. At the end of missions, tethers may be retracted to reduce the possibility
of collision with other objects or both end masses may be released to accelerate the
orbital decay of the tether.

(c)

Solid rocket motor effluents, paint and other exterior materials

97.

Other mission-related particles may be generated unintentionally, as in the

release of slag (up to several centimetres in diameter) during and after the burn of
solid rocket motors. The precise nature of the amount and distribution of these slag
ejecta are unclear, and the improvement of solid propellant and motor insulation to
minimize the released solids is difficult. Attempts should be made to inhibit the
generation of very small debris caused by the effects of the space environment, for
example, atomic oxygen erosion, solar radiation effects and the bombardment of
small meteoroids. The application of more long-lasting paint and protective cover-
ing could be an effective remedial measure.

Prevention of on-orbit break-ups

98.

The consequences of fragmentations of upper stages and spacecraft constitute

approximately 43 per cent of the current identified satellite population and may
account for as much as 85 per cent of all space debris larger than 5 cm in diameter.
At least 153 space objects, with a total dry mass of more than 385,000 kg, are
known to have broken up in Earth orbit as at 1 September 1998. Fortunately, 60 per
cent of the catalogued debris generated in those events have fallen back to Earth.
Such fragmentations are primarily caused by explosions and to a much lesser
extent by collisions.

(a)

On-orbit explosions

99.

Thirty-six per cent of all resident space object break-ups are upper stages or

their components that operated successfully but were abandoned after the space-
craft delivery mission was completed. Such incidents have affected a wide range
of launch vehicles operated by the United States, the Russian Federation, China
and ESA. Accidental explosions can also be caused by malfunctioning propulsion
systems, overcharged batteries or explosive charges. Intentional break-ups have
also been conducted.

100.

Analyses of accidental fragmentations for both spacecraft and upper stages

have shown that vehicle deorbiting or passivation, i.e. the removal of all forms of
stored energy, would eliminate most such events. Effective measures include the
expulsion of residual propellants by burning or venting, the discharge of batteries,
the release of pressurized fluids, thermal control and safing of unused destruct
devices and the unloading (despinning) of momentum wheels and similar attitude
control apparatus. These measures should be performed soon after the vehicle has
completed its mission.

(b)

On-orbit collisions

101.

The probability of an accidental collision in Earth orbit is currently slight,

but it is becoming greater as the number and size of satellites are increasing. There
has been only one proven case of an accidental collision between two catalogued
objects. In 1996, the French CERISE spacecraft was struck and partially disabled
by the impact of a fragment which, according to the United States Space Command
monitoring network, came from an exploded Ariane upper stage. In addition, the
possibility of other break-ups being caused by collision cannot be denied because
the causes of many break-up events remain unknown. Effective measures to miti-
gate the consequences of break-ups caused by collision include the spacecraft
design, selection of an orbit where the probability of collision is low, and collision
avoidance manoeuvres (see paragraphs 113-119 below).

Deorbiting and reorbiting of space objects

(a)

Mission termination of space systems

102.

For space objects in LEO reaching end of mission, deorbiting or placing the

vehicle in a reduced lifetime orbit will significantly reduce the possibility of an
accidental collision. Studies have shown that the growth of space debris can be
mitigated by limiting orbital lifetimes. This may be done with a controlled re-entry
manoeuvre or by transferring the vehicle to a lower altitude.

103.

For space objects at higher altitudes, moving vehicles into disposal orbits

can also be effective for the foreseeable future. For example, the transfer of geo-
stationary orbit spacecraft to orbits above GEO not only protects operational space-
craft but also reduces the probability of derelict objects colliding with one another
and creating debris that might threaten the GEO regime. A standardized minimum
reorbit distance value should be determined by taking into consideration factors
such as perturbation effects by the gravitational force of the Sun and the Moon and
solar radiation pressure. To plan and conduct both deorbit and reorbit manoeuvres,
technical research and development is required, to measure the residual propellant
more precisely for example. The upper stages or components of launch vehicles
left in GTO may be manoeuvred to prevent interference with systems in GEO. The
perigee altitude of the upper stage could be selected to ensure a limited orbital
lifetime.

(b)

In case of failure

104.

Space systems on orbit should be routinely monitored especially for critical

malfunctions that could lead to the generation of large amounts of fragments or to
loss of the ability to conduct mitigation measures. The propulsion system, batteries
and the attitude and orbit control subsystem should be monitored in that context.
If a malfunction occurs and the mission cannot be maintained, procedures should
be implemented to preclude accidental explosion and to prevent as much as pos-
sible interference with useful orbits.

Protection strategies

105.

Given the current space debris population, spacecraft designers should con-

sider incorporating implicit and explicit protection concepts into their space vehi-
cles. A hazard for space objects and orbital stations is posed by hypervelocity
impact with meteoroids and space debris particles 1-2 mm or larger. High-velocity
impacts by particles as small as 1 mm in diameter could potentially lead to a loss
of function or mission failure if they were to hit a particularly vulnerable part of
the satellite. Even small impacts on pressure vessels may result in container rup-
tures. Such damage may also prevent planned passivation measures or post-mission

disposal options. In many cases, the relocation of vulnerable components can
greatly increase spacecraft survivability. Prudent selection of the orbital regime and
collision avoidance are other potential protection strategies.

Shielding

106.

Space debris shields for both manned and unmanned spacecraft can be quite

effective against small particles. Protection against particles 0.1-1 cm in size can
be achieved by shielding spacecraft structures. All objects 1-10 cm in size cannot
currently be dealt with by on-orbit shielding technology, nor can they be routinely
tracked by operational surveillance networks. However, protection against particles
1-10 cm in size can be achieved through special features in the design of space
systems (redundant subsystems, frangible structures, pressure vessel isolation capa-
bilities, maximum physical separation of redundant components and paths of elec-
trical and fluid lines etc.). Physical protection against particles larger than 10 cm
is not yet technically feasible.

107.

Shielding designs may vary from simple single sheet Whipple bumpers,

located in front of the spacecraft wall, to complex layers of metal and ceramic/
polymer fabrics that are designed first to break up the impacting particle and then
to absorb the energy of the resulting ejecta. Bumper shields should be positioned
at sufficient distance from the shielded object to ensure a wide dispersion of the
fragment cloud, created as a result of the impact of the debris particles on the
shield. Thus, the impact loads should be distributed over a considerable area of the
protected object’s body. Successful shield designs may take advantage of the struc-
ture of the vehicle and the directionality of space debris to protect critical com-
ponents. In addition, spacecraft can be designed to place critical components in the
geometric shadow of the prevailing direction of debris flux. The application of
lightweight, multilayer insulation may provide protection against small debris, and
the placement of sensitive equipment behind existing vehicle structures may also
improve survivability.

108.

The penetration depth, or damage potential, of an impacting object depends

on its mass, density, velocity and shape and on the material properties of the shield.
Different modelling and simulation tools are available to predict the damage result-
ing from impacts on various shield designs (e.g. the NASA BUMPER model, the
ESA ESABASE model, the Russian BUFFER and COLLO models and several
hydrocodes to perform simulations under conditions not possible using ground-
based test facilities). Ground-based tests of spacecraft shields are limited, as testing
for the entire range of possible impact velocities is not possible. Ground-based
accelerators are currently limited to velocities of the order of 13 km/s (e.g. using
shaped charge devices), but most existing data are for 7 km/s. New methods are
being developed and further refined for calculating the processes involved in
hypervelocity collisions between space debris particles and shields at impact ve-
locities of 5-15 km/s.

(a)

Human space flight

109.

Manned spacecraft, particularly space stations, are normally larger than

most unmanned vehicles and must demonstrate higher safety standards. Protection
strategies for manned missions can incorporate both shielding measures and
on-orbit repair of damage caused by penetrations. Current shield designs offer
protection against objects smaller than 1 cm. Since it is impossible to protect
completely from even debris smaller than 1 cm, in some cases, the probability of
no penetration (PNP) is the main criterion for shield design. PNP calculations are
based on meteoroid and debris environment models and on the ballistic limit curves
obtained in hydrocode simulations and hypervelocity impact experiments. The
reliability of the PNP calculations is strongly linked to the accuracy of the debris
and meteoroid environment model and from the structural point of view on the
ballistic limit curves. The degree of shielding required is highly dependent upon
the nature (material, thickness etc.), location and orientation of the surface to be
protected. Consequently, the International Space Station will employ over 200
different types of space debris and micrometeoroid shields.

110.

On manned spacecraft it is possible to install automatic detection systems

to locate damage. In case of a puncture of a pressurized module, isolation of the
module or reaction time in sealing the puncture is of primary importance. The
amount of time available depends on the size of the puncture, and the time required
for repair is a function of the means employed and the strategy adopted.

111.

Crew members engaged in extravehicular activities (EVA) need protection

from natural and man-made debris. Current spacesuits have many features with
inherent shielding qualities to offer protection from objects of sizes up to 0.1 mm.
By properly orienting their spacecraft, astronauts may be able to use their vehicles
as shields against the majority of space debris or direct meteoroid streams. In
particular, such measures have already been undertaken on the Mir Space Station.

(b)

Unmanned spacecraft

112.

For unmanned spacecraft, lower PNPs are tolerable. An acceptable level of

protection against small debris and meteoroid objects (smaller than 1 mm) may be
attained through the use of reinforced multilayer insulation materials and via de-
sign modifications, such as internal installation of fuel lines, cables and other
sensitive components (for example, as implemented by RADARSAT of Canada).
Solar array designs can minimize the effects of damage from collisions with small
particles by using designs that have multiple electrical paths and that minimize
structural mass, i.e. frangible configurations.

Collision avoidance

113.

Current space surveillance systems do not reliably track objects in LEO

with a radar cross-section of less than 10 cm in equivalent diameter. In addition,

it is difficult to maintain orbital parameters on small catalogue objects due to
factors such as a high area-to-mass ratio and, consequently, a higher susceptibility
to atmospheric density variations. For space objects large enough to be tracked by
ground-based space surveillance systems, collision avoidance during orbital inser-
tion and on-orbit operations is technically possible.

114.

Collision avoidance manoeuvres impact satellite operations in several ways

(e.g. propellant consumption, payload data and service interruptions, and tempo-
rary reduction in tracking and orbit determination accuracy), and they should be
minimized, consistent with spacecraft safety and mission objectives. Collision
avoidance strategies are most effective when the uncertainty in the close approach
distance is kept small, preferably less than 1 km. Collision avoidance is always
probabilistic. NASA uses an acceptable risk criterion of 1 in 100,000 as a chance
of collision.

(a)

On orbit

115.

The United States Space Surveillance Network (SSN) and the Russian

Space Surveillance System (SSS) monitor the LEO environment to warn crewed
spacecraft if an object is projected to come within a few kilometres. For example,
if an object is predicted to pass through a box measuring 5 km x 25 km x 5 km
oriented along the flight path of the United States Space Shuttle, the SSN sensor
network intensifies its tracking of the potential risk object. If the improved fly-by
prediction indicates a conjunction within a box measuring 2 km x 5 km x 2 km,
an avoidance manoeuvre may be performed. During the period 1986-1997, the
United States Space Shuttle executed four such evasive manoeuvres. The Russian
SSS and the Russian Space Agency perform similar collision avoidance assess-
ments for the Mir space station.

116.

Russian specialists have compiled a catalogue of dangerous approaches to

space objects (several million approaches) and an algorithm for deciding whether
to proceed with an avoidance manoeuvre. It is proposed to identify hazardous
situations involving the predicted approach of space debris to intensify data cov-
erage of such events and to control the flight of the spacecraft requiring protection.
Work is under way to establish a special telecommunication system linking RSA
management with the mission control centre in Korolev, Russian SSS and other
space observation facilities.

117.

ESA and CNES are using orbit determinations of their LEO spacecraft to

forecast conjunction events and to initiate evasive manoeuvres if certain fly-by
range limits or estimated collision risk levels are violated. For an acceptable risk
criterion of 1 in 10,000 as a chance of collision, the ERS-1 and ERS-2 spacecraft
of ESA would need to perform one or two manoeuvres each year. Collision avoid-
ance manoeuvres were performed by the ESA satellite ERS-1 in June 1997 and
March 1998 and by the CNES satellite SPOT-2 in July 1997.

118.

As more spacecraft are launched into the GEO region, coordinated station-

keeping is becoming increasingly beneficial. Inclination and eccentricity vector
separation strategies can be efficiently employed to keep co-located GEO space-
craft at safe distances. Eccentricity vector control may also be employed to reduce
the risk of collision between members of a given LEO satellite constellation.

(b)

Launch

119.

Calculations made prior to the launch of United States spacecraft permit the

establishment of safe launch windows, ensuring that the spacecraft will not pass
near resident manned spacecraft (i.e. Space Shuttle, Mir or the International Space
Station). For the Space Shuttle, similar alert procedures are used as for the on-orbit
conjunction analysis. In the case of a predicted conjunction, the launch is delayed;
to date two Space Shuttle launches have been delayed to avoid potential collisions.

Effectiveness of debris mitigation measures

120.

Probably one of the most important mitigation measures has been the in-

creased awareness of the threats posed by the space debris environment and of the
many sources of space debris. Incorporation of debris mitigation measures early in
the vehicle design phase could be cost-effective. Educational efforts among the
aerospace industries and national space agencies have reaped the rewards of
voluntary action, guided by the principles of good stewardship of near-Earth space.

121.

Since the early 1980s, the adoption of mitigation measures has had an effect

on the growth of the space debris environment. The frequency of significant
satellite fragmentations, both accidental and intentional, has dropped, moderating
the rate of growth of space debris. For long-lived mission-related debris even a
decrease is noticeable. New debris shield technologies and designs have substan-
tially reduced the weight of protection while increasing its effectiveness.

122.

The aerospace community is working to illustrate the effectiveness and cost

of typical mitigation scenarios. Long-term environment simulation models are
useful in such work. The models cannot provide accurate predictions of the space
environment several decades into the future, but they can evaluate the relative
influences of different operational practices.

Scenarios of mitigation measures

123.

Mission-related objects, satellite fragmentations and end-of-mission dis-

posal practices are important factors in the potential growth of the space debris
population. The five typical mitigation scenarios for all space missions presented
below show the potential effectiveness of mitigation measures; they are not

intended to be prescriptive in nature and should be used only for simulation pur-
poses. The scenarios are the following:

(a)

Reference scenario with current mitigation measures;

(b)

Elimination of mission-related objects;

(c)

Universal passivation at end of mission;

(d)

Universal disposal at end of mission for GEO;

(e)

Deorbiting at end of LEO and GTO mission: this includes both lowering

the orbit to reduce the satellite lifetime (e.g. to less than 25 years) and immediate
re-entry.

124.

The greatest near-term benefit, as initial studies have shown, can be gained

by the elimination of accidental explosions of spacecraft and upper stages. Such
break-ups are best controlled by the passivation of the vehicles at the end of
mission, as demonstrated by many spacecraft and launch vehicle operators. Elimi-
nation of accidental explosions alone will not prevent an increase in debris at
higher altitudes in LEO.

125.

In the long term, the accumulation of objects in orbit may pose a significant

increase of the threat to space operations in both low and high altitude regimes.
Without remediation of the debris environment or operational changes, the growing
number and total cross-section of resident space objects would increase the likeli-
hood of collisions, which in turn could generate new debris. Placing LEO and GTO
spacecraft into disposal orbits with limited orbital lifetime (e.g. 25 years or less)
may have a particular effect on curbing the growth of the debris population with
the condition of elimination of mission-related debris generated before mission
termination. Figure IX illustrates the total population of debris particles larger than
1 cm in LEO for a number of scenarios.

Cost or other impact of mitigation measures

126.

Debris mitigation measures can affect the design and cost of spacecraft and

launch vehicles as well as their operations.

(a)

System development cost

127.

Modifying the designs of spacecraft and launch vehicles to implement miti-

gation measures generally adds to the system development cost. However, allowing
for mitigation measures early in the design process is more cost-effective than
modifying a design later. Although increased vehicle complexity may arise, some
mitigation measures may lead to simpler designs as well as weight savings.

(b)

Launch performance and mass penalty

128.

Providing for the upper stages of launch vehicles to re-enter the atmosphere

directly or to have a short orbital lifetime may influence launch trajectory and
performance. Likewise, any weight added to the launch vehicle or the spacecraft
to meet mitigation objectives lowers the useful payload capacity. Additional
propellant or electrical power resources may be needed. The magnitude of these
consequences will vary depending upon the mitigation measure selected and the
vehicle.

(c)

Mission lifetime

129.

For a given design, implementing disposal or deorbiting strategies may

reduce the active mission lifetime. Many GEO spacecraft operators have accepted
this penalty in order to preserve their orbital regimes. If the penalty is considered

Figure IX.

Trends in population of space debris particles larger than

1 centimetre in low Earth orbit for different scenarios, 2000-2200

Relative number of objects larger than 1 cm

Historical launch and explosion rate, plus constellations; no mitigation

Historical launch rate, plus constellations; stop explosions after 2010

Historical launch rate, plus constellations; stop explosions and

deorbiting of upper stages in LEO, after 2010

Historical launch rate, plus constellations; stop explosions,

deorbiting of upper stages in LEO, after 2010, and deorbiting of

spacecraft at end of life (in LEO), after 2030

2000

2200

2150

2100

2050

Year

Note:

The curve for the mitigation case is not likely to occur, provided suitable mitigation measures

are taken.

IV.

Summary

131.

During its multi-year investigation of the space debris topic, the Scientific

and Technical Subcommittee of the Committee on the Peaceful Uses of Outer
Space has examined: (a) the state of knowledge of the near-Earth debris population
from both in situ and terrestrial-based sensors; (b) the capabilities of computer
models to assess debris risks and to forecast the growth of space debris; and (c) a
variety of space debris mitigation measures.

132.

With the use of ground-based optical and radar surveillance systems around

the world, space objects with diameters larger than 10 cm in LEO and larger than
1 m in GEO can be observed and tracked. More than 8,500 catalogued objects are
in Earth orbit. The number of in-orbit catalogued objects has been increasing at a
relatively linear rate for the past several decades.

133.

Some nations have developed computer models of space debris based upon

the large, catalogued population and upon statistical observations obtained by a
wide variety of sensors. Despite the differences in the techniques applied in the
models, the trends and tendencies predicted for the future space debris environment
are qualitatively in agreement (see figure IX). Currently, collision risk in LEO is
not great, and the collision risk in GEO is correspondingly lower. However, due to
the long residence-time of fragments in GEO as compared to LEO, the environ-
mental consequences of a collision are greater. It is therefore necessary to continue
joint comparison and validation of the initial data, applied techniques and results
of the different models.

134.

Of the debris mitigation measures identified, the limitation of

mission-related debris and the prevention of accidental explosions have been found
effective and have already been introduced to some extent. Also, the transfer of
GEO spacecraft into disposal orbits at the end of their active life is already a
practice, followed as an intermediate measure to prevent future problems in GEO.
IADC has suggested an algorithm for the determination of the minimum altitude
of the disposal orbit above GEO. For some satellites on long lifetime LEO orbits,
a transfer to shorter lifetime orbits is planned at the end of their active life. Such
procedures, in general, could be effective in limiting the density of objects in those
altitude bands that are most highly populated at present. Since most of the mitiga-
tion measures introduce some cost burden to missions, it would be beneficial that
similar mitigation measures are considered for all missions globally.

135.

Many organizations involved in space operations have become aware of the

potential threats of space debris, and some of those organizations have initiated
efforts to mitigate debris generation and to share the results of those efforts with
the international community. The activities of international organizations such as

Annex

List of documents relevant to the

subject “Space debris”

Reports on sessions of the Scientific and Technical Subcommittee

Report of the Scientific and Technical Subcommittee on the work of its thirty-first session
(A/AC.105/571, 10 March 1994)

Report of the Scientific and Technical Subcommittee on the work of its thirty-second ses-
sion (A/AC.105/605, 24 February 1995)

Report of the Scientific and Technical Subcommittee on the work of its thirty-third session
(A/AC.105/637 and Corr.1, 4 March 1996)

Report of the Scientific and Technical Subcommittee on the work of its thirty-fourth session
(A/AC.105/672, 10 March 1997)

Report of the Scientific and Technical Subcommittee on the work of its thirty-fifth session
(A/AC.105/697 and Corr.1, 25 February 1998)

Report of the Scientific and Technical Subcommittee on the work of its thirty-sixth session
(A/AC.105/719, 18 March 1999)

Reports on national research on space debris

Use of nuclear power sources in outer space (A/AC.105/C.1/WG.5/L.24, 15 January 1990)

Use of nuclear power sources in outer space (A/AC.105/C.1/WG.5/L.24/Add.1, 14 February
1990)

Use of nuclear power sources in outer space (A/AC.105/C.1/WG.5/L.24/Add.2, 26 February
1990)

Use of nuclear power sources in outer space (A/AC.105/C.1/WG.5/L.24/Add.3, 28 February
1990)

Space debris; status of work in Germany: working paper by Germany (A/AC.105/C.1/L.170,
12 February 1991)

National research on the question of space debris (A/AC.105/510, 20 February 1992)

National research on the question of space debris (A/AC.105/510/Add.1, 21 February 1992)

National research on the question of space debris (A/AC.105/510/Add.2, 26 February 1992)

National research on the question of space debris (A/AC.105/510/Add.3, 26 February 1992)

National research on space debris; safety of nuclear-powered satellites; and problems of
collisions of nuclear-powered sources with space debris (A/AC.105/542, 8 February 1993)

National research on space debris; safety of nuclear-powered satellites; and problems
of collisions of nuclear-powered sources with space debris (A/AC.105/542/Add.1,
17 February 1993)

National research on space debris; safety of nuclear-powered satellites; and problems
of collisions of nuclear-powered sources with space debris (A/AC.105/542/Add.2,
19 February 1993)

National research on space debris; safety of nuclear-powered satellites; and problems
of collisions of nuclear-powered sources with space debris (A/AC.105/565 and Corr.1,
16 December 1993)

National research on space debris; safety of nuclear-powered satellites; and problems
of collisions of nuclear-powered sources with space debris (A/AC.105/565/Add.1,
21 February 1994)

National research on space debris; safety of nuclear-powered satellites; and problems
of collisions of nuclear- powered sources with space debris (A/AC.105/565/Add.2,
23 February 1994)

National research on space debris; safety of nuclear-powered satellites; and problems of
collisions of nuclear- powered sources with space debris (A/AC.105/593, 1 December 1994)

National research on space debris; safety of nuclear-powered satellites; and problems of
collisions of nuclear- powered sources with space debris (A/AC.105/593/Add.1, 24 January
1995)

National research on space debris; safety of nuclear-powered satellites; and problems of
collisions of nuclear- powered sources with space debris (A/AC.105/593/Add.2, 6 February
1995)

National research on space debris; safety of nuclear-powered satellites; and problems of
collisions of nuclear- powered sources with space debris (A/AC.105/593/Add.3, 7 February
1995)

National research on space debris; safety of nuclear-powered satellites; and problems
of collisions of nuclear- powered sources with space debris (A/AC.105/593/Add.4,
24 February 1995)

National research on space debris; safety of nuclear-powered satellites; and problems of
collisions of nuclear- powered sources with space debris (A/AC.105/619, 21 November
1995)

National research on space debris; safety of nuclear-powered satellites; and problems of
collisions of nuclear- powered sources with space debris (A/AC.105/619/Add.1, 1 February
1996)

National research on space debris; safety of nuclear-powered satellites; and problems of
collisions of nuclear- powered sources with space debris (A/AC.105/659, 13 December
1996)

National research on space debris; safety of nuclear-powered satellites; and problems of
collisions of nuclear- powered sources with space debris (A/AC.105/659/Add.1, 6 February
1997)

National research on space debris; safety of nuclear-powered satellites; and problems of
collisions of nuclear- powered sources with space debris (A/AC.105/659/Add.2,
14 February 1997)

National research on space debris; safety of nuclear-powered satellites; and problems of
collisions of nuclear- powered sources with space debris (A/AC.105/680, 1 December 1997)

National research on space debris; safety of nuclear-powered satellites; and problems of
collisions of nuclear- powered sources with space debris (A/AC.105/680/Add.1, 2 February
1998)

National research on space debris; safety of nuclear-powered satellites and problems of
collisions of nuclear- powered sources with space debris (A/AC.105/708, 8 December 1998)

National research on space debris; safety of nuclear-powered satellites and problems of
collisions of nuclear- powered sources with space debris (A/AC.105/708/Add.1, 19 January
1999)

National research on space debris; safety of nuclear-powered satellites and problems
of collisions of nuclear- powered sources with space debris (A/AC.105/708/Add.2,
25 February 1999)

Documents on mitigation steps taken by space agencies

Steps taken by space agencies for reducing the growth or damage potential of space debris
(A/AC.105/620, 21 November 1995)

Steps taken by space agencies for reducing the growth or damage potential of space debris
(A/AC.105/663, 13 December 1996)

Steps taken by space agencies for reducing the growth or damage potential of space debris
(A/AC.105/681, 17 December 1997)

Scientific and technical presentations

Scientific and technical presentations to the Scientific and Technical Subcommittee
(A/AC.105/487, 9 May 1991)

Scientific and technical presentations to the Scientific and Technical Subcommittee
(A/AC.105/516, 29 May 1992)

Scientific and technical presentations to the Scientific and Technical Subcommittee
(A/AC.105/546, 18 May 1993)

Scientific and technical presentations to the Scientific and Technical Subcommittee at its
thirty-first session (A/AC.105/574, 12 May 1994)

Scientific and technical presentations to the Scientific and Technical Subcommittee at its
thirty-second session (A/AC.105/606, 27 April 1995)

Scientific and technical presentations to the Scientific and Technical Subcommittee at its
thirty-third session (A/AC.105/638, 7 May 1996)

Scientific and technical presentations to the Scientific and Technical Subcommittee at its
thirty-fourth session (A/AC.105/673, 7 May 1997)

Scientific and technical presentations to the Scientific and Technical Subcommittee at its
thirty-fifth session (A/AC.105/699, 20 April 1998)

Working papers and reports

Space debris: a status report submitted by the Committee on Space Research (A/AC.105/
403, 6 January 1988)

Environmental Effects of Space Activities: report submitted by the Committee on Space
Research and the International Astronautical Federation (A/AC.105/420, 15 December
1988)

The problem of space debris: working paper submitted by Australia, Belgium, Canada, the
Federal Republic of Germany, the Netherlands, Nigeria and Sweden (A/AC.105/L.179,
1 June 1989)

Use of nuclear power sources in outer space; space debris: working document submitted by
the Russian Federation (A/AC.105/C.1/L.193, 21 February 1994)

Space debris: report of the International Astronautical Federation (A/AC.105/570, 25 Feb-
ruary 1994)

Collisions between nuclear power sources and space debris: working paper submitted by the
Russian Federation (A/AC.105/C.1/L.204, 13 February 1996)

Brief review of the work done by Russian scientists on the problem of the technogenic
pollution of near space: working paper submitted by the Russian Federation (A/AC.105/C.1/
L.205, 13 February 1996)

Space debris: working paper submitted by the International Academy of Astronautics (A/
AC.105/C.1/ L.217, 12 January 1998)

Space debris: working paper submitted by the Russian Federation (A/AC.105/C.1/L.219,
10 February 1998)

The forecast of technogenous contamination of the near-Earth space with various measures
of its mitigation: document presented by the Russian Federation (A/AC.105/C.1/1999/
CRP.4, 23 February 1999)

Revisions to the technical report

Revisions to the technical report on space debris of the Scientific and Technical Subcom-
mittee (A/AC.105/C.1/ L.214, 26 February 1997)

Revisions to the technical report on space debris of the Scientific and Technical Subcom-
mittee (A/AC.105/C.1/ L.224, 19 February 1998)

Draft technical report on space debris of the Scientific and Technical Subcommittee (A/
AC.105/707, 14 December 1998)