(Apr 2002 edition)
1A US Category A object: Development of spaceflight techniques and
technology. (After Oct 1976, description is: Space craft engaged in
investigation of spaceflight techniques and technology).
1B US Category B object: Space research and exploration. (After Oct 1976,
description is: Spacecraft engaged in research and exploration of the
upper atmosphere or outer space).
1C US Category C object: Practical applications of space based technology.
(After Oct 1976, description is: Spacecraft engaged in practical
applications and uses of space technology such as weather or
communication).
1D US Category D object: Non-functional objects. (After Oct 1976,
description is: Spent boosters, spent maneuvering stages, shrouds and
other non-functional objects).
2 Investigation of the upper atmosphere and outer space.
3 Investigation of the upper atmosphere and outer space; development of
elements in the design of space craft.
4 Conduct of experiments necessary for further flights under the
established programme of lunar exploration.
5 Television programme transmission and long-range two-way multi-channel
telephone, phototelegraph and telegraph communicaitons.
6 Further development and experimental operation of long-range two-way
television and telephone-telegraph radio-communication.
7 Scientific research in outer space
8 Operation of a system of long range telephone-telegraph
radiocommunication, and transmission of USSR Central Television
programmes to the stations of the Orbita network.
9 Acquisition of meteorological information needed for use by the weather
service.
10 Investigation of the upper atmosphere and outer space. Eight satellites
launched by a single carrier rocket.
11 Solar orbit: 398 days, 0.9871 x 1.1421 AU x 0.127 deg
12 Solar orbit: 311.6 days, 0.8061 x 0.9951 AU x 0.127 deg
13 Solar orbit: 406.4 days, 0.9839 x 1.163 AU x 0.3988 deg
14 Launching of first ever artificial satellite of the Earth; physical study
of the atmosphere.
15 Study of the physical processes and conditions of life in outer space.
16 Research in the upper atmosphere and outer space
17 Attainment of escape velocity and exploration of interplanetary space.
18 Impacting on the Moon; delivery of a pennant to the surface of the Moon,
and research during flight to the Moon.
19 Placing an automatic interplanetary station in orbit around the Moon;
photographing the surface of the far side of the Moon; exploring outer
space.
20 Development and checking of the main systems of the space ship satellite,
which ensure its safe flight and control in flight, return to Earth and
conditions needed for a man in flight.
21 Development of systems ensuring man's life functions and safety in flight
and his return to Earth.
22 Medical and biological research under space flight conditions.
23 Development of heavier space craft.
24 Name is "Space rocket toward Venus". Checking of methods of setting space
objects on an interplanetary course. Checking of extra-long-range
communications with and control of the space station; more accurate
calculation of the dimension of the solar system; a number of physical
investigations in space.
25 Development of the design of the space ship satellite and of the systems
on board, which ensure necessary conditions for man's flight.
26 Development of the design of the space ship satellite and of the systems
on board, designed to ensure man's life functions during flight in outer
space and return to Earth.
27 Name given as: Space ship satellite "Vostok" ("The East"). Placing in
orbit around the Earth of the first ever space ship satellite with a man
on board.
28 Name given as: Space ship satellite "Vostok-2" ("The East-2").
Investigation of the effects on the human organism of a prolonged flight
in orbit and subsequent return to the surface of the Earth; investigation
of man's ability to work during a prolonged period of weightlessness.
29 Name corrected from 'satellite' to 'sputnik' in A/AC.105/INF.2/Corr.1.
30 Report on the Orbital Flight of Colonel Glenn: On 20 February 1962, John
Glenn was launched into earth orbit by an Atlas booster on top of which
was the Mercury spacecraft. The flight conditions attained were as
follows: 1. Perigee altitude - 86.7 nmi 2. Apogee altitude - 141 nmi 3.
Velocity at injection - 25709 feet per second 4. Orbital inclination -
32.54 deg. 5. Orbital period - 83 min 29 sec. After four hours and 43
minutes the spacecraft reentered the atmosphere and landed at 2:43 pm EST
in the planned recovery area NE of the Island of Puerto Rico. All flight
objectives were achieved. Beacuse of failure of one of the automatic
systems, the astronaut took over manual control of the spacecraft during
part of the flight. The astronaut's performance in flight agreed closely
with that he had displayed during ground simulation training operations.
The weight of the spacecraft assembly at launch was slightly over two
tons and the weight in orbit was slightly less than 3000 lbs.
Post flight examinations of the spacecraft indicated that reentry had
been in accordance with pre-flight calculations. Detailed examination of
the spacecraft and its systems and engineering analysis of these results
are presently underway.
31 A/AC.105/INF.3 noted that these objects decayed prior to Feb 15, 1962 and
should not have been included in A/AC.105/INF.1
32 Launch vehicle corrected from Atlas to Thor Delta (INF.5).
33 Decay date corrected from Mar 9 to Mar 4 (INF.5)
34 United Kingdom satellite launched by a United States launch vehicle.
35 Study of man's ability to function under conditions of weightlessness;
conduct of scientific observations; further improvement of space ship
systems, communications, guidance and landing.
36 Acquisition of experimental data on the possibility of establishing a
direct link between two space ships ("Vostok 3" and "Vostok 4");
coordination of astronauts' operations; study of the effects of identical
spaceflight conditions on the human organism.
37 Canadian satellite launched by a United States launch vehicle
38 Name is: Space rocket carrying the "Mars 1" automatic station.
Description: Prolonged exploration of outer space during flight to the
planet Mars; establishment of inter-planetary radio communications;
photgraphing of the planet Mars and subsquent radio-transmission to Earth
of the photographs of the surface of Mars thus obtained.
39 Orbital data from A/AC.105/INF.28.
40 Name: Automatic Station "Luna-4". Description: Experiments necessary for
future flights in the programme for conquest of the moon.
41 Orbital data from A/AC.105/INF.37.
42 Further study of the effect of various space-flight factors in the human
organism; extensive medico-biological experiments under conditions of
prolonged flight; further elaboration and improvement of spaceship
systems.
43 Comparative analysis of the effect of various space-flight factors on the
male and female organisms; medico-biological research; further
elaboration and improvement of spaceship systems under conditions of
joint flight.
44 This space vehicle also carried 50 lb of copper dipoles which were
dispensed so as to form an orbital belt for experimental space
communication. The orbital characteristics of the belt are expected to be
approximately the same as for 1963-14A.
45 Orbital data from A/AC.105/INF.44.
46 1963-25B was launched into orbit on 27 June as a passenger aboard
1963-25A. 1963-25B was injected into new orbital parameters on 1 Jul
1963.
47 Data as corrected in A/AC.105/INF.50.
48 Controlled manouevring space apparatus "Polet 1". Purpose - elaboration
of system providing for the extensive manoeuvring of space apparatuses.
Orbit given is final orbit after manoeuvres.
49 Electron I and II launched by a single carrier rocket. Electron I:
simultaneous study of the Earth's inner and outer radiation belts, cosmic
rays and upper atmosphere. Electron II: simultaneous study of the Earth's
inner and outer radiation belts, cosmic rays and outer space.
50 A/AC.105/INF.61 identifies the objects 1961 Omicron 4 to 206 by
implication for the first time.
51 Orbital data from A/AC.105/INF.62.
52 Elaboration of a long range space system and conduct of scientific
research.
53 Controlled manouevring space apparatus "Polet 2". Elaboration of systems
providing for the extensive manouevring of space apparatuses.
54 Debris object 1964-03C registered on A/AC.105/INF.68 is spurious.
(Editor's note: Orbit is that of a debris object of 1963-47.)
Object was deleted in A/AC.105/INF.69. Details were:
US 1964-03C, 1964 Jan 21, 107.8 min, 573 x 1672 km x 30.4 deg,
category D.
55 The United Kingdom provided the payload for 1964-15A.
56 Electron 3 and 4 launched by a single carrier rocket. Simultaneous study
of the inner and outer radiation belts of the earth, cosmic rays and the
upper atmosphere.
57 Cosmos-38 to Cosmos-40 launched with a single carrier rocket
58 Cosmos-42 to Cosmos-43 launched with a single carrier rocket
60 Space ship "Voskhod". Test of a new multi-seat space ship; investigation
of the in flight work potential and co-operation of a group of cosmonauts
consisting of specialists in different branches of science and
technology; scientific physico-technical and medico-biological research.
61 Initally registered as category B (A/AC.105/INF.85).
62 Elaboration of station systems and scientific research in interplanetary
space.
63 Initially registered as 1964-76I (A/AC.105/INF.90).
64 Launched by the Government of Italy from United States territory using
United States facilities. Object also noted as launched by Italy in
United States registration notice A/AC.105/INF.90. The San Marco I
satellite is a scientific space craft containing two experiments: (1)
consisting in special instrumentation for measurement of ionospheric
density at a continuous rate; (2) consisting in a transceiver for studies
on radio propagation through the upper limits of the atmosphere.
65 Object also noted in A/AC.105/INF.90; debris object, orbital data from
A/AC.105/INF.95.
66 Cosmos 54 to Cosmos 56 launched by a single carrier rocket.
67 Cosmos 61 to 63 launched by a single carrier rocket.
68 Egress of a man from a space ship into outer space; testing of space ship
systems; medico-biological research under space flight conditions; and
other scientific research.
69 Television programme transmission and long range two way multi channel
telephone and telegraph communications. Orbital characteristics after
correction of 2 May 1965.
70 1965-28A was launched by the United States for the Communications
Satellite Corporation.
71 Cosmos 71 to 75 launched by a single carrier rocket.
72 Space station "Proton 1". Investigation of ultra-high-energy cosmic
particles.
73 Automatic station "Zond 3". Development of station systems and scientific
research in interplanetary space.
74 Satellite initially registered as category A; corrected to category D in
A/AC.105/INF.114.
75 Cosmos 81 to 84 launched by a single carrier rocket. Cosmos 86 to 90
launched by a single carrier rocket.
76 Experiments necessary for future flights in the programme for conquest of
the moon.
77 Second communications satellite "Molniya-1". Television programme
transmission and long-range, two-way multi-channel telephone,
phototelegraph and telegraph communications.
78 Investigation of ultra-high-energy cosmic particles
79 Canada provided the payload for 1965-98A.
80 Investigation of the properties of the ionized layers of the atmosphere
by observation of the propagation of the properties of very low frequency
waves in the ionosphere. First registered by the United States in
A/AC.105/INF.125. Orbit given there was 99.9 min, 749 x 753 km x 75.9
deg, with note: France provided the payload for 1965-101A.
81 French scientific satellite "A-I". Launched from Hammaguir (Algeria) in
order to test the "Diamant" launching vehicle for the first time.
82 Scientific satellite "D-I" launched from Hammaguir (Algeria).
83 Experiments necessary for future flights in the programme for the
conquest of the moon, transmission to earth of television pictures on the
moon's surface.
84 Biological research.
85 Development of system to permit the creation of an artificial lunar
satellite for the investigation of circumlunar space; development of
onboard systems for putting a station into a selenocentric (circumlunar)
orbit. Orbit: 350 x 1017 km, inclination 71.9 deg to plane of the lunar
equator.
86 Space station 'Proton 3'. Investigation of ultra high energy cosmic
particles
87 Automatic station Luna 11. Further development of artificial lunar
satellite systems and conduct of scientific experiments in circumlunar
space. Lunar orbit 160 x 1200 km x 27 deg.
88 Automatic station "Luna 12". Further development of artificial lunar
satellite systems and conduct of scientific experiments in circumlunar
space. Orbit 100 x 1740 km (lunar).
89 Conduct of further scientific investigation of the moon and circumlunar
space.
90 Tests of a new manned spaceship, conduct of scientific experiments and
research in the upper atmosphere and outer space.
91 Scientific satellite launched from a mobile range off Formosa Bay
(Kenya).
92 Launch time of Diadem I was 10:39:40 on 8 Feb 1967. Launch time of Diadem
II was 11:06:57 on 15 Feb 1967.
93 Investigation of outer space, development of new systems and elements to
be used in the construction of space devices.
94 WRESAT 1 launched for upper atmosphere and space research at 1419 h
central standard time, from Woomera, South Australia. Launch vehicle
based on Redstone.
95 Study of remote regions of circumterrestrial space, development of new
on-board systems and units of space stations.
96 Further scientific experiments in cicrumlunar space. Orbit 140 x 870 km x
42 deg around Moon.
97 Impacted the moon on Jan 31, 1968.
98 Flight around the moon; scientific investigation of outer space in the
region of the moon; return to earth at second space speed (Ed. note:
second cosmic velocity) and soft landing in target area.
99 Complex testing of spaceship systems in conditions of space flight.
100 Complex testing of spaceship systems; development, in joint flight with
space ship "Soyuz 2" of processes of space ship manoeuvring and docking
in artificial earth satellite orbit; development of elements of
celestial navigation; conduct of research under space flight conditions.
101 Study of the nature of high and ultra-high energy cosmic rays and their
interaction with atomic nuclei.
102 Investigation of the planet Venus and outer space.
103 Scientific, technical and medico-biological research, checking and
testing of onboard systems and design elements of space craft, docking of
piloted space craft and construction of an experimental space station,
transfer of cosmonauts from one craft to another in orbit.
104 A/AC.105/INF.207: France registered two satellites which are the property
of the European Space Research Organization (ESRO). The French government
is acting on behalf of all States members (Belgium, Denmark, the
Federal Republic of Germany, France, Italy, the Netherlands, Spain,
Sweden, Switzerland and the United Kingdom) of this international
organization which has its headquarters in Paris, and as depository of
the Convention for the establishment of this organization, which has been
registered with the United Nations. Editor's note: The satellite IRIS was
first registered as a United States satellite, 1968-41A, by the United
States in A/AC.105/INF.193. Its orbital parameters were then given as 330
x 1090 km, 97.2 deg, 98.9 min and its type as category B. The satellite
Aurorae was first registered as a United States satellite, 1968-84A, by
the United States in A/AC.105/INF.200. Its orbital parameters were then
given as 260 x 1499 km, 93.7 deg, 102.5 min and its type as category B.
105 Testing of on-board systems of the automatic station and further
scientific investigation of the moon and circumlunar space.
106 Flight around the moon; further study of the moon and circumlunar space;
testing of improved on-board systems and assemblies of the station;
return to earth at second cosmic speed, guided descent and soft landing
in target area.
107 Fourth satellite of ESRO. Also registered by the United States in
A/AC.105/INF.220 as United States space object 1969-83A, with category B
and orbital parameters 90.6 min, 280 x 339 km x 85.1 deg.
108 Testing of space craft systems and designs, manoeuvring of space craft
with respect to each other in orbit, conduct of scientific, technical and
medico-biological experiments in group flight.
109 Investigation of solar radiation and its effect on the atmosphere of the
earth.
110 Engineering test for the launching of scientific satellites. Injection
point 29.7 N, 145.8 E
111 A/AC.105/INF.216. Payload separated from adapter and recovered prior to
31 Jul 1969. Adapter remained in orbit.
112 Investigation of the characteristics of the earth's ionosphere and of
concentrations of electrons and positive ions.
113 Medico-biological, scientific and technical studies and experiments in
prolonged orbital flight.
114 Revisions made on A/AC.105/INF.223:
The rocket body associated with launch 1969-82 disintegrated before the
nine payloads had separated enough to properly catalog and identify them.
When the blow-up occurred, it could not be determined whether or not the
payloads had blown up with the rocket body. The only identification that
could properly be made of this launch were fragments. It was not until
Feb 1970 that sufficient data had been acquired to designate and catalog
the payloads and determine that the payloads had not disintegrated
with the rocket body. The 1969-82 objects were redesignated in INF.223;
the original data is noted below.
1969-82B was registered in INF.220 as 1969-82CZ, category D.
1969-82C was registered in INF.220 as 1969-82DA, category D.
1969-82D was registered in INF.220 as 1969-82DC, category D.
1969-82E was registered in INF.220 as 1969-82CP, category D.
1969-82F was registered in INF.220 as 1969-82CW, category D.
1969-82G was registered in INF.223 as 1969-82DP, category D.
1969-82H was registered in INF.220 as 1969-82AL, category D.
1969-82J was registered in INF.220 as 1969-82AJ, category D.
1969-82K was registered in INF.220 as 1969-82E, category D
1969-82AJ was registered in INF.220 as 1969-82K
1969-82AL was registered in INF.220 as 1969-82J
1969-82CP was registered in INF.220 as 1969-82F
1969-82CW was registered in INF.220 as 1969-82G
1969-82CZ was registered in INF.220 as 1969-82B, category A.
1969-82DA was registered in INF.220 as 1969-82C
1969-82DC was registered in INF.220 as 1969-82D
1969-82DP was registered in INF.220 as 1969-82H
115 Scientific investigation of the moon and near-lunar space; automatic
return to Earth of lunar soil.
116 Biological investigations and study of the physical characteristics of
outer space.
117 Investigation of the ultra-violet and x-radiation of the sun and its effect
on the structure of the Earth's upper atmosphere.
118 Investigations along the flight path and in near-lunar space; photographing
of Earth and Moon; testing of improved onboard systems, assemblies and
spacecraft designs.
119 Delivery to the moon of an automatic, self-propelled lunar vehicle,
Lunokhod 1, operated from Earth for purposes of scientific investigations.
120 These objects were registered in A/AC.105/INF.230, at which time they could
not be associated with any particular launch.
121 Testing of design elements and on-board systems; conduct of research and
experiments in space flight.
122 Conduct of joint experiments with the Salyut scientific station; compound
checking of improved on-board spacecraft systems in different conditions of
flight; conduct of medico-biological research.
123 San Marco 3 was launched by Italy from the San Marco Range aboard a US
launch vehicle.
124 Conduct of a series of scientific investigations of the planet Mars and the
space around it.
125 Scientific observations in outer space. Injection point 29 deg 7 min N, 145
deg 8 min E.
126 To test in space equipment for future satellites and to conduct a
scientific experiment to measure the incidence of micro-meteoroids. Launch
time 0409 GMT, injection point 13.7 deg S, 137.9 deg E. Anticipated life
100 years.
127 Testing of methods for automatic near-lunar navigation, investigation of
the moon and near-lunar space.
128 Investigation of the moon and near-lunar space from the orbit of an
artificial satellite.
129 1971-63D is a sub-satellite deployed in lunar orbit by the Apollo 15
Command and Service Module.
130 Continued operation of the long-range telephone and telegraph
radio-communication system within the Soviet Union and transmission of USSR
central television programmes to stations in the Orbita and participating
international networks (international cooperation scheme).
131 Study of radiation levels in near-Earth space, investigation of dipole
corpuscular streams in near space in connexion with solar activity and
investigation of the nature and spectrum of low-frequency electromagnetic
oscillations in natural plasma.
132 Investigation of physical phenomena in the Earth's upper atmosphere at high
latitudes and study of the nature of auroras.
133 Fifth satellite of ESRO. Also registered as US object 1972-05A in
A/AC.105/INF.248 with orbit 7835.4 min, 439 x 248160 km x 90.2 deg,
category B.
134 Sixth satellite of ESRO. Also registered as US object 1972-14A in
A/AC.105/INF.255 with orbit 95.3 min, 525 x 548 km x 97.5 deg, category B.
135 Continuation of investigation of Venus previously conducted by Venera
automatic stations.
136 Investigation of primary cosmic radiation and meteoritic particles in
near-earth outer space.
137 Study of the processes of solar activity and of their influence on
interplanetary space and the Earth's magnetosphere.
138 Continued operation of the long-range telephone and telegraph
radio-communication system; transmission of USSR central television
programmes to stations in the Orbita network and international cooperation.
139 Continuation of joint studies of the sun's ultra-violet and x-radiation and
its effects on the structure of the earth's upper atmosphere.
140 Scientific observations in the ionosphere and magnetosphere. Interjection
point 31 deg 15' N 11 deg 05' E.
141 Orbital parameters in lunar orbit: 91 x 130 km x 169.3 deg, 119.0 min.
142 Seventh ESRO satellite. Mass 115 kg. Also registered by the United States as
1972-92A, in A/AC.105/INF.267, with orbital parameters 98.8 min, 244 x 1160
km x 91.1 deg, category B.
143 A/AC.105/INF.265: Launch vehicle amended from Titan IIIB Agena to Thorad
Agena.
144 Continued joint investigation of the characteristics of the earth's
ionosphere and recording of electron and proton fluxes.
145 Delivery to the Moon of an automatic, self-propelled, lunar vehicle,
Lunokhod 2, operated from Earth for purposes of scientific investigation.
146 Testing of improved design, on-board systems and equipment; conduct of
scientific and technical research and experiments.
147 Name is "Intercosmos Copernicus 500". Investigation of solar radio-frequency
radiation and the characteristics of the earth's ionosphere.
148 Investigation of the planet Mars and surrounding space.
149 Lunar orbit (selenocentric referenced to earth's equator) 1052 x 1063 km x
38.7 deg.
150 Experimental flight for the purpose of further development of manned space
craft.
151 Decay notice in A/AC.105/INF.280 read 1965-82VU. This was corrected in
A/AC.105/INF.282 to read 1965-82UA.
152 Anik I and Anik II also registered as United States objects. State of
registry (INF.284): "United States of America and Canada". Telsat Canada
purchased launch services from the US National Aeronautics and Space
Administration. Anik I and II comprise the space segment of the Canadian
satellite telecommunications system which is owned and operated by Telsat
Canada, a private corporation in which the Government, telecommunications
common carriers, and the public are authorized to hold shares. The
satellites, located in geostationary orbit, act as space repeaters capable
of receiving transmissions from earth stations and retransmitting them to
other earth stations in Canada. The antenna coverage of the satellite
provides the system with the system with the capability of serving virtually
all of Canada. Anik I and II had weights of 1240.59 lb and 1246.48 lb. Each
satellite has 12 RF channels, two of which be protection channels for the
traffic carrying channels. Up-link transmission is in the 5.925-6.425 GHz
band, and the down-link transmission operates in the 3.7-4.2 GHz band. Each
RF channel is capable of transmitting a color television signal
or up to 900 one-way voice channels.
Anik I US registration info in A/AC.105/INF.267: category C.
Anik II US registration info in A/AC.105/INF.275: category C.
153 Geophysical research at high latitudes to study the electromagnetic coupling
of the earth's magnetosphere and ionosphere.
154 Attitude control satellite (performance test of launch vehicle).
155 Astrophysical observations of stars in the ultraviolet range, spectrozonal
photography of specific areas of the earth's surface, and continued testing
of space craft's on-board systems.
156 Continued investigations in the earth's upper atmosphere at high latitudes
and study of the nature of polar aurorae begun on board the Oreol satellite
in 1971.
157 Satellite technology. Miranda was launched at 02:22:11.4 GMT on 1974 Mar 9.
Interjection point 13.9N, 126.0E. Anticipated life: longer than 50 years.
158 Investigation of outer space.
159 Investigation of solar ultraviolet rays and X-rays and the earth's upper
atmosphere.
160 Scientific investigation of the moon and circumlunar space from the orbit of
an artificial satellite of the Moon, which was begun by the Luna 19
automatic station.
161 Futher testing of improved station design, on-board systems and equipment;
conduct of scientific and technical research and experiments in space
flight.
162 Conduct of joint experiments with the Salyut-3 orbital scientific station;
comprehensive checking of improved on-board systems of the Soyuz spacecraft
under various flight conditions.
163 Arrangements for experimental television broadcasts and establishment of
long-range radio-communications.
164 Conduct of joint experiments with the Salyut-3 orbital scientific station.
165 Cosmic X-ray astronomy. Injection point: 2.7S, 58.2E. Anticipated life: 5
years. Time of launch: 07:47:00.25 GMT. Decay also (belatedly) noted in
ST/SG/SER.E/216.
166 Comprehensive investigation of the earth's atmosphere and ionosphere and of
micrometeorite fluxes.
167 Jointly registered by the Federal Republic of Germany (A/AC.105/INF.305) and
France (A/AC.105/INF.306). Symphonie flying model no. 1, constructed jointly
by France and the Federal Republic of Germany. Description: Experimental
telecommunications satellite. Orbit: geostationary.
168 Operation of the long-range telephone and telegraph radiocommunications
system in the USSR; transmission of television programmes to stations in the
Orbita network.
169 Checking of the Soyuz space craft's on-board systems which had been
modernized to meet the requirements of the 1975 joint lfight in accordance
with the programme of the Soviet-United States experiment; conduct of
scientific and technical investigations.
170 Further testing of station design, on-board systems and equipment; conduct
of scientific and technical research and experiments in outer space.
171 Measurement of density, temperature, composition of atmosphere. Launch time
10:05:28.5 GMT. Anticipated life: 3 years.
172 Joint experiments with the Salyut scientific orbital station.
173 SRATS (Solar and Thermospheric Radiation Satellite) is the third Japanese
scientific satellite, to study the intereffects of solar radiation and the
thermosphere of the earth. National name: Taiyo. Launch time 0525 GMT.
174 Geodesic satellite.
175 Study of dynamic processes in the earth's magnetosphere and polar ionosphere
and investigation of low-frequency electromagnetic waves.
176 Experimental satellite for satellite technology and some scientific
experiments. Launched from a cosmodrome in the USSR.
177 Continuation of scientific investigation of Venus and the space surrounding
it and of the physical characteristics of interplanetary space.
178 Experimental flight under the Soyuz-Apollo programme.
179 Eighth CERS/ESRO satellite, first European Space Agency satellite. Launch
time 0147:59 GMT. Argument of perigee 344.7 deg. Also registered by the
United States in A/AC.105/INF.331 as 1975-72A, category B satellite with
orbit 2203.9 min, 442 x 99002 km x 90.3 deg.
180 Entry for Molniya-2 omitted from A/AC.105/INF.327. The satellite was
registered in A/AC.105/INF.327/Corr.1.
181 JETS-1 (Japanese Engineering Test Satellite -1, national name 'Kiku') is
intended for preliminary experiments for confirmation of the launching
technologies, acquiring the satellite tracking and control technologies, and
for extension tests of the extendable antennas, measurement of satellite
environment, measurement of satellite attitudes, etc. Launch time 0530 GMT.
182 Jointly registered by the Federal Republic of Germany (A/AC.105/INF.329) and
France (A/AC.105/INF.330). Symphonie flying model no II. Experimental
telecommunications satellite. Orbit: geostationary. Also registered by the
United States in A/AC.105/INF.331 as 1975-77A, category C, with orbit 1427.4
min, 35364 x 35870 km x 0.0 deg
183 Original registration gave launch vehicle as Titan III. Corrected in
A/AC.105/INF.331 to Atlas Agena.
184 Comprehensive checking of improved on-board systems of the space craft under
various flight conditions.
185 Originally registered as category A. Amended to category D in
A/AC.105/INF.335.
186 Study of low-frequency electromagnetic vibrations in the magnetosphere of
the earth, of the structure of the ionosphere and of the intensity of
micrometeorite fluxes.
187 Investigation of the corpuscular and electromagnetic radiation of the sun
and of solar plasma fluxes, study of the magnetic fields in
circumterrestrial space in order to determine the effects of solar activity
on the interplanetary medium and in the magnetosphere of the earth.
188 Statsionar-1. Provision of uninterrupted round-the-clock telephone and
telegraph radio-communications system in the USSR, transmission of USSR
central television programmes to stations in the Orbita network and
international cooperation.
189 D5A: Weight 36 kg. Testing in space of a hydrazine catalytic decomposition
micropropulsion unit. Responsible organization: Societe Europeene de
Propulsion.
D5B: Weight 76 kg. Testing in space of the CACTUS accelerometer
(ultrasensitive triaxial capacitive accelerometric sensor). Responsible
organization: ONERA, Chatillon-sous-Berneux, France.
190 SRET 2 technological research and study satellite. Launched from Soviet
Union with a Soviet launch vehicle with the Molniya satellite. Mass 30 kg.
Study of the behaviour of a passive cryogenic radiation system,
study of the aging of thermal casings and plastic films.
191 Study of solar and stellar ultraviolet radiation. 1. Spectral analysis of
small and large sources located close to the plane of the ecliptic.
Responsible organization: Laboratoire d'Astronomie Spatiale, Traverse
du Siphon, 13000- Marseille (France). 2. Study of solar ultraviolet
radiation and its absorption by the earth's atmosphere. Responsible
organization: Laboratoire de Physique Stellaire et Planetaire, Meudon,
France. Weight 106.6 kg.
192 Japanese Ionospheric Sounding Satellite (JISS - national name "Ume") is
intended for regular observations by means of radio waves of the global
distribution of the critical frequencies of the ionosphere, and for
utilization of the results of the observation for radio wave forecasts and
warning necessary for effective operation of short-wave radio-communication.
Time of launch 0330UT.
193 Testing of new systems and components of satellite under space flight
conditions.
194 Further testing of station design, on-board systems and equipment; conduct
of scientific and technical research and experiments in outer space.
195 Conduct of joint experiments with the Salyut-5 orbital research station.
196 Investigation of the ultraviolet and X-ray radiation of the Sun and the
influence of such radiation on the structure of the Earth's upper
atmosphere.
197 Scientific investigation of the Moon and circumlunar space and transfer of
lunar soil to earth.
198 Statsionar 1. Provision of uninterrupted round the clock telephone and
telegraph radiocommunication in the USSR and simultaneous transmission of
colour and black-and-white USSR central television programmes to stations
in the Orbita network.
199 Testing and perfecting of scientific-technical methods and devices for
studying the geological characteristics of the earth's surface from outer
space for economic purposes.
200 Continuation of scientific-technical research and experiments with the
Salyut-5 orbital station.
201 Statsionar T. Transmission of colour and black-and-white USSR central
television programmes to the network of public receiving units located in
population centres in Siberia and the Far North.
202 Originally registered as category D. Corrected to category B in
A/AC.105/INF.354
203 Investigation of the upper atmosphere and outer space. Two satellites
launched by a single rocket.
204 Tentative name before launching: MS-T3. Launching organization: Institute of
Space and Aeronautical Science, University of Tokyo. Radio frequencies:
136.725 MHz, tracking; 400.500 MHz, telemetry. Active life: two weeks.
Function: (1) Test of the overall performance of the newly developed launch
vehicle, M-3H-1. (2) Experiment of magnetic stabilization. (3) Observation
of ultraviolet radiation.
205 Engineering Test Satellite Type II (ETS II), Kiku 2. Launch by N launch
vehicle no 3. Geographical longitude of the geostationary orbit: 130 deg E.
Telemetry 136.1123 MHz, 2 W. Measurement of range and range rate,
1705 MHz, 4W. Propagation experiment: 1705 MHz (0.4W), 11508.75 MHz (0.4W),
34526.25 MHz (0.1W). Experiment 1 (NASDA):
Preliminary experiments to acquire technologies to launch geostationary
satellites, acquire the geostationary satellite tracking and control
technologies, for testing the attitude control functions of geostationary
satellites, etc.
Experiment 2 (Radio research laboratories of the Ministry of Posts and
Telecommunications): Propagation experiment of millimetre and
quasi-millimetre waves. Characteristics of the satellite: Weight at launch
245 kg. Configuration: cylindrical. Height 191 cm including antenna.
Diameter 141 cm. Attitude control: spin stabilization. Expected life at
least 6 months.
206 Continuation of scientific and technical research and experiments with the
Salyut-5 orbital research station, commenced on 7 July 1976 during the joint
flight of the Soyuz-21 transport spacecraft and the Salyut-5 station.
207 Continuation of experimental work in studying the natural resources of the
earth. Acquisition of meteorological information required for use in the
operational weather service.
208 Statsionar-2. Provision of uninterrupted round the clock telephone and
telegraph radiocommunication in the USSR and simultaneous transmission of
colour and black-and-white USSR central television programmes to stations
in the Orbita network.
209 Geostationary Meteorological Satellite (GMS) "Himawari" ("Sunflower" in
English). Launch vehicle Delta 2914-132. Time of launch 1039UT. Launching
organization NASDA (National Space Development Agency of Japan), NASA
(National Aeronautics and Space Administration of the USA). Note: NASA
furnished launching and associated services to NASDA, at the request of
NASDA and on a reimbursable basis for the launching of the GMS. NASDA
injected the GMS into the geostationary satellite orbit. Geographical
longitude in geostationary orbit, 140 deg E. General function:
1) (NASDA) Tracking and control of the GMS
2) (NASDA) Acquiring the data concerning the geostationary satellite
tracking and control technologies. 3) Organization in charge of
meteorological services: Japan Meteorological Agency (JMA): Mission of
the GMS: (a) Weather watch by visible and infra-red spin scan radiometer
(VISSR) aboard the spacecraft. Imaging the earth's surface and cloud, and
measuring the temperature of both surface and cloud top. (b)
Dissemination of facsimile, transmission of processed data via the GMS to
user stations with LR-FAX and HR-FAX. (c) Collection of meteorological
data: acquisition of data from drifting and fixed sensor platforms which
are either interrogated by the GMS or self-timed. (d) Monitoring of space
environment: measurement of solar protons, alpha particles and electrons.
Satellite characteristics: Weight 315 kg at an early stage in geostationary
orbit. Configuration: cylindrical. Height 2.7m in operational configuration.
Diameter 2.2m. Attitude control: spin stabilization. Probability
of survival in three years, more than 50 percent.
209 Continued investigation of the effects of space flight on living organisms.
210 Investigation of the influence of space flight on living organisms and
testing of life-support systems for biological entities.
211 Investigation of energetic charged and neutral particles and micrometeorite
fluxes in circumterrestrial space.
212 Conduct of scientific and technical research and experiments; further
testing of station design, on-board system and equipment.
213 Conduct of joint experiments with the Salyut-6 scientific station.
214 Ionosphere Sounding Satellite-b (Japanese name: Ume-2). Launch time 0400 UT.
Launch vehicle: N Launch vehicle flight number 4. Spin-stabilized ISS-b is
equipped with basic systems such as attitude control system, TT and C
system (136 MHz, 148 MHz, and 400 MHz), electric power supply system and so
on, and mission equipment such as Ionospheric Sounder, Radio Noise Receiver,
Plasma Measuring Equipment, Ion Mass Spectrometer, and so on.
The satellite is intended for regular observation of global distribution of
critical frequencies of the ionosphere by means of radio waves. And the
results of the observation are to be utilized for radio propagation,
and radio disturbance warning necessary for effective short-wave radio
communications. Weight about 141 kg. Shape: cylindrical, 3.9m diameter and
0.8m height. Expected lie: probability of survival in 1.5 years is more
than 70 percent.
215 Medium-capacity Communications Satellite for Experimental Purposes (CS -
Japanese name Sakura). Launch vehicle Delta 2914-137. Launch time 0047 UT.
Launching organization: NASDA and NASA. NASA furnished spacecraft
launching and associated services to NASDA at the request of NASDA on a
reimbursable basis. NASDA injected the CS into geostationary orbit.
Geographical longitude on geostationary orbit: 135 deg E. CS is a spin
stabilized geostationary communications satellite. The satellite is equipped
with basic systems such as TT and C system (2 GHz band and 6/4 GHz band),
electric power supply system and so on, and mission equipment
such as two transponders of 6/4 GHz band, six of 30/20 GHz band and so on.
Following experiments are to be carried out: (1) Measurement of on-board
mission equipment characteristics. (2) Measurement and evaluation of
propagation characteristics, especially in quasi-millimetric waves. (3)
Experiments on signal transmission through satellite communication system.
(4) Experiments on satellite communications system operation. (5)
Experiments on satellite operation and control.
Characteristics of satellite: Weight approx 340 kg at an early stage in
orbit, configuration: cylindrical, height 3.48 m, diameter 2.18m, Expected
life more than three years.
216 Orbital data originally reported erroneously in nautical miles. Corrected to
km in ST/SG/SER.E/1.
217 Transport to the Salyut 6 station a crew composed of V A Dhanibekov, O.G
Makarov, to carry out scientific work.
218 Delivery of fuel, consumable materials and equipment to the Salyut 6
station.
219 Launching organization: Institute of Space and Astronautical Science,
University of Tokyo. Tracking freq. 136.725 MHz, Telemetry freq. 400.450
MHz. Active life - two years. Function: 1) Observation of wide angle global
auroral pictures using UV television camera. 2) Spectrophotometry of
ultraviolet air glow. 3) Observation of the energy spectrum of
photoelectrons and auroral electrons. 4) Mass spectrometry of the ionized
atmospheric species in the thermosphere. 5) Measurements of density and
temperature of ambient electrons in the thermosphere. 6) Observation
of electromagnetic and plasma waves with special reference to the emission
associated with auroral phenomena.
220 European Space Agency satellite. Launch time 0135 GMT. Reached definitive
position, 0 deg longitude over the Gulf of Guinea, on 7 December. Launched
by United States Delta rocket.
221 European Space Agency satellite. Launch time 2259 GMT. Reached definitive
position, 10 deg east longitude, on May 24 at 0800 GMT. Launch by US Delta
rocket.
222 Medium-scale broadcasting satellite for experimental purposes (BSE). Launch
vehicle Delta 2914-140. Launch time 2201 GMT. Launch organization: NASDA and
NASA. NASA furnished spacecraft launching and associated services to
NASDA at the request of NASDA on a reimbursable basis. NASDA injected BSE
into the geostationary orbit. Location 110 deg E. Frequency: a) Tracking,
Telemetry and Command (TT and C) 2 GHz band; b) Broadcasting Satellite
service: 14/12 GHz band, 2 channels. General function: (1) Test of the
characteristics of television signal transmission; 2) Measurement of the
rainfall effect on the 12 GHz radio wave propagation; (3) Evaluation
of the performance of the on-board equipment and ground terminals; (4)
Experiments on the frequency sharing with the terrestrial communications
systems; (5) Acquisition of the satellite control technologies; (6)
Experiments on the satellite broadcasting operation; (7) Assessment of
television signals reception quality. Characteristics of satellite: Weight
approx 355 kg in an early stage in orbit. Configuration - box shaped
satellite with 2 solar array panels with overall span of 8.95m. Height
3.09m, width 1.32m, length 1.19m. 3-axis stabilized attitude control.
Expected life 3 years.
223 European Space Agency satellite. Launch time 1043 GMT. Reached initial
operational position of 6 deg East on 26 Jul 1978. During the two years of
its mission, it will be maintained in position between longitude
0 and 35 deg east in geosynchronous orbit.
224 SIRIO (Satellite Italiano Ricerca Industriale Orientata - Industrial
Research-oriented Italian Satellite). Launch time 2350:00 GMT. Launching
organization: CNR - Consiglio Nazionale delle Richerche (National Research
Council) of Italy, and NASA. Geographical longitude of geostationary orbit
15 deg W. SIRIO is a spin stabilized geostationary experimental
communications satellite. The satellite is equipped with basic system
such as: (1) TLM (telemetry) 136.14 MHz. (2) TCM (telecommand) 148.26 MHz.
(3) Power supply (4) Thermal control, (5) Attitude and orbit control, (6)
Apogee boost motor. The experiment performs propagation and
telecommunicaiton experiments to study the influence of various
meteorological conditions on the propagation medium at 12 and 18
GHz super high frequenicies (SHF) bands. The SHF experiment consists of a
transponder assembly and a mechanically despun antenna. The principal
objectives of the SHF telecommunications experiments are to -
perform a systematic evaluation of the propagation performance at the 12 and
18 GHz bands; measure absolute and relative attenuation at the edges of the
band; perform a narrow band telecommunications experiment for a single
television link. Characteristics of satellite: Weight at launch 398 kg, in
orbit 218 kg. Configuration - cylindrical, height 1.981m, diameter 1.433m,
nominal life two years.
225 Launched by the United States and the Federal Republic of Germany. Helios A
(Helios I). Heliocentric orbit 190 days, 0.309 x 0.985 AU x 0 deg.
Exploration of the interplanetary space between the earth and
the sun and study of solar influences on that area.
226 Launching organization: Institute of Space and Aeronautical Science,
University of Tokyo. Stimulated plasma wave experiment, natural plasma wave
measurement, plasma parameter measurement by VLF Doppler technique, electric
field probe and plasma density measurement, energetic particle
analysis, and controlled electron beam emission experiment.
Characteristics: weight 90.5 kg, configuration - polyhedron with 38 faces,
height 0.6m , diameter 0.75m, attitude control spin stabilization, life two
years.
227 Delivery to the Salyut-6 station of the first international 'Intercosmos'
team consisting of A.A. Gubarev (USSR) and V. Remek (Czechoslovak Socialist
Republic) to carry out scientific research and experiments jointly developed
by Soviet and Czechoslovak specialists.
228 Completion of work on a space navigation system designed to permit
determination of the position of Soviet naval and fishing vessels.
229 Registered a second time in ST/SG/SER.E/11 with orbit 634.0 min, 167 x 35978
km x 26.4 deg.
230 The placing on board the Salyut-6 station of a crew consisting of V.V.
Kovalenko and A.S. Ivanchenkov to conduct scientific and technological
investigations and experiments.
231 The placing on board the Salyut-6 station, under the Intercosmos programme,
of a second, international, crew consisting of P.I. Klimuk (USSR) and M.
Hermaszewski (Poland) to conduct scientific investigations and
experiments.
232 Provision of uninterrupted round the clock telephone and telegraph
radiocommunication in the USSR and simultaneous transmission of colour and
black-and-white USSR central television programmes to stations
in the Orbita network.
233 Delivery to the Salyut-6 station of the third international 'Intercosmos'
crew consisting of V F Bykovsky (USSR) and S J\"ahn (German Democratic
Republic) to carry out scientific research and experiments.
234 Scientific investigation of the planet Venus and interplanetary space. In
addition to Soviet instruments, carried scientific apparatus for the
investigation of gamma rays developed by specialists of the USSR and France
under the Soviet-French programme of co-operation in the study and mastery
of outer space for peaceful purposes.
235 Conduct of complex investigations on the interaction between the
magnetosphere and ionosphere of the earth. Launched under the Intercosmos
programme by the USSR in cooperation with the Czechoslovak Socialist
Republic, the German Democratic Republic, the Hungarian People's Republic,
the Polish People's Republic and the Socialist Republic of Romania. On 14
Nov 1978, Magion, a small Czechoslovak scientific satellite, separated from
object 1296.
236 Launched with Cosmos-1045. Amateur radiocommunication and scientific and
technical experiments and study projects by students at higher educational
establishments.
237 Investigation of the corpuscular and electromagnetic radiation of the sun,
of solar plasma fluxes and of the magnetic fields in circumterrestrial space
in order to determine the effects of solar activity on the interplanetary
medium and the magnetosphere of the earth; investigation of galactic
ultraviolet rays, X-rays and gamma rays. In addition to Soviet apparatus,
carried scientific apparatus produced in the USSR, the Czechoslovak
Socialist Republic, France, the Hungarian People's Republic and Sweden under
programmes of international cooperation in the exploration and use of outer
space for peaceful purposes.
238 Operation of telephone and telegraph radiocommunications and transmission of
television programmes.
239 1978-26B: Category amended to C from D in ST/SG/SER.E/19. 1978-26C: Category
amended from D to A plus D in ST/SG/SER.E/19.
240 1978-106B orbital data from amendment in ST/SG/SER.E/21. Original data in
ST/SG/SER.E/19 was 92.1 min 169 x 582 km x 28.2 deg, category C.
241 Obtaining information needed for research into the natural resources of the
earth and the development of methods for remote sensing of the underlying
surface, and obtaining meteorological information. In addition
to Soviet apparatus, carried scientific apparatus from the German Democratic
Republic.
242 Development of methods for obtaining operational information on the Pacific
Ocean.
243 Transmission of color and black-and-white USSR central television programmes
to a network of receivers for collective use.
244 Transport of a team consisting of V A Lyakhov and V V Ryumin to the Salyut-6
space station to conduct scientific investigations and experiments and
repair work.
245 Comprehensive investigations of the structure of the earth's ionosphere, the
characteristics of wave processes and the propagation of radio waves in the
ionospheric plasma. Launched under the Intercosmos programme by the USSR in
cooperation with the People's Republic of Bulgaria, the Czechoslovak
Socialist Republic, the Hungarian People's Republic and the Polish People's
Republic.
246 Perigee corrected from 6.5 km to 615 km in ST/SG/SER.E/21.
247 The Czechoslovak satellite MAGION was launched into orbit by the Soviet
spacecraft Intercosmos 18. It forms a part of the scientific programme of
Intercosmos 18, launched from USSR territory on 24 Oct 1978. MAGION was
separated into an autonomous orbit on 14 Nov 1978. General function:
Reasearch of the magnetosphere and ionosphere of the earth
(magnetosphere-ionosphere satellite).
248 Longitude 109.0. Function - telecommunications. Operating entity - Telesat
Canada.
249 Launched from a cosmodrome in the USSR. Experimental satellite for
conducting earth resources survey over India.
250 Experimental Communications Satellite (ECS). Japanese name: AYAME. Launch
time 0846 GMT. Launching organization, National Space Development Agency of
Japan (NASDA). ECS was injected into the planned transfer orbit. On
9 Feb, however, ECS ceased radio transmissions about 10 seconds after the
apogee kick motor was fired. The present ECS orbit cannot be confirmed.
General function: communications and propagation experiments of
satellite-communication systems in the quasi-millimetre wave band as well as
in the microwave band. Operation and control experiment for geostationary
satellites. Characteristics: Mass at launch 260 kg. Configuration -
cylindrical. Height 1.9m including antenna. Diameter 1.4m. Spin stabilized.
251 Launching organization: Institute of Space and Aeronautical Science,
University of Tokyo. Function: Observation of X-ray radiation of celestial
bodies with good time resolution over a wide spectrum range. Characterstics:
weight 96 kg, configuration regular octagonal prism, height 0.66 m, diameter
0.76m, spin stabilized. Expected life 2 years.
252 Detection of heavy cosmic particles and X-ray astronomy. Launch time 2326
GMT. Also registered by the United States in ST/SG/SER.E/26, with parameters
97.2 min, 601 x 653 km x 55.0 deg, category A.
253 Acquisition of meteorological information required for use in the
operational weather service with the aid of advanced equipment.
254 Flight under the Intercosmos programme of an international team consisting
of N N Rukavishnikov (USSR) and G I Ivanov (Bulgaria).
255 Investigation of the natural resources of the earth in the interests of
various branches of the national economy of the USSR and international
cooperation.
256 Checking of the operation of the spacecraft propulsion unit; transportation
of the crew of the Salyut-6 station back to earth.
257 Biosatellite for the continued investigation of the effects of space flight
on living organisms. Carried scientific apparatus and biological objects
from the USSR, the Czechoslovak Socialist Republic, France and the United
States of America.
258 Technological Capsule (CAT). ESA registration number: ESA/79/2. Principal
mission of the technological capsule (with ballast), which was equipped with
batteries having a lifetime of approximately 8 orbits, was to transmit back
to earth technological data on the first developmental flight L01 of the
ARIANE launch vehicle. When the batteries were exhausted, the capsule ended
its radio transmissions, and it is now inoperative but still in orbit.
ST/SG/SER.E/31 also registered the third stage of the ARIANE L01
launch vehicle, registration number ESA/79/1, with the same orbital
parameters.
259 Testing of methods for comprehensive study of the oceans and the surface of
the earth, and testing of automatic gathering of scientific information from
experimental sea and land stations. Launched under the INTERCOSMOS programme
by the Soviet Union together with the Czechoslovak Socialist Republic,
the German Democratic Republic, the Hungarian People's Republic and the
Socialist Republic of Romania.
260 Complex experimental testing of new on-board systems and assemblies under
various flight conditions and operation in conjunction with the Salyut-6
orbital station.
261 Testing of methods for obtaining operational information on the oceans.
262 Delivery of various cargoes to the Salyut-6 orbital station.
263 Experimental-technology mission. Rohini satellite RS-1.
264 Transport of a crew comprising L I Popov and V V Ryumin to the Salyut-6
station to carry out scientific and technical research and experiments.
265 Transport of the fifth international crew under the INTERCOSMOS programme,
comprising V N Kubasov (USSR) and B Farkas (Hungary) to the Salyut-6 station
to carry out scientific research and experiments.
266 Testing and development of on-board systems in the improved Soyuz T series
transport vehicle under piloted conditions. Cosmonauts Y V Malyshev and V V
Aksenov, crew.
267 Acquisition of information required for continued investigation of the
natural resources of the earth; development of remote sensing methods for
measuring the status of the earth's surface and the atmosphere
beneath the satellite.
268 Transport to the Salyut-6 station of the sixth international crew under the
Intercosmos programme, comprising V V Gorbatko (USSR) and Pham Tuan (Viet
Nam), to conduct scientific research and experiments.
269 Gathering meteorological information and data on penetrating radiation
fluxes in circumterrestrial space.
270 Transport to the Salyut-6 station of the seventh international crew under
the INTERCOSMOS programme, comprising Y V Romanenko (USSR) and A. Tomaio
Mendez (Cuba), to conduct scientific research and experiments.
271 Tests of the improved transport ship of the "SOYUZ T" series; transport to
the Salyut-6 orbital station of a crew consisting of L D Kizim, O G Makarov
and G M Strekalov to carry out repair and preventive work and scientific and
technical investigation and experiments.
272 Investigation of the corpuscular and electromagnetic radiation of the sun
and of solar plasma fluxes, study of the magnetic fields in
circumterrestrial space in order to determine the effects of solar activity
on the interplanetary medium and in the magnetosphere of the earth.
In addition to Soviet apparatus, carried scientific apparatus produced in
the USSR, the Czechoslovak Socialist Republic, the Polish People's Republic,
and Sweden under programmes of international cooperation in the exploration
and use of outer space for peaceful purposes.
273 Additional orbit given in ST/SG/SER.E/47: 1445.4 min, 35762 x 36172 km x 2.3
deg, with the note: change due to injection into final orbit.
274 Development of methods for comprehensive study of the oceans and the surface
of the earth, and testing of the experimental system of automatic gathering
of scientific information from sea and land stations. Launched under
the INTERCOSMOS programme by the USSR together with the Czechoslovak
Socialist Republic, the German Democratic Republic, the Hungarian People's
Republic and the Socialist Republic of Romania.
275 Transport to the Salyut-6 orbital station of cosmonauts V V Kovalenko and V
P Savinykh to carry out repairs and preventive maintenance and scientific
and technical investigations and experiments.
276 Transport to the Salyut-6 orbital station of the eighth international crew
under the INTERCOSMOS programme, comprising V A Dzhanibekov (USSR) and Z.
Gurragchi (Mongolian People's Republic) to conduct scientific
investigations and experiments.
277 Kiku 3 (ETS-IV). Launching organization NASDA. Acquisition of the technology
to handle a large-scale heavy satellite and test of the functions of
on-board equipment and devices, as well as confirmation of the
launching capacity of the N-II launch vehicle.
278 Hinotori (ASTRO-A). Launching organisation: Institute of Space and
Aeronautical Science, University of Tokyo. Investigation of solar flare by
X-ray telescope and spectrograph.
279 Rohini satellite D-1. This was the first developmental flight of the SLV-3
launch vehicle. The Rohini satellite carried a landmark tracker payload for
accurate orbit and attitude determination. The satellite reentered the
earth's atmosphere on 8 June 1981.
280 Experimental communications satellite. Geosynchronous altitude, longitude 10
deg East.
281 Geostationary meteorological satellite 2 (GMS-2) "Himawari-2". N launch
vehicle flight number 8 (N-II launch vehicle). Launch time 2003 UT, from
Osaki launch site at Tanegashima Space Center. Launching organization:
National Space Development Agency of Japan (NASDA). Geostationary longitude
140 deg E. Function: 1) Observation of meteorological phenomena by the
visible and infra-red spin scan radiometer. 2) Collection of weather data
from various stations. 3) Distribution of weather data to earth stations.
4) Monitoring of solar particles.
282 Experimental earth observations. Launched from a cosmodrome in the USSR.
283 Technological capsule. ESA registration ESA/81/02. Launch time 1233:03 UT.
The technological capsule, equipped with batteries for a lifetime of about
six orbital revolutions, transmits to earth technological data about test
flight L-03 of ARIANE. After discharge of the battery the capsule will stop
its transmissions and remain in orbit on inactive status. Frequency 136-138
MHz (transmission until 65h after launch only). Projected time of reentry
1986.
284 Ariane third stage. Designator ESA/81/01. Time of launch 1233:03 UT.
Frequency 2200-2300 MHz, transmission till 30 minutes after launch.
Projected time of reentry mid 1983.
285 Meteosat 2 is a geostationary meteorological satellite, operating within the
world wide network of the World Weather Watch of WMO. Its main missions are:
Imaging in the visible, IR and water vapour region of the spectrum; data
reception from so-called data collection platforms (DCPs); data distribution
to meteorological services and other interested parties (research institutes
etc). Frequency plan: 136-138 MHz (S-E); 148-149.9 MHz (E-S); 401-403 MHz
(E-S); 460-470 MHz (S-E); 1670-1700 MHz (S-E); 2025-2210 MHz (E-S). Launch
time 1233:03 UT. Geostationary position 0 deg E. Designator ESA/81/03.
286 Transport to the Salyut-6 orbital station of the ninth international crew
under the INTERCOSMOS programme, comprising L I Popov (USSR), and D.
Prunariu (Romania), to conduct scientific research and experiments.
287 Operation of the long-range telephone and telegraph radio communications
system in the USSR; transmission of USSR Central Television programmes to
stations in the Orbita network and within the framework of international
cooperation.
288 Operation of the long-range telephone and telegraph radio communications
system in the USSR; transmission of USSR Central Television programmes to
stations in the Orbita network.
289 Transmission of Central Television programmes to a network of receivers for
collective use.
290 Acquisition of information required for continued investigation of the
natural resources of the earth; development of remote sensing methods for
measuring the parameters of the atmosphere and the earth's surface
beneath the satellite. Carried scientific instruments developed in the
People's Republic of Bulgaria, as well as Soviet equipment. Objects 1595 and
1596 launched by a single rocket.
291 Conduct of scientific experiments to study diffusion and heat processes in
weightlessness.
292 Continuing research on the planet Venus; investigation of x-rays, gamma rays
and magnetic fields in space, and the characteristic features of solar wind,
cosmic rays and interplanetary plasma. Carried instruments built by Austrian
and French specialists, as well as Soviet scientific equipment.
293 Ariane L-04 technological capsule, ESA designator ESA/81/04. The
technological capsule, equipped with batteries for a lifetime of about 6
orbital revolutions (65h), transmits to earth technological data about test
flight L-04 of Ariane. After discharge of the battery the capsule will stop
its transmissions and remain in orbit in an inactive status. Frequency
136-138 MHz, projected time of reentry before 1990.
294 Ariane third stage, L04. Frequency 2200-2290 MHz. Transmission until 30 min
after launch. Projected time of reentry - end 1986.
295 MARECS-A is a geostationary maritime communications satellite, which will
form part of INMARSAT's world-wide maritime communications satellite
network. ESA designator ESA/81/06. Position in geostationary orbit 334 deg
E. Frequencies: 136-138 MHz (S-E), 148-149.9 MHz (E-S), 1535-1543.5 MHz
(S-E), 1636.5-1645 MHz (E-S), 3400-4200 MHz (S-E), 5925-6425 MHz (E-S).
ST/SG/SER.E/266: MARECS-A is a geostationary maritime mobile communications
satellite, which after being decommissioned from the International Maritime
Satellite Organization (INMARSAT) services, is used by ESA for experimental
purposes. Move of MARECS-A Spacecraft to a new position on the geostationary
orbit. Old position: 334E. New position: 22.5 E. Designator ESA/81/06. Name:
MARECS-A-EXP.
296 Intercosmos-Bulgaria 1300.
Comprehensive investigation of physical processes in the earth's ionosphere
and magnetosphere. Carried scientific equipment developed and manufactured
in the People's Republic of Bulgaria with the assistance of Soviet
scientists.
297 Investigation of physical processes in the earth's magnetosphere and
ionosphere, and study of the nature of polar aurorae. Carried scientific
equipment developed by Soviet and French specialists under the joint
Soviet-French project 'Arkad-3'.
298 Amateur radiocommunication. Radio-3 to Radio-8 launched by a single carrier
rocket.
299 Acquisition of meteorological information and data on fluxes of penetrating
radiation in circumterrestrial space.
300 Reusable space transportation system.
301 Provision of telephone and telegraph radiocommunications and transmission of
television programmes.
302 Continuation of the scientific research in progress on board manned space
complexes in the interests of science and the national economy; testing of
advanced systems and apparatus for orbital stations.
303 Transport of a crew consisting of A N Berezovoi and V V Lebedev to the
Salyut-7 station to conduct scientific research and experiments.
304 Experiments in amateur radio communications. Launched into orbit from aboard
the Salyut-7 orbital scientific station.
305 Investigation of outer space; experiments in relaying telegraph and
telephone information in the centimetre wavelength range.
306 Transport of various cargoes to the Salyut-7 orbital station.
307 Transport to the Salyut-7 orbital station of the Soviet-French international
crew, comprising V A Dzhanibekov (USSR), A S Ivanchenkov (USSR) and
Jean-Loup Chretien (France) to conduct scientific research and experiments.
308 Investigation of the upper atmosphere and outer space; trials of
experimental equipment for testing systems to determine the location of
vessels and aircraft in distress.
309 Operational multipurpose satellite for telecommunications, meteorological,
imaging and data relay, radio and television programme distribution and
direct television broadcasting for community reception. Geosynchronous orbit
longitude 74 E. A/AC.105/INF.391 was reissued as ST/SG/SER.E/79.
Also registered by the United States as 1982-31A in ST/SG/SER.E/67, with
category C and orbital parameters 1416.7 min, 35032 x 35783 km x 0.5 deg.
310 Also registered by India in A/AC.105/INF.391 and ST/SG/SER.E/79. Spent
Payload Assist Module (PAM) motor and non-functional objects originally part
of PAM and PAM-Spacecraft adapter used for Insat IA spacecraft launching.
Used to put INSAT-1A satellite into transfer orbit upon separation from
Delta 3910 in a ballistic trajectory. Orbit 166.25 km x 35126 km x 28.4 deg.
311 Engineering Test Satellite III (ETS-III) launched 0500 GMT 3 Sep 1982 from
Osaki launch site, Tanegashima. Launching organization: National Space
Development Agency of Japan (NASDA). Verification of three axis attitude
control function; verification of solar array paddle deployment function;
verification of active thermal control function; functional test of mission
equipment in the space. N launch vehicle flight no 9.
312 Transport to the Salyut-7 orbital station of a crew comprising L I Popov, A
A Serebrov and S E Savitskai to conduct scientific and technical research
and experiments.
313 Documents ST/SG/SER.E/72/Add.1 to Add.2 include the following information:
Cosmos-1402, carrying on board a small nuclear energy unit of the reactor
type, completed its programme of work and, on command from earth, ended its
active existence on 28 Dec 1982. The safety system with which the satellite
was equipped then split it into three fragments, one of which burnt up on
entry into the dense layers of the atmosphere on 30 Dec 1982. The two
remaining fragments consist of the main part of the satellite structure and
the reactor core, which has been separated from it. Before the satellite was
split into fragments, the reactor was shut off on command from earth.
According to preliminary calculations, the main part of the satellite
structure will enter the dense layers of the atmosphere during the last few
days of January and the core separated from the reactor will enter those
layers in mid February 1983. The extraction of the core from the reactor
ensures that the core will burn up in the dense layers of the atmosphere and
be dispersed into fine particles. Radio communication with the main part of
the satellite structure, maintained for two days after the satellite was
split into fragments, confirmed the fact that the reactor had been shut off
and its core had been separated. The fragments of Cosmos-1402
are being observed in order to forecast the most probable time and place of
their entry into the dense layers of the atmosphere.
Radiation after the fragments of Cosmos-1402 enter the dense layers of the
atmosphere will be within the limits recommended by the International
Commission on Radiological Protection.
Add.2: According to more precise data furnished by the competent Soviet
authorities at 7 am Moscow time, 21 January 1983, the fragment of the
Cosmos-1402 satellite's structure consisting of its main part without the
core of the nuclear reactor has a ballistic coefficient of 0.00453 sq m per
kg of weight; its altitude at apogee is 206 km, and at perigee 187 km.
The entry of the above mentioned fragment of the Cosmos-1402 satellite's
structure into the dense layers of the atmosphere is expected between 2 am
and 9 am Moscow time, 24 Jan 1983, over the area of the Arabian Sea.
Add.3: According to data furnished by the competent Soviet organizations
monitoring the flight of Cosmos-1402, the fragment of the satellite
consisting of the main part of its structure entered the dense layers of the
atmosphere over the central area of the Indian Ocean at 1:10 am Moscow time,
on 24 Jan 1983, and ended its existence. The satellite's other fragment -
the core of the energy unit reactor - will, according to projections, enter
the dense layers of the atmosphere between 3 and 8 Feb 1983 and will burn up
completely.
Add.4: According to data from the competent Soviet organizations which have
been monitoring the flight of Cosmos-1402, at 1356 hours Moscow time, a
fragment consisting of the reactor core of the nuclear energy unit entered
the dense layers of the atmosphere over the southern part of the Atlantic
Ocean and was completely burnt up.
From that time, Cosmos-1402, launched in the Soviet Union on 30 Aug 1982,
completely ceased to exist.
--------------------------------------------------------------------------------
314 Meteosat 1: positions
ST/SG/SER.E document: 73 95 132 132 132
Epoch 1982 Dec 1 1983 Dec 1 1985 May 1 1985 Jun 1 Jul 1
Position (deg E) 8.6 7.6 4.24 6.39 9.23
Drift (deg/d) 0.023 -0.052 0.0367 0.552 0.082
W station limit (deg E) 9.0 9.0
E station limit (deg E) 11.0 11.0
Ecc 0.0024 0.00133 0.000898 0.000956 0.000967
Inc 2.55 3.374 4.626 4.713 4.802
RA Node 86.74 83.488 79.184 78.636 78.228
RA Attitude 359.5 296.92 -91.297 -89.99 -88.16
Dec Attitude 87.63 88.12 87.96 87.86 88.28
Fuel press (PSI) 113.8
Fuel press (bar) 7.83
Fuel remaining (kg) 1.34 0.0 0.0 0.0
Sat RPM 110.50 101.06 99.49 99.49 99.49
315 Meteosat 2: positions
ST/SG/SER.E document: 73 95 132 132 132
Epoch 1982 Dec 1 1983 Dec 1 1985 May 1 1985 Jun 1 Jul 1
Position (deg E) 359.37 359.65 359.05 0.47 0.59
Drift (deg/d) -0.033 -0.024 -0.0170 -0.0085 0.0095
W station limit (deg E) 359.0 359.0 -1 -1 -1
E station limit (deg E) 1.0 1.0 +1 +1 +1
Ecc 0.000122 0.00026 0.00021 0.000246 0.000245
Inc 0.146 0.257 0.202 0.28377 0.205
RA Node 147.72 291.692 83.701 81.779 291.219
RA Attitude 72.74 113.77 -104.49 -91.92 -112.32
Dec Attitude 89.74 89.86 89.903 89.89 89.91
Fuel press (PSI) 159.5
Fuel press (bar) 11.0
Fuel remaining (kg) 23.92 17.64 17.64 17.64
Sat RPM 99.59 101.07 101.07 101.07
316 Geos-2 positions
ST/SG/SER.E document: 73 95 132 132 132
Epoch 1982 Dec 1 1983 Dec 1 1985 May 1 1985 Jun 1 Jul 1
Position (deg E) 33.88 32.89 322.72 222.83 126.56
Drift (deg/d) 0.06 0.052 -3.268 -3.254 -3.257
W station limit (deg E) 35.0 32.0
E station limit (deg E) 33.0 34.0
Ecc 0.000623 0.00033 0.00065 0.000745 0.00077
Inc 2.38 3.192 4.481 4.563 4.658
RA Node 80.82 80.616 77.247 76.70 76.49
RA Attitude 137.22 250.72 175.76 175.76 175.76
Dec Attitude -87.96 74.72 66.98 66.98 66.98
Fuel press (PSI) 159.5
Fuel press (bar) 11.0
Fuel remaining (kg) 3.68 0.0 0.0 0.0
Sat RPM 9.386 9.33 9.53 9.53 9.53
317 OTS-2
ST/SG/SER.E document: 73 95 132 132 132
Epoch 1982 Dec 1 1983 Dec 1 1985 May 1 1985 Jun 1 Jul 1
Position (deg E) 4.92 4.97 4.98 4.93 5.11
Drift (deg/d) -0.043 -0.026 -0.0357 -0.017 -0.0564
W station limit (deg E) 4.9 4.9 4.5 4.5 4.5
E station limit (deg E) 5.1 5.1 5.5 5.5 5.5
Ecc 0.000188 0.00020 0.000342 0.00036 0.000336
Inc 0.005 0.272 1.557 1.639 1.737
RA Node 69.98 92.914 91.481 90.285 89.745
Attitude: 3-axis
Fuel press (PSI) 156.6
Fuel press (bar) 10.8
Fuel remaining 3.69 0.85 0.84 0.83
318 MARECS-A
ST/SG/SER.E document: 73 95 132 132 132
Epoch 1982 Dec 1 1983 Dec 1 1985 May 1 1985 Jun 1 Jul 1
Position (deg E) 334.15 334.02 334.07 334.09 333.98
Drift (deg/d) -0.038 -0.028 -0.0388 -0.038 -0.026
W station limit (deg E) 333.9 334.15 334.15 334.15 334.15
E station limit (deg E) 334.1 333.85 333.85 333.85 333.85
Ecc 0.00028 0.00026 0.000298 0.000293 0.000308
Inc 1.6 0.815 0.83 0.780 0.716
RA Node 335.25 310.902 309.81 313.857 318.852
Fuel remaining (kg) 71.49 49.58 49.58 49.58
Attitude: 3-axis
319 Testing of the components and equipment of the space navigation system
established in order to locate the Soviet Union's civil aircraft and its
merchant and fishing vessels. Three satellites launched by a single carrier
rocket.
320 Conduct of experiments in the field of amateur radiocommunications.
321 CS-2a (Saukra 2-a). Launch time 0837 GMT. Launching organization NASDA
(National Space Development Agency of Japan). N launch vehicle No. 10(F)
(N-II launch vehicle). Osaki launch site, NASDA Tanegashima Space Center,
Kagoshima, Japan. Geostationary position 132 deg E. Establishment of
domestic satellite telecommunications network mainly for natural disaster,
emergency and for remote islands using submillimetre wavelength and
microwavelength signals. Development of the technology of communications
satellite.
322 Astro-B (Tenma). Launch 0510 GMT. Launching organization: ISAS (Institute of
Space and Astronautical Science). X-ray observation of X-ray stars in our
galaxy as well as X-ray galaxies using a scintillating proportional counter,
a transient X-ray source monitor, an X-ray foucsing collector, a radiation
belt monitor, a gamma ray burst detector and a star sensor.
323 CS-2b (Sakura 2b). Launch time 2029 GMT. Launching organization NASDA
(National Space Development Agency of Japan). N launch vehicle flight no. 11
(N-II launch vehicle). Domestic satellite communications; development of
communications satellite technology.
324 Experimental satellite "Offeq-1". Launch time 0934 GMT. Location: site on
the coast south of Tel-Aviv. Launching organization: Israel Aircraft
Industries, Ltd (IAI) and Israeli Space Agency (ISA). Function: 1)
Experimentation in generation of solar power; 2) Experimentation in
transmission reception from space; 3) Verification of system's
ability to withstand vacuum and weightless conditions; 4) Data collection on
space environment conditions and Earth's magnetic field.
325 Rohini satellite D-2. Second developmental flight of an SLV-3 launch
vehicle. The Rohini satellite D-2 carried a sensor payload for conducting
remote-sensing experiments and for accurate orbit and attitude
determination.
326 Testing of onboard systems, appliances and construction units of the
satellite in various flight regimes, including joint flight with the
Salyut-7 station.
327 Electrophysical research of galactic and extragalactic sources of
ultraviolet ray and X-ray emission. The scientific apparatus was built
jointly by scientists and specialists from the USSR and France.
328 Investigation of the upper atmosphere and outer space; testing of systems
for locating the position of ships and aircraft in difficulties
(COSPAS-SARSAT system).
329 Designator ESA/83/1. Launch time 1518 UT. Launching agency ESA. EXOSAT is a
space research satellite of the European Space Agency. The scientific
objectives of the EXOSAT mission are to measure the position, structural
features, spectral and temporal characteristics of cosmic X-ray sources in
the energy range from less than 0.1 keV to greater than 50 keV. Frequency
plan: E-S 2081.82 MHz + 150 kHz, S-E 2260.8 MHz + 500 kHz.
Also registered by the United States in ST/SG/SER.E/96, as category B
spacecraft with orbit 5430.4 min, 355 x 191570 km x 72.5 deg.
330 ESA/83/2: Ariane third stage. Launch time 1159 GMT. Frequency plan 2203 MHz
(S-E) till 30 min after launch. Projected time of reentry 1987. ESA/83/3:
Sylda. Upper part of dual launch adaptor 1.89m. Diameter at one end 2.815m
incurving to diameter at other end of 954 mm. Projected date of reentry
1984.
331 Designator ESA/83/4. Launch time 1159 GMT. Launch agency ESA. Geostationary
position 10+/- 0.1 deg E. EUTELSAT 1 is a regional geostationary
telecommunication Satellite for European countries. It is operated by the
EUTELSAT organization. Frequency plan: 136-138 MHz (S-E). 148-149.9 MHz
(E-S). 10.7-11.7 GHz (S-E). 14-14.5 GHz (E-S).
Positions:
Document ST/SG/SER.E/95 132 132 132
Epoch 1983 Dec 1 1985 May 1 1985 Jun 1 1985 Jul 1
East long 13.01 12.96 12.977 12.98
Drift (deg/d) -0.030 -0.0023 0.0015 0.016
Station lim W 12.9 12.95 12.95 12.95
Station lim E 13.1 13.05 13.05 13.05
Ecc 0.00029 0.000275 0.000212 0.000199
Inc 0.054 0.012 0.055 0.0606
Node 304.801 357.574 312.457 317.36
Fuel remaining kg 96.8 82.73 77.7 76.02
3-axis stabilized
332 Continued scientific investigation of the surface and atmosphere of Venus,
carried out from the orbit of its artificial satellite.
333 Transport to the Salyut-7 orbital station of a crew consisting of V A
Lyakhov, commander of the spacecraft, and A P Aleksandrov, flight engineer,
to conduct scientific and technical research and experiments.
334 Operational multipurpose satellite for telecommunications, meteorological
imaging and data relay, radio and television programme distribution and
direct television broadcasting for community reception. Geostationary
longitude 74.0 +/- 0.1 deg E. Deployment from US Space Transportation
System flight no 8, orbiter Challenger, on 31 Aug 1983.
335 Spent payload assist module (PAM) motor and non-functional objects
originally part of PAM and PAM-satellite adapter used for INSAT-1B satellite
launching. Used to put INSAT 1B into geostationary transfer orbit upon
separation from STS in 296 km circular low-earth orbit.
336 Radio telephone and telegraph communications and television broadcasting.
337 Investigation of residual radiation from the Big Bang and gamma flares in
deep space, and solar corpuscular and electromagnetic radiation plasma flows
and magnetic fields in circumterrestrial space to determine the effects of
solar activity on the interplanetary medium and the earth's magnetosphere.
In addition to Soviet scientific apparatus, carried instruments built in
Czechoslovakia and France.
338 Gathering regular information on the natural resources of the earth for use
in various branches of the Soviet economy, and conducting further tests on
new types of measuring apparatus and methods of remote sensing of the
earth's surface and atmosphere.
339 Testing components and apparatus from the space navigation system being set
up to determine the position of the Soviet civil aircraft and vessels in the
Soviet navy and fishing fleet. Three satellites launched by a single carrier
rocket.
340 Ariane third stage. Launched by European Space Agency. Launch time 0045:36
GMT. Launched spacecraft Intelsat V F7.
341 Elaboration of new kinds of information-measuring apparatus and methods of
remote investigation of the Pacific Ocean in the interests of science and of
various branches of the national economy of the USSR.
342 Continued investigation of the influence of space flight factors on living
organisms.
343 Ariane 3rd stage. Launch time 0050:03 GMT, from Kourou. Designator
ESA/84/01. Launched spacecraft Intelsat V F8.
344 Transporting a crew consisting of ship's commander L D Kizim, flight
engineer V A Solovyov and cosmonaut-research O Y Atkov to the SALYUT-7
orbital station to conduct scientific and technical studies and experiments.
345 Radio telephone and telegraph communications and transmission of television
programmes.
346 BS-2a (Yuri-2a). Domestic satellite broadcasting; development of
broadcasting satellite technology. Launch 0758 GMT. N launch vehicle flight
no 12. Launching organization NASDA.
347 EXOS-C (OHZORA). Optical study of the stratosphere and middle atmosphere.
Study of the specific phenomena of the ionospheric plasma over the southern
Atlantic geomagnetic anomaly zone which was discovered by the third
scientific satellite "TAIYO". Launch vehicle Mu-3S-4, launching organization
ISAS (Institute of Space and Astronautical Science). Launch time 0800 GMT.
348 Orbital data added in ST/SG/SER.E/104. Original registration noted "Current
elements not maintained".
349 Investigation of outer space; experiments in relaying telegraph and
telephone information in the centimetre wavelength range.
350 Continued investigations of outer space.
351 Transporting a Soviet-Indian international crew comprising ship's commander
Y V Malyshev, flight engineer G M Strekalov (USSR) and cosmonaut-researcher
R Sharma (India) to the SALYUT-7 orbital station to conduct scientific and
technical studies and experiments.
352 Provision of telephone and telegraph radiocommunications and television
broadcasting.
353 Testing components and apparatus from the space navigation system being set
up to determine the position of Soviet civil aircraft and vessels in the
Soviet merchant marine and fishing fleet. Three satellites launched by a
single rocket.
354 Telecommunications. Operating entity Telesat Canada. Longitude 104.5W.
Anik D-1 Transmit frequencies (MHz): 3720, 3740, 3760, 3780, 3800, 3820,
3840, 3860, 3880, 3900, 3920, 3940, 3960, 3980, 4000, 4020, 4040, 4060,
4080, 4100, 4120, 4140, 4160, 4180. Power 8.9 watts on each frequency.
355 Telecommunications. Operating entity Telesat Canada. Longitude 117.5W.
Transmit power 11.2 W per frequency at input of transmit antenna (typical
saturated carrier). Anik C-3 Transmit frequency (MHz): 11730, 11743, 11791,
11804, 11852, 11865, 11913, 11926, 11974, 11987, 12035, 12048, 12096, 12109
, 12157, 12170.
356 EUTELSAT 2. Launching authority European Space Agency. Launch time 1333 UT.
Geostationary orbit position 10 +/- 0.1; afterwards 7 +/- 0.1 deg E.
EUTELSAT 2 is a regional geostationary satellite for European countries. It
is operated by the EUTELSAT organization. Frequency plan: 136-138 MHz (S-E);
148-149.9 MHz (E-S); 10.7-11.7 GHz (S-E); 14-14.5 GHz (E-S). ESA designator
ESA/84/2.
ECS 2
ST/SG/SER.E document: 132 132 132
Epoch 1985 May 1 1985 Jun 1 1985 Jul 1
Position (deg E) 6.94 6.98 6.98
Drift (deg/d) 0.0012 -0.0015 -0.002
W station limit (deg E) 6.9 6.9 6.9
E station limit (deg E) 7.1 7.1 7.1
Ecc 0.000243 0.000212 0.000321
Inc 0.074 0.0187 0.0230
RA Node 228.854 64.002 63.49
Fuel remaining (kg) 100.64 94.76 93.03
Attitude: 3-axis
357 Transporting a crew comprising ship's commander V A Dzhanibekov, flight
engineer S E Savitskaya and cosmonaut-research I P Volk to the Salyut-7
orbital station to conduct scientific and technical studies and experiments.
358 ESA designator ESA/84/3. Launch time 0114:15 GMT. Launching authority ESA.
Geostationary position 177.5 deg E. MARECS PAC 1 is a geostationary maritime
mobile communication satellite which will form part of the INMARSAT
world-wide maritime communication satellite network. Frequency plan: 136-138
MHz (S-E), 148-149.9 MHz (E-S), 1535-1543.5 MHz (S-E), 1636-1645 MHz (E-S),
3400-4200 MHz (S-E), 5925-6425 MHz (E-S). MARECS B:
ST/SG/SER.E document: 132 132 132
Epoch 1985 May 1 1985 Jun 1 1985 Jul 1
Position (deg E) 177.58 177.52 177.54
Drift (deg/d) 0.0399 -0.046 -0.0195
W station limit (deg E) 177.35 177.35 177.35
E station limit (deg E) 177.65 177.65 177.65
Ecc 0.000386 0.000453 0.000504
Inc 2.82 2.743 2.662
RA Node 237.43 236.393 234.744
Fuel remaining (kg) 85.55 88.54 88.52
Attitude: 3-axis
ST/SG/SER.E/266: MARECS-B-ATL. Move to a new position. Old position: 177.5E.
New position: 345 deg E.
359 Three stage launch vehicle which placed the SPACENET F1 satellite (USA) into
orbit. Launch time 0133:29 GMT. Ariane V9 launch vehicle launched by
Arianespace S.A.
360 AMPTE-Ion Release Module, reg. no. D-R 002. Scientific research on the
Earth's magnetosphere and plasma physics, in particular active
experimentation by releasing ion clouds of lithium or barium (total of 7) in
and outside the magnetosphere. Creation of an artificial comet (1 barium
cloud inside the magnetosheath). Diagnosis and experimentation in
conjunction with the simultaneously launched satellites CCE (United States)
and UKS (United Kingdom). Frequency plan: 2103.64375 MHz (uplink), 2284.50
MHz (downlink).
361 Gathering of operational information and continued trials of new kinds of
information and measurement apparatus and methods of remote investigation of
the seas and oceans and the earth's surface in the interests of science and
of various branches of the national economy of the USSR.
362 GMS-3 (Himawari-3). Launch 2030 GMT. Improvement of meteorological
observation. Development of meteorological satellite technology. N Launch
vehicle flight no 13. Launching organization NASDA.
363 Investigations of the planet Venus and Halley's Comet. Fitted with
scientific apparatus and equipment built in the USSR, Austria, Bulgaria,
Hungary, German Democratic Republic, Poland, France, Federal Republic of
Germany and Czechoslovakia.
364 MS-T5 (Sakigake). Launch time 1926 GMT. Verification of the fundamental
technology related to the interplanetary missions, including deep-space
communication, attitude control, attitude determination and so forth. Study
and observation of solar wind and plasma waves and interplanetary magnetic
field. Launching organisation: Institute of Space and Astronautical Science
(ISAS). Heliocentric orbit parameters: 318.8 days, 151.4 x 121.9 million km
(0.815 x 1.012 AU), inclination 1.439 deg.
365 Investigation of the upper atmosphere and outer space. Six satellites
launched by a single carrier rocket.
366 Communication and geophysics research satellite. Launch time 1127 GMT.
Also registered by the United States in ST/SG/SER.E/59, with category D and
orbital parameters 95.3 min, 531 x 533 km x 97.5 deg.
367 Communication and geophysics research satellite. Launch time 1759 GMT.
368 Magnetosphere research satellite. Launch time 1447 GMT. [Document quotes
geocentric distances, which have been converted to orbital heights.]
369 ESA designator ESA/85/2. Launch time 1123:13 GMT. Giotto is a scientific
spacecraft carrying more than 10 experiments with the objective to
investigate Halley's Comet. Giotto is scheduled to encounter the
comet on 13 March 1986. Its distance from the comet at encounter is 500 km.
The spacecraft will be destroyed at encounter. Frequency plan: 2116.723 MHz
(E-S), 2298.704 and 8428.580 MHz (S-E). Launching authority: European Space
Agency. Orbital parameters: Trajectory towards Halley's Comet.
370 ESA designator ESA/85/2. Launch time 1123:13 GMT. Ariane third stage.
371 Prognoz-10-Intercosmos. Investigation of the structure of interplanetary and
circumterrestrial shock waves generated by the interaction of the solar wind
and the earth's magnetosphere. Carries scientific apparatus developed by
scientists and specialists of the USSR and the Czechoslovak Socialist
Republic in the 'Intercosmos' programme of international cooperation in the
exploration and peaceful uses of outer space.
372 Delivery to the Salyut-7 orbital station of a crew consisting of flight
commander V A Dzhanibekov and flight engineer V P Savinykh to carry out
routine preventive maintenance and scientific and technical research and
experiments.
373 Delivery to the Salyut-7 orbital station of a mixed cargo with a total mass
of 2000 kg.
374 Orbital data from ST/SG/SER.E/134.
375 PLANET-A (SUISEI). Launch time 2333 GMT. Imaging of the hydrogen coma of
Halley's comet by the hydrogen Lyman alpha line. Measurement of the solar
wind in the cruising phase and in the vicinity of the comet. Launching
organization ISAS. Heliocentric orbit parameters 282 days, inclination 0.888
deg, 151.42 x 100.5 million km (1.0122 x 0.6718 AU).
376 Continued investigations of the influence of space flight factors on living
organisms and radiation physics research.
377 Telecommunications. Longitude 111.5 deg W. Operating entity Telesat Canada.
Transmitter power 8.9 watts at each frequency. Frequencies 3720 to 4180 MHz
spaced by 20 MHz.
378 Transporting a crew comprising ship's commander V V Vasyutin, flight
engineer G M Grechko and cosmonaut-researcher A A Volkov to the Salyut-7
orbital station to conduct scientific and technical studies and experiments.
379 Testing the equipment, assemblies and design components of a satellite in
various modes of flight, including joint flight with the Salyut-7 station.
380 AMSAT Oscar 10, registration no D-R 001. Scientific and communication
satellite for the amateur radio service. Frequency plan: Transponder U:
435.1 MHz (uplink), 145.9 MHz (downlink), Bandwidth +/- 75 kHz.
Transponder L: 1269.45 MHz (uplink), 436.55 MHz (downlink), bandwidth +/-
400 kHz. Two beacons adjacent to passband. Launch vehicle Ariane L6.
381 Acquisition of operational information on the natural resources of the earth
in the interests of various branches of the national economy of the USSR;
continued trials of new types of informational and measurement
apparatus and methods of remote sensing of the earth's surface and
atmosphere.
382 Further improvement of the meteorological system using artificial earth
satellite, including development of informational and measurement apparatus
and remote sensing methods.
383 Continuation of the investigation of outer space; experimental
retransmission of telephone and telegraph data in the centimetre band.
384 ST/SG/SER.E/141: Some fragments remain in and around the 1979-17A orbit.
385 Inclination corrected from 75.9 to 65.9 in ST/SG/SER.E/144.
386 Orbital scientific station for conducting studies and experiments in the
interests of science and the national economy.
387 Scientific satellite for the investigation of space plasma physics in the
part of the magnetosphere close to the Earth, particularly in connection
with the auroral phenomena. The nominal mission period is eight months but
an extension can be envisaged. ST/SG/SER.E/167: The satellite Viking has
ceased to function on 12 May 1987 due to a gradual degradation of its
electrical power supply system. The satellite remains, however, in Earth
orbit. See also ST/SG/SER.E/352.
388 Transporting a crew comprising ship's commander L D Kizim and flight
engineer V A Solovyov to the Mir orbital station to conduct scientific and
technical studies and experiments.
389 Transporting sundry cargoes to the Mir orbital station.
390 BS-2b (Yuri-2b). Domestic satellite broadcasting; development of
broadcasting satellite technology. Launching organization NASDA. N launch
vehicle flight no 14. Launch time 0755 GMT.
391 Comprehensive experimental testing of spacecraft in independent flight and
jointly with the Mir orbital station.
392 Continuation of research on materials science in space.
393 Acquisition of operational oceanographic information in the interests of
various branches of the national economy of the USSR and international
cooperation; continued trials of new types of informational and measurement
apparatus and methods of remote sensing of the earth's surface and
atmosphere.
394 Telecommunications. Operating entity TELESAT Canada. Longitude 110 W.
Transmit power 11.2 W on each frequency. Frequencies 11730, 11743, 11791,
11804, 11852, 11865, 11913, 11926, 11974, 11987, 12035, 12048, 12096, 12109,
12157, 12170 MHz.
395 Telecommunications. Operating entity TELESAT Canada. Longitude 107.5 W.
Transmit power 11.2 W on each frequency. Frequencies 11730, 11743, 11791,
11804, 11852, 11865, 11913, 11926, 11974, 11987, 12035, 12048, 12096, 12109,
12157, 12170 MHz.
396 EGS (Ajisai). Improvement of the accuracy of domestic geodetic triangulation
network. Determination of accurate location of remote islands. Clarification
of the relationship between Japanese geodetic system network and those of
other areas of the world. Launch vehicle H-I (two-stage) test
flight no. 1. Launch time 2045 GMT. Launching organization NASDA.
397 JAS-1 (Fuji). Amateur satellite communications. Development of amateur
satellite technology. Launch vehicle H-I (two-stage) test
flight no. 1. Launch time 2045 GMT. Launching organization NASDA.
398 MABES (Jindai). Experiment on the levitation of the magnetic bearing
flywheel under zero-g condition.
399 Third stage of a three stage launch vehicle, launched from Kourou (CSG).
400 Communications satellite. Registration France 1984-2.B (Telecom 1A) 1985-2.B
(Telecom 1B). 1988-1-C (Telecom 1C).
401 Remote sensing satellite. Registration 1986-1.B
402 MOS-1 (Momo-1). Observation of marine phenomena such as sea color and
temperature. Establishment of common technology necessary for Earth
observation satellites. Launching organization NASDA. Launch time 0123 GMT.
403 ASTRO-C (Ginga). Observation of variabilities of X-rays from active galactic
nuclei and galactic compact sources. Launching organization ISAS. Launch
time 0630 GMT.
404 Development of research apparatus and methods of remote sensing and
monitoring of the Earth's ionosphere, and also study of the propagation of
radio waves in the ionosphere.
405 Transport of a crew consisting of ship's commander Y V Romanenko and flight
engineer A I Laveikin to the orbital station to conduct scientific and
technical research and experiments. Orbital parameters are after correction.
406 Extra-atmospheric astronomic research and resolution of a number of problems
with scientific and economic applications.
407 Conduct of experiments on the production of semi-conducting materials and
super-pure biological preparations in micro-gravity.
408 Location of vessels in the Soviet merchant marine and shipping fleet
anywhere at sea; facilitation of amateur radio communication and conduct of
experiments for scientific and educational purposes.
409 Acquisition of operational oceanographic information in the interests of
various branches of the national economy of the USSR and international
cooperation.
410 Transport to the Mir orbital space station of a Soviet-Syrian crew
comprising cosmonauts A S Viktorenko, A P Aleksandrov and M A Faris to
conduct joint research and experiments with cosmonauts Y Romanenko and
A Laveykin.
411 Remote sensing of the earth's surface, oceans and seas in the interests of
various branches of science and the economy.
412 ETS-V (Kiku-5). Establishment of basic technology for bus systems needed for
3-axis stabilized geostationary satellites. Accumulation of key technologies
required for high performance in the next generation of applications
satellites; Experiment of mobile satellite communications for the
control of aircrafts over the Pacific Ocean, and for the communication,
navigational aid, search and rescue of ships. H-I (3-stage) launch vehicle.
Launching organization NASDA. Launch time 0920 GMT.
413 Investigation of outer space; relaying of telephone and telegraph
information.
414 Transporting a crew comprising ship's commander V G Titov, flight engineer M
K Manarov and cosmonaut-investigator A S Levchenko to the Mir orbital
station to conduct scientific research and experiments.
415 Transmitting USSR Central Television programmes to a network of communal
receivers.
416 ST/SG/SER.E/176/Add.1: The artificial earth satellite Cosmos-1900 with a
nuclear power plant on board was launched on 12 Dec 1987 in the Soviet
Union. According to data from the competent Soviet organizations, radio
contact with the satellite was lost in Apr 1988. The satellite is still
in a steady trajectory and the main support systems are working to
programme. The satellite will continue its flight in orbit until Aug-Sep
1988, after which it will cease to exist. The Cosmos-1900 satellite has
systems ensuring radiation safety on completion of its flight. The flight of
the Cosmos-1900 satellite is being monitored constantly.
ST/SG/SER.E/176/Add.2: As has already been reported, on board the
Cosmos-1900 spacecraft is a nuclear power plant. The plant includes a small
nuclear reactor, the core of which consists of fuel elements containing
uranium-235 enriched uranium. The core is surrounded by a beryllium
reflector which contains the regulating devices making it possible to
control the reactor and to shut it down after its work has been completed.
The radiation safety of the Cosmos-1900 spaceraft is ensured by transferring
the nuclear power plant to an orbit higher than 800 km, in which decay of
the reactor's radioactive products takes place. The ejection of the power
plant, which is separable from the spacecraft, is carried out from Earth by
radio command, or automatically after the satellite's systems have attained
the established levels of work. In the case of a failure of the device for
automatic ejection of the power plant into a high orbit, a system is
activated which dismantles the nuclear reactor as the satellite enters the
atmosphere. This system ensures that the radiation situation will be within
the limits recommended by the International Commission on Radiological
Protection. According to data from the competent Soviet organizations, the
satellite is still in a steady trajectory, and its entry into the atmosphere
cannot occur earlier than Aug or Sep 1988. The flight of the Cosmos-1900
satellite is being constantly monitored.
ST/SG/SER.E/176/Add.3: The Cosmos-1900 satelllite, launched into orbit in
the Soviet Union on 12 Dec 1987 with a nuclear power plant on board and
intended for observation of the ocean surface. The satellite is at present
still in a steady trajectory, and its main support systems are operating
normally. On 22 Sep 1988 the orbital parameters of Cosmos-1900 were: apogee
214 km and perigee 193 km. The Cosmos-1900 satellite is equipped with main
and backup radiation safety systems, as recommended by the UN Committee on
the Peaceful Uses of Outer Space. The main system is designed to eject the
nuclear power plant into a high altitude orbit in which it will remain for a
time sufficient to reduce the radioactivity to a safe level. The design of
the satellite provides for the ejection system to engage automatically if
the satellite's stability is impaired, if the instrument compartment
loses pressure or if irregularities occur in the on-board energy supply
system. In the absence of radio communications with the satellite, this
system may go into operation at any moment up to the cut-in of the backup
safety system. The backup system, which cuts in if the main system fails,
separates the reactor core from the reactor housing when reentry and heating
take place (at an altitude of about 100 km). This separation of the core and
its independent reentry into the atmosphere ensure that it will burn up
completely in the dense layers of the atmosphere and the fuel will be
dispersed (scattered in fine particles) in sich a way as to have no
substantial impact whatsoever on radiation levels in the fallout zone.
Forecasts indicate that, if a stable trajectory is maintained and if the
nuclear power plant is not previously ejected, the satellite's
entry into the dense layers of the atmosphere is likely to take place
between 4 and 8 Oct 1988. At present, while the Cosmos-1900 satellite
continues in a steady trajectory, accurate prediction of when and where it
will enter the dense layers of the atmosphere is not possible. The competent
services of the Soviet Union are continuing to monitor the satellite
closely. Official notification of the trajectory of the Cosmos-1900
satellite has been transmitted to the International Atomic Energy Agency
(IAEA). Further information on the satellite's trajectory will be supplied
in due course.
ST/SG/SER.E/176/Add.4: As of 0800 hours on 30 Sep 1988, the Cosmos-1900
satellite is continuing a steady trajectory. The orbital parameters are:
apogee 192 km and perigee 174 km. If the steady trajectory is maintained,
reentry of the satellite into the dense layers of the atmosphere
is forecast for the period between 1500 hours on 4 Oct and 0600 hours on 6
Oct 1988 (Moscow local time in all cases). The reactor core of the
Cosmos-1900 satellite comprises 37 cylindrical fuel elements surrounded by
beryllium reflectors. The nuclear fuel (total mass of 31.1 kg) consists of
a uranium-molybdenum alloy (3 percent by weight) with a 90 per cent
enrichment of uranium-235. Upon reentry into the dense layers of the
atmosphere and after the cut-in of the back-up safety system, the reactor
core will be destroyed, becoming fine particles of between 60 and 880
micrometres in size which are indissoluble in the natural environment and do
not enter the food chain. Furthermore, the level of irradiation in the
population, in the event of maximum fall-out, will not exceed
0.5 rem/year. The reactor incorporates a lateral beryllium reflector which
includes 6 cylindrical rods, each having a mass of 3.6 kg and measuring 100
mm x 250 mm, the radioactivity of which will be insignificant. Should they
reach the Earth's surface, no direct danger will be posed to the
population, unless, however, the rods are exposed. The remaining components
of the Cosmos-1900 satellite, should they reach the Earth's surface, will
present no radiation danger. The competent services of the Soviet Union
continue to observe the satellite closely and are making the relevant
calculations. ST/SG/SER.E/176/Add.5: On 1 October 1988 at 0008 hours Moscow
time, the radiation safety system on the Cosmos-1900 satellite with a
nuclear power plant on board, launched into orbit in the Soviet
Union on 12 Dec 1987, automatically cut in. The reactor was shut off and the
nuclear power plant was separated from the satellite and transferred to a
long-life orbit at an altitude of about 720 km in which it will remain for a
time sufficient to reduce the radioactivity to a safe level. The
remaining part of the satellite (the instrument compartment), which will
soon burn up in the dense layers of the atmosphere, does not pose any
radiation hazard. ST/SG/SER.E/176/Add.6: As has already been reported, on 1
Oct 1988 the radiation safety system on the Cosmos-1900 satellite with a
nuclear power plant on board automatically cut in. In accordance
with the programme of the spacecraft's on board systems, the reactor was
shut off; it was separated from the satellite and transferred to a long-life
orbit where the radioactive products of the reactor will decay to a safe
level. On 2 Oct 1988 at 0126 hours Moscow time, the remaining
part of the satellite, which poses no radiation hazard, entered into the
dense layers of the atmosphere and ceased to exist above the Indian Ocean.
417 A Proton carrier rocket was put into staging orbit to test components, also
apparatus for a space navigation system. The satellites were not put into
their designed orbit owing to a malfunction in the separation assembly
controls.
418 Indian Remote Sensing Satellite (IRS-1A). Operational remote sensing of the
Earth for natural resources management applications. Also registered by the
USSR as object no. 2387 in ST/SG/SER.E/182 and orbital parameters 102.7 min,
863 x 917 km x 99.01 deg.
419 Because of a malfunction of the solar generator, the satellite is being used
only for technical tests. Geostationary position 19 W. Launch by Ariane-2
flight no. 20. Additional info in ST/SG/SER.E/231: Due to a malfunction of
the solar generator, TV-SAT 1 was taken out of commission and sent to a
so-called parking orbit beyond the geostationary orbit. Semi-major axis
42485.605 km. Eccentricity 0.00116. Inc 0.716, Arg of perigee 216.66,
RA 76.77, Mean anomaly 47.1 Mean drift -4.071 deg/day, E long 350.617,
latitude -0.713.
420 Research in material science in space (production of semiconductor materials
with improved properties and very pure biologically active substances)
421 Investigation of the seas and oceans and the processes occurring in the
earth's atmosphere.
422 Coverage of the national territory with television, radio and telephony
signals and data transmission. Geostationary satellite.
423 Testing of components and systems for a space-based navigation system being
constructed to track Soviet civil aircraft and naval and fishing vessels.
424 CS-3A (Sakura 3-A). To continue communications services provided by the
communications satellite 2 (CS-2). To meet increasing and diversifying
demands for communications. To develop technologies for communications
satellites. Launch vehicle H18F. Launching organization NASDA. Launch time
1005 GMT.
425 Meteosat P2 is a geostationary meteorological satellite operating within the
world wide network of the World Weather Watch of the World Meteorological
Organization. Its main missions are: Imaging in the visible, IR and water
vapour region of the spectrum; data reception from so-called Data Collection
Platforms (DCPs); data distribution to meteorological services and other
interested parties (research institutes, etc). Frequency plan 136-138 MHz
(S-E), 148-149.9 MHz (E-S), 401-403 MHz (E-S), 1670-1700 MHz (S-E),
2025-2110 MHz (E-S). Geostationary position 0 deg E. ESA designator
ESA/88/02. Launch time 1119:33 UT.
426 Third stage of the three-stage Ariane IV launch vehicle. Frequency plan
2200-2300 MHz, transmission until 30 min after launch. ESA designator
ESA/88/01.
427 ECS-5/Eutelsat I F5 is a regional geostationary telecommunications satellite
for European countries. It is operated by the EUTELSAT organization.
Frequency plan 136-138 MHz (S-E), 148-149.9 MHz (E-S), 10.7-11.7 GHz (S-E),
14.0-14.5 GHz (E-S). Launch time 2334:00 UT. ESA designator ESA/88/03.
428 Transport to the Mir orbital station of a Soviet/Bulgarian crew comprising
cosmonauts A Y Solovyev, V P Savinykh and A P Aleksandrov (Bulgaria) to
conduct joint research and experiments with cosmonauts V G Titov and M K
Manarov.
429 Outer space research.
430 Gathering of up-to-date oceanographic information and data on ice conditions
in the interests of the Soviet economy and international cooperation.
431 Investigation of the planet Mars, its moon Phobos, the Sun and
interplanetary space jointly with Austria, Bulgaria, Czechoslovakia,
Finland, France, the German Democratic Republic, the Federal Republic of
Germany, Hungary, Ireland, Poland, Sweden, Switzerland, and the European
Space Agency.
432 Continued improvement of the meteorological system using artificial earth
satellites, including the testing of information-gathering and measuring
apparatus and of remote sensing methods.
433 Operational multipurpose satellite for telecommunications, meteorological
imaging and data relay, radio and television programme distribution and
direct television broadcasting for community reception. Geosynchronous orbit
longitude 93.5 +/- 0.1 deg east. Launch vehicle Ariane 3 launch
vehicle of Arianespace, 24th flight of Ariane and 9th flight of the Ariane 3
version.
434 Investigation of outer space and relay of telegraph and telephone messages.
435 Transport to the Mir orbital station of a Soviet-Afghan crew comprising the
cosmonauts V A Lyakhov, V V Polyakov and A A Momand (Afghanistan) to conduct
joint research and experiments with the cosmonauts V G Titov and M K
Manarov.
436 Dual launching system (SYLDA) of a three stage launch vehicle.
437 Direct broadcasting satellite. French registration: TDF-1, 1988-5-B.
438 Dual launching carrier structure (SPELDA).
439 Two-orbit test flight of a reusable orbital vessel around the Earth and
automatic landing at the Baikonur cosmodrome. On 15 Nov 1988 at 0925 hours
Moscow Time the orbital vessel made an automatic landing at the Baikonur
cosmodrome.
440 Transport to the Mir orbital station of a Soviet-French international crew
comprising cosmonauts A A Volkov, S K Krikalev and J-L Chretien (France) to
conduct research and experiments jointly with cosmonauts V Titov, M Manarov
and V Polyakov.
441 Communication satellite. Launching states: Australia and France. Longitude
164 deg E +/- 0.5. (orbit given is geocentric 42164 km, which corresponds to
altitude 35787 km).
442 Acquisition of data to enhance accuracy in identifying and forecasting
movements of space apparatus, and for geophysical and geodetic research.
443 Investigation of the natural resources of the earth in the interests of the
national economy of the USSR and international cooperation; survey of
seismically active regions of the country, including the Armenian SSR, in
the interests of industrial and non-industrial construction.
444 CS-3B (Sakura 3-B). To continue communications services provided by the
communications satellite 2 (CS-2). To meet increasing and diversifying
demands for communications; to develop technologies for communications
satellites. Launch vehicle H-I (H19F). Launching organization NASDA. Launch
time 0959 GMT.
445 EXOS-D (Akebono). Observation in high precision of behaviour and
acceleration mechanism of aurora particles in Earth magnetosphere. Launching
organization ISAS. Launch time 2330 GMT.
446 High power telecommunications satellite with a dual mission; direct TV
broadcasting and data communications. Four active transponders with two
redundant; power output 200 W per transponder. Coverage area -
East Nordic coverage zone as defined by ITU (WARC-77). Mission period
estimated to be 6 to 8 years. Position 5 deg E.
ST/SG/SER.E/335: The Swedish satellite TELE-X, registration number 89.027.01,
has ceased functioning. The satellite was switched off on 16 January 1998,
after having been transferred to a graveyard orbit, 300 km above the
geostationary orbit. See also ST/SG/SER.E/352.
447 Investigation of the natural resources of the Earth in the interests of
various branches of the Soviet economy and international cooperation;
space-based survey of the central part of Antarctica for purposes of mapping
inaccessible regions of that continent.
448 Space materials research (production of enhanced performance semiconductors
and especially pure biologically active substances in microgravity
conditions). Jointly with France.
449 Resurs-F: Investigation of the natural resources of the earth in the
interests of various branches of the Soviet economy and international
cooperation. Satellite carries two passive separable "Pion" probes to
investigate upper atmospheric density.
450 Maintenance of telephone and telegraph radio communications.
451 Location of vessels in the Soviet merchant marine and fishing fleet; work
within the international space search and rescue system for locating vessels
and aircraft in distress (COSPAS-SARSAT).
452 Testing of on-board systems under different conditions and delivery of
expendable materials and sundry cargo to the Mir manned space station.
Advanced cargo carrier.
453 Transport to the Mir orbital station of a team consisting of A S Viktorenko,
commander of the spacecraft, and A A Serebrov, on-board engineer, to carry
out scientific and technological research and experiments.
454 Investigation of the natural resources of the Earth in the interests of the
Soviet economy and international cooperation; and the conduct of
biotechnological experiments under a commercial agreement with the firm
Interspace (Federal Republic of Germany).
455 Investigation of the effect of weightlessness and cosmic radiation on the
vital processes of biological specimens in co-operation with Canada,
Czechoslovakia, France, the German Democratic Republic, Hungary, Poland,
Romania, the United States and the European Space Agency.
456 Comprehensive study of the processes of propagation of low-frequency
electromagnetic waves in the earth's magnetosphere and their interaction
with charged particles of the radiation belts, in cooperation with Bulgaria,
Czechoslovakia, the German Democratic Republic, Hungary, Poland
and Romania (the international scientific project entitled 'Aktivny').
Carrying the Czechoslovak Magion-2 satellite.
457 Operation of the long-range telephone and telegraph radio-communications
system and transmission of television programmes.
458 Research of the magnetosphere and the ionosphere of the Earth. The
Czechoslovak satellite Magion 2 was launched into orbit by the Soviet
spacecraft Intercosmos 24. Magion 2 forms a part of the scientific programme
of Intercosmos 24 (project Aktivnyj) launched from USSR territory on
28 Sep 1989. The Czechoslovak satellite Magion 2 was separated into an
autonomous orbit on 3 Oct 1989. Magion 2 was also registered by the USSR in
ST/SG/SER.E/215, with the following information: Execution of the scientific
programme of the "Aktivny" project in conjunction with Intercosmos-24,
permitting simultaneous spatially separating investigations of plasma
processes in circumterrestrial space. Czechoslovak satellite, separated from
Intercosmos-24 (launched on 28 Sep 1989) on 3 Oct. ST/SG/SER.E/215 assigned
Magion 2 the registration number 2547; however in ST/SG/SER.E/215/Add.1,
the dual registration was noted and the USSR registration of Magion 2 was
cancelled. The number 2547 was reassigned to Progress M-3.
459 Military communications. Previously registered by the United States in
A/AC.105/INF.220: 1969-101A, orbital data 276 x 36716 km x 28.0 deg,
category C.
460 Military communications.
461 Testing data-measuring equipment and methods for remote sensing of the
atmosphere and Earth's surface to benefit the Soviet economy and science.
462 Delivery to the Mir orbital station of additional equipment and apparatus
for the purpose of expanding the research and experiments conducted in the
interests of science and the national economy.
463 Granat orbital observatory.
Conduct of studies of X-ray and soft gamma ray radiation sources in space by
the USSR jointly with France, Denmark and Bulgaria.
464 Delivery of various cargoes to the Mir orbital station, including scientific
apparatus produced in the United States of America and intended, pursuant to
a commercial agreement, for the conduct of experiments on space
biotechnology.
465 Relaying of telegraph and telephone information.
466 Direct broadcasting system. Expected operational life, 10 years.
Owner/operator: British Satellite Broadcasting Ltd, The Marcopolo Building,
Chelsea Bridge, Queenstown Rd, London SW8 4NQ.
See also ST/SG/SER.E/352 and 377: 1989-67A bought by Sweden and renamed Sirius 1.
Re-registered by Sweden with the UN in 1999 and in 2000.
467 Military communications. Expected life approx 7 years. Owner/operator:
Ministry of Defence, Main Building, Whitehall, London SW1A 2HB.
468 Demonstration of store and forward communications with extensive radiation
monitoring experiments. Still transmitting on 1 Mar 1990. Owner/operator
University of Surrey, Dept of Electronic and Electrical Engineering,
Guildford, Surrey GU2 5XH.
469 Technology demonstration mission carrying solar cell experiments. Not
thought to be still transmitting. Owner/operator University of Surrey, Dept
of Electronic and
Electrical Engineering, Guildford, Surrey GU2 5XH.
470 ST/SG/SER.E/222: State of registry was United Kingdom. (15th in register)
Fixed-satellite telecommunication services and transmission of television
signals. Operational life about 10 years. Orbital position 105.5E.
Owner/operator: Asia Satellite Telecommunications Co, Ltd. 23-24/F, East
Exchange Tower, 38-40 Leighton Rd, Hong Kong. Telex 68345 ASAT HX Fax 852
576 4111.
ST/SG/SER.E/333: UK ceased to be the state of registry.
ST/SG/SER.E/334: With effect from 1 July 1997 carried on the register of
Space Objects of the Hong Kong Special Administrative Region of the
People's Republic of China. Therefore from that date the People's Republic
of China has been the State of registry.
471 Transport to the Mir orbital station of a crew comprising the cosmonauts A Y
Solovyov and A N Balandin to conduct an extensive programme of geophysical
and astrophysical research, experiments on biology and biotechnology and
work on space materials science.
472 Domestic communication. Launching states: Japan, France, USA. Launch vehicle
Ariane 29 (Ariane IV). Launching organization ARIANE SPACE. Launch time 1129
GMT.
473 GMS-4 (Himawari-4). Improvement of meteorological observation. Development
of meteorological satellite technology. Launch vehicle H-I (H20F). Launching
organization NASDA. Launch time 1911 GMT.
474 Domestic communications. Launching organization Martin Marietta. Launch time
0007 GMT.
475 Development of swingby technique for future missions. MUSES-A "Hiten".
Launching organization ISAS. ST/SG/SER.E/272: Launch time 1146 UT. Decay
date Apr 11, 1993. Orbit parameters:
M50-EM Period 6.665 days, inc 30.63 deg, 262.49 x 286182.72 km, epoch 1990
Jan 25.
M50-EC Period 4.53 days, inc 38.90 deg, perilune 2289.67 km, apolune
49013.93 km, epoch 1992 Feb 17.
476 Continuation of Earth observation functions of MOS-1; establishment of
common technology necessary for Earth-observation satellites. Launching
organization NASDA. Name MOS-1b "Momo-1b". Launch time 0133 UT.
477 DEBUT "Orizuru". Experiment of extending and contracting boom; experiment of
expanding and contracting aerodynamic brake. Launching organization NASDA.
Launch time 0133 UT.
478 JAS-1b "Fuji-2". Continuation of amateurradio services of JAS-1; extension
of amateur radio communications area; advancement of amateur radio
technology. Launching organization NASDA. Launch time 0133 UT.
479 Operational multi-purpose satellite for telecommunications, meteorological
imaging and data relay, radio and television programme distribution and
direct television broadcasting for community reception. Orbital position 83
deg E. Also registered as 1990-51A in ST/SG/SER.E/250 by the United States,
with category B and orbital parameters 1426.3 min, 35768 x 35811 km x 0.2
deg.
480 Space materials research.
481 Testing of components and apparatus of the Glonass global space navigation
system being set up to determine the position of the Soviet Union's civil
aircraft and vessels in its merchant marine and fishing fleet.
482 Investigation of the natural resources of the Earth in the interests of
various branches of the national economy of the USSR; solution of problems
relating to ecology and international cooperation. In accordance with a
commercial agreement, apparatus belonging to the Federal Republic of
Germany is also being carried for the purpose of conducting
biotechnological experiments.
483 Specialized module. Experimental-industrial production of semi-conducting
materials; refinement of biologically active substances for the production
of new medicinal preparations. Cultivation of crystals of different
albumine compositions and hybridization of cells. Conduct of astrophysical
and technical experiments.
484 National operational communications satellite. Designation 1990-2.
485 Third stage of a three stage rocket.
486 Second stage of a two stage rocket. Apogee originally given as 965.1 km but
was amended to 985.1 km in ST/SG/SER.E/229/Corr.1
487 Provision of telephone and telegraph communications and transmission of
television programmes, continuation of work in the context of the
"Intercosmos" programme for the development of new frequency ranges and the
creation of long-range systems of space communications jointly with the
Byelorussian SSR, GDR, Hungary and Czechoslovakia.
488 Launched on an erroneous orbit. There is no communication with the
satellite.
489 Gathering round-the-clock meteorological information.
490 Direct broadcasting satellite. Position 19 deg W. Ariane 4, flight no 33.
491 Communications satellite, position 23.5E, Ariane 4 flight no 20.
492 Communications satellite, position 28.5E Ariane 4 flight no 37.
493 Research in the field of high-energy astrophysics conducted jointly with
France and Poland. Gamma automatic observatory.
494 Investigation of the natural resources of the Earth in the interests of
various branches of the national economy of the USSR; solution of problems
relating to ecology and international cooperation.
495 Transport to the Mir manned orbital station of the crew consisting of the
cosmonauts G M Manakov and G M Strekalov for the purpose of carrying out a
programme of geophysical and astrophysical research, biological and
biotechnological experiments, and work on space-materials science.
496 Telecommunications satellite. Registered by France in ST/SG/SER.E/234 and
239 until EUTELSAT can register the satellite. EUTELSAT is the European
Telecommunications Satellite Organization. Also registered by France in
ST/SG/SER.E/287, where it was given the designation 1991-1B.
497 Continuation of broadcasting services by BS-2; accommodations to increasing
and diversifying demands for broadcasting; establishment of common
technology necessary for broadcasting satellite. Launching organization
NASDA. Launch time 0905 GMT. BS-3a "Yuri-3a".
498 Transport to the Mir manned orbital station of the international crew
consisting of the cosmonauts V M Afanasyev, M Kh Manarov, and T Akiyami
(Japan) for the purpose of carrying out joint work with the cosmonauts G M
Manakov and G M Strekalov. Launch jointly with the private Japanese company
TBS.
499 Further expansion of the long-range telephone and telegraph
radio-communications system in the territory of the USSR.
500 Earth observation satellite. Registration 1990-1-B.
501 Direct broadcasting satellite. Registration 1990-2-B.
502 Routine communications, collection and relaying of information in the
interests of the Ministry of Geology of the USSR and other branches of the
country's national economy, and the development of communications between
amateur radio-operators.
503 Testing of components and equipment of a space navigation system being set
up to determine the position of civil aircraft and ships of the USSR
merchant marine and fishing fleet at any point on the oceans and seas.
504 Investigation of outer space and of processes occurring in the Earth's
atmosphere.
505 Direct broadcasting system. Expected operational life 12.5 yr.
Owner/operator: British Sky Broadcasting Ltd, 6 Centaurs Business Park,
Grant Way, Isleworth, Middlesex TW7 5QD.
506 Surveying of the territory of the Soviet Union and of other countries for
purposes of geology, cartography, oceanology, ecology and agriculture, and
study of the ice situation at high latitudes.
507 United Kingdom military communications satellite. Owner/operator: UK
Ministry of Defence. Expected operational life 10 years.
508 Transport to the Mir orbital station of an international crew comprising
the cosmonauts A. Artsebarsky (USSR), S. Krikalev (USSR) and H. Sharman
(United Kingdom) to conduct joint work with the cosmonauts V. Afanasev
(USSR) and M. Manarov (USSR).
509 Investigation of the natural resources of the earth in the interests of the
various branches of the national economy of the USSR, and solution of
problems relating to the environment and to international cooperation.
510 Investigation of features at the Earth's atmosphere. Launched with the Mir
orbital station.
511 Operational remote sensing satellite for natural resources management.
512 Maintenance of telephone and telegraph radio communications and
transmission of television broadcasts.
513 Engineering research. Expected operational life 5 years. Owner/operator
Surrey Satellite Technology, Ltd. University of Surrey, Guildford, Surrey.
514 Telecommunications satellite. French registration 1991-8. Transfer orbit
was 663 min, 200 x 36000 km x 7.0 deg. Registered by France in
ST/SG/SER.E/249 and ST/SG/SER.E/287 until EUTELSAT
can register the satellite. EUTELSAT is the European Telecommunications
Satellite Organization.
515 Research and exploration of the upper atmosphere and outer space. The
McDonnell Douglas Corporation has provided the following information for
its launch of the Losat spacecraft on 14 Feb 1990: LACE spacecraft
(Losat-L), launch time 1615:00.626 GMT,
ETR Launch Complex 17. Programmed orbital parameters 95.6 min, apogee 551
km, inc. 43.1 deg. Evaluate laser beam distortion in space.
516 "Spent boosters, spent manouevring stages, shrouds and other non-functional
objects" (sic). The McDonnell Douglas Corporation has provided the
following information for its launch of the Losat spacecraft on 14 Feb
1990: RME spacecraft (Losat-R), launch time 1615:00.626 GMT,
ETR Launch Complex 17. Programmed orbital parameters 94.0 min, apogee 480
km, inc 43.1 deg. Measure absolute intensity of low energy laser beam.
Orbit corrected in ST/SG/SER.E/269. Original orbit in SER.E/250 was 94.0
459 x 479 x 43.1.
517 Spent boosters, spent manouevring stages, shrouds and other non-functional
objects. The McDonnell Douglas Corporation has provided the following
information for its launch of the Losat spacecraft on 14 Feb 1990: Delta
second stage. Programmed orbital parameters 93.7 min, apogee 484 km, inc
41.6 deg.
518 ST/SG/SER.E/250: McDonnell Douglas Commercial Delta, Inc. (MDCI) provided
information for the Palapa B2R spacecraft which is the responsibility of
SATTEL, a United States company, during initial on-orbit checkout, after
which time the satellite will be turned over to PERMUTAL (sic),
an Indonesian government corporation. Communication services for Indonesia,
the Association of South-East Asian Nations (ASEAN), and Papua New Guinea.
Launch time 2227:59.719 Z. Launch complex 17, ETR.
519 1990-34B: Delta second stage. Programmed parameters 104.3 min, apogee 1423
km, inc 22.8 deg. 1990-34C: PAM-D, launch vehicle third stage. Programmed
parameters 665.4 min, apogee 37526 km, inc 18.9 deg. [Editorial note:
registered on page 7 of ST/SG/SER.E/250 as payloads, category B, but this
is clearly an error based on the info on page 8].
520 Commercial Titan Launch no. 3, State (sic) II. Launch time 1119 GMT.
Reentry 26 Jun 1990.
521 Insat 1D second stage: 1990-51B, period 91.4 min, inc. 27.3 deg, apogee 419
km. Launch from Launch Complex 17 ETR at 0055200.301 Z (sic) on 1990 Jun
12. 1990-51C, Launch vehicle 3rd stage, period 707.8 min, inc 27.2, apogee
39727 km.
522 These objects occur twice in the registration documents. Alternative orbits
given were 356.7 min, 157 x 20410 km x 37.7 deg (1990-68A), 86.1 min, 87 x
96 km x 30.1 deg (1990-68B), and 342.5 min, 150 x 19525 km x 37.6 deg
(1990-68C).
523 ST/SG/SER.E/250: McDonnell Douglas Corporation provided information
pertaining to the Delta second stage (1990-74B) and the Pam-D (1990-74C),
which boosted the BSB-R-2 into orbit. Launch time 0041:59.891Z, launch
complex 17. Programmed orbital parameters: 74B, 102.9 min, 24.8 deg, 1313
km apogee. 74C (launch vehicle third stage), 672.9 min, 20.7 deg, 37609 km
apogee.
524 Research of magnetosphere nad the ionosphere of the Earth by passive and
active methods. Launched on 18 Dec 1991. The Czechoslovak satellite Magion
3 forms, together with the spacecraft Intercosmos 25, part of the Apex
scientific project. Magion 3 was separated into an autonomous orbit on 28
Dec 1991. Magion 3 was launched into orbit by the Soviet spacecraft
Intercosmos 25.
525 ITALSAT is a body stabilized geostationary satellite and it is proposed to
provide pre-operational domestic telecommunications services on the 20/30
GHz bands. In addition, the ITALSAT satellite carries a propagation
experiment on the 40/50 GHz bands, both used in the space-to-Earth
direction. The satellite will used frequencies for space operations service
within the 2025 to 2110 MHz and 2200 to 2290 MHz bands. The satellite is
fitted with service equipment to provide the following functions: (a)
Telecommunication, (b) Propagation measure, (c) Power supply, (d) Attitude
control, (e) orbit control, (f) Thermal control, (g) Telemetry, telecommand
and ranging. The telecommunications payload provides restoration and
domestic telecommunciations services, while the propagation measure payload
provides experiments to study the influence of various meteorological
conditions about propagation on the 20, 40 and 50 GHz bands.
Launching organization: Agenzia Spaziale Italiana (ASI), Arianespace.
Geographic longitude 13.2 deg E. Longitudinal tolerance +/- 0.1 deg.
526 JERS-1 (FUYO-1). To verify functions and performance of optical sensors and
a Synthetic Aperture Radar and to establish an integrated system for
observing the Earth's resources; to perform observations and
measurements for land survey, agriculture, forestry, fishery, environmental
preservation, disaster prevention and coastal surveillance. Launch time
0150 GMT. Launching organization NASDA.
527 Domestic communications. Launching organization Arianespace. Launch time
2358 GMT.
528 Gathering of hydrometeorological data; testing of data-gathering and
measuring equipment, of optical and mechanical television and radiometric
scanning apparatus, of instruments for geophysical research and of methods
for the remote sensing of the atmosphere and the Earth's surface for
various branches of the USSR economy and science; charting the state of the
ozone layer, using American TOMS equipment.
529 Transport to the Mir manned orbital station of an international crew
comprising the cosmonauts A Volkov (USSR), T Aubakirov (USSR) and F.
Viehbock (Austria), to conduct joint scientific and technical
research with the cosmonauts A. Artsebarsky and S Krikalev.
530 Continuation of space materials research conducted jointly with Germany and
France.
531 Comprehensive study of the effects of artificial impact of modulated
electron flows and plasma beams on the ionosphere and magnetosphere of the
Earth (forming part of the Apex international scientific project, conducted
jointly with Bulgaria, Czechoslovakia, Germany, Hungary, Poland and
Romania.) Launched with the Czechoslovak satellite Magion-3, separated from
the space object Intercosmos-25 on 28 Dec 1991, in accordance with the
scientific programme of the Apex project.
532 Telephone and telegraph communications and transmission of television
programmes.
533 Testing of components and apparatus of the Glonass global space navigation
system being set up to determine the position of civil aircraft and vessels
of the merchant marine and fishing fleet.
534 SROSS-C satellite carries two scientific payloads: 1) Retarding Potential
Analyser (RPA), consisting of two planar detectors to measure plasma
parameters and investigate energetics of the equatorial ionosphere. (2)
Gamma Ray Burst (GRB) detectors, consisting of two scintillation detectors
to study celestial gamma ray bursts in the energy range of 20 keV to 3000
keV. Launch vehicle: Augmented Satellite Launch Vehicle.
535 Operation of the long-range telephone and telegraph radio-communications
system and transmission of Central Television programmes.
536 Determination of the position of ships of the merchant marine and fishing
fleet in the world's oceans and seas as part of the Tsikada space navigation
system.
537 Transport to the Mir manned orbital station of an international crew
comprising the cosmonauts A Viktorenko and A Kaleri together with
Klaus-Dietrich Flade (Germany), to conduct joint research and
experiments with cosmonauts A Volkov and S Krikalev.
538 Transmission of Russian radio and television programmes in Siberia and the
solution of communications problems in Russia's eastern regions.
539 Investigation of the natural resources of the Earth for the various branches
of the national economy, the solution of environmental problems, and
international cooperation.
540 INSAT-2A is a multi-purpose satellite, and it will provide the following
services: Domestic long-distance telecommunications, meteorological earth
observation and data collection services, direct satellite TV
broadcasting to community TV receivers in rural and remote areas, radio and
TV progamme distribution, and Satellite Aided Search and Rescue services.
Geostationary longitude 74 +/0 0.1 deg E. Inclination will be reduced to 0.1
deg and maintained. Launch vehicle Arianespace flight 51. (Geocentric
distances have been corrected to apogee and perigee heights - Ed.)
541 Freja is a Swedish/German satellite designed for research into the aurora.
The satellite was launched piggyback on a Long March 2C (CZ-2C) rocket and
weighs 214 kg in orbit. It is a sun-pointing spinner (10 rpm) with a 2.2 m
diameter. It will make high resolution measurements in the upper ionosphere
and lower magnetosphere. Data will be received at Esrange, Kiruna, Sweden
and at the Prince Albert Satellite Station in Canada's Saskatchewan
Province. Launch time 0620 UT.
ST/SG/SER.E/257 reported: Freja ceased to function 14 Oct 1996.
See also ST/SG/SER.E/352.
542 Orbital data from ST/SG/SER.E/258.
543 Additional data in ST/SG/SER.E/258: 1335.0 min, 33724 x 33852 km x 11.7 deg.
544 Commercial communications. Longitude 160 +/- 0.05 deg E. Launched fromn
China.
545 To investigate the structure and dynamics of the geomagnetic tail that
extends on the nightside of the Earth. Launch time 1426 GMT. Launching
states Japan and the United States of America. Launching organization NASA.
546 Investigation of the natural resources of the Earth in the interests of the
various branches of the national economy.
547 Development of the communications and television broadcasting system.
Launched in the interests of the Ministry of Communications of the Russian
Federation.
548 Transport to the Mir manned orbital station of an international crew
comprising the cosmonauts A Solovyev, S Avdeev and M Tonini (France) to
conduct joint work with the cosmonauts A Viktorenko and A Kaleri.
549 Operation of the long-range telephone and telegraph radio communications
system, transmission of television programmes to stations in the Orbita
network.
550 Investigation of the natural resources of the Earth in the interests of the
various branches of the national economy and solution of problems relating
to the environment and to international cooperation (the satellite's
equipment included two Pion passive satellites for the investigation of the
upper atmosphere).
551 Space materials research (conducted jointly with Germany).
552 Operation of the long-range telephone and telegraph radio communications
system, transmission of television programmes to stations in the Orbita
network and international cooperation.
553 Transmission of television programmes to a network of multiple user
receiving stations.
554 Delivery of a humanitarian cargo (messages to the American people,
promotional materials of Russian and foreign firms, etc.) to the United
States of America in connection with the 500th anniversary of the
discovery of America by Columbus.
555 Conduct of experiments to study physical processes in the Earth's
ionosphere. Small satellite launched from the Mir station.
556 Development of the communications and television broadcasting system.
557 Communication satellite. Longitude 33.5 deg E. Delta II flight no 212.
558 Domestic communications. Launching states: Japan and France. Launch time
2248 GMT.
559 Imaging and spectroscopic observations of various astronomical objects
(stars and galaxies) in the X-ray band. Launching organization ISAS. Launch
time 0200 GMT. Astro-D "ASCA".
560 Operational communications.
561 Second stage of a two stage rocket. Aug 9 launch: designation 03. Oct 6
launch: designation 04.
562 Olympus-1 is a multi-payload communications satellite for direct TV
broadcast in the bands of the 1977 Geneva Plan of the International
Telecommunications Union (ITU) (including a national beam to Italy) plus
communication transponders in the 14/12 GHz, 2nd 30/20 GHz bands. The latter
are also used for a data relay experiment with ESA's EURECA satellite.
Frequency plan: 2026.7542 MHz/2201 MHz, 14/12 GHz, 17/12 GHz TV BSS, 28/19
GHz, position on geostationary orbit 341 deg E. Designator ESA/89/02,
Launch time 0014:00 UT.
563 Scientific satellite for astrometry. Frequency plan 2054.25 /2241 MHz.
Launch time 2325:53 UT. Designator ESA/89/03.
564 Ulysses is a scientific spacecraft, within the framework of the
international solar/polar mission. It will be the first spacecraft to fly
over the poles of the sun. Frequency 2111.6073/2293.1481 MHz,
8408.2099 MHz., interplanetary trajectory into a polar flyby over the sun.
Designator ESA/90/01. Also registered by the United States in
ST/SG/SER.E/250, orbital data are taken from that document.
565 Geostationary meteorological satellite, operating within the world-wide
network of the World Weather Watch of the World Meteorological Organization
(WMO). Its main missions are: imaging in the visible, infrared and water
vapour region of the spectrum. Data reception from so called Data Collection
Platforms (DCPs); data distribution to meteorological services and other
interested parties (research institutes, etc). Frequency plan: 136-138 MHz
(S-E); 148-149.9 MHz (E-S), 401-403 MHz (E-S), 1670-1700 MHz (S-E),
2025-2110 MHz (E-S). Position on geostationary orbit, 0 deg E. Designator
ESA/91/01. Meteosat 4: Launch time 2329:00 UT. The ownership of Meteosat 4
has been transferred to EUMETSAT by an act of transfer signed by both
parties on 19 Jun 1989.
Meteosat 5: Launch time 2336:00 UT. The ownership of Meteosat 5 has been
transferred to EUMETSAT by an act of transfer signed by both parties on 14
Jan 1992.
566 ERS-1 is an Earth exploration satellite, using active and passive sensors
for oceanography etc. Frequency plan: 2048.85/2225 MHz (TTC), 7225.2960/8489
MHz (PRARE), 8040, 8140 MHz (data transmission). Launch time 0146:31 UT.
Designator ESA/91/02.
567 EURECA is a European scientific and technology mission, launched by the US
Space Transportation System. The spacecraft is scheduled to be retrieved
likewise by the US/STS in late spring/early summer 1993. Designator
ESA/92/01. Frequency plan: 2053.4583/2230 MHz, 28 GHz/ 18 GHz (data-relay
via Olympus).
568 Investigation of outer space and of processes occurring in the Earth's
atmosphere. Prognoz series.
569 Study of the adaptation of living organisms to conditions of space flight,
jointly with the countries of the Commonwealth of Independent States,
Austria, Canada, China, Czechoslovakia, France, Germany, Lithuania,
the United States of America, and the European Space Agency.
570 Transport to the Mir manned orbital station of a crew of the thirteenth main
expedition comprising the cosmonauts G M Manakov and A F Poleschuk.
571 Work on the Glonass global space navigation system being set up to
determine the position of civil aircraft and vessels of the merchant marine
and fishing fleet.
572 Full-scale mock-up (actual weight) for the flight-design testing of the
Start-1 carrier rocket. Experimental satellite launched by a Start-1 carrier
rocket from the Plesetsk launch site.
573 Delivery of consumables and various cargoes to the Mir manned orbital
station.
574 The SCD-1 (Data Collection Satellite 1) is a Brazilian satellite designed
for the collection of meteorological data relayed by data collection
platforms spread throughout the Brazilian territory. It was launched by a
Pegasus launch vehicle from Orbital Science Corporation. SCD-1 weighs 110
kg. Launch time 1442 UT.
575 The TEMISAT programme allows the implementation of a data collection and
distribution service for geophysical environmental monitoring, through a
micro-satellite called TEMISAT and based on the Autonomous Managed Network.
This Network adopts very innovative and effective communications
technologies to environmental protection services. The main applications
are: Pollution monitoring, Basin level monitoring, Oceanographic monitoring,
Snow level monitoring, Traffic monitoring, Monitoring of the structures
(buildings, dams, etc), Geological monitoring, seismic monitoring,
Climatological monitoring. The environmental data, whose measurements are
acquired through sensor subsystems, are collected, temporarily stored on the
ground, and logged by an autonomous and automatic terminal untils the
uploading request is received from TEMISAT. Once the data are received on
board, they are transmitted from TEMISAT to user data collection centres.
The system is composed of two micro-satellite units with low cost satellite
based TDMA/SCPC scheme, the Mission Control Centre and two different types
of terminal: Collection Centre Terminal and User Terminal. (a) Temisat
Space Segment. The TEMISAT space segment consists of two micro-satellites.
These are professional micro-satellites, which for the first time introduce
a low cost satellite based TDMA/SCPC access scheme. The expected operational
life of each satellite is five years. The major characteristics of the
satellite are high reliability, full redundancy, store-and-forward service,
direct or on request access. (b) Temisat ground segment. The TEMISAT ground
segment consists of the Mission Control Centre. This Centre processes,
manages, and stores the mission data and prepares the user routing matrix,
which contains the polling sequence, the synchronization and the addressee
identification codes. The Mission Control Centre is responsible for: Mission
Planning, Polling Optimization. (c) Temisat user segment. The TEMISAT user
segment consists of two different types of terminal: Data Collection Centre
Terminal (DC) and User Terminal (UT). The user terminals are connected with
the block of sensors, which are set for acquiring measurements and for
storing them temporarily. As soon as the satellite polls the user terminals,
the commands exchange between the interface user terminal equipment and
sensor terminal adopting the standard RS232, will make available the data
for the packetizations and transmission provided by the User Terminal
equipment. The main characteristics of the User Terminal are: Standard
interfaces, Low power consumption, Easy installation. The Data Collection
Centre is able to recieve the down link flow data from TEMISAT corresponding
to all the information collected from the user terminals belonging to its
Closed User Group (CUG). The main characteristics of the Data Collection
Centre are: High flexibility, CUG Control, Low cost and low complexity.
Characteristics of the satellite: (a) Mass 42 kg (b) Dimension 35 x 35 x 35
cm, (c) Electric power 62 W Max, (d) Attitude control : 2 magnetic coil, 1
Am**2, (e) On-board memories - 2 of 8.5 Mbytes each, (f) Lifetime 5 years.
Drift of the ascending node of orbital plane: 0.8 deg/d westwards.
Copassenger of METEOR 2 satellite. Eccentricity less than 0.0001.
576 INSAT-2B is a multi-purpose satellite, and it will provide the following
services: Domestic long range communications, meteorological Earth
observation and data collection service, Direct satellite TV broadcasting to
community TV recievers in rural and remote areas, Radio and TV
programme distribution, satellite aided search and rescue services.
Inclination will be reduced to 0.1 deg and maintained. Geostationary
longitude 93.5 +/- 0.1 deg E. Launch on Arianespace flight 58.
577 Vehicle Evaluation Payload (VEP) MYOJO. Provides a ranging function as well
as functions to measure the acceleration and deformation, in order to
confirm the accuracy of the H-II rocket orbit injection and understand the
environment of the payload equipment. Launch vehicle H-II rocket test flight
H-II 1F. Launching organization NASDA. Launch time 2220:00 UT.
578 Orbital Re-entry Experiment Vehicle (OREX) Ryusei. Acquisition of data
related to atmospheric reentry. Launch vehicle H-II rocket test flight H-II
1F.
Launching organization NASDA. Launch time 2220:00 UT.
579 SROSS-C2 satellite carries two scientific payloads: (i) Retarding Potential
Analyser (RPA), consisting of two planar detectors to measure plasma
parameters and investigate energetics of the equatorial ionosphere.
(ii) Gamma Ray Burst (GRB) detectors, consisting of two scintillators to
study celestial gamma ray bursts in the energy range of 20 keV to 3000 keV.
Launch vehicle Augmented Satellite Launch Vehicle ASLV-D4.
580 Investigation of the natural resources of the Earth in the interests of
various branches of the national economy; solution of problems relating to
ecology and international cooperation.
581 Transport to the Mir manned orbital station of an international crew
composed of the cosmonauts V V Tsibliev, A A Serebrov and J P Haignere
(France) for carrying out joint operations with the cosmonauts G Manakov
and A Poleshchuk.
582 Photography of the earth's surface for the purpose of the natural resource
mapping and area monitoring on behalf of various branches of the Russian
economy and in the interests of international cooperation. Alternate name:
Resurs-T.
583 Operation of the long range telephone and telegraph radio-communications
system.
584 Obtaining meteorological data and information on the radiation status of
geovicinal outer space. The satellite included the Temisat German small
space facility, which was separated from Meteor-2 on the seventh transit of
the flight. The Temisat facility will, in agreement the Kaiser-Threde
Company (Munich), be registered by the Italian partner.
585 Operation of telephone and telegraph radio communications and transmission
of television programmes.
586 Communications satellite. Intended for use under commercial conditions.
587 Transport to the Mir orbital station of a crew comprising the cosmonauts V
M Afanasev, Y V Usachev, and V V Polyakov for the fifteenth main
expedition.
588 Direct broadcasting satellite (new generation of satellites) intended for
development of the Russian television system and international cooperation.
589 Obtain meterological and solar-terrestrial data. The space object Meteor 3
included the small German satellite Tubsat which was separated from the
space object Meteor 3 on the second orbit.
590 Extension of the telephone and telegraph radio communications system on the
territory of the Russian Federation.
591 The space object serves the Ministry of Defence of the Russian Federation.
592 Conduct of comprehensive investigations of the sun under the Coronas-I
international project developed by Russian and Ukranian experimts in
cooperation with specialists from Poland, the Czech Republic, the Slovak
Republic, Bulgaria, France, and the United Kingdom.
593 Orbit corrected in May 93 section of ST/SG/SER.E/269. Mar 93 section in
which object was registered gave orbit as:
193.2 222 x 9164 x 27.3
594 ST/SG/SER.E/274 noted that USSPACECOM reported that these satellites did
not decay as previously reported, and gave orbits:
1962 A Alpha 5 (=62-25E): 97.2 528 x 717 x 58.1
1961 Omi 272 (=61-15LH): 104.1 868 x 1037 x 65.7
595 This space object is intended for assignments on behalf of the Ministry of
Defense of the Russian Federation.
596 ST/SG/SER.E/276 amended the orbit to the values given. Initial registered
orbit from ST/SG/SER.E/274 was 90.8 256 x 315 x 66.9.
597 Operation as part of the GLONASS space navigation system.
598 Study of materials under space conditions. The object carries a Biopan
container with equipment developed by German specialists.
599 Transport to the Mir orbital station of the crew for the 16th main mission,
consisting of the cosmonauts Y I Malenchenko and T A Musabayev.
600 Determination of the location of merchant marine and fishing fleet vessels
of the Russian Federation, and operation as part of the Space System for
Tracking Ships in Distress and the Search and Rescue Satellite Tracking
System (COSPAS-SARSAT).
601 This space object is designed to relay telegraph and telephone information.
602 Third stage of Ariane.
603 Carrier structure.
604 ASTRID launched 24 Jan 1994 at 0354:22 UT, Plesetsk, Russian Federation;
catalog number 23464. The Astrid satellite is a cube with 0.4m side. It has
four deployed solar panels, each measuring 0.4x0.4m. The satellite weighs
26 kg and is spin stabilized. ASTRID carries scientific instruments
designed to investigate near-space plasma with emphasis on neutral particle
phenomena.
By making high resolution measurements in the upper atmosphere and lower
magnetosphere, it will be possible to greatly increase the knowledge of
basic processes of fundamental importance to the physics of neutral
particles.
The payload, designed by the Swedish Institute of Space Physics in Kiruna,
Sweden, consists of three instruments: A Neutral Particle Imager (PIPPI)
which will measure energetic neutral particles in the Earth's magnetosphere.
It is the first time ever that an instrument of this type will fly on a
spacecraft.
A miniature ultraviolet imaging system (MIO) which will measure UV and
visible light in two pass bands and provide the Lyman alpha intensity,
an important parameter for evaluation of the Neutral Particle Imager data.
An electron spectrometer (EMIL) that will provide the electron distribution
function, thus supporting the Neutral Particle Imager in terms of relating
the measurements of neutrals to different magnetospheric regions.
(Also recorded in ST/SG/SER.E/284, with description: Study of plasma in a
near-earth space.)
ST/SG/SER.E/311 reports: ASTRID ceased to function on 27 Sep 1995.
See also ST/SG/SER.E/352.
605 Satellite engaged in practical applications of space technology for remote
sensing of natural resources. Launched from the territory of India.
606 Telecommunications satellite. Longitude 107.3 deg W +/- 0.005 deg.
Longitude of Service Arc: 104.5 deg W to 117.5 deg W. Geostationary orbit.
Operation entity - Telesat Canada.
607 Telecommunications satellite. Longitude 111.1 deg W +/- 0.005 deg.
Longitude of Service Arc: 118.0 deg W to 104.0 deg W. Geostationary orbit.
Operation entity - Telesat Canada.
608 Canadian Target Assembly (CTA). Passive target spacecraft for use in
on-orbit tests of a machine vision system known as Space Vision System
(SVS). Operation entities: The National Research Council of Canada and
the Canadian Space Agency. Released from Remote Manipulator System
("Canadarm") 1992 Oct 30, 10:05:29, 211 km above 1.41 deg N, 40.33 deg E.
609 ERS-1/2, Second Flight Model. ERS-1/2 is an Earth exploration satellite
using active and passive sensors mainly for oceanographic observations.
Designator ESA/95/1. Frequency plan:
Earth-space: 2048.8542 MHz (TC/TR); 7225.2960 MHz(PRARE Instrument)
Space-Earth: 2225.0000 MHz (TM/TR); 8040.0 MHz (Data transmission),
8140.0 MHz (Data Transmission); 8489.0 MHz (Data Transmission).
610 Launched from site on the coast south of Tel Aviv. Launching organization
Israel Aircraft Industries Ltd. and Israeli Space Agency (ISA). Function:
a. Experimentation in generation of solar power. b. Experimentation in
transmission reception from space. c. Verification of system's ability
to withstand vacuum and weightlessness condition. d. Data collection
on space and earth environment conditions.
611 Transport to the Mir manned orbital station of an international crew
consisting of the cosmonauts A. Viktorenko, E. Kondakova and U. Merbold
(representative of the European Space Agency and citizen of the FRG)
to conduct joint work with cosmonauts Y. Malenchenko, T. Musabaev, and
V. Polyakov.
612 Acquisition of current oceanographic information and data on the ice
situation in arctic latitudes.
613 Long-distance, zonal and local telephone-telegraph communications, the
relay of radio and television programmes, and the expansion of
possibilities in the area of international communications.
614 Observation of large-scale hydro-meteorological processes influencing the
weather on Earth, and the collection and dissemination of environmental
information, including data on the weather in outer space.
615 Investigation of natural Earth resources, ecological monitoring and current
observations in the interests of the economy of Russia and the countries of
the Commonwealth of Independent States.
616 The space object is designed to gather geodetic data required for solving
problems in the interests of the national economy and for the Ministry
of Defence of the Russian Federation.
617 Operation of the long-range telephone and telegraph radio communications
system, transmission of television programmes to points in the Orbita network.
618 Communications with the Mir manned orbital station and organization of
quick-response communication channels in emergency situations; transmission
of television information. It is also planned to use the satellite for
assignments on behalf of the Ministry of Defense of the Russian Federation.
619 The space object is designed for communications between radio amateurs.
620 The space object is intended for operation as part of the Tsikada space
navigation system, which ensures locating naval and fishing craft at any
point in the Pacific. At the same time as the Tsikada space object,
the single Cosmos carrier rocket put into orbit the American Faisat
satellite and the Swedish Astrid satellite.
621 Registered in ST/SG/SER.E/288 by United States, as spacecraft engaged
in practical applications and uses of space technology such as
weather or communications. Also noted in ST/SG/SER.E/284 by the Russian
Federation, described as: Operation as part of a low orbit satellite
communications system.
622 Research in space technology and biotechnology. Apart from the Russian
programme, the space object was used for experiments for the benefit
of ESA and CNES.
623 Transport to the Mir manned orbital station of a Russian-American crew
consisting of V. Dezhurov, G. Strekalov and Norman Thagard.
624 ST/SG/SER.E/286: A German microsatellite GFZ-1 was placed in Earth orbit
from aboard the Mir manned orbital station. The GFZ-1 satellite is
intended for the investigation of the Earth's gravitational field.
625 Scientific satellite SARA. French registration 1991-4A.
626 Telecommunications satellite. French registration 1991-9A.
627 Telecommunications satellite. French registration 1992-2A.
628 Debris.
629 Telecommunications satellite. French registration 1992-3B. Registered
temporarily by France until EUTELSAT is able to do so.
630 Scientific satellite. Also registered in ST/SG/SER.E/287 with
French registration 1992-4A. Orbital parameters
from ST/SG/SER.E/287 are 112.2, 1350 x 1350 x 66.1.
631 Technology satellite. French registration 1992-4B.
632 Amateur radio satellite. French registration 1993-1A.
633 CYCLADE carrier structure.
634 SPOT 3: Observation satellite, French registration 1993-4A. STELLA:
scientific satellite, French registration 1993-4B.
635 Telecommunications satellite. French registration 1995-1A. Registered
temporarily by France until EUTELSAT is able to do so. Also registered
in ST/SG/SER.E/331.
636 Module 'Spektr'. The module is designed for scientific research and
experiments as part of the Mir orbital station, including work under
the multi year Russia-USA collaboration programme in the area of
manned flights, as well as for re-equipping the manned station with
additional solar batteries and equipment.
637 Earth observation from space.
638 Traffic control of ships at sea, determination of their position,
transmission of various forms of operational information.
639 Conduct of long-term basic studies on processes in the geomagnetic
tail of the Earth's magnetosphere under the 'Interball' international
project. The Czech satellite Magion-4 was separated from the space object
Prognoz-M2 during the latter's first orbit, and is intended for
conducting coordinated space-time measurements.
640 Registration ROLEU ESP 001: Validation of space technology; first satellite
based on Spanish technology. Taken out of operation Nov 1976.
641 Registration ROLEU ESP 002 (Hispasat 1A) and ROLEU ESP 003
(Hispasat 1B): Telecommunications.
642 Registration ROLEU ESP 004: Scientific and communications
satellite.
643 Satellite engaged in experimental applications of space technology
such as: Earth imaging, packet communication, cosmic particles
measurement, and digital signal processing.
644 Satellite engaged in experimental applications of space technology
such as: Earth imaging, packet communication, low energy particles
measurement, digital signal processing, and 32-bit onboard computer.
645 Earth observations and natural resources management related applications.
646 Broadcasting Satellite-3N, backup of Broadcasting Satellite-3 (BS-3).
Launch by Ariane rocket flight 65. Launching organization: Arianespace.
647 Engineering Test Satellite-VI (ETS-VI, Kiku-6). Purpose is to
establish bus technology for large-scale geostationary three-axis
stabilized satellites necessary for development of future operational
satellites as well as to develop advanced satellite communications
technologies such as fixed satellite communications, mobile satellite
communications and intersatellite communications. Launch 0750 GMT
on 28 Aug 1994 by H-II rocket test flight 2F. Launching organization: NASDA
648 The SFU (Space Flyer Unit) is an unmanned, reusable and free flying
space platform for multiple use. After conducting various space
observations and experiments in orbit, it is planned to be retrieved
by the USA's Space Shuttle. Launching organization: NASDA
649 Geostationary Meteorological Satellite 5 (Himawari-5). GMS-5,
the successor of GMS to GMS-4, is to continue this meteorological satellite
service and contribute not only to improvement of meteorological satellite
service but also to development of related technology. Launch
on H-II rocket test flight 3F, 0801 GMT 1995 Mar 18.
Launching organization: NASDA.
650 Domestic telecommunications/International communications. Entrusted
domestic broadcasting, entrusted domestic and overseas broadcasting.
651 Domestic telecommunications.
652 Owner: APT Satellite Co Ltd., Hong Kong. Fixed-satellite telecommunications
services and transmission of television signals. Orbital position 138 E.
ST/SG/SER.E/333: UK ceased to be the state of registry.
ST/SG/SER.E/334: With effect from 1 July 1997 carried on the register of
Space Objects of the Hong Kong Special Administrative Region of the
People's Republic of China. Therefore from that date the People's Republic
of China has been the State of registry.
653 Owner: Asia Satellite Telecommunications Co. Ltd., Hong Kong.
Fixed-satellite telecommunications
services and transmission of television signals. Orbital position 100.5 E.
ST/SG/SER.E/333: UK ceased to be the state of registry.
ST/SG/SER.E/334: With effect from 1 July 1997 carried on the register of
Space Objects of the Hong Kong Special Administrative Region of the
People's Republic of China. Therefore from that date the People's Republic
of China has been the State of registry.
654 Insat 2C is a multipurpose satellite and will provide the following
services: Domestic telecommunication services, direct satellite
television broadcasting to community, TV receivers in rural and remote
areas, radio and television programme distribution, mobile satellite
services.
655 ISO is a scientific satellite for exploration of infrared astronomy
in the wavelength range of approximately 1 to 200 micrometres. Frequency
plan: Earth-Space: 2087.0688 MHz (telecommand/tracking), Space-Earth
2266.5 MHz (Telemetry/tracking). Designator ESA/95/2.
656 SOHO is a scientific satellite with an orbit around the L1 libration
point about 1.4 million km from the Earth in the direction of the Sun
on the Earth-Sun line. It forms part of a major international effort for
the study of solar-terrestrial physics. Frequency plan: Earth-Space:
2067.2708 MHz (telecommand/trackin), Space-Earth 2245.0 MHz (Telemetry/
tracking). Designator ESA/95/3.
657 The major communications and broadcasting services and characteristics are:
Major services: direct broadcasting satellite service, video relay,
digital trunking for inter-city communication, remote/rural area communication,
wide band digital data, and VSAT (very small aperture terminals).
General characteristics: Direct Broadcast Service (DBS) frequency
bands 14.5-14.8 / 11.7-12.0 GHz. Fixed Satellite Service (FSS) frequency
bands 14.0-14.5/12.25-12.75 GHz. Transponder: DBS 27 MHz x 3, FSS 36 MHz x 12.
Mass (beginning of life) 910 kg.
658 Earth observation for land and ocean applications; and X-ray astronomical
studies. Launch vehicle PSLV-D3, Indian Space Research Organization.
659 Designed to relay television programs in the centimetre wavelength range
to small receivers operated for professional, group or individual
purposes.
660 ST/SG/SER.E/307: The Indian satellte IRS-1C and the American satellite
SKIPPER were launched into artificial earth satellite orbit.
SKIPPER has experiments to register ultraviolet and visible-band
radiation at various flight altitudes of the space object and on
its reentry into the Earth's atmosphere.
661 Operation of telephone and telegraph radiocommunications system and
transmission of radio programmes.
662 Satellite from the Gonets series is designed to operate as part of the
new low-orbit satellite communications system being set up under
Russia's Federal Space Programme.
663 The Raduga communications satellite failed to reach the planned orbit.
664 Transport to the Mir manned orbital station of a crew consisting of
the cosmonauts Y I Onufrienko and Y V Usachev.
665 Remote sensing - Earth observation with enhanced imaging capabilities
producing high resolution images of the Earth's surface. Arctic mode:
essentially entire globe excluding South Pole to 79 deg latitude.
Antarctic mode: essentially the same as Arctic mode except that there
is no coverage above about 79 deg north latitude. Operating entity:
Canadian Space Agency.
666 Advanced Earth Observing Satellite (ADEOS), (MIDORI). Verify functions
and performance of two NASDA sensors, Ocean Color and Temperature Scanner
(OCTS) and Advanced Visible and Near IR Radiometer (AVNIR), and to
provide Earth observation data. In addition, ADEOS has the technical
development mission such as inter-orbit communication experiment.
H-II rocket flight 4F, NASDA.
667 JAS-2 (Fuji-3). Amateur satellite communications. Development of
amateur radio communications satellite technology.
668 Fixed-satellite telecommunications services and transmission of
television signals. APT Satellite Co. Ltd, Hong Kong. 134 deg E.
ST/SG/SER.E/333: UK ceased to be the state of registry.
ST/SG/SER.E/334: With effect from 1 July 1997 carried on the register of
Space Objects of the Hong Kong Special Administrative Region of the
People's Republic of China. Therefore from that date the People's Republic
of China has been the State of registry.
669 Experimental platform capable of taking and sending images of the
national territory and of receiving, storing and retransmitting
messages between low-cost ground stations (PC type). Owner is
Coratec SE and AIT. Launching organization is NPO Lavochkin.
Registration RA1.
670 Scientific applications satellite. Hard and soft solar X-ray observation.
Detection of background non-solar X-ray levels; detection of neutral
particles in orbital altitudes; technological demonstration.
Owner: Comision Nacional de Actividades Espaciales. Registration RA2.
671 93-01; Scientific experimental satellite.
672 94-01; Communications satellite.
673 94-02; Scientific experimental satellite.
674 Launching of communications satellite APstar 1.
675 Launching of communications satellite Optus B3
676 Launching of communications satellite Asiasat 2
677 Launching of communications satellite Echostar 1
678 94-05. Communications satellite
679 Transport to the Mir manned orbital station of an international crew
consisting of an international crew consisting of the cosmonauts
Y. Gidzenko, S. Avdeev, and T. Reiter (representative of the European
Space Agency and citizen of Germany).
680 The space object is intended for assignments on behalf of the Ministry
of Defense of the Russian Federation and the national economy.
681 Research of plasma-processes in the near-Earth space as part of the
international Solar-Terrestrial Energy Programme.
The satellite MAGION 4 was manufactured in the Czech republic
in cooperation with Austria and the Russian Federation and was launched into
orbit by the Russian spacecraft Interball 1.
The satellite forms together with the spacecraft Interball 1, part of the
INTERBALL mission. Also registered in ST/SG/SER.E/295; see note 639
682 The Priroda module is intended for the performance of research and
experiments by the crew of the Mir orbital station, partly under the
programme of cooperation between the Russian Federation and the United
States of America.
683 The Astra 1F satellite is owned and operated by the Societe europeene des
Satellites.
Transmission in analog and digital mode of radio and television
broadcasting services. Owner: SES (Societe Europeene des Satellites).
Located above 19.2 E longitude.
Note: ASTRA 1F launch first noted by Russian Federation in ST/SG/SER.E/320.
684 Operation of telephone and telegraph radio communications and transmission
of television and radio programmes.
685 Transport to the Mir orbital station of an international crew consisting
of the cosmonauts Valery Korzun, Aleksandr Kaleri and Claude Andre-Deshays
(research scientist of the French National Center for Space Studies).
686 Study of processes in the plasma of the Earth's geomagnetic field in the
context of the Interball international programme for research on the nature
and mechanisms of solar-terrestrial interactions. The Czech subsatellite
Magion-5, intended to carry out research with the Prognoz-M2 space object,
and the Argentine satellite MUSAT, designed for imaging the Earth's surface
to facilitate the study of its natural resources and the retransmission
of information on amateur radio frequencies, were launched into Earth orbit
simultaneously with the launching of the Prognoz-M2 space object by a
single Molniya carrier rocket.
687 Long-distance, zonal and local telephone-telegraph communications, the
relay of radio and television programmes, the transmission of data in the
interests of various branches and ministries of the Russian Federation and
the expansion of international communications.
688 The Mexican satellite UNAMSAT-B, designed to determine the speed of meteors
entering the Earth's atmosphere and to carry out experiments on radio links
with satellites, was placed in Earth orbit simultaneously with the launching
of the space object Cosmos-2334.
689 The communications satellite INMARSAT-3 was placed in Earth orbit. The
satellite belongs to the International Mobile Satellite Organization
(Inmarsat).
690 Operation of the long-range telephone and telegraph radio communications
system, transmission of television programmes to points in the Orbita network
and international cooperation.
691 Global study of the surface of the planet Mars, its atmosphere, internal
structure and surrounding plasma. Transfer of the unmanned interplanetary
station Mars-96 from artificial Earth satellite orbit to flight path to the
planet Mars did not take place. The Mars-96 station entered the dense layers
of the atmosphere and broke up, with individual fragments falling into the
water area of the Pacific Ocean.
692 Investigation of the effects of weightlessness and other aspects of
spaceflight on living organisms in the interests of basic and applied
research connected with the conquest of outer space. Specialists from the
Russian Federation, the USA, France, Ukraine and Lithuania are involved in
the joint study.
693 Studies of the techniques and technology of space objects. Registration
1995-5A and 1995-5C.
694 Third stage of ARIANE 4.
695 Mini-SPELDA, upper section.
696 EUTELSAT Hot Bird 2 communications satellite. EUTELSAT and France
agreed that France should register this satellite until EUTELSAT has
met the conditions for registering it.
697 Telecommunications. Owner NahuelSat S.A. Registration RA3.
698 INSAT-2D is a multipurpose satellite and will provide the following
services: Domestic telecommunication services, direct satellite
broadcasting, Radio and TV programme distribution, Mobile satellite
services. Arianespace Flight V97.
699 Scientific research, astrophysics, microgravity research, technology
demonstration. Launching organization: Instituto Nacional de Technica
Aerospacial (INTA), Spain; Orbital Sciences Corporation, USA.
Launch from Gran Canaria, Spain. Receive on 2047.0175 MHz, Transmit
on 2223.0000 MHz. Registration ROLEU.ESP 005.
700 Operational remote sensing satellite for natural resources
management. Indian Space Research Organization.
701 APSTAR-IIR Fixed satellite telecommunication services and transmission
of television signals. Owner/operator, APT Satellite Co. Ltd.,
Room 3111-3112 31/F, One Pacific Place, 88 Queensway,
Hong Kong Special Administrative Region of China.
Orbital position 76.5E. Expected operational life about 15 years.
702 Satellite per Astronomia a raggi X. ASI (Italian Space Agency).
SAX is an Italian/Dutch celestial X-ray monitoring telescope which will
have the capability of observing sources over more than three orders
of energy - from 0.1 to 200 keV - with a relatively large area, a good
energy resolution, associated with imaging capabilities (resolution of
about 1 arc-minute) in the range of 0.1 to 10 keV. It carries a 64 MB
tape recorder to unload data from Earth orbit to Malindi, Kenya via
a geostationary INTELSAT spacecraft. This will allow a prompt operation
and control of the satellite, particularly important in the cases of
targets of opportunity (TOO) that need timely follow-up observations.
During each orbit, up to 450 Mbits of data will be stored on board and
relayed to the ground during station passage. The average data rate
available to instruments will be about 70 kbit/s, but peak rates up to
100 kbit/s can be achieved. SAX will provide significant and
unique contributions in many X-ray astronomy areas by observing
compact galactic sources, active galactic nuclei, clusters of galaxies,
supernova remnants, normal galaxies, and stars. Mass at launch 1400 kg;
height 3 metres, width deployed 9 metres, stabilization 3-axis, EIRP 1dbW,
operational lifetime 2 years (nominal) 4 years (expected).
703 ITALSAT second flight unit (F2) is a body-stabilized geostationary satellite
that provides operational communications for domestic services in Ka-band
and European services in Ku- and L-bands. Mass at launch 1990 kg,
propulsion bipropellant, operational lifetime not less than 7.5 years,
the satellite uses S-band for telemetry, command and tracking during its
lifetime. Uplink 2200 MHz and 2290 MHz, downlink 2025 MHz and 2110 MHz.
The satellite has three communications payloads: Multibeam payload,
six operative transponders covering Italian territory with six partially
overlapped spots, uses the Ka-band. Uplink 27621.0 MHz and 29473 MHz,
Downlink 18820 MHz and 20070 MHz. National payload and telemetry beacon,
three operational transponders with domestic coverage, both use the Ka-band.
Uplink 29517 MHz and 29977 MHz, Downlink 19720 MHz and 20180 MHz, Beacon
18685 MHz. European Mobile Service payload (EMS): The EMS payload provides
coverage over western and eastern Europe, most of N Africa and the Middle East.
Two operative transponders, one for the forward link from fixed Earth
stations (FES) to mobile terminals and the other for the return link from
mobile terminals to FES. The feeder link between FES and the satellite
is in Ku-band, while the link between mobile terminals and satellite is in
L-band. Uplink: Ku 14236 MHz and 14250 MHz, L 1631.5 MHz and 1660.5 MHz.
Downlink Ku 12736 MHz and 12750 MHz, L 1530 MHz and 1559 MHz.
704 High power television broadcasting and data communication satellite. 32
active transponders with redundancy; power output 57-85W per transponder.
Three coverage areas within Europe. Mission period estimated to be 15 years.
Position 4.8E. See also ST/SG/SER.E/352.
705 Technical experiment including large antenna deployment and radio astronomy
using space VLBI. Launching organization: Institute of Space and Astronautical
Science, Ministry of Education, Science, Sports and Culture. Launch time
0450 GMT.
706 Domestic and international communication, domestic and international
broadcasting. Launching org. Lockheed Martin Commercial Launch Services
Inc. Launch time 0142 GMT.
707 Domestic direct broadcasting. Launching org. Arianespace. Launch time 2308
GMT.
708 Domestic and international communications. Launching org. Lockheed
Martin Commercial Launch Services Inc. Launch time 0115 GMT.
709 Engineering Test Satellite-VII (ETS-VII) [Kiku VII (Orihime-Hikoboshi)].
ETS-VII consists of two satellites, named "Chaser" (Hikoboshi) and
"Target" (Orihime). After launching, the Chaser will release the Target
satellite on orbit, and then the Chaser satellite will conduct
rendezvous docking experiments with the Target satellite automatically
and by remote pilot. It will also conduct the space robotic experiments
by using the robot arm, orbital replacement unit etc., installed on the
Chaser satellite. These experiments will be conducted via data relay
satellites to study integrated on-orbit capability.
Launch vehicle H-II rocket flight 6F. Launching org NASDA, National
Space Development Agency of Japan. Launch time 2127 GMT.
Orbit given is as of 28 Nov. As of 20 Dec, orbit was 95.0 min,
550 x 546 km x 34.9 deg.
710 Domestic and international communications. Launching org. Arianespace.
Launch time 2252 GMT.
711 Transport to the Mir manned orbital station of an international crew
consisting of the cosmonauts Vasiliy Tsibliev and Aleksandr Lazutkin
and astronaut Rainhold Ewald (research scientist, citizen of the
Federal Republic of Germany).
712 The satellite from the Gonets series is designed to operate as part of
the new low-orbit satellite communications system being set up under
Russia's Federal Space Programme.
713 Apparatus on the Zeya space object is designed to permit operation of
radio amateur communications and also to determine the orbital parameters
of this space object by means of the GLONASS and NAVSTAR navigation
systems.
714 ST/SG/SER.E/327 (Russia): The direct television broadcasting satellite
TELSTAR-5 was placed in orbit. The satellite belongs to and is operated by
American Telephone and Telegraph (AT&T).
715 ST/SG/SER.E/327 and 332 and 343 (Russia):
Seven Iridium satellites were placed in orbit.
These satellites form part of a global personal communications system
designed to serve regions with inadequate infrastructure for the
transmission of data and maintenance of communications during natural
disasters. The satellites are owned and operated by the Motorola
company (USA).
716 Transport of a crew consisting of the cosmonauts Anatoly Solovyev and
Pavel Vinogradov to the Mir manned orbital station.
717 The United States satellite FAISAT-2v, intended for operation as part of
the low-orbit satellite communications system, placed in orbit with the
space object Cosmos-2346. The satellite is owned and operated by the
Final Analysis corporation.
718 Open or coded transmission, in analog mode, of sound and television
broadcasting services. Owner: SES (Societe Europeene des Satellites).
Located above 19.2 E longitude.
719 Transmission in analog and digital mode of radio and television
broadcasting services. Owner: SES (Societe Europeene des Satellites).
Located above 19.2 E longitude.
720 Meteorological services.
721 Artificial Earth Satellite (ISZ) (launched into orbit from the Mir manned
orbital station). This is a working model of the first artificial Earth
satellite launched into orbit, to honour the fortieth anniversary of its
launching.
722 This satellite is designed to servie subscribers to the Bankir interurban
and international fixed communications system.
723 Investigation of the Earth's natural resources and study of the
environment and ecological situation.
724 Circling and external inspection of the Progress M-36 vessel and the
Mir orbital station. Launched from the Progress M-36 unmanned transport
craft.
725 The direct TV broadcasting satellite Astra 1 Zh was placed in Earth orbit.
The satellite is owned by the European Satellite Society (ESS).
(ST/SG/SER.E/340).
Launch 23:10 GMT 2 Dec 1997. Distribution of digital television and
radio signals, encrypted and unencrypted and multimedia services.
ASTRA 1G also provides backup capacity for ASTRA 1E and 1F.
726 The American satellite Early Bird, intended for remote sensing of the
earth, was placed in orbit. The Early Bird is owned and operated by
the American firm Earth Watch Incorporated. (ST/SG/SER.E/340).
727 The Asiasat-3 direct television and radio broadcasting satellite was
launched into non-calculated Earth orbit. The satellite was launched
on behalf of the Hong Kong company Asisat. (ST/SG/SER.E/340).
728 Scientific experiment satellite which will carry on board as the main
payload, sensors for monitoring the ozone layer. Expected operational
life at least six years. Owner and operator: Chilean Air Force,
Satellite Control Station, Av P A Cerda 5500, Santiago, Chile;
Tel 56 2 5380017 Fax 56 2 5579771; email [email protected]
Launch 10 Jul 1998 at 0232LT (0632GMT). See also note 737.
729 Delivery to the Mir manned orbital station of an international crew
consisting of the cosmonauts Talgat Musabaev, Nikolai Budarin and
the French citizen, Leopold Eyharts.
730 TUBSAT-N, register number D-R010 entered into aircraft register
of Federal Republic of Germany - Spacecraft on Jul 20 1998.
Experimental satellite for mobile communications launched near
Murmansk, Russian Federation by the SS-N-23 rocket together with
TUBSAT-N1, register number D-R011, experimental satellite for
mobile communications.
(ST/SG/SER.E/350, Russia:)
The German satellite TUBSAT-N was placed in orbit by the RSM-54
ballistic missile fired from a Novomoskovsk submarine in the Barents Sea.
The satellite is intended for operation of the worldwide subscriber
network and also for monitoring of animal migrations in the polar regions
and collection of data from sea buoys. It is owned by the Technical
University of Berlin and registered with the Federal German Government.
731 EUTELSAT Hot Bird 4 communications satellite. EUTELSAT and France
agreed that France should register this satellite until EUTELSAT has
met the conditions for registering it.
732 The American satellite Echostar 4 was placed in Earth orbit. The
satellite is intended for television broadcasting and video and
telephone communications for subscribersin the USA. The satellite
is owned and operated by the EchoStar Communications Corporation.
(ST/SG/SER.E/347, Russia).
733 WPLTN-1 'FIZEAU' (WESTPAC), laser ranging satellite. Register number
AUST/DIST/98-1. See also note 737.
734 Broadcasting satellite for television, radio and data with 15
high EIRP (effective isotropic radiated power) transponders.
Planned mission lifetime 12 years. Position 28E to Oct 1999, thereafter 5E.
See also ST/SG/SER.E/352 and ST/SG/SER.E/364.
735 Investigation of the Earth's natural resources and environment,
environmental monitoring, hydrometeorological coverage, investigation of
the Earth's radiation balance, and solar and geophysical observation.
736 Direct television broadcasting satellite Astra 2A was placed in Earth orbit.
The satellite is owned by the European Satellite Society (ESS).
(ST/SG/SER.E/340).
Launch 00:31 GMT 30 Aug 1998. Distribution of digital television and
radio signals, encrypted and unencrypted and multimedia services.
ASTRA 2A is operated at 28.2E (second orbital slot).
(A/AC.105/INF/402).
737 The Australian subsatellite FIZEAU (laser ranging), the German
subsatellite SAFIR 2 (communications), the Israeli satellite TECHSAT
(scientific research), the Thai subsatellite TMSAT (remote sensing
of the Earth) and the Chilean subsatellite FASAT-BRAVO (remote sensing
of the Earth) were placed in orbit with Resurs-O1 by a single
Zenit carrier rocket.
738 Delivery to the Mir manned orbital station of a crew consisting of
the cosmonauts Gennady Padalka, Sergei Avdeev and Yuri Baturin.
739 Technology. Operator CONAE; launch from Space Shuttle Endeavour (STS-88).
Registration number RA4.
740 Spin-stabilized, sun-pointing microsatellite (30 kg) for research.
The scientific mission: High-resolution measurements of electrical
and magnetic fields in the auroral region, electron density measurements,
high resolution measurements of the electron and ion distribution functions
and ultraviolet auroral imaging and atmospheric ultraviolet absorption
measurements. (ST/SG/SER.E/352).
The Swedish satellite Astrid-2 was placed in Earth orbit
simultaneously with the space object Nadezhda. The Astrid-2 satellite
is intended for measurement of electromagnetic field characteristics
in the region of polar auroras. (ST/SG/SER.E/354, Russia).
It ceased functioning on 24 Jul 1999 (ST/SG/SER.E/364).
741 Working model of the first artificial Earth satellite, produced by
Russian and French schoolchildren. Launched into Earth orbit from the
Mir manned station.
742 The American direct television broadcasting satellite PANAMSAT-8
was placed in Earth orbit. The satellite is owned and operated
by the PanAmSat Corporation. (ST/SG/SER.E/354, Russia).
743 The Zarya functional cargo block is the first element of the
International Space Station (ISS), designed to fulfil a number
of interrelated functions in connection with both the
assembly of the station and throughout its entire operation.
American registration. (ST/SG/SER.E/354, Russia).
744 The direct television broadcasting satellite belonging to the
Russian company BONUM-1 is intended for transmission of
television programmes on the NTV-Plus network.
745 The space object is intended for determination of the position
of Russian Federation shipping at all points on all oceans and for
assignments as part of the COSPAS-SARSAT system.
746 Microsatellite, data communications
747 Communications and Broadcasting Engineering Test Satellite (COMETS).
Launch 0755 GMT. Experiments on advanced mobile satellite communications,
inter-orbit communications, advanced satellite broadcasting, etc.
Launching agency National Space Development Agency of Japan. H-II flight
No. 5. Injection into the geostationary orbit was not successful because
of the short second burning period of the upper-stage engine.
748 Domestic direct broadcasting.
749 PLANET-B (NOZOMI). Interaction between solar wind and Martian upper
atmosphere. Launching organization - Institute of Space and Aeronautical
Science. The orbit is to be changed to perform Earth swingbys.
Heliocentric orbit as of 6 Jan 1999: 146 x 216 million km x 3 deg, 485 d.
750 Mass and frequency simulators (MFS) of Motorola Iridium.
751 Motorola Iridium system used for telecommunication service.
752 INSAT 2E is a multi-purpose satellite that will provide the following
services: Domestic and international telecommunication services. Radio
and TV programme distribution, meteolorogical satellite services.
753 The Indian Remote Sensing (IRS-P4) satellite carries an Ocean Colour
Monitor (OCM) payload and a Multi-frequency Scanning Microwave Radiometer
(MSMR). OCM will observe the optical properties of phyloplankton pigments,
inorganic suspended sediments and yellow substance of the oceans.
MSMR operates in four frequencies and measures geophysical parameters
such as atmospheric water vapour, sea surface temperatures, precipitation
over oceans, ocean surface winds, etc.
754 Satellite engaged in experimental applications of space technology
as follows: Earth imaging, high energy particle experiment, electron
temperature experiment, measurement of radiation effects on microelectronics,
investigation of the Earth magnetic field.
755 Owned by Asia Satellite Telecommunications Co. Ltd, Hong Kong Special
Administrative Region of China. Orbital position 105.5E. Provides
fixed satellite telecommunication and broadcasting services. Its operational
lifetime is about 16 years. CNSA registration 1999/07.
756 Polar orbiting meteorological satellite, CNSA 1999/08A.
757 Scientific experimental satellite, CNSA 1999/08B.
758 Manufactured in Czech Republic in cooperation with Austria
for studies of the mechanisms for transporting energy from the
solar wind into the magnetosphere.
The satellite experienced serious defects after the first two
days in orbit and was reactivated on 7 May 1998.
See also ST/SG/SER.E/320 and note 686.
759 MuKungHwa-3 (Koreasat-1B) satellite communications and broadcasting
services over 116E.
760 Delivery to the Mir manned orbital station of an international crew
consisting of the cosmonauts Viktor Afanasev, Jean-Pierre Haignere,
(a French citizen), and Ivan Bella, a Slovak citizen
761 Communications satellite
762 Model of the first artificial Earth satellite. Launched into Earth
orbit from the Mir manned station.
763 China-Brazil Earth Resources Satellite. Sun-synchronous earth orbit
resource satellite. Also registered by Brazil in A/AC.105/INF.404.
764 Scientific application satellite made by Brazil. Instituto Nacional de
Pequisas Espacias of Brazil is responsible for SACI-1 orbital operation.
765 Observation of ice conditions in the Arctic regions, study of the
Earth's natural resources and ecological monitoring.
766 Operation of modern communication systems for enterprises in the
Russian gas industry and provision of telecommunication services
to national and foreign users.
767 Fundamental and applied research in the area of materials science,
development of technology of production of semiconductor materials
and biological research
768 Investigation of the Earth's natural resources, and research on
environmental and ecological conditions.
769 Collection and processing of images for cartography and biological
oceanography and scientific experiments.
770 Four American Globalstar satellites intended for mobile telephone
communications, data transmission and the location of means of transport
were placed in Earth orbit by a Soyuz carrier rocket from the Baykonur
launch site. (ST/SG/SER.E/370 - Russia; but not registered as Russian
space objects).
771 Domestic communications and domestic broadcasting
772 Trial of the Fregat upper stage under actual conditions for the launch of
space objects into preassigned orbits and also of the new system of
delivering returnable cargos to the Earth. After completing 4 orbits of the
Earth, the Demonstrator/Fregat was separated into two objects, which were
returned to the Earth.
773 The Indonesian Garuda-1 satellite intended for telephone communications for
subscribers in South-east Asia. [ST/SG/SER.E/372]
774 Trial of the upper stage in the course of which the Dumsat/Fregat space
object was placed in Earth orbit. Dumsat is a full scale mockup of a pair
of European Cluster 2 satellites.
775 Telecommunications satellite. EUTELSAT and France have agreed that France
should register this satellite unilt EUTELSAT has met the conditions
(definite geostationary orbit indicated) for registering it.
776 Studies on techniques and technology of space objects.
777 The XMM mission (Newton satellite) is mainly intended for X-ray
spectroscopic observations. Registration ESA/99/1.
778 The Cluster II mission is made up of 4 satellites, Rumba, Tango, Salsa and
Samba. Its scientific objective is to study the solar wind and its
influence on the climate of the Earth. Registration ESA/00/1-4.
779 Telecommunications service. Registration ROLEU. ESP. 006.
780 Onwer: Ministry of Defense, Main Building, Whitehall, London.
781 Owner: Ministry of Defense, Main Building, Whitehall, London.
Military communications. Position 34W.
Licence issued to Matra Marconi Space UK Ltd on 12 Aug 1997 to procure the
launch of and subsequently operate the satellite. Technical transfer
to the MoD on 20 May 1998.
782 Owner: Ministry of Defense, Main Building, Whitehall, London.
Military communications. Position 53E.
Licence issued to Matra Marconi Space UK Ltd on 20 May 1998 to procure the
launch of and subsequently operate the satellite. Technical transfer
to the MoD on 7 Jul 1999
783 Owner: Surrey Satellite Technology Ltd. Engineering and technology
research. (See also ST/SG/SER.E/383)
784 Owner: Surrey Satellite Technology Ltd. Research spacecraft for evaluating
the use of commercial micro-miniature technologies for highly advanced
yet tiny satellites.
785 Owner: GE Capital Satellites (Gibraltar) Ltd. Communications repeater.
786 Scientific and Earth observation satellite. Registration RA 5.
Operator CONAE.
787 Space Department, DERA, Farnborough. Scientific research and technology
demonstration.
788 The FY-2 B is a geostationary meteorological satellite. The operation of
the satellite has been normal since launching.
789 The scientific disciplines that Odin will serve are astrophysics
and atmospheric science. [details omitted]
788 Civilian science nanosatellite. 6-kg tech. development satellite carries
three instruments for auroral research [details omitted].
789 Tsingua University, China, and Surrey Satellite Tech Ltd, UK, developed
jointly the Tsinghua-1 microsatellite. It will be sued for data
transmission and scientific experiments.
Registration CNSA/REG.No 04 2000/11/10
790 Delivery to the Mir manned orbital station of a crew consisting of
the cosmonauts Segei Zeletin and Aleksandr Kaleri.
791 ST/SG/SER.E/384 (Russia): The SESAT satellite [...] was launched [...]
on behalf of the European organization EUTELSAT.
792 This dummy space object acted as a payload in the test flight of the Rokot
carrier rocket with a Breeze-KM booster block.
793 Base module of the International Space Station.
794 Delivery to the International Space Station of consumables and various
cargoes.
795 Communications satellite.
796 Work on the Global Navigation Satellite System (GLONASS)
797 Delivery to the Mir orbital station of fuel to permit essential course
correction of the station, and of consumables and various cargoes.
798 Delivery to the International Space Station of a Russian and American crew
consisting of the cosmonauts Yuri Gidzenko and Sergei Krikalev and the
astronaut William Shepherd.
799 Telecommunications. Owner: Europe*Star Ltd, 5 New Square, Bedfont Lakes,
Feltham, Middlesex TW14 8HA.
800 Mobile satellite communications services. Sea launch. Geostationary orbit
over 44 degrees E.
801 Chinasat-32 experimental navigation satellite.
Chinasat-32 is used for radio position determination and telecommunication.
It is located at 140E above the equator. The satellite operation is normal
after launching.
802 Chinasat-31 experimental navigation satellite.
Chinasat-31 is used for radio position determination and telecommunication.
It is located at 80E above the equator. The satellite operation is normal
after launching.
803 Delivery to the Mir orbital station of fuel for its controlled and
safe descent from orbit.
804 Experimental communication satellite on the first developmental flight
of the GSLV launch vehicle.
805 Complete sampling of the sky in the energy range of 0.1-2 keV and
0.04-0.2 keV. Subsequent detailed observation in the EUV range as
well as the soft X-ray range.
Date of registration in the aircraft register of the FRG under
'Spacecraft': 6 October 1999.
806 Experimental satellite for mobile communcations.
Date of registration in the aircraft register of the FRG under
'Spacecraft': 6 October 1999.
807 With ORFEUS it was for the first time possible to acquire high
resolution spectra of white dwarfs, the interstellar matter and
other astronomical objects in the ultraviolet range.
Date of registration in the aircraft register of the FRG under
'Spacecraft': 6 October 1999.
808 With CRISTA high resolution spectra were acquired of more than
15 trace gases in the Earth atmosphere. A fast measuring method
was used to investigate small scale structures.
Date of registration in the aircraft register of the FRG under
'Spacecraft': 6 October 1999.
809 Sampling of the entire sky in the medium-energy X-ray range
(0.5-10 keV)
Date of registration in the aircraft register of the FRG under
'Spacecraft': 6 October 1999.
810 Small satellite mission for geo-scientific basic research
(gravity and magnetic field measurements and atmospheric physics).
Pilot project for the 'neue Bundeslander' (NBL).
Date of registration in the aircraft register of the FRG under
'Spacecraft': 17 November 2000.
811 Transmission of television programmes to a network of shared
receiver installations.
812 Delivery to the ISS of a crew consisting of Kazak astronaut
Talgat Musabaev, Russian astronaut Yuri Baturin and United States
citizen Dennis Tito.
813 Owner/operator Ministry of Defence, Defence Procurement Agency.
Catalogue number IRON 5907. Military communications services.
Licence issued to Astrium on 2 February 2001 to procure the launch
of, and subsquently operate, the Skynet-4F satellite.
814 Owner/operator: ICO Global Communications (Operations) Ltd.,
Huntlaw Building, PO Box 1350, Fort St, Georgetown, Grand Cayman,
Cayman Islands. Telecommunication services. Licence issued under the
Outer Space Act 1986 (Cayman Islands) Order 1998, 11 June 2001.
815 Study of the Sun and solar-terrestrial relations.
816 Technology experiment satellite.
817 EUTELSAT EUROBIRD telecommunications satellite. (Registered by
France temporarily).
818 Acquire data on space weather and Earth resources for peaceful
purposes. SUP002.
819 Delivery to the ISS of the Pirs docking module.
820 Delivery to ISS of a crew consisting of Viktor Afanasyev,
Konstantin Kozeev and the French astronaut Claudie Haignere'.
821 Telecommunications satellite, EUTELSAT.
822 Domestic and international communications
823 Domestic communications and domestic broadcasting
824 Large Deployable Reflector Experiment (LDREX) is a small-scale and
partial model of the Large Deployable Reflector (LDR) of Engineering
Test Satellite VIII, [...], and was to conduct experiments in orbit
for validating the design of LDR.
825 Multispectral narrow angle camera for remote sensing; wide angle camera
for meteorology; CEDEX for scientific experiments. Registration
BAKSA 003/RS/TiungSAT-1.
826 Communication transponders.
Registration BAKSA 002/COMM/MEASAT-2.
827 Owner Binariang Satellite Systems Sdn Bhd. Mass 1395 kg liftoff mass;
Communications transponders. Ground control station MEASAT satellite
control center, Gunung Raya, Pulau Langkawi, Kedah at 06 22N 99 49E.
Registration BAKSA 001/COMM/MEASAT-1.
828 Launch org: Centre national des techniques spatiales of Arzew, Algeria.
Earth observation and disaster monitoring. Operational life 5 years.
Launch provider Russian enterprise Rosoboronexport. Manufacturer
Surrey Satellite Technology, Guildford, Surrey, UK
829 Intended for educational purposes and amateur radio comms.
830 CNSA registration 2003/19
831 BRD register D-R024. Small satellite mission...
--------------------------------------------------------------------------------