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  • UN Registry
    dates and launch vehicles A HREF un key2 html Old key to tables Section B United States non functional objects not up to date Table 1 Index to registrations Table 2 Orbital data and notes Table 3 Decay dates and

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  • UN Registry: Key to Tables
    in the table They were not registered with the UN Some of the satellites registered by France were the property of the European Space Research Organization ESRO or of ESA 2 Number of object launched by State of Registry for older satellites only For USSR satellites this number is the registration serial number provided to the United Nations except for a few cases U1 U2 etc of satellites which were launched secretly by the USSR without registration For all other satellites the number is an unofficial serial number assigned by the editor Serial numbers in square parentheses indicate that the object was not registered with the United Nations For objects registered by France for ESRO serials E1 E2 etc are used This column is no longer being updated 3 International designation originally Harvard number also known as COSPAR designation This designation is the official registration identification for United States satellites For satellites launched by other states which did not provide this information or for US satellites not registered with the UN the designation has been taken from the COSPAR Bulletin The original Harvard number system COSPAR Bulletin No 1 gave the year of launch a Greek letter for the order of launch within the year and a serial number for objects within a single launch Thus 1961 Delta 2 is the second object from the fourth launch of 1961 In 1963 the system was changed to replace the Greek letters with numbers and the serial numbers with alphabetic suffixes The suffixes ran from A to Z then from AA to AZ BA to BZ etc except that the letters I and O are never used to avoid confusion with 1 and 0 Thus 1965 82AB is the 26th object from the 82nd launch of 1965 4 Name of satellite The

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  • UN Registry: Editorial Notes
    have been unable to find a simple error which could have generated these parameters from a sensible orbit The given orbit heights correspond to a period of 613 5 min rather than 720 0 min If the apogee only were in error the orbit would be 805 x 39681 km I have replaced these parameters in Table 1 with the orbit parameters given in SER E 7 for the rocket body 1978 21B EN046 Registered in ST SG SER E 47 as 1965 27C a typo for 1965 27G EN047 Category given as D but carries a payload should have been designated as category A B or C EN048 ST SG SER E 11 Orbit given as 615 5 min 6528 x 41411 km x 28 4 deg Inconsistent with Kepler s third law I have given values which assume that the compilers of the UN submission forgot to subtract off the Earth radius of 6378 km from the perigee and apogee heights this gives a consistent orbit EN049 ST SG SER E 16 Orbit given as 101 3 min 17 x 146 km which is impossible Other sources indicate that a decimal point has slipped in the heights which should be about 170 x 1460 km EN050 ST SG SER E 16 Registered as 1978 78B should have been 1978 78C EN051 ST SG SER E 16 Apogee of 1978 79A was given as 108920 km but should have read 1089200 km EN052 ST SG SER E 19 1978 93A orbital heights were given as 86 x 10825 km These values were actually nautical miles to be consistent with the orbital period and I have multiplied them by 1 852 EN053 ST SG SER E 40 1966 96C orbit given as 597 7 min 33889 x 35783 km x 17 8 deg This orbit is impossible EN054 The four Pioneer Venus Probes which impacted Venus on 1978 Dec 9 were registered in ST SG SER E 47 The only information given for each was the international designation the launch date and the fact that they were no longer in orbit on 31 Dec 1980 EN055 Minor typo corrected in orbital parameters EN056 First satellite in this group of 8 given in report as Cosmos 1308 an error for Cosmos 1320 EN057 Typo in ST SG SER E 77 registered as 1976 32K instead of 1976 23K EN058 Registered as category D non functional object but external sources suggest the object is a payload EN059 Apogee given as 2 7 km which is a typo EN060 Registered under an incorrect international designation typographical error in document EN061 Orbital heights given in ST SG SER E document are in error they conflict with the orbital period I have subtracted off the Earth radius of 6378 km to give a consistent orbit EN062 Debris from Zenit rocket test launch No payload was orbited Not registered by the USSR EN063 Orbital period is incorrect ST SG SER E 141 gives it as 639

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  • not launched on this vehicle 2004 25B is just the SL 24 Dnepr final stage and is a Russian object N2 2005 05A XTAR EUR Owned by Hisdesat a joint Spanish US organization Registered by the USA even though Hisdesat is mainly Spanish N3 1974 Nov 5 China Recoverable satellite Chinese registration 2005 22 This registration is erroneous The satellite launched on 1974 Nov 5 failed to reach orbit The

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  • UN Registry: General Notes
    AC 105 INF 77 1964 Sep 1 D Titan IIIA A AC 105 INF 82 1964 Oct 8 A Atlas Agena A AC 105 INF 85 1965 Jan 21 A Atlas A AC 105 INF 98 1965 Mar 2 A Atlas Centaur A AC 105 INF 101 1965 May 28 B Atlas A AC 105 INF 114 1965 Jul 14 A Atlas Agena A AC 105 INF 111 1965 Aug 25 B Delta A AC 105 INF 114 1965 Sep 2 A Thor Agena A AC 105 INF 120 1965 Oct 25 A Atlas Agena A AC 105 INF 121 1966 Jan 7 A Thor Altair A AC 105 INF 131 1966 May 3 A Thor Agena A AC 105 INF 139 1966 May 17 A Atlas Agena A AC 105 INF 140 1966 Aug 26 A Titan IIIC A AC 105 INF 147 1967 Jan 31 A Scout A AC 105 INF 169 1967 Apr 26 A Titan IIIB A AC 105 INF 170 1967 May 30 B Scout A AC 105 INF 175 1968 May 18 C Thor Agena A AC 105 INF 193 1968 Sep 19 C Delta A AC 105 INF 197 1969 Aug 27 B Delta A AC 105 INF 217 1970 Nov 30 B Atlas Centaur A AC 105 INF 227 1971 Feb 17 A Thor Agena A AC 105 INF 230 1971 May 8 B Atlas Centaur A AC 105 INF 235 1971 Oct 21 C Delta A AC 105 INF 244 1972 Feb 16 A Titan IIIB Agena A AC 105 INF 253 1972 May 20 A Titan IIIB Agena A AC 105 INF 258 1973 Jul 16 C Delta A AC 105 INF 280 1974 Feb 11 B Titan III Centaur A AC 105 INF 292 1975 Dec DAD A B

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  • UN Registry: Notes
    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

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  • concentrate on what actually happened in space and usually don t get into associated events on the ground such as who won a particular contract how the telecoms industry should be regulated or what the policy for the military use of space should be Many of those readers are in aerospace and military jobs which are stereotypically associated with political views on the conservative end of the spectrum which as

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