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Cronología de Lanzamientos Espaciales

Año 1993

Recopilación de datos Ing. Eladio Miranda Batlle. Los textos, imágenes y tablas fueron obtenidos de la National Space Science. Data Center. NASA NASA - NSSDC - Spacecraft - Query Results

Wednesday, 04 May 2011

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Publications There were 116 spacecraft returned.

Maps Spacecraft Name NSSDC ID Launch Date New/Updated Data ACTS 1993-058B 1993-09-11

Lunar/Planetary Events Alexis 1993-026A 1993-04-24 Arasene 1993-031B 1993-05-11 ASCA 1993-011A 1993-02-19 Astra 1C 1993-031A 1993-05-11 Atlas 2 ATLAS2 1993-04-07 Cosmos 2230 1993-001A 1993-01-11 Cosmos 2231 1993-004A 1993-01-18 Cosmos 2232 1993-006A 1993-01-25 Cosmos 2233 1993-008A 1993-02-08 Cosmos 2234 1993-010A 1993-02-16 Cosmos 2235 1993-010B 1993-02-16 Cosmos 2236 1993-010C 1993-02-16 Cosmos 2237 1993-016A 1993-03-25 Cosmos 2238 1993-018A 1993-03-29 Cosmos 2239 1993-020A 1993-04-01 Cosmos 2240 1993-021A 1993-04-01 Cosmos 2241 1993-022A 1993-04-05 Cosmos 2242 1993-024A 1993-04-15 Cosmos 2243 1993-028A 1993-04-26 Cosmos 2244 1993-029A 1993-04-27 Cosmos 2245 1993-030A 1993-05-10 Cosmos 2246 1993-030B 1993-05-10 Cosmos 2247 1993-030C 1993-05-10 Cosmos 2248 1993-030D 1993-05-10 Cosmos 2249 1993-030E 1993-05-10 Cosmos 2250 1993-030F 1993-05-10 Cosmos 2251 1993-036A 1993-06-15 Cosmos 2252 1993-038A 1993-06-23 Cosmos 2253 1993-038B 1993-06-23 Cosmos 2254 1993-038C 1993-06-23 Cosmos 2255 1993-038D 1993-06-23 Cosmos 2256 1993-038E 1993-06-23 Cosmos 2257 1993-038F 1993-06-23 Cosmos 2258 1993-044A 1993-07-06 Cosmos 2259 1993-045A 1993-07-13

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Cosmos 2260 1993-047A 1993-07-21 Cosmos 2261 1993-051A 1993-08-09 Cosmos 2262 1993-057A 1993-09-06 Cosmos 2263 1993-059A 1993-09-15 Cosmos 2264 1993-060A 1993-09-16 Cosmos 2265 1993-067A 1993-10-25 Cosmos 2266 1993-070A 1993-11-01 Cosmos 2267 1993-071A 1993-11-04 DBS-1 1993-078A 1993-12-17 DSCS III-10 1993-046A 1993-07-18 DSCS III-11 1993-074A 1993-11-27 DXS DXS 1993-01-12 EYESAT 1 1993-061C 1993-09-25 Galaxy 4 1993-039A 1993-06-24 Gorizont 28 1993-069A 1993-10-27 Gorizont 29 1993-072A 1993-11-17 Healthsat 1 1993-061E 1993-09-25 Hispasat 1B 1993-048A 1993-07-21 INSAT 2B 1993-048B 1993-07-21 INTELSAT 7 F-1 1993-066A 1993-10-21 ITAMSAT 1993-061D 1993-09-25 Jianbing 93 1993-063A 1993-10-07 KITSAT 2 1993-061F 1993-09-25 Landsat 6 LNDSAT6 1993-10-04 Meteor 2-21 1993-055A 1993-08-30 Meteosat 6 1993-073B 1993-11-19 Molniya 1-85 1993-002A 1993-01-12 Molniya 1-86 1993-035A 1993-05-25 Molniya 1-87 1993-079A 1993-12-21 Molniya 3-44 1993-025A 1993-04-20 Molniya 3-45 1993-049A 1993-08-03 MOP 3 MOP3 1992-12-31 NATO 4B 1993-076A 1993-12-07 Navstar 2A-09 1993-007A 1993-02-02 Navstar 2A-10 1993-017A 1993-03-29 Navstar 2A-11 1993-032A 1993-05-12 Navstar 2A-12 1993-042A 1993-06-25 Navstar 2A-13 1993-054A 1993-08-29 Navstar 2A-14 1993-068A 1993-10-25 NOAA 13 1993-050A 1993-08-08 ORFEUS-SPAS I 1993-058C 1993-09-11 OXP 1 1993-009A 1993-02-08 POSAT 1 1993-061G 1993-09-25 Progress M-16 1993-012A 1993-02-20 Progress M-17 1993-019A 1993-03-30 Progress M-18 1993-034A 1993-05-21 Progress M-19 1993-052A 1993-08-09 Progress M-20 1993-064A 1993-10-10 RADCAL 1993-041A 1993-06-24

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Raduga 29 1993-013A 1993-03-24 Raduga 30 1993-062A 1993-09-29 Regatta-A REGTTAA 1992-12-31 Resurs-F17 1993-033A 1993-05-20 Resurs-F18 1993-040A 1993-06-24 Resurs-F19 1993-053A 1993-08-23 SCD 1 1993-009B 1993-02-08 SEDS-I 1993-017B 1993-03-29 SLS 2 SLABLS2 1993-10-17 Solidaridad 1 1993-073A 1993-11-19 Soyuz TM-16 1993-005A 1993-01-23 Soyuz TM-17 1993-043A 1993-06-30 Spacelab-D2 SPLABD2 1993-04-25 Spartan 201-01 1993-023B 1993-04-07 SPOT 3 1993-061A 1993-09-25 SSBUV05 SSBUV05 1993-04-07 START 1 1993-014A 1993-03-24 Stella 1993-061B 1993-09-25 STS 51 1993-058A 1993-09-11 STS 54 1993-003A 1993-01-12 STS 55 1993-027A 1993-04-25 STS 56/Atlas 2 1993-023A 1993-04-07 STS 57/SPACEHAB 1 1993-037A 1993-06-20 STS 58 1993-065A 1993-10-17 STS 61 1993-075A 1993-12-01 TDRS-F 1993-003B 1993-01-12 Telstar 401 1993-077A 1993-12-15 TEMISAT 1993-055B 1993-08-30 THAICOM 1A 1993-078B 1993-12-17 UFO 1 1993-015A 1993-03-24 UFO 2 1993-056A 1993-09-02

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Personnel ACTS

Publications NSSDC ID: 1993-058B Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The objectives of the Advanced Communications Technology Advanced Satellite (ACTS) include: (1) maintaining U.S. leadership in Communications satellite communications; (2) providing advanced Technology Satellite communications technology for NASA missions and other 22796 government agencies; (3) testing and verifying advanced technologies including high power, fast hopping spot-beam antennas, Ka Band (30/20 GHz) components, and on-board Facts in Brief processing and switching; and (4) testing and demonstrating technologies through an experiment program with participation Launch Date: 1993-09- by telecommunications users, service, and product providers. 12 Launch On 28 April 2004, ACTS was permanently shut down. It is Vehicle: Shuttle electrically inert at this time. It will remain at 105 Re in an Launch Site: Cape inclined geosynchronous orbit indefinitely. Canaveral, United States Mass: 2733.0 kg Nominal Power: 1770.0 W

Funding Agency

NASA-Office of Space Science Applications (United States)

Disciplines

Communications Engineering

Additional Information

Launch/Orbital information for ACTS Telecommunications information for ACTS

Experiments on ACTS

Data collections from ACTS

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1993-058B[06/05/2011 23:59:45] NASA - NSSDC - Spacecraft - Details

Office.

Personnel

Name Role Original Affiliation E-mail Dr. Richard T. Project NASA Lewis Research Gedney Manager Center Mr. James R. Program NASA Headquarters [email protected] Greaves Manager

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Personnel Alexis

Publications NSSDC ID: 1993-026A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Alexis was a small satellite which carried an ultrasoft X-ray 22638 telescope array for astronomy studies and and a high-speed VHF receiver/digitizer (Blackbeard) for studying the effect of lightning and electromagnetic impulse from exploding nucear Facts in Brief devices on the ionospheric transmission. It was launched on a Launch Date: 1993-04- Pegasus booster from the wing of a B-52, but a solar paddle 25 was damaged during the flight. No contact with the satellite Launch was established until three months after launch. New attitude Vehicle: Pegasus control techniques were developed and the satellite was Launch Site: Edwards brought under control. The telemetry system performed Air Force Base, United nominally. The spacecraft is spin-stabilized with a period of 2 States rpm and the axis points sunward. The Blackbeard experiment Mass: 113.0 kg operated successfully. The astronomy data needed a full Nominal Power: 50.0 W pointing and aspect solution in order to be interpreted.

Funding Agency

Department of Energy (United States)

Disciplines

Astronomy Communications Surveillance and Other Military

Additional Information

Launch/Orbital information for Alexis PDMP information for Alexis Telecommunications information for Alexis

Experiments on Alexis

Data collections from Alexis

Questions or comments about this spacecraft can be directed to: Coordinated

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Personnel

Name Role Original Affiliation E-mail Dr. William C. Project Los Alamos National [email protected] Priedhorsky Scientist Laboratory Dr. Jeffrey J. Bloch Project Los Alamos National [email protected] Scientist Laboratory

Other Sources for ALEXIS Information/Data

The ALEXIS Project (LANL) The ALEXIS Project (UC Berkeley)

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Personnel Arasene

Publications NSSDC ID: 1993-031B Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Arasene was a French amateur radio relay spacecraft Arsene launched by an Ariane 4 rocket from the Kourou Space Center Oscar 24 in French Guiana. It was built by university students. Some of the systems were to serve as prototypes for future small 22654 communications satellites. Unfortunately, the VHF antenna failed immediately after launch, and operations with the Facts in Brief vehicle's SHF antenna ultimately led to power supply problems and loss of the 154-kg spacecraft after only three months in Launch Date: 1993-05- orbit. 11 Launch Vehicle: Ariane 4 Launch Site: Kourou, French Guiana Mass: 154.0 kg

Funding Agency

Unknown (France)

Discipline

Communications

Additional Information

Launch/Orbital information for Arasene

Experiments on Arasene

Data collections from Arasene

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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Personnel ASCA

Publications NSSDC ID: 1993-011A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The objective of this mission was to perform spectroscopic X- Asuka Ray astronomy in the wavelength band 1--12 KeV, with Astro-D particular emphasis on spectroscopy of the iron K band. Another objective of ASCA was imaging of the structure of 22521 extended sources such as clusters of galaxies and supernova remnants. ASCA carried four identical telescopes with a total Facts in Brief effective area of 1300 cm**2 at 1 KeV and 600 cm**2 at 6--7 KeV. ASCA was a cooperative mission between Japan (ISAS) Launch Date: 1993-02- and NASA. NASA provided four conical grazing incidence, 19 multilayer thin foil mirrors. Two CCD-based detectors were Launch Vehicle: M-3SII provided by MIT. Japan provided the imaging gas scintillation Launch Site: Uchinoura proportional counters (IGSPC), the spacecraft, the launch Space Center, Japan vehicle, and a ground station. In return for its scientific Mass: 420.0 kg instrument contribution, NASA was allocated 15% of the Nominal observing time after the initial seven or eight month Power: 602.0 W Performance Verification (PV) period. In addition, 25% of the observing time was set aside for collaborative proposals between US and Japanese scientists. Funding Agencies National Aeronautics and The satellite was launched on February 20, 1993. A solar flare Space Administration on 14 July 2000 caused heating and expansion of the upper (United States) atmosphere, which increased the drag and external torque on ASCA. The attitude was perturbed, so the solar panels lost Institute of Space and lock on the Sun, resulting in discharge of the batteries. ASCA Aeronautical Science, U reentered the atmosphere on March 2, 2001. of Tokyo (Japan)

Discipline

Astronomy

Additional Information

Launch/Orbital information for ASCA PDMP information for ASCA Telecommunications information for ASCA

Experiments on ASCA

Data collections from ASCA

Questions or comments

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Personnel

Name Role Original Affiliation E-mail Dr. Nicholas Deputy NASA Goddard Space Flight [email protected] E. White Project Center Scientist Dr. Alan N. Program NASA Headquarters Bunner Scientist Dr. Stephen Project NASA Goddard Space Flight [email protected] S. Holt Scientist Center Mr. Jerre B. Project NASA Goddard Space Flight [email protected] Hartman Manager Center Prof. Yasuo Project Institute of Space and Tanaka Scientist Aeronautical Science Dr. Guenter Project NASA Headquarters [email protected] R. Reigler Manager

Selected References

Tanaka, Y., The ASTRO-D mission, In--Observatories in Earth Orbit and Beyond, edited by Y. Kondo, IAU Colloq. 123, Kluwer, 81-87, 1990.

US Active Archive for ASCA Information/Data

The ASCA Archive at HEASARC

Other Sources of ASCA Information/Data

Japan ASCA Data Archive at ISAS ASCA mission page at ISAS The UK ASCA Data Archive at Leicester

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Personnel Astra 1C

Publications NSSDC ID: 1993-031A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Astra 1-C was a Luxembourg geostationary communications 22653 spacecraft launched by an Ariane 4 rocket from the Kourou Space Center in French Guiana. It joined its two predecessors, 1-A and 1-B, at 19.2 deg longitude. It had the capacity of 16 Facts in Brief transponders that cater for 48 channels, all to become Launch Date: 1993-05- operational by August 1993. It's design life is 15 years. 11 Launch Vehicle: Ariane 4 Launch Site: Kourou, French Guiana Mass: 2790.0 kg

Funding Agency

Societe Europeenne des Satellites (Luxembourg) (Luxembourg)

Discipline

Communications

Additional Information

Launch/Orbital information for Astra 1C

Experiments on Astra 1C

Data collections from Astra 1C

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Personnel Atlas 2

Publications NSSDC ID: ATLAS2 Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The second flight in a series of Space Shuttle-Spacelab STS 56/Atlas 2 missions, designated the Atmospheric Laboratory for Applications and Science (ATLAS), was part of NASA's Mission to Planet Earth. The first ATLAS was flown on STS 45 Facts in Brief in March 1992. The ATLAS series was intended to study the Launch Date: 1993-04- composition of the middle atmosphere and its possible 07 variations due to solar changes over the course of an 11-year Launch solar cycle. The second flight of ATLAS focused on Vehicle: Shuttle atmospheric and solar physics studies and did not include the Launch Site: Cape experiments on space plasma physics and astronomy that Canaveral, United States were flown with the ATLAS 1 payload. The ATLAS 2 Mass: 18430.6 kg instruments were mounted on Spacelab pallets (provided by ESA) in the Shuttle payload bay. The ATLAS 2 instrument power supply, command and data handling system and Funding Agency temperature control systems were housed in a pressurized container called an igloo located in front of the pallet. The NASA-Office of Space Shuttle's changing orientation to Earth placed the experiments Science Applications in advantageous orbiting locations to observe the atmosphere (United States) and the Sun. The Shuttle orbiter orientation was either inertially fixed so that selected instruments were pointed at the Disciplines Sun, or nadir pointed for observations of the Earth's atmosphere. Crew members were in consultation with the Earth Science investigators while controlling and monitoring the experiments. Solar Physics The atmospheric and solar instrument data were also used to provide correlative measurements with the Upper Atmosphere Research Satellite (UARS) and the Solar-Backscattered Additional Ultraviolet (SBUV/2) instruments on board the NOAA polar Information orbiters. The ATLAS 2 core instruments consisted of: (1) Active Cavity Radiometer Irradiance Monitor (ACRIM); (2) Launch/Orbital Measurement of the Solar Constant (SOLCON); (3) Solar information for Atlas 2 Spectrum Measurement (SOLSPEC); (4) Solar Ultraviolet PDMP information for Spectral Irradiance Monitor (SUSIM); (5) Atmospheric Trace Atlas 2 Molecule Spectroscopy (ATMOS); and, (6) Millimeter-Wave Telecommunications Atmospheric Sounder (MAS). The ATLAS 2 payload was co- information for Atlas 2 manifested with the Shuttle Solar Backscatter Ultraviolet (SSBUV 05) experiment and integrated into the ATLAS Experiments on Atlas 2 Science Plan. Data collections from Atlas 2

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Personnel

Name Role Original Affiliation E-mail Dr. Earl J. Project NASA Headquarters Montoya Manager Dr. Jack A. Program NASA Goddard Space Kaye Scientist Flight Center Dr. Timothy L. Mission NASA Marshall Space [email protected] Miller Scientist Flight Center Mr. Anthony M Mission NASA Marshall Space [email protected] O'Neil Manager Flight Center

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Saturday, 07 May 2011

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Personnel Cosmos 2230

Publications NSSDC ID: 1993-001A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2230, a C.I.S. navigational spacecraft in the Cicada 22307 series for locating the whereabouts of ships on the ocean, was launched by a Cosmos rocket from the Plesetsk cosmodrome. Facts in Brief

Launch Date: 1993-01- 12 Launch Vehicle: Cosmos Launch Site: Plesetsk, Russia Mass: 825.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Navigation & Global Positioning

Additional Information

Launch/Orbital information for Cosmos 2230

Experiments on Cosmos 2230

Data collections from Cosmos 2230

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Cosmos 2231

NSSDC ID: 1993-004A Description

Cosmos 2231 was a Russian photo surveillance satellite launched from the Plesetsk cosmodrome aboard a Soyuz rocket. Two small film capsules were recovered in flight and the main reentry capsule with remaining film, camera, and computer systems at end of flight. Alternate Names

22317

Facts in Brief

Launch Date: 1993-01-19 Launch Vehicle: Soyuz Launch Site: Plesetsk, Russia Mass: 6600.0 kg Funding Agency

Unknown (U.S.S.R)

Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for Cosmos 2231

Experiments on Cosmos 2231

Data collections from Cosmos 2231

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Sunday, 08 May 2011

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Personnel Cosmos 2232

Publications NSSDC ID: 1993-006A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2232 was a Russian missile early warning satellite 22321 launched from the Plesetsk cosmodrome aboard a Molniya rocket. It was part of the Oko constellation of satellites and covered the plane 4 - 34 degree longitude of ascending node. Facts in Brief Launch Date: 1993-01- 26 Launch Vehicle: Molniya-M Launch Site: Plesetsk, Russia Mass: 1900.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for Cosmos 2232

Experiments on Cosmos 2232

Data collections from Cosmos 2232

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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Personnel Cosmos 2233

Publications NSSDC ID: 1993-008A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2233 was part of a 6-satellite Russian military 22487 navigation system distributed in orbital planes spaced 30 degrees apart, and launched from the Plesetsk cosmodrome aboard a Cosmos rocket. Navigation information was derived Facts in Brief from Doppler-shifted VHF transmissions (approximately 150 Launch Date: 1993-02- and 400 MHz) of the satellite position and orbital data. By 08 acquiring fixes from several satellite, a user's location could be Launch calculated with an accuracy of 100 m. The time needed to Vehicle: Cosmos ascertain a position was dependent upon the user's latitude Launch Site: Plesetsk, and the number of operational spacecraft in orbit. Normally, Russia accurate location determination could be made within 1-2 Mass: 825.0 kg hours.

Funding Agency

Unknown (U.S.S.R)

Discipline

Navigation & Global Positioning

Additional Information

Launch/Orbital information for Cosmos 2233

Experiments on Cosmos 2233

Data collections from Cosmos 2233

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Personnel Cosmos 2234

Publications NSSDC ID: 1993-010A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2234 was a Russian Global Navigation Satellite 22512 System (GLONASS) satellite launched from the Baikonur cosmodrome aboard a Proton rocket. Originally established in order to locate the Soviet Union's civil aircraft and its merchant Facts in Brief and fishing vessels, the signals were used by many American Launch Date: 1993-02- GPS system receivers as a complement/backup to the GPS 17 system itself. The operational system contained 21 satellites in Launch Vehicle: Proton 3 orbital planes, with 3 on-orbit backups. Each satellite was Launch Site: Tyuratam identified by its slot number, which defined the orbital plane (1- (Baikonur Cosmodrome), 8, 9-16, 17-24) and the location within the plane. The 3 orbital Kazakhstan planes were separated 120 degrees, and the satellites within Mass: 1400.0 kg the same orbit plane by 45 degrees. The orbits were roughly Nominal circular with an inclination of about 64.8 degrees, a semi-axis Power: 1600.0 W of 25,440 km, and a period of 11h 15m 44s.

The 3-axis stabilized spacecraft possessed a mass of about Funding Agency 1,400 kg, a slight increase over the 1,250 original model. The diameter and height of the satellite bus were approximately 2.4 Scientific Production m and 3.7 m, respectively, with a solar array span of 7.2 m for Association(Russia) an electrical power generation capability of 1.6 kW at (Russia) beginning of life. The aft payload structure housed 12 primary antennas for L-band transmissions. Laser corner-cube Discipline reflectors were also carried to aid in precise orbit determination and gedetic research. Navigation & Global Positioning

Additional Information

Launch/Orbital information for Cosmos 2234

Experiments on Cosmos 2234

Data collections from Cosmos 2234

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Personnel Cosmos 2235

Publications NSSDC ID: 1993-010B Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2235 was a Russian Global Navigation Satellite 22513 System (GLONASS) satellite launched from the Baikonur cosmodrome aboard a Proton rocket. Originally established in order to locate the Soviet Union's civil aircraft and its merchant Facts in Brief and fishing vessels, the signals were used by many American Launch Date: 1993-02- GPS system receivers as a complement/backup to the GPS 17 system itself. The operational system contained 21 satellites in Launch Vehicle: Proton 3 orbital planes, with 3 on-orbit backups. Each satellite was Launch Site: Tyuratam identified by its slot number, which defined the orbital plane (1- (Baikonur Cosmodrome), 8, 9-16, 17-24) and the location within the plane. The 3 orbital Kazakhstan planes were separated 120 degrees, and the satellites within Mass: 1400.0 kg the same orbit plane by 45 degrees. The orbits were roughly Nominal circular with an inclination of about 64.8 degrees, a semi-axis Power: 1600.0 W of 25,440 km, and a period of 11h 15m 44s.

Additional Information

Launch/Orbital information for Cosmos 2235

Experiments on Cosmos 2235

Data collections from Cosmos 2235

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Personnel Cosmos 2236

Publications NSSDC ID: 1993-010C Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2236 was a Russian Global Navigation Satellite 22514 System (GLONASS) satellite launched from the Baikonur cosmodrome aboard a Proton rocket. Originally established in order to locate the Soviet Union's civil aircraft and its merchant Facts in Brief and fishing vessels, the signals were used by many American Launch Date: 1993-02- GPS system receivers as a complement/backup to the GPS 17 system itself. The operational system contained 21 satellites in Launch Vehicle: Proton 3 orbital planes, with 3 on-orbit backups. Each satellite was Launch Site: Tyuratam identified by its slot number, which defined the orbital plane (1- (Baikonur Cosmodrome), 8, 9-16, 17-24) and the location within the plane. The 3 orbital Kazakhstan planes were separated 120 degrees, and the satellites within Mass: 1400.0 kg the same orbit plane by 45 degrees. The orbits were roughly Nominal circular with an inclination of about 64.8 degrees, a semi-axis Power: 1600.0 W of 25,440 km, and a period of 11h 15m 44s.

Additional Information

Launch/Orbital information for Cosmos 2236

Experiments on Cosmos 2236

Data collections from Cosmos 2236

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Personnel Cosmos 2237

Publications NSSDC ID: 1993-016A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2237 was a Russian ELINT (Electronic and Signals 22565 Intelligence) satellite launched from the Baikonur cosmodrome aboard a Zenit 2 rocket. Facts in Brief

Based on the first generation Tselina ELINT, TSNII-KS at the Launch Date: 1993-03- beginning of the 1970's developed the specifications for an 25 improved model with increased frequency range and on-board Launch Vehicle: Zenit method of determining the position of fixed transmitters. The Launch Site: Tyuratam Tselina-2 was authorised in March 1973 and handled by prime (Baikonur Cosmodrome), contractor TsNIRTI Minradioprom (M E Zaslovskiy) for the Kazakhstan ELINT equipment and KB Yuzhnoye (KB-3, B S Khimrov) for Mass: 6000.0 kg the spacecraft bus. The launch vehicle was by OKB MEI Minvuza (A F Bogomolov) and the encrypted communications system by 0-TsNII KS MO. The draft project was drawn up in Funding Agency the first quarter of 1974 and the MO approved the TTZ in May 1974. After a long review process the VPK issued the project Unknown (U.S.S.R) plan for development of the system in December 1976. It would now use the new Zenit launch vehicle. The first flight Discipline trials system was completed in December 1980, but delays in the development of the Zenit launch vehicle meant that the first Surveillance and Other two trials flights had to be aboard Proton boosters in 1984 and Military 1985. Zenit-boosted flights began in 1985 and the system was accepted into service in 1987. Additional Information

Launch/Orbital information for Cosmos 2237

Experiments on Cosmos 2237

Data collections from Cosmos 2237

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.16, 26 April 2011

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Personnel Cosmos 2238

Publications NSSDC ID: 1993-018A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2238 was a Russian naval reconnaisance satellite 22585 launched from the Baikonur cosmodrome aboard a Tsyklon 2 rocket. This naval forces monitoring spacecraft was used to determine the position of enemy naval forces through detection Facts in Brief and triangulation of their electromagnetic emissions (radio, Launch Date: 1993-03- radar, etc). 30 Launch Vehicle: Tsiklon-2 Launch Site: Tyuratam (Baikonur Cosmodrome), Kazakhstan Mass: 3150.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for Cosmos 2238

Experiments on Cosmos 2238

Data collections from Cosmos 2238

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.16, 26 April 2011

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Personnel Cosmos 2239

Publications NSSDC ID: 1993-020A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2239 was part of a 6-satellite Russian military 22590 navigation system distributed in orbital planes spaced 30 degrees apart, and launched from the Plesetsk cosmodrome aboard a Cosmos rocket. Navigation information was derived Facts in Brief from Doppler-shifted VHF transmissions (approximately 150 Launch Date: 1993-04- and 400 MHz) of the satellite position and orbital data. By 02 acquiring fixes from several satellite, a user's location could be Launch calculated with an accuracy of 100 m. The time needed to Vehicle: Cosmos ascertain a position was dependent upon the user's latitude Launch Site: Plesetsk, and the number of operational spacecraft in orbit. Normally, Russia accurate location determination could be made within 1-2 Mass: 825.0 kg hours.

Funding Agency

Unknown (U.S.S.R)

Discipline

Navigation & Global Positioning

Additional Information

Launch/Orbital information for Cosmos 2239

Experiments on Cosmos 2239

Data collections from Cosmos 2239

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.16, 26 April 2011

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Personnel Cosmos 2240

Publications NSSDC ID: 1993-021A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2240 was a Russian photo surveillance satellite 22592 launched from the Plesetsk cosmodrome aboard a Soyuz rocket. Two small film capsules were recovered in flight and the main re-entry capsule with remaining film, camera, and Facts in Brief computer systems at end of flight. Launch Date: 1993-04- 02 Launch Vehicle: Soyuz-U Launch Site: Plesetsk, Russia Mass: 6600.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for Cosmos 2240

Experiments on Cosmos 2240

Data collections from Cosmos 2240

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.16, 26 April 2011

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Personnel Cosmos 2241

Publications NSSDC ID: 1993-022A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2241 was a Russian missile early warning satellite 22594 launched from the Plesetsk cosmodrome aboard a Molniya rocket. It was part of the Oko constellation of satellites and covered the plane 7 - 161 degree longitude of ascending node. Facts in Brief Launch Date: 1993-04- 06 Launch Vehicle: Molniya-M Launch Site: Plesetsk, Russia Mass: 1900.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for Cosmos 2241

Experiments on Cosmos 2241

Data collections from Cosmos 2241

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.16, 26 April 2011

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Personnel Cosmos 2242

Publications NSSDC ID: 1993-024A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2242 was a Russian ELINT (Electronic and Signals 22626 Intelligence) satellite launched from the Plesetsk cosmodrome.

From 1965 to 1967 two dedicated ELINT systems were tested: Facts in Brief the Tselina and the Navy's US. Both reached service, since the Launch Date: 1993-04- Ministry of Defence could not force a single system on the 16 military services. Launch Vehicle: Tsiklon-3 Tselina was developed by Yuzhnoye and consisted of two Launch Site: Plesetsk, satellites: Tselina-O for general observations and Tselina-D for Russia detailed observations. ELINT systems for Tselina were first Mass: 2000.0 kg tested under the Cosmos designation in 1962 to 1965. The first Tselina-O was launched in 1970. The Tselina-D took a long time to enter service due to delays in payload development Funding Agency and weight growth. The whole Tselina system was not operational until 1976. Constant improvement resulted in Unknown (U.S.S.R) Tselina-O being abandoned in 1984 and all systems being put on Tselina-D. Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for Cosmos 2242

Experiments on Cosmos 2242

Data collections from Cosmos 2242

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.16, 26 April 2011

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Personnel Cosmos 2243

Publications NSSDC ID: 1993-028A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2243 was a variation of the Yantar-class spacecraft 22641 used to conduct high-precision topographic surveys. These spacecraft, now referred to as Kometa, typically remained in orbit for 44-45 days and were distinguished by their relatively Facts in Brief circular orbits between 210 and 280 km. These missions were Launch Date: 1993-04- always launched from the Baikonur cosmodrome into 27 inclinations of 65 degrees or 70 degrees at the rate of one or Launch two per year. Vehicle: Soyuz-U Launch Site: Tyuratam (Baikonur Cosmodrome), Kazakhstan Mass: 6600.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Earth Science

Additional Information

Launch/Orbital information for Cosmos 2243

Experiments on Cosmos 2243

Data collections from Cosmos 2243

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.16, 26 April 2011

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Personnel Cosmos 2244

Publications NSSDC ID: 1993-029A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2244 was a Russian naval reconnaisance satellite 22643 launched from the Baikonur cosmodrome aboard a Tsyklon 2 rocket. This naval forces monitoring spacecraft was used to determine the position of enemy naval forces through detection Facts in Brief and triangulation of their electrmagnetic emissions (radio, Launch Date: 1993-04- radar, etc). 27 Launch Vehicle: Tsiklon-2 Launch Site: Tyuratam (Baikonur Cosmodrome), Kazakhstan Mass: 3150.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for Cosmos 2244

Experiments on Cosmos 2244

Data collections from Cosmos 2244

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.16, 26 April 2011

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Personnel Cosmos 2245

Publications NSSDC ID: 1993-030A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Strela 3 system was a communications satellite 22646 constellation devoted to military and government communications. It was a simple store-dump repeater system which were particulatly useful in relaying non-essential traffic Facts in Brief between the Russian Federation and overseas stations or Launch Date: 1993-05- forces. The Strela 3 system, which began in 1985, was 11 launched by the Tsyklon-3 booster from the Plesetsk Launch cosmodrome into orbits near 1400 km at inclinations of 82.6 Vehicle: Tsiklon-3 degrees with six spacecraft stacked atop each launch vehicle. Launch Site: Plesetsk, Two orbital planes were spaced 90 degrees apart, apparently Russia each contained 10-12 operational spacecraft. Normally, two Mass: 220.0 kg missions were conducted per year, suggesting an average spacecraft life-time of approximately 24 months. The 220 kg spacecraft had a diameter of 1.0 m and a main bus height of Funding Agency 1.5 m. A gravity-gradient beam was extended on-orbit to provide attitude stabilization. Unknown (U.S.S.R)

Discipline

Communications

Additional Information

Launch/Orbital information for Cosmos 2245

Experiments on Cosmos 2245

Data collections from Cosmos 2245

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.16, 26 April 2011

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Personnel Cosmos 2246

Publications NSSDC ID: 1993-030B Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Strela 3 system was a communications satellite 22647 constellation devoted to military and government communications. It was a simple store-dump repeater system which were particulatly useful in relaying non-essential traffic Facts in Brief between the Russian Federation and overseas stations or Launch Date: 1993-05- forces. The Strela 3 system, which began in 1985, was 11 launched by the Tsyklon-3 booster from the Plesetsk Launch cosmodrome into orbits near 1400 km at inclinations of 82.6 Vehicle: Tsiklon-3 degrees with six spacecraft stacked atop each launch vehicle. Launch Site: Plesetsk, Two orbital planes were spaced 90 degrees apart, apparently Russia each contained 10-12 operational spacecraft. Normally, two Mass: 220.0 kg missions were conducted per year, suggesting an average spacecraft life-time of approximately 24 months. The 220 kg spacecraft had a diameter of 1.0 m and a main bus height of Funding Agency 1.5 m. A gravity-gradient beam was extended on-orbit to provide attitude stabilization. Unknown (U.S.S.R)

Discipline

Communications

Additional Information

Launch/Orbital information for Cosmos 2246

Experiments on Cosmos 2246

Data collections from Cosmos 2246

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.16, 26 April 2011

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Personnel Cosmos 2247

Publications NSSDC ID: 1993-030C Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Strela 3 system was a communications satellite 22648 constellation devoted to military and government communications. It was a simple store-dump repeater system which were particulatly useful in relaying non-essential traffic Facts in Brief between the Russian Federation and overseas stations or Launch Date: 1993-05- forces. The Strela 3 system, which began in 1985, was 11 launched by the Tsyklon-3 booster from the Plesetsk Launch cosmodrome into orbits near 1400 km at inclinations of 82.6 Vehicle: Tsiklon-3 degrees with six spacecraft stacked atop each launch vehicle. Launch Site: Plesetsk, Two orbital planes were spaced 90 degrees apart, apparently Russia each contained 10-12 operational spacecraft. Normally, two Mass: 220.0 kg missions were conducted per year, suggesting an average spacecraft life-time of approximately 24 months. The 220 kg spacecraft had a diameter of 1.0 m and a main bus height of Funding Agency 1.5 m. A gravity-gradient beam was extended on-orbit to provide attitude stabilization. Unknown (U.S.S.R)

Discipline

Communications

Additional Information

Launch/Orbital information for Cosmos 2247

Experiments on Cosmos 2247

Data collections from Cosmos 2247

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.16, 26 April 2011

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Personnel Cosmos 2248

Publications NSSDC ID: 1993-030D Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Strela 3 system was a communications satellite 22649 constellation devoted to military and government communications. It was a simple store-dump repeater system which were particulatly useful in relaying non-essential traffic Facts in Brief between the Russian Federation and overseas stations or Launch Date: 1993-05- forces. The Strela 3 system, which began in 1985, was 11 launched by the Tsyklon-3 booster from the Plesetsk Launch cosmodrome into orbits near 1400 km at inclinations of 82.6 Vehicle: Tsiklon-3 degrees with six spacecraft stacked atop each launch vehicle. Launch Site: Plesetsk, Two orbital planes were spaced 90 degrees apart, apparently Russia each contained 10-12 operational spacecraft. Normally, two Mass: 220.0 kg missions were conducted per year, suggesting an average spacecraft life-time of approximately 24 months. The 220 kg spacecraft had a diameter of 1.0 m and a main bus height of Funding Agency 1.5 m. A gravity-gradient beam was extended on-orbit to provide attitude stabilization. Unknown (U.S.S.R)

Discipline

Communications

Additional Information

Launch/Orbital information for Cosmos 2248

Experiments on Cosmos 2248

Data collections from Cosmos 2248

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.16, 26 April 2011

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Personnel Cosmos 2249

Publications NSSDC ID: 1993-030E Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Strela 3 system was a communications satellite 22650 constellation devoted to military and government communications. It was a simple store-dump repeater system which were particulatly useful in relaying non-essential traffic Facts in Brief between the Russian Federation and overseas stations or Launch Date: 1993-05- forces. The Strela 3 system, which began in 1985, was 11 launched by the Tsyklon-3 booster from the Plesetsk Launch cosmodrome into orbits near 1400 km at inclinations of 82.6 Vehicle: Tsiklon-3 degrees with six spacecraft stacked atop each launch vehicle. Launch Site: Plesetsk, Two orbital planes were spaced 90 degrees apart, apparently Russia each contained 10-12 operational spacecraft. Normally, two Mass: 220.0 kg missions were conducted per year, suggesting an average spacecraft life-time of approximately 24 months. The 220 kg spacecraft had a diameter of 1.0 m and a main bus height of Funding Agency 1.5 m. A gravity-gradient beam was extended on-orbit to provide attitude stabilization. Unknown (U.S.S.R)

Discipline

Communications

Additional Information

Launch/Orbital information for Cosmos 2249

Experiments on Cosmos 2249

Data collections from Cosmos 2249

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.16, 26 April 2011

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Personnel Cosmos 2250

Publications NSSDC ID: 1993-030F Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Strela 3 system was a communications satellite 22651 constellation devoted to military and government communications. It was a simple store-dump repeater system which were particulatly useful in relaying non-essential traffic Facts in Brief between the Russian Federation and overseas stations or Launch Date: 1993-05- forces. The Strela 3 system, which began in 1985, was 11 launched by the Tsyklon-3 booster from the Plesetsk Launch cosmodrome into orbits near 1400 km at inclinations of 82.6 Vehicle: Tsiklon-3 degrees with six spacecraft stacked atop each launch vehicle. Launch Site: Plesetsk, Two orbital planes were spaced 90 degrees apart, apparently Russia each contained 10-12 operational spacecraft. Normally, two Mass: 220.0 kg missions were conducted per year, suggesting an average spacecraft life-time of approximately 24 months. The 220 kg spacecraft had a diameter of 1.0 m and a main bus height of Funding Agency 1.5 m. A gravity-gradient beam was extended on-orbit to provide attitude stabilization. Unknown (U.S.S.R)

Discipline

Communications

Additional Information

Launch/Orbital information for Cosmos 2250

Experiments on Cosmos 2250

Data collections from Cosmos 2250

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.16, 26 April 2011

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Personnel Cosmos 2251

Publications NSSDC ID: 1993-036A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The lowest level of the three-tier communications satellite 22675 constellation is now populated with two distinct systems devoted to military and government communications. Both systems are assessed to be simple store-dump repeaters Facts in Brief which were particularly useful in relaying non-essential traffic Launch Date: 1993-06- between the Russian Federation and overseas stations of 16 forces. The first Strela (which means "Arrow" in Russian) Launch system debuted in 1970 and consisted of 750-1000 kg Vehicle: Cosmos satellites deployed at mean altitudes of 800 km in three orbital Launch Site: Plesetsk, planes inclined 74 degrees to the equator and spaced 120 Russia degrees apart. These Strela 2 spacecraft were launched Mass: 900.0 kg separately by the Kosmos launch vehicle from the Plesetsk cosmodrome into each orbital plane at intervals of 24-36 months. The activity of these satellites could be monitored via Funding Agency a characteristic CW beacon emitted on a frequency of 153.660 MHz. Unknown (U.S.S.R)

On 10 February 2009 at approximately 16:56 UT the Cosmos Discipline 2251 satellite collided with Iridium 33 (1997-051C). The collision took place at about 800 km altitude. Communications

Additional Information

Launch/Orbital information for Cosmos 2251

Experiments on Cosmos 2251

Data collections from Cosmos 2251

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.16, 26 April 2011

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Personnel Cosmos 2252

Publications NSSDC ID: 1993-038A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Strela 3 system was a communications satellite 22687 constellation devoted to military and government communications. It was a simple store-dump repeater system which were particulatly useful in relaying non-essential traffic Facts in Brief between the Russian Federation and overseas stations or Launch Date: 1993-06- forces. The Strela 3 system, which began in 1985, was 24 launched by the Tsyklon-3 booster from the Plesetsk Launch cosmodrome into orbits near 1400 km at inclinations of 82.6 Vehicle: Tsiklon-3 degrees with six spacecraft stacked atop each launch vehicle. Launch Site: Plesetsk, Two orbital planes were spaced 90 degrees apart, apparently Russia each contained 10-12 operational spacecraft. Normally, two Mass: 220.0 kg missions were conducted per year, suggesting an average spacecraft life-time of approximately 24 months. The 220 kg spacecraft had a diameter of 1.0 m and a main bus height of Funding Agency 1.5 m. A gravity-gradient beam was extended on-orbit to provide attitude stabilization. Unknown (U.S.S.R)

Discipline

Communications

Additional Information

Launch/Orbital information for Cosmos 2252

Experiments on Cosmos 2252

Data collections from Cosmos 2252

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.16, 26 April 2011

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Personnel Cosmos 2253

Publications NSSDC ID: 1993-038B Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Strela 3 system was a communications satellite 22688 constellation devoted to military and government communications. It was a simple store-dump repeater system which were particulatly useful in relaying non-essential traffic Facts in Brief between the Russian Federation and overseas stations or Launch Date: 1993-06- forces. The Strela 3 system, which began in 1985, was 24 launched by the Tsyklon-3 booster from the Plesetsk Launch cosmodrome into orbits near 1400 km at inclinations of 82.6 Vehicle: Tsiklon-3 degrees with six spacecraft stacked atop each launch vehicle. Launch Site: Plesetsk, Two orbital planes were spaced 90 degrees apart, apparently Russia each contained 10-12 operational spacecraft. Normally, two Mass: 220.0 kg missions were conducted per year, suggesting an average spacecraft life-time of approximately 24 months. The 220 kg spacecraft had a diameter of 1.0 m and a main bus height of Funding Agency 1.5 m. A gravity-gradient beam was extended on-orbit to provide attitude stabilization. Unknown (U.S.S.R)

Discipline

Communications

Additional Information

Launch/Orbital information for Cosmos 2253

Experiments on Cosmos 2253

Data collections from Cosmos 2253

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.16, 26 April 2011

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Personnel Cosmos 2254

Publications NSSDC ID: 1993-038C Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Strela 3 system was a communications satellite 22689 constellation devoted to military and government communications. It was a simple store-dump repeater system which were particulatly useful in relaying non-essential traffic Facts in Brief between the Russian Federation and overseas stations or Launch Date: 1993-06- forces. The Strela 3 system, which began in 1985, was 24 launched by the Tsyklon-3 booster from the Plesetsk Launch cosmodrome into orbits near 1400 km at inclinations of 82.6 Vehicle: Tsiklon-3 degrees with six spacecraft stacked atop each launch vehicle. Launch Site: Plesetsk, Two orbital planes were spaced 90 degrees apart, apparently Russia each contained 10-12 operational spacecraft. Normally, two Mass: 220.0 kg missions were conducted per year, suggesting an average spacecraft life-time of approximately 24 months. The 220 kg spacecraft had a diameter of 1.0 m and a main bus height of Funding Agency 1.5 m. A gravity-gradient beam was extended on-orbit to provide attitude stabilization. Unknown (U.S.S.R)

Discipline

Communications

Additional Information

Launch/Orbital information for Cosmos 2254

Experiments on Cosmos 2254

Data collections from Cosmos 2254

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.16, 26 April 2011

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Personnel Cosmos 2255

Publications NSSDC ID: 1993-038D Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Strela 3 system was a communications satellite 22690 constellation devoted to military and government communications. It was a simple store-dump repeater system which were particulatly useful in relaying non-essential traffic Facts in Brief between the Russian Federation and overseas stations or Launch Date: 1993-06- forces. The Strela 3 system, which began in 1985, was 24 launched by the Tsyklon-3 booster from the Plesetsk Launch cosmodrome into orbits near 1400 km at inclinations of 82.6 Vehicle: Tsiklon-3 degrees with six spacecraft stacked atop each launch vehicle. Launch Site: Plesetsk, Two orbital planes were spaced 90 degrees apart, apparently Russia each contained 10-12 operational spacecraft. Normally, two Mass: 220.0 kg missions were conducted per year, suggesting an average spacecraft life-time of approximately 24 months. The 220 kg spacecraft had a diameter of 1.0 m and a main bus height of Funding Agency 1.5 m. A gravity-gradient beam was extended on-orbit to provide attitude stabilization. Unknown (U.S.S.R)

Discipline

Communications

Additional Information

Launch/Orbital information for Cosmos 2255

Experiments on Cosmos 2255

Data collections from Cosmos 2255

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.16, 26 April 2011

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Personnel Cosmos 2256

Publications NSSDC ID: 1993-038E Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Strela 3 system was a communications satellite 22691 constellation devoted to military and government communications. It was a simple store-dump repeater system which were particulatly useful in relaying non-essential traffic Facts in Brief between the Russian Federation and overseas stations or Launch Date: 1993-06- forces. The Strela 3 system, which began in 1985, was 24 launched by the Tsyklon-3 booster from the Plesetsk Launch cosmodrome into orbits near 1400 km at inclinations of 82.6 Vehicle: Tsiklon-3 degrees with six spacecraft stacked atop each launch vehicle. Launch Site: Plesetsk, Two orbital planes were spaced 90 degrees apart, apparently Russia each contained 10-12 operational spacecraft. Normally, two Mass: 220.0 kg missions were conducted per year, suggesting an average spacecraft life-time of approximately 24 months. The 220 kg spacecraft had a diameter of 1.0 m and a main bus height of Funding Agency 1.5 m. A gravity-gradient beam was extended on-orbit to provide attitude stabilization. Unknown (U.S.S.R)

Discipline

Communications

Additional Information

Launch/Orbital information for Cosmos 2256

Experiments on Cosmos 2256

Data collections from Cosmos 2256

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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Personnel Cosmos 2257

Publications NSSDC ID: 1993-038F Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Strela 3 system was a communications satellite 22692 constellation devoted to military and government communications. It was a simple store-dump repeater system which were particulatly useful in relaying non-essential traffic Facts in Brief between the Russian Federation and overseas stations or Launch Date: 1993-06- forces. The Strela 3 system, which began in 1985, was 24 launched by the Tsyklon-3 booster from the Plesetsk Launch cosmodrome into orbits near 1400 km at inclinations of 82.6 Vehicle: Tsiklon-3 degrees with six spacecraft stacked atop each launch vehicle. Launch Site: Plesetsk, Two orbital planes were spaced 90 degrees apart, apparently Russia each contained 10-12 operational spacecraft. Normally, two Mass: 220.0 kg missions were conducted per year, suggesting an average spacecraft life-time of approximately 24 months. The 220 kg spacecraft had a diameter of 1.0 m and a main bus height of Funding Agency 1.5 m. A gravity-gradient beam was extended on-orbit to provide attitude stabilization. Unknown (U.S.S.R)

Discipline

Communications

Additional Information

Launch/Orbital information for Cosmos 2257

Experiments on Cosmos 2257

Data collections from Cosmos 2257

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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Personnel Cosmos 2258

Publications NSSDC ID: 1993-044A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2258 was a Russian naval reconnaisance satellite 22709 launched from the Baikonur cosmodrome aboard a Tsyklon 2 rocket. This naval forces monitoring spacecraft was used to determine the position of enemy naval forces through detection Facts in Brief and triangulation of their electromagnetic emissions (radio, Launch Date: 1993-07- radar, etc). 07 Launch Vehicle: Tsiklon-2 Launch Site: Tyuratam (Baikonur Cosmodrome), Kazakhstan Mass: 3150.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for Cosmos 2258

Experiments on Cosmos 2258

Data collections from Cosmos 2258

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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Personnel Cosmos 2259

Publications NSSDC ID: 1993-045A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2259 was a Russian photo surveillance satellite 22716 launched from the Plesetsk cosmodrome aboard a Soyuz rocket. Two small film capsules were recovered in flight and the main re-entry capsule with remaining film, camera, and Facts in Brief computer systems at end of flight. Launch Date: 1993-07- 14 Launch Vehicle: Soyuz-U Launch Site: Plesetsk, Russia Mass: 6600.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for Cosmos 2259

Experiments on Cosmos 2259

Data collections from Cosmos 2259

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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Personnel Cosmos 2260

Publications NSSDC ID: 1993-047A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2260, a CIS natural resources satellite, was launched 22721 from the Plesetsk cosmodrome aboard a Soyuz rocket. It provided photography of the earth's surface for the purpose of the natural resource mapping and area monitoring on behalf of Facts in Brief various branches of the Russian ecomony and in the interest Launch Date: 1993-07- of international cooperation. 22 Launch Vehicle: Soyuz-U Launch Site: Plesetsk, Russia Mass: 6300.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Earth Science

Additional Information

Launch/Orbital information for Cosmos 2260

Experiments on Cosmos 2260

Data collections from Cosmos 2260

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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Personnel Cosmos 2261

Publications NSSDC ID: 1993-051A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2261 was a Russian missile early warning satellite 22741 launched from the Plesetsk cosmodrome aboard a Molniya rocket. It was part of the Oko constellation of satellites and covered the plane 9 - 235 degree longitude ascending node. Facts in Brief Launch Date: 1993-08- 10 Launch Vehicle: Molniya-M Launch Site: Plesetsk, Russia Mass: 1900.0 kg

Funding Agency

Russian Space Agency (U.S.S.R)

Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for Cosmos 2261

Experiments on Cosmos 2261

Data collections from Cosmos 2261

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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Personnel Cosmos 2262

Publications NSSDC ID: 1993-057A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2262 was the fifth of the sixth generation photo 22789 reconnaisance satellites launched from the Baikonur cosmodrome using the Soyuz-U2 launch vehicle, which had otherwise been restricted to supporting Soyuz-TM and Facts in Brief Progress-M missions. The spacecraft was inserted into an Launch Date: 1993-09- orbital inclination of 64.8 degrees with mean operational 07 altitudes normally between 240 and 260 km. The sixth Launch generation spacecraft, believed to carry both film return Vehicle: Soyuz-U2 capsules and digital transmission capabilities, have only flown Launch Site: Tyuratam six times; once each year during 1989-1993 and once in 1997. (Baikonur Cosmodrome), Kazakhstan Mass: 6500.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for Cosmos 2262

Experiments on Cosmos 2262

Data collections from Cosmos 2262

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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Personnel Cosmos 2263

Publications NSSDC ID: 1993-059A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2263 was a Russian ELINT (Electronic and Signals 22802 Intelligence) satellite launched from the Baikonur cosmodrome aboard a Zenit 2 rocket. Facts in Brief

Based on the first generation Tselina ELINT, TSNII-KS at the Launch Date: 1993-09- beginning of the 1970's developed the specifications for an 16 improved model with increased frequency range and on-board Launch Vehicle: Zenit method of determining the position of fixed transmitters. The Launch Site: Tyuratam Tselina-2 was authorised in March 1973 and handled by prime (Baikonur Cosmodrome), contractor TsNIRTI Minradioprom (M E Zaslovskiy) for the Kazakhstan ELINT equipment and KB Yuzhnoye (KB-3, B S Khimrov) for Mass: 6000.0 kg the spacecraft bus. The launch vehicle was by OKB MEI Minvuza (A F Bogomolov) and the encrypted communications system by 0-TsNII KS MO. The draft project was drawn up in Funding Agency the first quarter of 1974 and the MO approved the TTZ in May 1974. After a long review process the VPK issued the project Unknown (U.S.S.R) plan for development of the system in December 1976. It would now use the new Zenit launch vehicle. The first flight Discipline trials system was completed in December 1980, but delays in the development of the Zenit launch vehicle meant that the first Surveillance and Other two trials flights had to be aboard Proton boosters in 1984 and Military 1985. Zenit-boosted flights began in 1985 and the system was accepted into service in 1987. Additional Information

Launch/Orbital information for Cosmos 2263

Experiments on Cosmos 2263

Data collections from Cosmos 2263

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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Personnel Cosmos 2264

Publications NSSDC ID: 1993-060A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2264 was a Russian naval reconnaisance satellite 22808 launched from the Baikonur cosmodrome aboard a Tsyklon 2 rocket. This naval forces monitoring spacecraft was used to determine the position of enemy naval forces through detection Facts in Brief and triangulation of their electromagnetic emissions (radio, Launch Date: 1993-09- radar, etc). 16 Launch Vehicle: Tsiklon-2 Launch Site: Tyuratam (Baikonur Cosmodrome), Kazakhstan Mass: 3150.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for Cosmos 2264

Experiments on Cosmos 2264

Data collections from Cosmos 2264

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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Personnel Cosmos 2265

Publications NSSDC ID: 1993-067A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events In 1969 KB Yuzhnoye introduced targets for exercise and test 22875 of PVO air defence and space tracking systems. The second generation consisted of Taifun-1 and Taifun-2 satellites, which differed in the type of equipment installed. In 1972 KB-3 under Facts in Brief B E Khimrov, with the co-operation of assisting organisations Launch Date: 1993-10- and the Ministry of Defence, completed the draft project. The 26 first Taifun-2 was completed in 1976. Flight trials were Launch conducted in the second half of the 1970's using Kosmos-3M Vehicle: Cosmos launch vehicles from Plesetsk and Kapustin Yar. The heads of Launch Site: Plesetsk, the State Trials Commission were B N Karpov, N N Zhukov, Russia and B G Zudin. Taifun-2 satellites were spherical in shape, 2 Mass: 500.0 kg m in diameter, with no external solar cells or antennae.

Funding Agency

Unknown (Russia)

Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for Cosmos 2265

Experiments on Cosmos 2265

Data collections from Cosmos 2265

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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Personnel Cosmos 2266

Publications NSSDC ID: 1993-070A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2266 was part of a 6-satellite Russian military 22888 navigation system distributed in orbital planes spaced 30 degrees apart, and launched from the Plesetsk cosmodrome aboard a Cosmos rocket. Navigation information was derived Facts in Brief from Doppler-shifted VHF transmissions (approximately 150 Launch Date: 1993-11- and 400 MHz) of the satellite position and orbital data. By 02 acquiring fixes from several satellite, a user's location could be Launch calculated with an accuracy of 100 m. The time needed to Vehicle: Cosmos ascertain a position was dependent upon the user's latitude Launch Site: Plesetsk, and the number of operational spacecraft in orbit. Normally, Russia accurate location determination could be made within 1-2 Mass: 825.0 kg hours.

Funding Agency

Unknown (Russia)

Discipline

Navigation & Global Positioning

Additional Information

Launch/Orbital information for Cosmos 2266

Experiments on Cosmos 2266

Data collections from Cosmos 2266

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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Personnel Cosmos 2267

Publications NSSDC ID: 1993-071A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2267 was a Russian digital photo surveillance satellite 22904 launched from the Baikonur cosmodrome aboard a Soyuz-U rocket. It remained in orbit for 418 days. Facts in Brief

Launch Date: 1993-11- 05 Launch Vehicle: Soyuz-U Launch Site: Plesetsk, Russia Mass: 6600.0 kg

Funding Agency

Unknown (Russia)

Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for Cosmos 2267

Experiments on Cosmos 2267

Data collections from Cosmos 2267

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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Personnel DBS-1

Publications NSSDC ID: 1993-078A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events DBS-1, a U.S.A. geostationary, communications spacecraft for 22930 high resolution TV broadcast, was launched by an Ariane 44-L booster from Kourou, French Guiana. It will cover the U.S.A. and many American countries. Facts in Brief Launch Date: 1993-12- 17 Launch Vehicle: Ariane 44L Launch Site: Kourou, French Guiana Mass: 2860.0 kg

Funding Agency

Unknown (French Guiana)

Discipline

Communications

Additional Information

Launch/Orbital information for DBS-1

Experiments on DBS-1

Data collections from DBS- 1

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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Personnel DSCS III-10

Publications NSSDC ID: 1993-046A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Defense Satellite Communications System (DSCS III-10) was USA 93 part of a US military satellite constellation placed in 22719 geosynchronous orbit to provide high-volume, secure voice and data communications. Phase II was a successor to the IDSCS (Initial Defense Satellite Communications System) Facts in Brief program which began in 1966 with the launch of the first 8 satellites of this constellation. The DSCS III system was used Launch Date: 1993-07- for high priority communications such as the exchange of 19 wartime information between defense officials and battlefield Launch Vehicle: Atlas 2 commanders. The military also used DSCS to transmit space Launch Site: Cape operations and early warning data to various systems and Canaveral, United States users. Mass: 2615.0 kg

Each satellite orbits the earth at an altitude of more than Funding Agency 23,000 miles. They carried a single channel transponder used for disseminating emergency action and force direction Department of Defense- messages to nuclear capable forces. Each satellite utilized six Department of the Air super high frequency transponder channels capable of Force (United States) providing worldwide secure voice and high rate data communications. Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for DSCS III- 10

Experiments on DSCS III- 10

Data collections from DSCS III-10

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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Personnel DSCS III-11

Publications NSSDC ID: 1993-074A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Defense Satellite Communications System (DSCS III-11) was USA 97 part of a US military satellite constellation placed in 22915 geosynchronous orbit to provide high-volume, secure voice and data communications. Phase II was a successor to the IDSCS (Initial Defense Satellite Communications System) Facts in Brief program which began in 1966 with the launch of the first 8 satellites of this constellation. The DSCS III system was used Launch Date: 1993-11- for high priority communications such as the exchange of 28 wartime information between defense officials and battlefield Launch Vehicle: Atlas- commanders. The military also used DSCS to transmit space Centaur operations and early warning data to various systems and Launch Site: Cape users. Canaveral, United States Mass: 2615.0 kg Each satellite orbits the earth at an altitude of more than 23,000 miles. They carried a single channel transponder used Funding Agency for disseminating emergency action and force direction messages to nuclear capable forces. Each satellite utilized six Department of Defense- super high frequency transponder channels capable of Department of the Air providing worldwide secure voice and high rate data Force (United States) communications.

Disciplines

Communications Surveillance and Other Military

Additional Information

Launch/Orbital information for DSCS III- 11

Experiments on DSCS III- 11

Data collections from DSCS III-11

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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Personnel DXS

Publications NSSDC ID: DXS Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Diffuse X-ray Spectrometer (DXS) was a single Diffuse X-Ray experiment shuttle payload designed to fly on multiple Spectrometer missions. The primary objective of the DXS payload was to obtain measurements on the diffuse soft X-ray background radiation in the Milky Way Galaxy. DXS flew as a shuttle cargo Facts in Brief bay attached payload using the Hitchhiker avionics and Shuttle Launch Date: 1993-01- Payload of Opportunity Carrier (SPOC) hardware, which 12 provided support systems for power, command, and telemetry Launch to the DXS instruments. DXS was first flown on the STS 54 Vehicle: Shuttle mission. See the experiment description for details on the Launch Site: Cape science objectives and instruments utilized. Canaveral, United States Mass: 1115.0 kg Nominal Power: 900.0 W

Funding Agency

NASA-Office of Space Science Applications (United States)

Discipline

Astronomy

Additional Information

Launch/Orbital information for DXS PDMP information for DXS Telecommunications information for DXS

Experiments on DXS

Data collections from DXS

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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Personnel

Name Role Original Affiliation E-mail Dr. Francis E. Mission NASA Goddard Space [email protected] Marshall Scientist Flight Center Dr. Louis J. Program NASA Headquarters Kaluzienski Scientist Mr. S. Chris Mission NASA Goddard Space [email protected] Dunker Manager Flight Center Mr. David B. Program NASA Headquarters [email protected] Jarrett Manager

Related Information/Data at NSSDC

STS 54

US Active Archive for DXS Information/Data

The DXS Archive at HEASARC

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Personnel EYESAT 1

Publications NSSDC ID: 1993-061C Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events EYESAT 1, an American microsatellite was one of the six Oscar 27 microsatellites that were launched along with SPOT 3 (93- 22825 061A). It was a relay satellite to acquire and relay environmental data from ground-based stations and certain industrial facilities. Facts in Brief

Launch Date: 1993-09- 25 Launch Vehicle: Ariane Launch Site: Kourou, French Guiana Mass: 50.0 kg

Funding Agency

Unknown (United States)

Disciplines

Communications Earth Science

Additional Information

Launch/Orbital information for EYESAT 1

Experiments on EYESAT 1

Data collections from EYESAT 1

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Personnel Galaxy 4

Publications NSSDC ID: 1993-039A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Galaxy 4 was a US geostationary communications spacecraft 22694 launched by an Ariane 42P rocket from the Kourou Space Center in French Guiana. It carried 24 C-band and 24 Ku-band transponders. Facts in Brief Launch Date: 1993-06- After nearly five years of successful operation, the primary and 24 backup on-board computers ceased to function at 22:18 UT on Launch Vehicle: Ariane 19 May 1998. Since these computers regulated the attitude 42P control system, their failure resulted in a spinning motion. The Launch Site: Kourou, satellite, due to its key position, was responsible for over 90% French Guiana of pager traffic in the United States and caused widespread Mass: 2988.0 kg disruption not only for pagers, but for television and cable services as well as for numerous private networks which depended on it (e.g., fast-pay pumps at gas stations). Funding Agency

Pan American Satellite (United States)

Discipline

Communications

Additional Information

Launch/Orbital information for Galaxy 4 Telecommunications information for Galaxy 4

Experiments on Galaxy 4

Data collections from Galaxy 4

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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Personnel Gorizont 28

Publications NSSDC ID: 1993-069A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Gorizont 28 was a Russian geosynchronous communications 22880 satellite. It was launched to provide telephone, telegraph and fax communications services, in addition to relaying TV and radio broadcasts, as well as support maritime and international Facts in Brief communications. It was stationed at 90 deg E. Launch Date: 1993-10- 28 The Gorizont spacecraft possessed an initial mass in excess of Launch Vehicle: Proton 2.1 metric tons and have demonstrated a lifetime of nearly 10 Launch Site: Tyuratam years, although a 5-year service life was more common. The (Baikonur Cosmodrome), 3-axis stabilized satellite was approximately 2 m in diameter Kazakhstan and 5 m long with two large solar arrays capable of generating Mass: 2125.0 kg 1.3 kW of electrical power for the first 3 years. Seven separate transmission antennas allowed a variety of reception patterns for both broad and localized terrestrial regions. Funding Agency

A typical Gorizont communications payload included six Unknown (Russia) general purpose (TV, audio, facsimile) 6/4 GHz transponders (five 12.5 W and one 60 W), one Luch 14/11 GHz transponder Discipline (15 W), and one Volna 1.6/1.5 GHz transponder (20 W). The Volna transponders were INMARSAT-compatible and were Communications extensively used by the Russian merchant marine fleet via the primary GEO television rebroadcasting system, supporting all five Federation time zones: Zone 1 from 140 deg E, Zone 2 Additional from 90 deg E, Zone 3 from 80 deg E, Zone 4 from 53 deg E, Information and Zone 5 from 14 deg W. These transmissions were handled Launch/Orbital by Orbita (12-m receiving antenna) and Moskva (2.5-m information for Gorizont receiving antenna) ground stations in the 6/4 GHz band. The 28 Moskva Globalnaya system was inaugurated in 1989 using 4- m receiving antennas and serviced by Gorizonts at 96.5 deg E Experiments on Gorizont and 11 deg W. 28

Data collections from Gorizont 28

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Personnel Gorizont 29

Publications NSSDC ID: 1993-072A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Gorizont 29 was a Russian geosynchronous communications 22907 satellite. It was launched to provide telephone, telegraph and fax communications services, in addition to relaying TV and radio broadcasts, as well as support maritime and international Facts in Brief communications. It was stationed at 130 deg E. Launch Date: 1993-11- 18 The Gorizont spacecraft possessed an initial mass in excess of Launch Vehicle: Proton 2.1 metric tons and have demonstrated a lifetime of nearly 10 Launch Site: Tyuratam years, although a 5-year service life was more common. The (Baikonur Cosmodrome), 3-axis stabilized satellite was approximately 2 m in diameter Kazakhstan and 5 m long with two large solar arrays capable of generating Mass: 2125.0 kg 1.3 kW of electrical power for the first 3 years. Seven separate transmission antennas allowed a variety of reception patterns for both broad and localized terrestrial regions. Funding Agency

A typical Gorizont communications payload included six Unknown (Russia) general purpose (TV, audio, facsimile) 6/4 GHz transponders (five 12.5 W and one 60 W), one Luch 14/11 GHz transponder Discipline (15 W), and one Volna 1.6/1.5 GHz transponder (20 W). The Volna transponders were INMARSAT-compatible and were Communications extensively used by the Russian merchant marine fleet via the primary GEO television rebroadcasting system, supporting all five Federation time zones: Zone 1 from 140 deg E, Zone 2 Additional from 90 deg E, Zone 3 from 80 deg E, Zone 4 from 53 deg E, Information and Zone 5 from 14 deg W. These transmissions were handled Launch/Orbital by Orbita (12-m receiving antenna) and Moskva (2.5-m information for Gorizont receiving antenna) ground stations in the 6/4 GHz band. The 29 Moskva Globalnaya system was inaugurated in 1989 using 4- m receiving antennas and serviced by Gorizonts at 96.5 deg E Experiments on Gorizont and 11 deg W. 29

Data collections from Gorizont 29

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Personnel Healthsat 1

Publications NSSDC ID: 1993-061E Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Healthsat 1 was a U.K./U.S.A. microsatellite that was launched 22827 along with SPOT 3 (93-061A). It was intended to relay medical emergency information from Africa to hospitals and health documentation centers. Facts in Brief Launch Date: 1993-09- 25 Launch Vehicle: Ariane Launch Site: Kourou, French Guiana Mass: 50.0 kg

Funding Agencies

Unknown (United States) Unknown (United Kingdom)

Discipline

Communications

Additional Information

Launch/Orbital information for Healthsat 1

Experiments on Healthsat 1

Data collections from Healthsat 1

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Personnel Hispasat 1B

Publications NSSDC ID: 1993-048A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Hispasat 1B was a Spanish geostationary communications 22723 spacecraft launched by an Ariane 4 booster from the Kourou Space Center in French Guiana. It was launched 10 months after its sister satellite, Hispasat 1B. Based on the Eurostar Facts in Brief spacecraft bus developed by British Aerospace and Matra Launch Date: 1993-07- Marconi, Hispasat was designed to support civil, military and 22 government communications requirements through an array of Launch Vehicle: Ariane multi-frequency transponders. With an on-orbit mass of 1.1 4 metric tons, the government owned satellite carried 15 active Launch Site: Kourou, transponders: three X-band with one spare and 12 Ku-band (8 French Guiana at 55 W, 4 at 110 W) with six spares. The Hispasat bus Mass: 2120.0 kg measured 1.7 m by 1.9 m by 2.1 m with a solar array span of Nominal 22 m and an initial capacity of 3.2 kW. The spacecraft design Power: 3200.0 W life was 10 years.

Funding Agency

Unknown (Spain)

Discipline

Communications

Additional Information

Launch/Orbital information for Hispasat 1B

Experiments on Hispasat 1B

Data collections from Hispasat 1B

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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Personnel INSAT 2B

Publications NSSDC ID: 1993-048B Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Stationed at 93.5 deg E, INSAT 2B was a multipurpose Indian National Satellite satellite that provided the following services to India: domestic 2B long range communications, meteorological earth observation 22724 and data collection services, direct satellite TV broadcasting to community TV receivers in rural and remote areas, radio and TV program distribution, satellite aided search and rescue Facts in Brief services. Launch Date: 1993-07- 22 Launch Vehicle: Ariane 4 Launch Site: Kourou, French Guiana Mass: 1931.0 kg

Funding Agency

Indian Space Research Organization (India)

Disciplines

Communications Earth Science

Additional Information

Launch/Orbital information for INSAT 2B

Experiments on INSAT 2B

Data collections from INSAT 2B

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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Personnel INTELSAT 7 F-1

Publications NSSDC ID: 1993-066A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events INTELSAT 7-F1 (sometimes known as INTELSAT 701), an 22871 international geostationary communications spacecraft, was launched by an Ariane booster rocket from Kourou, French Guiana. It covered the Asia-Pacific region with resources for Facts in Brief three television channels and 18,000 telephone channels. It Launch Date: 1993-10- replaced an older INTELSAT, which will be moved over the 22 Indian Ocean. Launch Vehicle: Ariane Launch Site: Kourou, French Guiana Mass: 6350.0 kg

Funding Agency

International Telecommunications Satellite Corporation (International)

Discipline

Communications

Additional Information

Launch/Orbital information for INTELSAT 7 F-1

Experiments on INTELSAT 7 F-1

Data collections from INTELSAT 7 F-1

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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Personnel ITAMSAT

Publications NSSDC ID: 1993-061D Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events ITAMSAT was an Italian microsatellite that was launched Italian Amateur Sat along with SPOT 3 (93-061A). It was intended to receive and OSCAR 26 retransmit amateur radio communications. From its 500-km sun-synchronous orbit, ITAMSAT (Italian Amateur Satellite), 22826 like its amateur radio satellite predecessors, will connect radio enthusiasts around the world. The 10-kg, 23-cm cube satellite Facts in Brief was designed and built by the Associazione Radiomatori Italiani near Milan for only $200,000. A second ITAMSAT is Launch Date: 1993-09- under development. 25 Launch Vehicle: Ariane Launch Site: Kourou, French Guiana Mass: 10.0 kg

Funding Agency

Unknown (Italy)

Discipline

Communications

Additional Information

Launch/Orbital information for ITAMSAT

Experiments on ITAMSAT

Data collections from ITAMSAT

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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Personnel Jianbing 93

Publications NSSDC ID: 1993-063A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Jainbing 93, a People's Republic of China experimental, 22859 retrievable spacecraft, was launched by a Long March 2C rocket from Jiuquan launch center. The 2,099 kg spacecraft became inoperational soon after the separation and could not Facts in Brief be retrieved. Launch Date: 1993-10- 08 Launch Vehicle: Long March 2C Launch Site: Jiuquan, Peoples Republic of China Mass: 2099.0 kg

Funding Agency

Unknown (Peoples Republic of China)

Discipline

Microgravity

Additional Information

Launch/Orbital information for Jianbing 93

Experiments on Jianbing 93

Data collections from Jianbing 93

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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Personnel KITSAT 2

Publications NSSDC ID: 1993-061F Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events KITSAT 2 was a South Korean experimental microsatellite that OSCAR 25 was launched along with SPOT 3. Its mission was very similar 22828 to POSAT 1 (93-061D).

Facts in Brief

Launch Date: 1993-09- 25 Launch Vehicle: Ariane Launch Site: Kourou, French Guiana Mass: 13.0 kg

Funding Agency

Unknown (South Korea)

Disciplines

Communications Navigation & Global Positioning

Additional Information

Launch/Orbital information for KITSAT 2

Experiments on KITSAT 2

Data collections from KITSAT 2

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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Personnel Landsat 6

Publications NSSDC ID: LNDSAT6 Maps Description Facts in Brief New/Updated Data

Lunar/Planetary Events The Landsat 6 satellite was a commercial program jointly with Launch Date: 1993-10- the Department of Commerce (NOAA) and EOSAT Company 04 that provided data for a wide range of Earth resources Launch Vehicle: Titan II applications including environmental monitoring, natural Launch resource exploration, urban planning, and cartography. The Site: Vandenberg AFB, Landsat 6 satellite continued the series of operational Earth United States resource monitoring spacecraft begun with Landsat 1 in 1972. Mass: 2750.0 kg Landsat 6 differed from previous Landsat missions in that it Nominal carried only one remote sensing instrument - The Enhanced Power: 1259.0 W Thematic Mapper (ETM). The Landsat 6 spacecraft, built by GE Astro Space, was based on RCA's Advanced TIROS- N/DMSP spacecraft design used for the operational NOAA and Funding Agencies DMSP polar orbiting meteorological spacecraft. The Landsat 6 EOSAT (United States) sensors were mounted on the forward module of the central spacecraft bus which also housed three multichannel steerable NOAA National X-band antennas. Power was generated by a 16.74 sq. meter Environmental Satellite 4-panel single solar array backed up by two 50 Ahr NiCd Service (United States) batteries. Attitude and control was maintained by hydrazine and nitrogen thrusters. The spacecraft was 3-axis, zero Discipline momentum stabilized to an accuracy of 0.015 degrees. Two redundant on-board tape Odetics tape recorders were able to Earth Science store about 15 minutes (75 Gbits) of image data. Five transmitters permitted three simultaneous downlinks to three ground stations, two stations receiving different data sets. The Additional X-band subsystem provided simultaneous panchromatic Information downlink and playback to the central EOSAT ground station in Launch/Orbital Oklahoma. The ETM sensor continued the high-resolution information for Landsat 6 Landsat imagery begun with the Thematic Mapper (TM) on Landsats 4 and 5. The ETM consisted of 7 spectral channels PDMP information for (6 with a ground resolution of 30 meters and one (thermal IR) Landsat 6 with a ground resolution of 120 meters) plus a panchromatic Telecommunications channel providing a ground resolution of 15 meters. The information for Landsat 6 spacecraft lost contact with ground stations shortly after launch and before achieving orbit. The spacecraft apparently failed. Experiments on Landsat 6

Data collections from Landsat 6

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Personnel

http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=LNDSAT6[09/05/2011 23:25:08] NASA - NSSDC - Spacecraft - Details

Name Role Original Affiliation E-mail Mr. E. Moule Project Manager Earth Observation Satellite Dr. David Fischel Project Scientist Earth Observation Satellite

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Personnel Meteor 2-21

Publications NSSDC ID: 1993-055A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Meteor 2-21, a C.I.S meteorological spacecraft, was launched 22782 by a Cyclone Rocket from the Plesetsk cosmodrome.

Facts in Brief

Launch Date: 1993-08- 31 Launch Vehicle: Tsiklon-3 Launch Site: Plesetsk, Russia Mass: 2750.0 kg

Funding Agency

Unknown (Russia)

Discipline

Earth Science

Additional Information

Launch/Orbital information for Meteor 2- 21

Experiments on Meteor 2- 21

Data collections from Meteor 2-21

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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Personnel Meteosat 6

Publications NSSDC ID: 1993-073B Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Meteosat 6, a European meterological spacecraft, was 22912 launched by an Ariane 44 LP rocket from Kourou, French Guiana. It was stationed in a geosynchronous orbit at 0 deg. Facts in Brief

Launch Date: 1993-11- 19 Launch Vehicle: Ariane 44LP Launch Site: Kourou, French Guiana Mass: 704.0 kg

Funding Agency

European Meteorological Satellite Agency (French Guiana)

Discipline

Earth Science

Additional Information

Launch/Orbital information for Meteosat 6

Experiments on Meteosat 6

Data collections from Meteosat 6

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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Personnel Molniya 1-85

Publications NSSDC ID: 1993-002A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Molniya 1/85 was a first-generation Russian communications 22309 satellite (COMSAT) orbited to test and perfect a system of radio communications and television broadcasting using earth satellites as active transponders and to experiment with the Facts in Brief system in practical use. The basic function of the satellite was Launch Date: 1993-01- to relay television programs and long-distance two-way 12 multichannel telephone, phototelephone, and telegraph links Launch from Moscow to the various standard ground receiving stations Vehicle: Molniya in the 'Orbita' system. The satellite was in the form of a Launch Site: Plesetsk, hermetically sealed cylinder with conical ends -- one end Russia contained the orbital correcting engine and a system of Mass: 1600.0 kg microjets, and the other end contained externally mounted solar and earth sensors. Inside the cylinder were (1) a high- sensitivity receiver and three 800-MHz 40-w transmitters (one Funding Agency operational and two in reserve), (2) telemetering devices that monitored equipment operation, (3) chemical batteries that Unknown (Russia) were constantly recharged by solar cells, and (4) an electronic computer that controlled all equipment on board. Mounted Discipline around the central cylinder were six large solar battery panels and two directional, high-gain parabolic aerials, 180 deg apart. Communications One of the aerials was directed continually toward the earth by the highly sensitive earth sensors. The second aerial was held in reserve. Signals were transmitted in a fairly narrow beam Additional ensuring a strong reception at the earth's surface. The satellite Information received telemetry at 1000 MHz. Television service was Launch/Orbital provided in a frequency range of 3.4 to 4.1 GHz at 40 w. information for Molniya 1- Molniya 1/85, whose cylindrical body was 3.4 m long and 1.6 m 85 in diameter, was much heavier than corresponding U.S. COMSATs, and it had about 10 times the power output of the Experiments on Molniya 1- Early Bird COMSAT. In addition, it did not employ a 85 geosynchronous equatorial orbit as have most U.S. COMSATs because such an orbit would not provide coverage for areas Data collections from north of 70 deg n latitude. Instead, the satellite was boosted Molniya 1-85 from a low-altitude parking orbit into a highly elliptical orbit with two high apogees daily over the northern hemisphere -- one over Russia and one over North America -- and relatively low perigees over the southern hemisphere. During its apogee, Questions or comments Molniya 1/85 remained relatively stationary with respect to the about this spacecraft can earth below for nearly 8 of every 12 hr. By placing three or be directed to: Coordinated more Molniya 1 satellites in this type of orbit, spacing them Request and User Support suitably, and shifting their orbital planes relative to each other Office. by 120 deg, a 24-hr/day communication system could be obtained.

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Personnel Molniya 1-86

Publications NSSDC ID: 1993-035A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Molniya 1/86 was a first-generation Russian communications 22671 satellite (COMSAT) orbited to test and perfect a system of radio communications and television broadcasting using earth satellites as active transponders and to experiment with the Facts in Brief system in practical use. The basic function of the satellite was Launch Date: 1993-05- to relay television programs and long-distance two-way 26 multichannel telephone, phototelephone, and telegraph links Launch from Moscow to the various standard ground receiving stations Vehicle: Molniya in the 'Orbita' system. The satellite was in the form of a Launch Site: Plesetsk, hermetically sealed cylinder with conical ends -- one end Russia contained the orbital correcting engine and a system of Mass: 1600.0 kg microjets, and the other end contained externally mounted solar and earth sensors. Inside the cylinder were (1) a high- sensitivity receiver and three 800-MHz 40-w transmitters (one Funding Agency operational and two in reserve), (2) telemetering devices that monitored equipment operation, (3) chemical batteries that Unknown (Russia) were constantly recharged by solar cells, and (4) an electronic computer that controlled all equipment on board. Mounted Discipline around the central cylinder were six large solar battery panels and two directional, high-gain parabolic aerials, 180 deg apart. Communications One of the aerials was directed continually toward the earth by the highly sensitive earth sensors. The second aerial was held in reserve. Signals were transmitted in a fairly narrow beam Additional ensuring a strong reception at the earth's surface. The satellite Information received telemetry at 1000 MHz. Television service was Launch/Orbital provided in a frequency range of 3.4 to 4.1 GHz at 40 w. information for Molniya 1- Molniya 1/86, whose cylindrical body was 3.4 m long and 1.6 m 86 in diameter, was much heavier than corresponding U.S. COMSATs, and it had about 10 times the power output of the Experiments on Molniya 1- Early Bird COMSAT. In addition, it did not employ a 86 geosynchronous equatorial orbit as have most U.S. COMSATs because such an orbit would not provide coverage for areas Data collections from north of 70 deg n latitude. Instead, the satellite was boosted Molniya 1-86 from a low-altitude parking orbit into a highly elliptical orbit with two high apogees daily over the northern hemisphere -- one over Russia and one over North America -- and relatively low perigees over the southern hemisphere. During its apogee, Questions or comments Molniya 1/86 remained relatively stationary with respect to the about this spacecraft can earth below for nearly 8 of every 12 hr. By placing three or be directed to: Coordinated more Molniya 1 satellites in this type of orbit, spacing them Request and User Support suitably, and shifting their orbital planes relative to each other Office. by 120 deg, a 24-hr/day communication system could be obtained.

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Personnel Molniya 1-87

Publications NSSDC ID: 1993-079A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Molniya 1/87 was a first-generation Russian communications 22949 satellite orbited to test and perfect a system of radio communications and television broadcasting using earth satellites as active transponders and to experiment with the Facts in Brief system in practical use. The basic function of the satellite was Launch Date: 1993-12- to relay television programs and long-distance two-way 22 multichannel telephone, phototelephone, and telegraph links Launch from Moscow to the various standard ground receiving stations Vehicle: Molniya in the 'Orbita' system. The satellite was in the form of a Launch Site: Plesetsk, hermetically sealed cylinder with conical ends -- one end Russia contained the orbital correcting engine and a system of Mass: 1600.0 kg microjets, and the other end contained externally mounted solar and earth sensors. Inside the cylinder were (1) a high- sensitivity receiver and three 800-MHz 40-w transmitters (one Funding Agency operational and two in reserve), (2) telemetering devices that monitored equipment operation, (3) chemical batteries that Unknown (Russia) were constantly recharged by solar cells, and (4) an electronic computer that controlled all equipment on board. Mounted Discipline around the central cylinder were six large solar battery panels and two directional, high-gain parabolic aerials, 180 deg apart. Communications One of the aerials was directed continually toward the earth by the highly sensitive earth sensors. The second aerial was held in reserve. Signals were transmitted in a fairly narrow beam Additional ensuring a strong reception at the earth's surface. The satellite Information received telemetry at 1000 MHz. Television service was Launch/Orbital provided in a frequency range of 3.4 to 4.1 GHz at 40 w. information for Molniya 1- Molniya 1/87, whose cylindrical body was 3.4 m long and 1.6 m 87 in diameter, was much heavier than corresponding U.S. COMSATs, and it had about 10 times the power output of the Experiments on Molniya 1- Early Bird COMSAT. In addition, it did not employ a 87 geosynchronous equatorial orbit as have most U.S. COMSATs because such an orbit would not provide coverage for areas Data collections from north of 70 deg n latitude. Instead, the satellite was boosted Molniya 1-87 from a low-altitude parking orbit into a highly elliptical orbit with two high apogees daily over the northern hemisphere -- one over Russia and one over North America -- and relatively low perigees over the southern hemisphere. During its apogee, Questions or comments Molniya 1/87 remained relatively stationary with respect to the about this spacecraft can earth below for nearly 8 of every 12 hr. By placing three or be directed to: Coordinated more Molniya 1 satellites in this type of orbit, spacing them Request and User Support suitably, and shifting their orbital planes relative to each other Office. by 120 deg, a 24-hr/day communication system could be obtained.

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Personnel Molniya 3-44

Publications NSSDC ID: 1993-025A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events he Molniya-3 Russian communications satellites were used to 22633 create the 'Orbita' communications system for northern regions, with groups of four satellites. The first Molniya 3 spacecraft appeared in 1974, primarily to support civil Facts in Brief communications (domestic and international), with a slightly Launch Date: 1993-04- enhanced electrical power system and a communications 20 payload of three 6/4 GHz transponders with power outputs of Launch 40 W or 80 W. The land segment used a 12 m diameter Vehicle: Molniya parabolic antenna, which was pointed automatically at the Launch Site: Plesetsk, satellite using autonomous electromechanical equipment. Later Russia versions were to be part of the YeSSS Unified Satellite Mass: 1600.0 kg Communications System. Trials of this version began in the 1980's, with the system being accepted by the Russian military in 1983-1985. Funding Agency

Unknown (U.S.S.R)

Discipline

Communications

Additional Information

Launch/Orbital information for Molniya 3- 44

Experiments on Molniya 3- 44

Data collections from Molniya 3-44

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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Personnel Molniya 3-45

Publications NSSDC ID: 1993-049A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events he Molniya-3 Russian communications satellites were used to 22729 create the 'Orbita' communications system for northern regions, with groups of four satellites. The first Molniya 3 spacecraft appeared in 1974, primarily to support civil Facts in Brief communications (domestic and international), with a slightly Launch Date: 1993-08- enhanced electrical power system and a communications 03 payload of three 6/4 GHz transponders with power outputs of Launch 40 W or 80 W. The land segment used a 12 m diameter Vehicle: Molniya parabolic antenna, which was pointed automatically at the Launch Site: Plesetsk, satellite using autonomous electromechanical equipment. Later Russia versions were to be part of the YeSSS Unified Satellite Mass: 1600.0 kg Communications System. Trials of this version began in the 1980's, with the system being accepted by the Russian military in 1983-1985. Funding Agency

Russian Space Agency (U.S.S.R)

Discipline

Communications

Additional Information

Launch/Orbital information for Molniya 3- 45

Experiments on Molniya 3- 45

Data collections from Molniya 3-45

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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Personnel MOP 3

Publications NSSDC ID: MOP3 Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Meteosat Operational Programme (MOP-3) satellite will be METEOSAT 6 the third operational geostationary Meteosat satellite following 3 pre-operational Meteosat satellites (Meteosat-1,-2,-3/P2). The primary goals of the MOP satellites are (1) to provide Facts in Brief visible and IR day/night cloudcover data and radiances and (2) Launch Date: 1992-12- to disseminate image data to users through the Data Collection 31 Platform (DCP). MOP-3 (or Meteosat 6) is a 2.1 m diameter, Launch Vehicle: null 3.195 m high stepped cylindrical body with solar cells on six Launch Site: null main body panels. The spacecraft is spin-stabilized at 100 rpm around the main axis aligned almost parallel to the Earth's axis with spin regulated by two small hydrazine thrusters. Spin Funding Agency access control and east-west stationkeeping are provided by two pairs of large thrusters. Attitude information is provided by European Meteorological Earth horizon and Sun-lit sensors. A radiating dipole antenna Satellite Agency will direct S-band (333 kbs) transmission of DCP image data to (International) the Data Acquisition, Telemetry, and Tracking Station at Odenwald, Germany for relay to the Meteosat Ground Discipline Computer System and Meteosat Operations Control center at ESA's European Space Operations Center (ESOC). The MOP- Earth Science 3 will carry a single imaging radiometer in visible/infrared wavelengths in addition to the Data Collection Platform. Additional Information

Launch/Orbital information for MOP 3

Experiments on MOP 3

Data collections from MOP 3

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

Personnel

Name Role Original Affiliation E- mail Mr. J. Project ESA-European Space Research and Technology Aasted Manager Centre

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Personnel NATO 4B

Publications NSSDC ID: 1993-076A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events USA 98, a second of the NATO's NATO 4 series of encrypted USA 98 communications satellites, was launched from Cape Canaveral 22921 by a Delta 2 rocket. The NATO Satellite Communications System provided immediate communication links between officials of the various NATO nations. As of 1998, one NATO 3 Facts in Brief and two NATO 4 satellites were in earth orbit at an altitude of more than 23,000 miles. The satellites are ultra-high, super- Launch Date: 1993-12- high, and extremely-high frequency systems capable of 07 providing secure voice and fax services to hundreds of users Launch Vehicle: Delta simultaneously. Members of an Air Force Space Command II unit provided command and control for the NATO system. Launch Site: Cape Canaveral, United States Mass: 1430.0 kg

Funding Agency

North Atlantic Treaty Organization (International)

Discipline

Communications

Additional Information

Launch/Orbital information for NATO 4B

Experiments on NATO 4B

Data collections from NATO 4B

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Personnel Navstar 2A-09

Publications NSSDC ID: 1993-007A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Global Positioning System (GPS) was developed by the US GPS 2-18 Department of Defense to provide all-weather round-the-clock USA 88 navigation capabilities for military ground, sea, and air forces. Since its implementation, GPS has also become an integral 22446 asset in numerous civilian applications and industries around the globe, including recreational used (e.g., boating, aircraft, Facts in Brief hiking), corporate vehicle fleet tracking, and surveying. GPS employs 24 spacecraft in 20,200 km circular orbits inclined at Launch Date: 1993-02- 55 degrees. These vehicles are placed in 6 orbit planes with 02 four operational satellites in each plane. Launch Vehicle: Delta II 7925 GPS Block 2 was the operational system, following the Launch Site: Cape demonstration system comprised of Block 1 (Navstar 1 - 11) Canaveral, United States spacecraft. These spacecraft were 3-axis stabilized, nadir Mass: 840.0 kg pointing using reaction wheels. Dual solar arrays supplied 710 Nominal watts of power. They used S-band (SGLS) communications for Power: 710.0 W control and telemetry and UHF cross-link between spacecraft. The payload consisted of two L-band navigation signals at 1575.42 MHz (L1) and 1227.60 MHz (L2). Each spacecraft Funding Agency carried 2 rubidium and 2 cesium clocks and nuclear detonation Department of Defense- detection sensors. Built by Rockwell Space Systems for the Department of the Air US Air Force, the spacecraft measured 5.3 m across with solar Force (United States) panels deployed and had a design life of 7.5 years.

Disciplines

Surveillance and Other Military Navigation & Global Positioning

Additional Information

Launch/Orbital information for Navstar 2A-09

Experiments on Navstar 2A-09

Data collections from Navstar 2A-09

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Personnel Navstar 2A-11

Publications NSSDC ID: 1993-032A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Global Positioning System (GPS) was developed by the US GPS 2-11 Department of Defense to provide all-weather round-the-clock USA 91 navigation capabilities for military ground, sea, and air forces. Since its implementation, GPS has also become an integral 22657 asset in numerous civilian applications and industries around the globe, including recreational used (e.g., boating, aircraft, Facts in Brief hiking), corporate vehicle fleet tracking, and surveying. GPS employs 24 spacecraft in 20,200 km circular orbits inclined at Launch Date: 1993-05- 55 degrees. These vehicles are placed in 6 orbit planes with 12 four operational satellites in each plane. Launch Vehicle: Delta II 7925 GPS Block 2 was the operational system, following the Launch demonstration system comprised of Block 1 (Navstar 1 - 11) Site: Vandenberg AFB, spacecraft. These spacecraft were 3-axis stabilized, nadir United States pointing using reaction wheels. Dual solar arrays supplied 710 Mass: 840.0 kg watts of power. They used S-band (SGLS) communications for Nominal control and telemetry and UHF cross-link between spacecraft. Power: 710.0 W The payload consisted of two L-band navigation signals at 1575.42 MHz (L1) and 1227.60 MHz (L2). Each spacecraft carried 2 rubidium and 2 cesium clocks and nuclear detonation Funding Agency detection sensors. Built by Rockwell Space Systems for the Department of Defense- US Air Force, the spacecraft measured 5.3 m across with solar Department of the Air panels deployed and had a design life of 7.5 years. Force (United States)

Disciplines

Surveillance and Other Military Navigation & Global Positioning

Additional Information

Launch/Orbital information for Navstar 2A-11

Experiments on Navstar 2A-11

Data collections from Navstar 2A-11

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Personnel Navstar 2A-12

Publications NSSDC ID: 1993-042A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Global Positioning System (GPS) was developed by the US USA 92 Department of Defense to provide all-weather round-the-clock NSVSTAR 39 navigation capabilities for military ground, sea, and air forces. Since its implementation, GPS has also become an integral GPS 2-21 asset in numerous civilian applications and industries around GPS 2A-11 the globe, including recreational used (e.g., boating, aircraft, 22700 hiking), corporate vehicle fleet tracking, and surveying. GPS employs 24 spacecraft in 20,200 km circular orbits inclined at 55 degrees. These vehicles are placed in 6 orbit planes with Facts in Brief four operational satellites in each plane. Launch Date: 1993-06- GPS Block 2 was the operational system, following the 26 demonstration system comprised of Block 1 (Navstar 1 - 11) Launch Vehicle: Delta spacecraft. These spacecraft were 3-axis stabilized, nadir II 7925 pointing using reaction wheels. Dual solar arrays supplied 710 Launch Site: Cape watts of power. They used S-band (SGLS) communications for Canaveral, United States control and telemetry and UHF cross-link between spacecraft. Mass: 840.0 kg The payload consisted of two L-band navigation signals at Nominal 1575.42 MHz (L1) and 1227.60 MHz (L2). Each spacecraft Power: 710.0 W carried 2 rubidium and 2 cesium clocks and nuclear detonation detection sensors. Built by Rockwell Space Systems for the Funding Agency US Air Force, the spacecraft measured 5.3 m across with solar panels deployed and had a design life of 7.5 years. Department of Defense- Department of the Air Force (United States)

Disciplines

Surveillance and Other Military Navigation & Global Positioning

Additional Information

Launch/Orbital information for Navstar 2A-12

Experiments on Navstar 2A-12

Data collections from Navstar 2A-12

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Personnel Navstar 2A-13

Publications NSSDC ID: 1993-054A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Global Positioning System (GPS) was developed by the US GPS 2-22 Department of Defense to provide all-weather round-the-clock USA 94 navigation capabilities for military ground, sea, and air forces. Since its implementation, GPS has also become an integral 22779 asset in numerous civilian applications and industries around the globe, including recreational used (e.g., boating, aircraft, Facts in Brief hiking), corporate vehicle fleet tracking, and surveying. GPS employs 24 spacecraft in 20,200 km circular orbits inclined at Launch Date: 1993-08- 55 degrees. These vehicles are placed in 6 orbit planes with 30 four operational satellites in each plane. Launch Vehicle: Delta II 7925 GPS Block 2 was the operational system, following the Launch Site: Cape demonstration system comprised of Block 1 (Navstar 1 - 11) Canaveral, United States spacecraft. These spacecraft were 3-axis stabilized, nadir Mass: 840.0 kg pointing using reaction wheels. Dual solar arrays supplied 710 Nominal watts of power. They used S-band (SGLS) communications for Power: 710.0 W control and telemetry and UHF cross-link between spacecraft. The payload consisted of two L-band navigation signals at 1575.42 MHz (L1) and 1227.60 MHz (L2). Each spacecraft Funding Agency carried 2 rubidium and 2 cesium clocks and nuclear detonation Department of Defense- detection sensors. Built by Rockwell Space Systems for the Department of the Air US Air Force, the spacecraft measured 5.3 m across with solar Force (United States) panels deployed and had a design life of 7.5 years.

Discipline

Navigation & Global Positioning

Additional Information

Launch/Orbital information for Navstar 2A-13

Experiments on Navstar 2A-13

Data collections from Navstar 2A-13

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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Personnel Navstar 2A-14

Publications NSSDC ID: 1993-068A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Global Positioning System (GPS) was developed by the US GPS 2-23 Department of Defense to provide all-weather round-the-clock USA 96 navigation capabilities for military ground, sea, and air forces. Since its implementation, GPS has also become an integral 22877 asset in numerous civilian applications and industries around the globe, including recreational used (e.g., boating, aircraft, Facts in Brief hiking), corporate vehicle fleet tracking, and surveying. GPS employs 24 spacecraft in 20,200 km circular orbits inclined at Launch Date: 1993-10- 55 degrees. These vehicles are placed in 6 orbit planes with 26 four operational satellites in each plane. Launch Vehicle: Delta II 7925 GPS Block 2 was the operational system, following the Launch Site: Cape demonstration system comprised of Block 1 (Navstar 1 - 11) Canaveral, United States spacecraft. These spacecraft were 3-axis stabilized, nadir Mass: 840.0 kg pointing using reaction wheels. Dual solar arrays supplied 710 Nominal watts of power. They used S-band (SGLS) communications for Power: 710.0 W control and telemetry and UHF cross-link between spacecraft. The payload consisted of two L-band navigation signals at 1575.42 MHz (L1) and 1227.60 MHz (L2). Each spacecraft Funding Agency carried 2 rubidium and 2 cesium clocks and nuclear detonation Department of Defense- detection sensors. Built by Rockwell Space Systems for the Department of the Air US Air Force, the spacecraft measured 5.3 m across with solar Force (United States) panels deployed and had a design life of 7.5 years.

Discipline

Navigation & Global Positioning

Additional Information

Launch/Orbital information for Navstar 2A-14

Experiments on Navstar 2A-14

Data collections from Navstar 2A-14

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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Personnel NOAA 13

Publications NSSDC ID: 1993-050A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events NOAA-I continues the third-generation operational, polar NOAA-I orbiting, meteorological satellite series operated by the Advanced TIROS-N National Environmental Satellite Service (NESS) of the (ATN) National Oceanic and Atmospheric Administration (NOAA). NOAA-I continues the series of Advanced TIROS-N (ATN) POES spacecraft begun with the launch of NOAA-8 (NOAA-E) in 22739 1983. NOAA-I will be in an afternoon equator-crossing orbit and is intended to replace the NOAA-11 (NOAA-H) as the prime afternoon spacecraft. The goal of the NOAA/NESS polar Facts in Brief orbiting program is to provide output products used in Launch Date: 1993-08- meteorological prediction and warning, oceanographic and 09 hydrologic services, and space environment monitoring. The Launch Vehicle: Atlas polar orbiting system complements the NOAA/NESS E geostationary meteorological satellite program (GOES). The Launch NOAA-I Advanced TIROS-N spacecraft is based on the Site: Vandenberg AFB, Defense Meteorological Satellite Program (DMSP) Block 5D United States spacecraft and is modified version of the TIROS-N spacecraft Mass: 1421.0 kg (NOAA1-5). The spacecraft structure consists of four Nominal components: (1) the Reaction System Support (RSS); (2) the Power: 330.0 W Equipment Support Module (ESM), which has been expanded from the TIROS-N design; (3) the Instrument Mounting Platform (IMP); and (4) the Solar Array (SA). All of the instruments are Funding Agencies located on the ESM and the IMP. The spacecraft power is provided by a direct energy transfer system from the single NASA-Office of Space solar array which is comprised of eight panels of solar cells. Science Applications The power system for the ATN has been upgraded from the (United States) previous TIROS-N design. The in-orbit Attitude Determination NOAA National and Control Subsystem (ADACS) provides three-axis pointing Environmental Satellite control by controlling torque in three mutually orthogonal Service (United States) momentum wheels with input from the Earth Sensor Assembly (ESA) for pitch, roll, and yaw updates. The ADACS controls the spacecraft attitude so that orientation of the three axes is Disciplines maintained to within +/- 0.2 degrees and pitch, roll, and yaw to Engineering within 0.1 degree. The ADACS consists of the Earth Sensor Assembly (ESA), the Sun Sensor Assembly (SSA), four Earth Science Reaction Wheel Assemblies (RWA), two roll/yaw coils (RYC), Solar Physics two pitch torquing coils (PTC), four gyros, and computer Space Physics software for data processing. The ATN data handling subsystem, which is only slightly changed from the TIROS-N design to accomodate the additional instruments, consists of Additional the TIROS Information Processor (TIP) for low data rate Information instruments, the Manipulated Information Rate Processor (MIRP) for high data rate AVHRR, digital tape recorders (DTR), Launch/Orbital and a cross strap Unit (XSU). The NOAA-I instrument information for NOAA 13 complement consists of (1) the 5-channel Advanced Very High PDMP information for Resolution Radiometer/2 (AVHRR/2); (2) the TIROS NOAA 13 Operational Vertical Sounder (TOVS), which consists of the Telecommunications Stratospheric Sounding Unit (SSU), the Microwave Sounding Unit (MSU) and the High Resolution Infrared Radiation information for NOAA 13 http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1993-050A[09/05/2011 23:36:29] NASA - NSSDC - Spacecraft - Details

Sounder (HIRS/2); (3) the Solar Backscatter Ultraviolet Radiometer (SBUV/2), which is similar to the SBUV on Experiments on NOAA 13 Nimbus-7 and is only flown on the afternoon orbiters; (4) the Search and Rescue System (S&R); (5) the Space Environment Data collections from Monitor (SEM), which consists of the Total Energy Detector NOAA 13 (TED) and the Medium Energy Proton and Electron Detector (MEPED); (6) the French/CNES-provided ARGOS Data Collection System (DCS); and two experimental sensors Questions or comments sponsord by the Office of Naval Reseach (ONR): (7) about this spacecraft can Magnetospheric Atmospheric X-ray Imaging Experiment be directed to: Coordinated (MAXIE); and (8) the Energetic Heavy Ion Composition Request and User Support Experiment (EHIC). NOAA-I (NOAA-13) lost communications Office. shortly after launch amd no data was collected.

Personnel

Name Role Original Affiliation E-mail Dr. Joel Project NASA Goddard Space [email protected] Susskind Scientist Flight Center Mr. Charles E. Project NASA Goddard Space Thienel Manager Flight Center Mr. James R. Program NASA Headquarters [email protected] Greaves Manager

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Personnel ORFEUS-SPAS I

Publications NSSDC ID: 1993-058C Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The purpose of the ORFEUS-SPAS I mission was to conduct SPAS investigations of celestial sources in the far and extreme STS 51/ORFEUS ultraviolet spectral range. Specific objects targeted included the atmospheres of hot stars and the coronae of cool stars. ORFEUS Narrow interstellar absorption lines were studied to further STS 51/SPAS understanding of the interstellar medium (ISM). ORFEUS- 22798 SPAS I was the first of a series of planned joint DARA (German Space Agency) /NASA missions. The name arises from the reusable Astro-Shuttle Pallet Satellite (Astro-SPAS), Facts in Brief and the Orbiting Retrievable Far and Extreme Ultraviolet Spectrometers (ORFEUS) Telescope carried on Astro-SPAS. Launch Date: 1993-09- 12 ORFEUS-SPAS was a free-flying platform designed to be Launch deployed and retrieved from the space shuttle. The Astro- Vehicle: Shuttle SPAS carrier was powered by batteries, and data from the Launch Site: Cape instruments were stored on tape. Absolute pointing was Canaveral, United States accurate to within a few arc seconds. ORFEUS-SPAS is 4.5m Mass: 3500.0 kg length and has a 2.5m width base. Operation of ORFEUS- SPAS was approximately 40km from the shuttle. Funding Agencies

ORFEUS-SPAS carried three spectrometers operating over NASA-Office of Space the wavelength range 400 - 1250 Angstroms. The Tubingen Science Applications Ultraviolet Echelle Spectrometer (TUES) and the Berkeley (United States) Extreme and Far-UV Spectrometer (BEFS) were housed on German Space Agency the primary instrument - the ORFEUS 1-m telescope. The (Federal Republic of Interstellar Medium Absorption Profile Spectrograph (IMAPS) Germany) was operated independently from ORFEUS.

The ORFEUS-SPAS I mission was flown in September 1993. Discipline

Astronomy

Additional Information

Launch/Orbital information for ORFEUS- SPAS I PDMP information for ORFEUS-SPAS I Telecommunications information for ORFEUS- SPAS I

Experiments on ORFEUS- SPAS I

Data collections from http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1993-058C[09/05/2011 23:36:51] NASA - NSSDC - Spacecraft - Details

ORFEUS-SPAS I

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Personnel

Name Role Original Affiliation E-mail Mr. R. Project NASA Headquarters Wayne Manager Richie Dr. D.-R. Project Deutsche Forschungsenstalt Schmitt Engineer fuer Luft-und Raumfahrt Dr. Immo Mission Landessternwarte [email protected] Appenzeller Scientist heidelberg.de Dr. Gerhard Project Scientist Universitat Tubingen Kramer Dr. Klaus Project Deutsche Agentur fur [email protected] Steinberg Manager Ramfahrt-Angelegenheiten Dr. C. Stuart Mission University of California, [email protected] Bowyer Principal Berkeley Investigator Dr. Michael Mission Universitat Tubingen Grewing Principal Investigator Dr. Edward Mission Princeton University [email protected] B. Jenkins Principal Investigator Dr. Robert Project Scientist NASA Headquarters N. Stachnik

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Personnel OXP 1

Publications NSSDC ID: 1993-009A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events This spacecraft is a small secondary payload carried on the CDS Pegasus launch. It is a pathfinder to demonstrate two-way 22489 communications for a global network for the Orbital Communications Corporation (Orbcomm). Orbcomm is a wholly-owned subsidiary of Orbital Science Corp., the Facts in Brief manufacturer of the Pegasus launch vehicle. It carried an experimental payload to determine global VHF frequency Launch Date: 1993-02- utilization prior to the launch of ORBCOMM constellation 09 satellites. It measured user density, power levels and Launch interference worldwide. OPX featured integral solar panels and Vehicle: Pegasus antennas, and a passive attitude control system. It formed the Launch Site: Cape basis of the OSC pico-star bus. Canaveral, United States Mass: 15.0 kg

Funding Agency

Orbital Sciences Corp (United States)

Disciplines

Communications Engineering

Additional Information

Launch/Orbital information for OXP 1

Experiments on OXP 1

Data collections from OXP 1

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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Personnel POSAT 1

Publications NSSDC ID: 1993-061G Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events POSAT 1 was a Portuguese experimental microsatellite that Oscar 28 was launched along with SPOT 3 (93-061A). It was intended to 22829 receive and retransmit images, to determine its own position with the help of the GPS system, and to experiment with signal compression techniques. It was built at the University of Surrey Facts in Brief (UK) within a collaborative program in satellite technology between a consortium of Portuguese academia and industry Launch Date: 1993-09- and the University - managed through its technology transfer 25 company, Surrey Satellite Technology (SSTL). Launch Vehicle: Ariane Launch Site: Kourou, POSAT used the SSTL modular microsatellite platform, French Guiana already proven on the three research and two commercial Mass: 12.0 kg missions, S80/T and KITSAT-1, and carried the following experimental payloads: Funding Agencies

Earth Imaging System (EIS) - consisting of two charge-coupled Unknown (Portugal) device (CCD) imagers, two lenses, and a Transputer Data University of Surrey Processing Experiment to provide on-board image processing (United Kingdom) and data compression. One imager had a wide field of view with 2 km ground resolution; the second narrow field imager provided 200 m ground resolution. Disciplines

Star Sensor - based on the same technology as the EIS but Communications was optimized for imaging the faint light from stars for use as Engineering part of the spacecraft's attitude determination system. The star- Navigation & Global field image was analyzed by the Transputer Data Processing Positioning Experiment and the resulting measurement data returned to the on-board computer. Additional GPS Navigation Experiment - PoSat-1 carried a Global Information Positioning by Satellite (GPS) receiver based on the Trimble Trans-II receiver. The received data was decoded and filtered Launch/Orbital by the Transputer Data Processing Experiment and provided information for POSAT 1 the satellites position and velocity as well as an accurate on- board time reference. This enabled the satellite to generate its Experiments on POSAT 1 own orbital element set, provide scheduling and synchronization to other computers, and allowed ground Data collections from stations equipped with a GPS receiver to experiment with POSAT 1 applications for real-time differential GPS data.

Cosmic Ray Experiment (CRE) - the CRE monitored the space Questions or comments radiation environment experienced in orbit by the satellite and about this spacecraft can enabled analysis of its effect on spacecraft semiconductor be directed to: Coordinated electronics. The CRE contained a PIN diode and multi-channel Request and User Support analyzer capable of detecting energetic particles with a wide Office. range of Linear Energy Transfer to build up a spectrum of observed energies of particles within the spacecraft. Special RADFET's were also incorporated to monitor the accumulated ionizing dose. The larger memory devices in the on-board http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1993-061G[09/05/2011 23:37:35] NASA - NSSDC - Spacecraft - Details

computers were regularly "washed" to detect and log Single Event Upset (SEU) information.

Digital Signal Processing Experiment (DSPE) - consisted of two Texas Instruments processors from the TMS320 series, the C25 and C30. The DSPE was used as a programmable communications modem to modulate downlink data from or demodulate uplink data for the OBC thus enabling experiments with new modulation techniques optimized for Low Earth Orbit satellite mobile communications.

Store and Forward Communications - the main spacecraft On- Board Computer (OBC), based on an 80C186 8MHz processor with 16 MB of SRAM, also supported digital store and forward communications using AX25 packet protocols and communications links optimized for communications using very low cost, simple and portable ground stations. The design took advantage of the latest research developments undertaken at UoSAT/SSTL - including high data rate modems at 38.4 kbps data rate and a new synthesized transmitter design.

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Personnel Progress M-16

Publications NSSDC ID: 1993-012A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events An improved version of cargo freighters used to supply the Mir 22530 space station, the Progress M series had greater cargo capacity, a modernized approach/docking system and carried 2 solar panels to generate electrical power. Progress M can fly Facts in Brief for 30 days independently and 108 days docked with Mir. Launch Date: 1993-02- Spare propellent in Progress M's tanks can be transferred to 21 Mir before it is consigned to burn up in reentry. In the past, Launch Vehicle: Soyuz extra fuel was abandoned with the craft. Future Progress Launch Site: Tyuratam vehicles will carry a recoverable reentry capsule for the speedy (Baikonur Cosmodrome), return of up to 150 kg of material from Mir to earth. Kazakhstan Mass: 7250.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Resupply/Refurbishment/Repair

Additional Information

Launch/Orbital information for Progress M-16

Experiments on Progress M-16

Data collections from Progress M-16

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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Personnel Progress M-17

Publications NSSDC ID: 1993-019A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events An improved version of cargo freighters used to supply the Mir 22588 space station, the Progress M series had greater cargo capacity, a modernized approach/docking system and carried 2 solar panels to generate electrical power. Progress M can fly Facts in Brief for 30 days independently and 108 days docked with Mir. Launch Date: 1993-03- Spare propellent in Progress M's tanks can be transferred to 30 Mir before it is consigned to burn up in reentry. In the past, Launch Vehicle: Soyuz extra fuel was abandoned with the craft. Future Progress Launch Site: Tyuratam vehicles will carry a recoverable reentry capsule for the speedy (Baikonur Cosmodrome), return of up to 150 kg of material from Mir to earth. Kazakhstan Mass: 7250.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Resupply/Refurbishment/Repair

Additional Information

Launch/Orbital information for Progress M-17

Experiments on Progress M-17

Data collections from Progress M-17

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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Personnel Progress M-18

Publications NSSDC ID: 1993-034A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events An improved version of cargo freighters used to supply the Mir 22666 space station, the Progress M series had greater cargo capacity, a modernized approach/docking system and carried 2 solar panels to generate electrical power. Progress M can fly Facts in Brief for 30 days independently and 108 days docked with Mir. Launch Date: 1993-05- Spare propellent in Progress M's tanks can be transferred to 22 Mir before it is consigned to burn up in reentry. In the past, Launch Vehicle: Soyuz extra fuel was abandoned with the craft. Future Progress Launch Site: Tyuratam vehicles will carry a recoverable reentry capsule for the speedy (Baikonur Cosmodrome), return of up to 150 kg of material from Mir to earth. Kazakhstan Mass: 7250.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Resupply/Refurbishment/Repair

Additional Information

Launch/Orbital information for Progress M-18

Experiments on Progress M-18

Data collections from Progress M-18

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Personnel Progress M-19

Publications NSSDC ID: 1993-052A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events An improved version of cargo freighters used to supply the Mir 22745 space station, the Progress M series had greater cargo capacity, a modernized approach/docking system and carried 2 solar panels to generate electrical power. Progress M can fly Facts in Brief for 30 days independently and 108 days docked with Mir. Launch Date: 1993-08- Spare propellent in Progress M's tanks can be transferred to 10 Mir before it is consigned to burn up in reentry. In the past, Launch Vehicle: Soyuz extra fuel was abandoned with the craft. Future Progress Launch Site: Tyuratam vehicles will carry a recoverable reentry capsule for the speedy (Baikonur Cosmodrome), return of up to 150 kg of material from Mir to earth. Kazakhstan Mass: 7250.0 kg

Funding Agency

Russian Space Agency (U.S.S.R)

Discipline

Resupply/Refurbishment/Repair

Additional Information

Launch/Orbital information for Progress M-19

Experiments on Progress M-19

Data collections from Progress M-19

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Personnel Progress M-20

Publications NSSDC ID: 1993-064A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events An improved version of cargo freighters used to supply the Mir 22867 space station, the Progress M series had greater cargo capacity, a modernized approach/docking system and carried 2 solar panels to generate electrical power. Progress M can fly Facts in Brief for 30 days independently and 108 days docked with Mir. Launch Date: 1993-10- Spare propellent in Progress M's tanks can be transferred to 11 Mir before it is consigned to burn up in reentry. In the past, Launch Vehicle: Soyuz extra fuel was abandoned with the craft. Future Progress Launch Site: Tyuratam vehicles will carry a recoverable reentry capsule for the speedy (Baikonur Cosmodrome), return of up to 150 kg of material from Mir to earth. Kazakhstan Mass: 7250.0 kg Progress M-20 docked with the Kvant module of Mir and 23:25 UT on October 13, 1993. Funding Agency

Unknown (Russia)

Discipline

Resupply/Refurbishment/Repair

Additional Information

Launch/Orbital information for Progress M-20

Experiments on Progress M-20

Data collections from Progress M-20

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Personnel RADCAL

Publications NSSDC ID: 1993-041A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events This spacecraft was used to help calibrate radar target cross 22698 section data.

Facts in Brief

Launch Date: 1993-06- 25 Launch Vehicle: Scout Launch Site: Vandenberg AFB, United States Mass: 95.0 kg

Funding Agency

Department of Defense (United States)

Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for RADCAL

Experiments on RADCAL

Data collections from RADCAL

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Personnel Raduga 29

Publications NSSDC ID: 1993-013A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Raduga 29 was a Soviet communications satellite launched 22557 from the Baikonur cosmodrome aboard a Proton 8K82K/Block DM rocket. It provided uninterrupted round the clock telephone and telegraph radio communications in the USSR and Facts in Brief simultaneous transmission of color and black and white USSR Launch Date: 1993-03- central television programs to stations in the Orbita network. 24 Launch Vehicle: Proton Launch Site: Tyuratam (Baikonur Cosmodrome), Kazakhstan Mass: 1965.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Communications

Additional Information

Launch/Orbital information for Raduga 29

Experiments on Raduga 29

Data collections from Raduga 29

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Personnel Raduga 30

Publications NSSDC ID: 1993-062A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Raduga 30 was a Soviet communications satellite launched 22836 from the Baikonur cosmodrome aboard a Proton 8K82K/Block DM rocket. It provided uninterupted round the clock telephone and telegraph radio communications in the USSR and Facts in Brief simultaneous transmission of color and black and white USSR Launch Date: 1993-09- central television programs to stations in the Orbita network. It 30 was placed in a geostationary orbit at 83 deg E. Launch Vehicle: Proton Launch Site: Tyuratam (Baikonur Cosmodrome), Kazakhstan Mass: 1965.0 kg

Funding Agency

Unknown (Russia)

Discipline

Communications

Additional Information

Launch/Orbital information for Raduga 30

Experiments on Raduga 30

Data collections from Raduga 30

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Personnel Regatta-A

Publications NSSDC ID: REGTTAA Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Regatta series of small spacecraft (230 kg payloads) were Regatta/SSL-A being developed by the Institute of Space Research in Russia to perform a variety of space science investigations. The Regatta-Astro mission was specifically designed to conduct Facts in Brief astrometric and radiometric observations of stars and other Launch Date: 1992-12- celestial bodies. 31 Launch Vehicle: null In 1991, an opertional period for Regatta-Astro of 1994-1997 Launch Site: Tyuratam was proposed, but the current status of the project is unclear. If (Baikonur Cosmodrome), successful, a second Regatta-Astro could be flown with more Kazakhstan precise observational instrumentation. Mass: 500.0 kg

Funding Agency

Institut Kosmicheskich Issledovaniy(Inst. of Cosmophysical Research) (U.S.S.R)

Discipline

Astronomy

Additional Information

Launch/Orbital information for Regatta-A

Experiments on Regatta-A

Data collections from Regatta-A

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Personnel

Name Role Original Affiliation E-mail

http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=REGTTAA[09/05/2011 23:41:41] NASA - NSSDC - Spacecraft - Details

Dr. Lev M. Program Soviet Academy of Sciences [email protected] Zelenyi Scientist Dr. V. I. Project Soviet Academy of Sciences Kostenko Engineer Dr. Albert A. Program Institut Kosmicheskich [email protected] Galeev Scientist Issledovaniya (IKI) Dr. G. A. Project Soviet Academy of Sciences Avanesov Manager

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Personnel Resurs-F17

Publications NSSDC ID: 1993-033A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Resurs-F17, a C.I.S. natural resources spacecraft, was 22663 launched from the Plesetsk cosmodrome by a Soyuz booster. It carried spectro-photometers. Facts in Brief

Launch Date: 1993-05- 21 Launch Vehicle: Soyuz Launch Site: Plesetsk, Russia Mass: 6300.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Earth Science

Additional Information

Launch/Orbital information for Resurs- F17

Experiments on Resurs- F17

Data collections from Resurs-F17

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Personnel Resurs-F18

Publications NSSDC ID: 1993-040A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Resurs F-18, a C.I.S. natural resources spacecraft, was 22696 launched from the Plesetsk cosmodrome by a Soyuz rocket.

Facts in Brief

Launch Date: 1993-06- 25 Launch Vehicle: Soyuz Launch Site: Plesetsk, Russia Mass: 6300.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Earth Science

Additional Information

Launch/Orbital information for Resurs- F18

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Data collections from Resurs-F18

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Personnel Resurs-F19

Publications NSSDC ID: 1993-053A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Resurs-F19, a C.I.S. natural resources spacecraft, was 22777 launched from the Plesetsk cosmodrome by a Soyuz rocket.

Facts in Brief

Launch Date: 1993-08- 24 Launch Vehicle: Soyuz Launch Site: Plesetsk, Russia Mass: 6300.0 kg

Funding Agency

Unknown (Russia)

Discipline

Earth Science

Additional Information

Launch/Orbital information for Resurs- F19

Experiments on Resurs- F19

Data collections from Resurs-F19

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Personnel SCD 1

Publications NSSDC ID: 1993-009B Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Satellite de Coleta de Dados (SCD 1) was an Satelite de Coleta de environmental data collection and relay satellite. The primary Dados 1 objective of SCD 1 was to transmit environmental data Data Collection Satellite 1 collected on the ground by automatic Data Collection Platforms (DCPs) located throughout remote regions in Brazil's Amazon 22490 River Basin. The solar-powered satellite relayed data on two adjacent frequencies providing random access service to Facts in Brief hundreds of DCPs in remote locations. Data was received at the Cuiaba Ground Station at least once per day. The SCD 1 Launch Date: 1993-02- was 3-axis spin-stabilized and its attitude determined by a 09 magnetometer and sun sensors. A magnetometer coil allowed Launch attitude maneuvers by commands from the ground. SCD 1 was Vehicle: Pegasus carried into orbit commercially by the Orbital Sciences Launch Site: Cape Corporation (OSC) Pegasus rocket launched from a B-52 plane Canaveral, United States which took off from Kennedy Space Center in Florida, USA. Mass: 115.0 kg The B-52 dropped the Pegasus 128 Km east of there at Nominal 13.258 Km over the Atlantic. Power: 110.0 W

Funding Agency

Instituto Nacional de Pesquisas Espaciais, Brazil (Brazil)

Disciplines

Engineering Earth Science

Additional Information

Launch/Orbital information for SCD 1 Telecommunications information for SCD 1

Experiments on SCD 1

Data collections from SCD 1

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Request and User Support Office.

Personnel

Name Role Original Affiliation E-mail

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Personnel SEDS-I

Publications NSSDC ID: 1993-017B Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events SEDS-I (Small Expendable-tether Deployer Systems) was an 22582 engineering spacecraft that decayed the day after launch.

Facts in Brief

Launch Date: 1993-03- 29 Launch Vehicle: Delta II 7925 Launch Site: Cape Canaveral, United States Mass: 25.0 kg

Funding Agency

Department of Defense- Department of the Air Force (United States)

Discipline

Engineering

Additional Information

Launch/Orbital information for SEDS-I

Experiments on SEDS-I

Data collections from SEDS-I

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Personnel SLS 2

Publications NSSDC ID: SLABLS2 Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Spacelab Life Sciences 2

Facts in Brief

Launch Date: 1993-10- 17 Launch Vehicle: Shuttle Launch Site: Cape Canaveral, United States

Funding Agency

NASA Office of Life and Microgravity Sciences and Applications (United States)

Discipline

Life Science

Additional Information

Launch/Orbital information for SLS 2 Telecommunications information for SLS 2

Experiments on SLS 2

Data collections from SLS 2

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

Personnel

Name Role Original Affiliation E-mail http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=SLABLS2[09/05/2011 23:44:40] NASA - NSSDC - Spacecraft - Details

Mr. William P. Program NASA Headquarters Gilbreath Manager Dr. Frank M. Program NASA Headquarters Sulzman Scientist Dr. Howard J. Mission NASA Johnson Space Schneider Scientist Center Dr. Katherine E. Mission NASA Johnson Space [email protected] Newkirk Manager Center Mr. Gary W. Program NASA Headquarters [email protected] McCollum Manager

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Personnel Solidaridad 1

Publications NSSDC ID: 1993-073A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Solidaridad-1, a Mexican geostationary communcations 22911 spacecraft, was launched by an Ariane 44 LP rocket. It provided television, telecommunications, data, facsimile, and business network services in C-band and Ku-band, and mobile Facts in Brief communications in L-band. The Solidaridad satellites covered Launch Date: 1993-11- the Mexican republic, with spot beam for the Caribbean, the 19 southern US, and South America. Launch Vehicle: Ariane 44LP Launch Site: Kourou, French Guiana Mass: 2776.0 kg

Funding Agency

Unknown (Mexico)

Discipline

Communications

Additional Information

Launch/Orbital information for Solidaridad 1

Experiments on Solidaridad 1

Data collections from Solidaridad 1

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Personnel Soyuz-TM 16

Publications NSSDC ID: 1993-005A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Soyuz TM-16, a C.I.S. spacecraft, was launched from the 22319 Baikonur cosmodrome to transport two cosmonauts to the Mir station with which it docked on January 26, 1993. Designed and manufactured by RKK Energiya, the Soyuz TM was Facts in Brief capable of carrying three cosmonauts and had a gross weight Launch Date: 1993-01- of just over seven metric tons, a length of seven meters, and a 24 maximum diameter of 2.7 m. The spacecraft consisted of three Launch Vehicle: Soyuz main sections: the orbital module, the command and reentry Launch Site: Tyuratam module, and the service module. Two solar arrays (10.6 m (Baikonur Cosmodrome), span) provided electrical power for the typical 50-hour journey Kazakhstan to Mir and could be interconnected with the space station's Mass: 7150.0 kg electrical system to furnish additional 1.3 kW. The nominal flight time for Soyuz TM spaceship was 5-6 months. Funding Agency

Unknown (U.S.S.R)

Discipline

Human Crew

Additional Information

Launch/Orbital information for Soyuz-TM 16

Experiments on Soyuz-TM 16

Data collections from Soyuz-TM 16

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Russia

Launch, orbit and landing data

Launch date: 24.01.1993 Launch time: 05:58 UT Launch site: Baikonur Launch pad: 1 Altitude: 350 km Inclination: 51,6° Landing date: 22.07.1993 Landing time: 06:41 UT Landing site: 47° 23' N, 69° 22' E

Crew No Orbit Surname Given name Job Flight No. Duration . s Gennadi 179d 00h 2833 1 Manakov Commander 2 Mikhailovich 43m Poleshch Aleksandr Flight 179d 00h 2833 2 1 uk Fyodorovich Engineer 43m Crew seating arrangement

Launch Landing 1 Manakov 1 Manakov 2 Poleshchuk 2 Poleshchuk 3 3 Haigneré

Double Crew

No Surname Given name Job . Vasili Command 1 Tsibliyev Vasiliyevich er Usachyo Yuri Flight 2 v Vladimirovich Engineer

Flight Launch from Baikonur; landing 140 km east of Dzheskasgan.

Docking on MIR spacestation; crew exchange; Manakov and Poleshchuk became 13. MIR- resident crew; experiments in biology, astronomy, materials science and earth science; both cosmonauts performed two EVA's on 19.04.1993 (5h 25m) and on 18.06.1993 (4h 33m); installation of Kvant 1 solar array drive unit with some technical problems; Earth observation with special cameras; supplies with cargo space ships Progress M-16 - M-18.

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Personnel Soyuz-TM 17

Publications NSSDC ID: 1993-043A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Soyuz TM-17, a C.I.S. transportation spacecraft, was launched 22704 from the Baykonur cosmodrome to dock with the Mir space staion and transport cosmonauts. Designed and manufactured by RKK Energiya, the Soyuz TM was capable of carrying three Facts in Brief cosmonauts and has a gross weight of just over seven metric Launch Date: 1993-07- tons, a length of seven meters, and a maximum diameter of 01 2.7 m. The spacecraft consisted of three main sections: the Launch Vehicle: Soyuz orbital module, the command and reentry module, and the Launch Site: Tyuratam service module. Two solar arrays (10.6 m span) provided (Baikonur Cosmodrome), electrical power for the typical 50-hour journey to Mir and Kazakhstan could be interconnected with the space station's electrical Mass: 7150.0 kg system to furnish additional 1.3 kW. The nominal flight time for Soyuz TM spaceship was 5-6 months. Funding Agency

Unknown (U.S.S.R)

Disciplines

Human Crew Resupply/Refurbishment/Repair

Additional Information

Launch/Orbital information for Soyuz-TM 17

Experiments on Soyuz-TM 17

Data collections from Soyuz-TM 17

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Russia

Launch, orbit and landing data

Launch date: 01.07.1993 Launch time: 14:32 UT Launch site: Baikonur Launch pad: 1 Altitude: 350 km Inclination: 51,6° Landing date: 14.01.1994 Landing time: 08:18 UT Landing site: 49° 37' N, 70° 07' E

Crew No Surnam Orbit Given name Job Flight No. Duration . e s Tsibliye 196d 17h 3113 1 Vasili Vasiliyevich Commander 1 v 45m Serebr Aleksandr 196d 17h 3113 2 Flight Engineer 4 ov Aleksandrovich 45m Haigne Research 3 Jean-Pierre 1 20d 16h 08m 327 ré Cosmonaut

Crew seating arrangement

Launch Landing 1 Tsibliyev 1 Tsibliyev 2 Serebrov 2 Serebrov 3 Haigneré 3

Double Crew

No. Surname Given name Job

1 Afanasiyev Viktor Mikhailovich Commander

2 Usachyov Yuri Vladimirovich Flight Engineer

3 André-Deshays Claudie Research Cosmonaut

Flight Launch from Baikonur; landing 215 km west of Karaganda / 180 km southwest of Tselinograd.

Mission ALTAIR; docking on MIR spacestation; scientific work with the 13th resident crew; after returning to Earth of the 13th crew (together with Haigneré), Tsibilyev and Serebrov became the 14th MIR resident crew; experiments in materials science; both cosmonauts performed five EVA`s on 16.09.1993 (4h 18m), 20.09.1993 (3h 14m), 28.09.1993 (1h 52m), 22.10.1993 (0h 38m) and 29.10.1993 (4h 12m), in which the Rapana truss was installed and several experiment packages were retrieved during separation of Soyuz-spacecraft light collision with the MIR.

Note Haigneré returned to Earth on 22.07.1993 at 06:41 UT with Soyuz TM-16-spacecraft

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Personnel Spacelab-D2

Publications NSSDC ID: SPLABD2 Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The second flight of the German Spacelab (D-2) continued the STS 55/Spacelab-D2 German microgravity research program started with the Spacelab D-1 in 1985. NASA, ESA and Japan also contributed some of the 90 experiments conducted on D-2. The Facts in Brief experiments were conducted by the Shuttle crew in two shifts Launch Date: 1993-04- round-the-clock in fluid physics, materials science, life 25 sciences, technology, Earth science, atmospheric physivs, and Launch astronomy. The D-2 experiments consist of the following Vehicle: Shuttle Spacelab Module Experiments: Robotic Technology Launch Site: Cape Experiment (ROTEX); Werkstofflabor (or Materials Sciences Canaveral, United States Laboratory); Holographical Optical Laboratory; Anthrorack, or Mass: 11351.1 kg human medical research facility; Baroreflex; Materials Sciences Double Rack for Experiment Modules and Apparatus (MEDEA); Exterior Unique Support Structure Experiments; Funding Agencies Galactic Ultra-Wide-Angle Schmidt System (GAUSS) Camera; and, Modular Optoelectronic Multispectral Stereo Scanner Centre National d'Etudes (MOMS-02). Spatiales (France) NASA-Office of Space Science Applications (United States) Deutsche Forschunganstalt fuer Luft- und Raumfahrt (DLR, nee DFVLR) (Federal Republic of Germany) Institute of Space and Aeronautical Science, U of Tokyo (Japan)

Disciplines

Astronomy Engineering Earth Science Life Science Microgravity

Additional Information

Launch/Orbital information for Spacelab- D2 PDMP information for

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Spacelab-D2 Telecommunications information for Spacelab- D2

Experiments on Spacelab- D2

Data collections from Spacelab-D2

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

Personnel

Name Role Original Affiliation E-mail Dr. Ronald J. Program NASA Headquarters White Scientist Mr. William P. Program NASA Headquarters Gilbreath Manager Dr. Bradley M. Program NASA Headquarters [email protected] Carpenter Scientist Mr. Hauke Mission Deutsche Forschungsenstalt [email protected] Dodeck Manager fuer Luft-und Raumfahrt

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Personnel Spartan 201-01

Publications NSSDC ID: 1993-023B Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The scientific objective of the Solar Spartan mission is to probe Solar Spartan the physics of solar-wind acceleration by observing the 22623 hydrogen, proton and electron temperatures and densities, and the solar-wind velocities in a variety of coronal structures at locations from 1.5 to 3.5 solar radii from the Sun. The Facts in Brief instruments are an ultraviolet coronal spectrometer and a white-light coronagraph. The spectrometer measures the Launch Date: 1993-04- intensities of Lyman alpha (1215 A) and the intensities of the 08 Oxygen VI lines (1031.9 and 1037.6 A). The white-light Launch coronagraph measures the intensity and polarization of the Vehicle: Shuttle electron-scattered white-light corona. Both of these Launch Site: Cape instruments have been used in previous sounding rocket Canaveral, United States flights. The instruments are housed together in a cylinder that Mass: 1360.0 kg is 0.43 m in diameter and 3 m long. The Spartan program provides a series of low-cost, free-flying space platforms to Funding Agency perform various scientific studies. A Spartan is launched aboard the Space Shuttle and deployed from the Orbiter, National Aeronautics and where it performs a pre-programmed mission. Scientific data Space Administration are collected during each mission using a tape recorder and, in (United States) many cases, film cameras. There is no command and control capability after deployment. The Spartan is then retrieved by the Orbiter and returned to Earth for recovery of the data, Discipline refurbishment and preparation for future missions. Power Solar Physics during the deployed phase of the mission is provided by on- board batteries, and attitude control is accomplished with pneumatic gas jets. The onboard tape recorder provides Additional approximately 6E9 bits of storage capacity for experiments. Information More information on the mission may be obtained from the instrument Principal Investigators, Dr. John Kohl (Smithsonian Launch/Orbital Astrophysical Observatory) and Dr. Richard Fisher (High information for Spartan Altitude Observatory). 201-01

Experiments on Spartan 201-01

Data collections from Spartan 201-01

Questions or comments about this spacecraft can be directed to: Dr. H. Kent Hills.

Personnel

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Mr. Francis M. Collins, Project Manager NASA Goddard Space Flight Jr. Center Dr. J. David Bohlin Program NASA Headquarters Scientist Mr. Louis J. Demas Program NASA Headquarters Manager

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Personnel SPOT 3

Publications NSSDC ID: 1993-061A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events SPOT 3, a French natural resources satellite weighing 1,907 22823 kg, was launched by an Ariane rocket from Kourou, French Giuana, along with six microsatellites. It was black and white, and six color imaging instruments were similar to the earlier Facts in Brief SPOT, it had a resolution of ten meters. It had the ability to Launch Date: 1993-09- take images of the same location from different angles so as to 25 provide elevation information. Launch Vehicle: Ariane Launch Site: Kourou, French Guiana Mass: 1907.0 kg

Funding Agency

Centre National d'Etudes Spatiales (France)

Discipline

Earth Science

Additional Information

Launch/Orbital information for SPOT 3

Experiments on SPOT 3

Data collections from SPOT 3

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Personnel SSBUV05

Publications NSSDC ID: SSBUV05 Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The fifth Shuttle Solar Backscatter Ultraviolet (SSBUV05) STS/SSBUV05 payload was co-manifested with the ATLAS-2 payload. The SSBUV was physically separated from the ATLAS-2 payload and consisted of two Get Away Special (GAS) canisters Facts in Brief mounted on one standard GAS adapter beam assembly with Launch Date: 1993-04- an interconnecting cable to provide communication and power 07 between the two canisters. The canister containing the SSBUV Launch instrument was equipped with a motorized door assembly. The Vehicle: Shuttle adjacent support canister contained data, command and Launch Site: Cape avionics systems. The light sources, quartz-halogen, Canaveral, United States deuterium, and mercury lamps, and a diffuser plate assembly Mass: 1615.9 kg were all contained in the instrument canister. SSBUV commands were sent directly from the Johnson Payload Operations Control Center (POCC) in Houston, TX. The Funding Agency payload is managed by NASA GSFC. The SSBUV was flown on three previous shuttle flights in addition to a flight on NASA-Office of Space ATLAS-1. The SSBUV program was based on Public Law 95- Science Applications 95 (an amendment to the Clean Air Act) and the National Plan (United States) of Ozone Monitoring and early detection of Stratospheric Change for providing calibration data to account for ozone Disciplines trends and drifts in instruments on NOAA operational weather satellites. The SSBUV is expected to be co-manifested with Earth Science subsequent ATLAS Shuttle flights. Solar Physics

Additional Information

Launch/Orbital information for SSBUV05 PDMP information for SSBUV05 Telecommunications information for SSBUV05

Experiments on SSBUV05

Data collections from SSBUV05

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Personnel

Name Role Original Affiliation E-mail Mr. Ernest Mission Principal NASA Goddard Space [email protected] Hilsenrath Investigator Flight Center

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Personnel START 1

Publications NSSDC ID: 1993-014A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Start 1, a C.I.S. experimental spacecraft, was launched by a 22561 booster (also called Start 1). The booster was a defanged and refitted ICBM (SS-25, also known as RS-12 M). Facts in Brief

Launch Date: 1993-03- 25 Launch Vehicle: ICBM RS-12M Topol or SS-25 Sickle, 3-stage SRM Launch Site: Plesetsk, U.S.S.R Mass: 260.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Engineering

Additional Information

Launch/Orbital information for START 1

Experiments on START 1

Data collections from START 1

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Personnel Stella

Publications NSSDC ID: 1993-061B Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Stella was a 48 kg French satellite that was launched along 22824 with SPOT 3. It was a dense sphere of uranium alloy with 60 laser reflectors on the surface. Reflected laser beams enabled accurate geodetic measurements for the determination, with Facts in Brief an accuracy of 1 cm, of the geoid, of oceanic and terrestrial Launch Date: 1993-09- tides, and of tectonic movements. It joined its still operational 25 twin, Starlette, that was launched in 1975. Launch Vehicle: Ariane Launch Site: Kourou, French Guiana Mass: 48.0 kg

Funding Agency

Unknown (France)

Discipline

Earth Science

Additional Information

Launch/Orbital information for Stella

Experiments on Stella

Data collections from Stella

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Personnel STS 51

Publications NSSDC ID: 1993-058A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events STS 51 was the seventeenth flight of the Discovery orbiter. Its 22795 main mission goals were to deploy the Advanced Communications Technology Satellite (ACTS) and ORFEUS- SPAS. In addition to the the two spacecraft in the cargo bay, Facts in Brief STS 51 also carried the Limited Duration Space Environment Launch Date: 1993-09- Candidate Materials Exposure (LDCE) experiment. Mid-deck 12 experiments included the fourth flight of the Chromosome and Launch Plant Cell Division in Space experiment (CHROMEX 4), the Vehicle: Shuttle third flight of the Radiation Monitoring Equipment (RME-III), the Launch Site: Cape Air Force Maui Optical Site (AMOS), the second flight of the Canaveral, United States Auroral Photography Experiment (APE-B), the Commercial Mass: 19360.0 kg Protein Crystal Growth (CPCG) experiment, the first flight of the High-Resolution Shuttle Glow Spectroscopy (HRSGS-A) experiment, the Investigations into Polymer Membrane Funding Agencies Processing (IPMP) experiment, and more IMAX photography. NASA-Office of Space Flight (United States) NASA-Office of Space Science Applications (United States)

Disciplines

Astronomy Communications Human Crew

Additional Information

Launch/Orbital information for STS 51 PDMP information for STS 51 Telecommunications information for STS 51

Experiments on STS 51

Data collections from STS 51

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Request and User Support Office.

Personnel

Name Role Original Affiliation E-mail

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Discovery (17)

USA

Launch, orbit and landing data

Launch date: 12.09.1993 Launch time: 11:45 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-B Altitude: 296 km Inclination: 28,45° Landing date: 22.09.1993 Landing time: 07:56 UT Landing site: Cape Canaveral (KSC)

Crew

No. Surname Given name Job Flight No. Duration Orbits

1 Culbertson Frank Lee, Jr. CDR 2 9d 20h 11m 157

2 Readdy William Francis "Bill" PLT 2 9d 20h 11m 157

3 Newman James Hansen MSP 1 9d 20h 11m 157

4 Bursch Daniel Wheeler MSP 1 9d 20h 11m 157

5 Walz Carl Erwin MSP 1 9d 20h 11m 157

Crew seating arrangement

Launch Landing Culbertso Culbertso 1 1 n n 2 Readdy 2 Readdy 3 Newman 3 Walz 4 Bursch 4 Bursch 5 Walz 5 Newman

Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC).

Deploying of ACTS; deploying of ORFEUS-satellite on a SPAS-platform; EVA by Newman and Walz on 16.09.1993 (7h 5m), to evaluate tools, tethers and a foot restraint platform; retrieval of ORFEUS/SPAS-platform.

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Personnel STS 54

Publications NSSDC ID: 1993-003A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The STS 54 mission was the third flight of the orbiter 22313 Endeavour and was used to launch the sixth satellite in the Tracking and Data Relay Satellite (TDRS) series, TDRS-F. In addition, STS 54 carried a shuttle bay instrument called the Facts in Brief Diffuse X-ray Spectrometer, or DXS, to make observations of Launch Date: 1993-01- the diffuse x-ray background in the Milky Way galaxy. Finally, 13 several mid-deck experiments were performed, including: (1) Launch the fourth flight of the CHROMEX series, this time studying the Vehicle: Shuttle developmental and physiological processes influencing seed Launch Site: Cape production in microgravity; (2) the second flight of the Canaveral, United States Commercial Generic Bioprocessing Apparatus (CGBA), a Mass: 21156.0 kg collection of 28 separate commercial investigations in STS 54 biomedical testing and drug development, controlled ecological life support systems, and agricultural development and Funding Agencies manufacture of biological-based materials; (3) the second flight of the Physiological and Anatomical Rodent Experiment NASA-Office of Space (PARE), investigating the short-term effects of microgravity on Flight (United States) the size, strength, and stamina of skeletal muscles; and, (4) NASA-Office of Space the first flight of the Solid Surface Combustion Experiment Science Applications (SSCE), to study the physical and chemical mechanisms of (United States) flame propagation over solid fueternally-imposed airflows.

Disciplines

Astronomy Human Crew Life Science Microgravity

Additional Information

Launch/Orbital information for STS 54 PDMP information for STS 54 Telecommunications information for STS 54

Experiments on STS 54

Data collections from STS 54

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Personnel

Name Role Original Affiliation E-mail

Related Information/Data at NSSDC

TDRS-F DXS

Other Sources of STS 54 Information/Data

STS 54 information (NASA KSC) STS 54 Press Release images (NASA JSC)

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Endeavour (3)

USA

Launch, orbit and landing data

Launch date: 13.01.1993 Launch time: 13:59 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-B Altitude: 305 km Inclination: 28,45° Landing date: 19.01.1993 Landing time: 13:37 UT Landing site: Cape Canaveral (KSC)

Crew

No. Surname Given name Job Flight No. Duration Orbits

1 Casper John Howard CDR 2 5d 23h 38m 96

2 McMonagle Donald Ray PLT 2 5d 23h 38m 96

3 Runco Mario, Jr. "Trooper" MSP 2 5d 23h 38m 96

4 Harbaugh Gregory Jordan MSP 2 5d 23h 38m 96

5 Helms Susan Jane MSP 1 5d 23h 38m 96

Crew seating arrangement

Launch 1 Casper McMonag 2 le 3 Runco 4 Harbaugh 5 Helms

Landing 1 Casper 2 McMonagle 3 Helms

4 Harbaugh 5 Runco

Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC).

Deploying communications satellite TDRS-F; Hitchhiker experiment Diffuse X-Ray Spectrometer (DXS); EVA by Harbaugh and Runco (4h 18m) performing a series of space-walking tasks, including testing abilities of free moving, climbing into foot restraints without using their hands and more; several experiments in physics and biology.

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Personnel STS 55

Publications NSSDC ID: 1993-027A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events STS-55 was the 54th flight of the Space Shuttle and the 14th Spacelab-D2/STS 55 flight of Columbia. The STS-55 mission was devoted primarily 22640 to the German Spacelab D-2 experiments in life science, microgravity, earth science, and astronomy. Facts in Brief The D-2 mission, as it was commonly called, augmented the German microgravity research program started by the D-1 Launch Date: 1993-04- mission. The German Aerospace Research Establishment 26 (DLR) had been tasked by the German Space Agency (DARA) Launch to conduct the second mission. DLR, NASA, the European Vehicle: Shuttle Space Agency (ESA), and agencies in France and Japan Launch Site: Cape contributed to D-2's scientific program. Eleven nations Canaveral, United States participated in the experiments. Of the 88 experiments Mass: 12185.0 kg conducted on the D-2 mission, four were sponsored by NASA. Funding Agency The crew worked in two shifts around-the-clock to complete investigations into the areas of fluid physics, materials NASA-Office of Space sciences, life sciences, biological sciences, technology, Earth Flight (United States) observations, atmospheric physics, and astronomy. Many of the experiments advanced the research of the D-1 mission by conducting similar tests, using upgraded processing hardware, Disciplines or implementing methods that take full advantage of the Astronomy technical advancements since 1985. The D-2 mission also contained several new experiments which were not previously Earth Science flown on the D-1 mission. Human Crew Life Science The D-2 Mission conducted 88 experiments to study life sciences, material sciences, technology applications, Earth Microgravity observations, astronomy, and atmospheric physics. It surpassed the 365th day in space for the Space Shuttle fleet. Additional Also surpassed the 100th day of flight time in space for Information Columbia, the fleet's oldest Orbiter on its fourteenth flight. Launch/Orbital D-2 also conducted the first tele-robotic capture of a free information for STS 55 floating object by flight controllers in Germany. The crew also PDMP information for conducted the first intervenus saline solution injection in space STS 55 as part of an experiment to study the human body's response to direct fluid replacement as a countermeasure for amounts Telecommunications lost during space flight. They also successfully completed an information for STS 55 in-flight maintenance procedure for collection of orbiter waste water allowing the mission to continue. Experiments on STS 55

STS-55 crew members also participated in two amateur radio Data collections from STS experiments, SAREX II from the United States and the German 55 SAFEX. The experiments allowed students and amateur radio operators from around the world to talk directly with the Space Shuttle in orbit and participated in a Space Medicine Questions or comments conference with the Mayo Clinic. about this spacecraft can

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Personnel

Name Role Original Affiliation E-mail Mr. Leonard Program NASA Johnson Space [email protected] Nicholson Manager Center

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STS-55

Columbia (14)

USA

Launch, orbit and landing data

Launch date: 26.04.1993 Launch time: 14:50 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-A Altitude: 302 km Inclination: 28,45° Landing date: 06.05.1993 Landing time: 14:30 UT Landing site: Edwards AFB

Crew

No. Surname Given name Job Flight No. Duration Orbits

1 Nagel Steven Ray CDR 4 9d 23h 40m 160

2 Henricks Terence Thomas PLT 2 9d 23h 40m 160

3 Ross Jerry Lynn MSP 4 9d 23h 40m 160

4 Precourt Charles Joseph MSP 1 9d 23h 40m 160

5 Harris Bernard Anthony, Jr. MSP 1 9d 23h 40m 160

6 Walter Ulrich Hans PSP 1 9d 23h 40m 160

7 Schlegel Hans Wilhelm PSP 1 9d 23h 40m 160

Crew seating arrangement

Launch Landing 1 Nagel 1 Nagel 2 Henricks 2 Henricks 3 Ross 3 Harris 4 Precourt 4 Precourt 5 Harris 5 Ross 6 Walter 6 Walter 7 Schlegel 7 Schlegel

Backup Crew

No Given Surname Job . name Brümme Renate PS 6 r Luise P Gerhar PS 7 Thiele d Paul P Julius

Flight Launch from Cape Canaveral (KSC); landing on Edwards AFB.

Mission Spacelab D-2; 88 experiments in materials science, physics, medicine, biology, Earth observations, astronomy and more; only four of this experiments were sponsored by NASA; amateur radio experiments (crew got contact to MIR space station).

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Personnel STS 56/Atlas 2

Publications NSSDC ID: 1993-023A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The STS-56 Space Shuttle Discovery mission's primary goal 22621 was the second flight of the Atmospheric Laboratory for Science and Applications (ATLAS 2) and the fifth flight of the Shuttle Backscatter Ultraviolet (SSBUV) experiment. The Facts in Brief ATLAS 2, part of NASA's Mission To Planet Earth (MTPE) Launch Date: 1993-04- program, was designed to study variations in solar activity and 08 in atmospheric composition. ATLAS 2 consisted of instruments Launch flown on ATLAS 1 in 1992 from NASA, France, Germany and Vehicle: Shuttle Belgium. In addition to ATLAS 2, STS-56 also carried the Launch Site: Cape Spartan-201 free-flying payload. Spartan-201 studied the solar Canaveral, United States wind and the sun's corona. Spartan-201 was lifted out of the Mass: 7441.0 kg Shuttle cargo bay by the Remote Manipulator System (RMS) and pulled back into the cargo bay at the end of the mission for return to Earth. STS-56 carried two educational Funding Agency experiments: the Solar Ultraviolet Experiment (SUVE) from the Colorado Space Grant Corporation, a consortium of NASA-Office of Space universities; and the Shuttle Amateur Radio Experiment Flight (United States) (SAREX II). Other mid-deck experiments included the Space Tissue Loss-3 (STL-3) and Physiological and Anatomical Disciplines Rodent Experiment (PARE-03). In-cabin experiments included the Hand-Held, Earth-Oriented, Real-Time, Cooperative, User- Earth Science Friendly, Location-Targeting and Environmental System Human Crew (HERCULES), developed by the Naval Research Lab (NRL) which allowed astronauts to point a camera at the Earth's Life Science surface and record the latitude and longitude of the feature; the Radiation Monitoring Equipment-III (RME-III), an experiment Additional that measured the exposure of ionizing radiation on the Space Information Shuttle; the Cosmic Radiation Effects and Activation Monitor (CREAM), designed to collect data on cosmic ray energy loss; Launch/Orbital and the Air Force Maui Optical Site (AMOS), an Air Force information for STS facility in Maui that records the shuttle glow phenomena. Also 56/Atlas 2 on-board STS-56 was the Commercial Material Dispersion PDMP information for Aapparatus (MDA) ITA Experiments (CMIX-2), a set of 30 STS 56/Atlas 2 experiments for research on microgravity effects on biology. Telecommunications information for STS 56/Atlas 2

Experiments on STS 56/Atlas 2

Data collections from STS 56/Atlas 2

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Personnel

Name Role Original Affiliation E-mail Mr. Leonard Program NASA Johnson Space [email protected] Nicholson Manager Center

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Discovery (16)

USA

Launch, orbit and landing data

Launch date: 08.04.1993 Launch time: 05:29 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-B Altitude: 296 km Inclination: 57° Landing date: 17.04.1993 Landing time: 11:37 UT Landing site: Cape Canaveral (KSC)

Crew

No. Surname Given name Job Flight No. Duration Orbits

1 Cameron Kenneth Donald CDR 2 9d 06h 08m 148

2 Oswald Steven Scot PLT 2 9d 06h 08m 148

3 Foale Colin Michael MSP 2 9d 06h 08m 148

4 Cockrell Kenneth Dale "Taco" MSP 1 9d 06h 08m 148

5 Ochoa Ellen Lauri MSP 1 9d 06h 08m 148

Crew seating arrangement

Launch Landing Camero Camero 1 1 n n 2 Oswald 2 Oswald 3 Foale 3 Ochoa 4 Cockrell 4 Cockrell 5 Ochoa 5 Foale

Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC).

Mission ATLAS-2 in the "Mission to Planet Earth program"; deploying of SPARTAN-201 platform and retrieval after 2 days of freely flight; scientific work (research of Earth atmosphere); radio contacts to schools all over the world and a brief radio contact to the MIR Space Station.

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Personnel STS 57/SPACEHAB 1

Publications NSSDC ID: 1993-037A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events STS 57 was the 56th shuttle mission and the fourth flight of the SPACEHAB 1/STS 57 Endeavour orbiter. It carried for the first time the Spacehab 22684 research laboratory, designed for six experiments on material science and six biotechnology experiments. In addition, it conducted five experiments of interest to the Johnson Space Facts in Brief Center, one experiment relatable to a future space station, and one designed to grow non-linear optical crystals. STS 57 Launch Date: 1993-06- retrieved the Eureca spacecraft that had been released during 21 the STS 46 mission. Launch Vehicle: Shuttle During the course of the eight-day flight, the astronauts Launch Site: Cape successfully conducted scores of biomedical and materials Canaveral, United States STS 57/SPACEHAB 1 sciences experiments inside the pressurized SPACEHAB Mass: 8931.0 kg module. Two astronauts particpated in a spacewalk and the European Retrievable Carrier (EURECA) was retrieved by the Funding Agency crew and stowed inside Endeavour's payload bay. EURECA was deployed from the Shuttle Atlantis in the summer of 1992 NASA-Office of Space and contains several experiments to study the longterm efects Flight (United States) of exposure to microgravity.

An improperly installed electrical connector on Endeavour's Disciplines Remote Manipulator System (RMS) arm (installed 180 degrees Engineering off its correct position) prevented Eureca from recharging its batteries with orbiter power. A flight rule was requiring antenna Human Crew stowage was waived and EURECA was lowered into the Microgravity payload bay without latching its antenna. Mission Specialists David Low and Jeff Wisoff safely secured EURECA's dual antennas against the science satellite during the spacewalk Additional performed on Friday. David Low was mounted an foot restraint Information on the end of Endeavour's robotic arm while Mission Specialist Launch/Orbital Nancy Sherlock positioned the arm so Low could gently push information for STS the arms against EURECA's latch mechanisms. Payload 57/SPACEHAB 1 controllers then drove the latches to secure each antenna. The five-hour, 50 minute spacewalk completed STS-57 mission's Telecommunications primary goal of retrieving the EURECA science satellite. information for STS Afterwards, Low and Wisoff completed maneuvers for an 57/SPACEHAB 1 abbreviated extravehicular activity (EVA) Detailed Test Objective using the robot arm. Activities associated with each Experiments on STS of the areas of investigation -- mass handling, mass fine 57/SPACEHAB 1 alignment and high torque -- were completed with both EVA crewmen taking turns on the robot arm. Low and Wisoff Data collections from STS wrapped up their spacewalk and returned to Endeavour's 57/SPACEHAB 1 airlock shortly before 3 p.m. Central.

During the rest of the mission, the crew worked on Questions or comments experiments in the Spacehab module in the Shuttle's lower about this spacecraft can deck. These experiments included studying body posture, the be directed to: Coordinated spacecraft environment, crystal growth, metal alloys, Request and User Support wastewater recycling and the behavior of fluids. Among the http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1993-037A[12/05/2011 23:28:29] NASA - NSSDC - Spacecraft - Details

Office. experiments was an evaluation of maintenance equipment that may be used on Space Station Freedom. The diagnostic equipment portion of the Tools and Diagnostics System experiment was performed by Nancy Sherlock. Using electronics test instruments including an oscilloscope and electrical test meter, Sherlock conducted tests on a mock printed circuit board and communicated with ground controllers via computer messages on suggested repair procedures and their results.

In addition, Brian Duffy and Jeff Wisoff ran experiments in transferring fluids in weightlessness without creating bubbles in the fluid. The experiment, called the Fluid Aquisition and Resupply Experiment, or FARE, studied filters and processes that may lead to methods of refueling spacecraft in orbit and transfers water between two foot-diameter transparent tanks on Endeavour's middeck, engineers can evaluate how the fluids behave while the shuttle's steering jets are fired for small maneuvers. Janice Voss worked on the Liquid Encapsulated Melt Zone, or LEMZ, experiment which uses a process called floating zone crystal growth. The low-gravity conditions of space flight permit large crystals to be grown in space.

Ron Grabe, Brian Duffy and Janice Voss participated in the Neutral Body Position study. Flight surgeons have noted on previous flights that the body's basic posture changes while in microgravity. This postural change, sometimes called the "zero-g crouch," is in addition to the one- to two-inch lengthening of the spine during space missions. To better document this phenomenon over the duration of a space mission, still and video p hotography of crew members in a relaxed position are taken early and late in the mission. Researchers will include these findings in the specifications for design of future spacecraft to make work stations and living areas efficient and more comfortable for astronauts.

Nancy Sherlock stepped through the electronics procedures portion of the Human Factors Assessment this morning. She set up a work platform then hooked up a notebook computer and went through a simulated computer procedure for a space station propulsion system.

On 6/28/93, Nancy Sherlock performed an impromptu plumbing job on the Environmental Control Systems Flight Experiment, a study of wastewater purification equipment that may be used aboard future spacecraft. EFE uses a mixture of water and potassium idodide to simulate wastewater. The solution is pumped through a series of filters to purify it. During the flight, experimenters have seen a reduced flow of water through the device and opted to perform the maintenance procedure. Sherlock loosened a fitting on one water line inside the experiment, wrapped the loose fitting with an absorbent diaper, and, using a laptop computer onboard, turned a pump on the experiment into reverse for about 20 minutes in an attempt to flush out the clog. Sherlock then retightened the fitting and put the experiment back into normal operation for ground experimenters, who will now spend about an hour and a half watching it run to see if the clog has been cleared.

The orbiter completed 155 orbits and had a total duration of 9 days, 23 hours, 44 minutes, and 54 seconds.

Related Information/Data at NSSDC

Eureca 1

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Endeavour (4)

Launch, orbit and landing data

Launch date: 21.06.1993 Launch time: 13:07 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-B Altitude: 466 km Inclination: 28,45° Landing date: 01.07.1993 Landing time: 12:52 UT Landing site: Cape Canaveral (KSC)

Crew

No. Surname Given name Job Flight No. Duration Orbits

1 Grabe Ronald John CDR 4 9d 23h 44m 155

2 Duffy Brian PLT 2 9d 23h 44m 155

3 Low George David MSP 3 9d 23h 44m 155

4 Sherlock Nancy Jane MSP 1 9d 23h 44m 155

5 Wisoff Peter Jeffrey Kelsay "Jeff" MSP 1 9d 23h 44m 155

6 Voss Janice Elaine MSP 1 9d 23h 44m 155

Crew seating arrangement

Launch Landing 1 Grabe 1 Grabe 2 Duffy 2 Duffy 3 Low 3 Wisoff 4 Sherlock 4 Sherlock 5 Wisoff 5 Low 6 Voss 6 Voss

Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC).

Retrieval of European-built platform EURECA (deployed on mission STS-46); EVA by Low and Wisoff on 25.06.1993 (5h 50m), to make final tests for repairing works on the Hubble Space Telescope; astronauts conducted scores of biomedical and materials sciences experiments inside Spacehab-module.

Photos / Drawings

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Personnel STS 58

Publications NSSDC ID: 1993-065A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events STS 58 was the 15 flight of the orbiter Columbia. The primary SLS 2/STS 58 payload for this mission was the second flight of the Spacelab 22869 Life Sciences (SLS 2) cargo bay payload. In addition to activities involved with the SLS 2 payload, seven experiments providing additional information for on-going medical studies Facts in Brief supporting the Extended Duration Orbiter (EDO) Medical Project were performed. The EDO Medical Project is designed Launch Date: 1993-10- to assess the impact of long duration spaceflight (>10 days) on 18 astronaut health, identify any operational medical concerns, Launch and test countermeasures for the adverse effects of Vehicle: Shuttle weightlessness on human physiology. Only three of the EDO Launch Site: Cape experiments took place in-flight; the other four occurred prior Canaveral, United States and/or subsequent to the mission. An additional experiment Mass: 10517.0 kg performed on this flight was the Orbital Acceleration Research Experiment, or OARE. The main goal of the experiment was to Funding Agencies measure the Shuttle's aeordynamic forces (drag) in orbit and during the early stages of re-entry. This was the third flight of NASA-Office of Space this experiment. Astronauts also participated in the eleventh Flight (United States) flight of the Shuttle Amateur Radio Experiment (SAREX). NASA Office of Life and Microgravity Sciences and Applications (United States)

Disciplines

Engineering Human Crew Life Science

Additional Information

Launch/Orbital information for STS 58 PDMP information for STS 58 Telecommunications information for STS 58

Experiments on STS 58

Data collections from STS 58

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Columbia (15)

Launch, orbit and landing data

Launch date: 18.10.1993 Launch time: 14:53 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-B Altitude: 287 km Inclination: 39° Landing date: 01.11.1993 Landing time: 15:05 UT Landing site: Edwards AFB

Crew

No. Surname Given name Job Flight No. Duration Orbits

1 Blaha John Elmer CDR 4 14d 00h 12m 225

2 Searfoss Richard Alan PLT 1 14d 00h 12m 225

3 Seddon Margaret Rhea MSP 3 14d 00h 12m 225

4 McArthur William Surles, Jr. "Bill" MSP 1 14d 00h 12m 225

5 Wolf David Alexander "Bluto" MSP 1 14d 00h 12m 225

6 Lucid Matilda Shannon Wells MSP 4 14d 00h 12m 225

7 Fettman Martin Joseph PSP 1 14d 00h 12m 225

Crew seating arrangement

Launch Landing 1 Blaha 1 Blaha 2 Searfoss 2 Searfoss 3 Seddon 3 Wolf 4 McArthur 4 McArthur 5 Wolf 5 Seddon 6 Lucid 6 Lucid 7 Fettman 7 Fettman

Backup Crew

No Surnam Given Job . e name Jay PS 7 Buckey Clark, Jr. P Laurenc PS 7 Young e P Retman

Flight Launch from Cape Canaveral (KSC); landing on Edwards AFB.

Second Spacelab Life Science mission; life sciences research; experiments focused on cardiovascular, regulatory, neurovestibular and musculoskeletal systems of the body; experiments performed on crew and on laboratory animals (48 rats); longest Shuttle-mission to date. Photos / Drawings

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Personnel STS 61

Publications NSSDC ID: 1993-075A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events STS 61 was the fifth flight of the Endeavour orbiter and the 22917 59th shuttle mission. Its objective was to repair, replace, and/or update the instruments on the Hubble Space Telescope. During several days of EVA, the crew installed Facts in Brief corrective optics (COSTAR) in the light path after removing the Launch Date: 1993-12- High Speed Photometer (HSP) instrument; replaced the older 02 Wide Field/Planetary Camera (WF/PC) with a newer version Launch (WFPC 2); and replaced malfunctioning solar arrays. Vehicle: Shuttle Launch Site: Cape The duration of the mission was 10 days, 19 hours, 58 Canaveral, United States minutes, and 37 seconds and lasted for 163 orbits. Mass: 8011.0 kg

Funding Agency

NASA-Office of Space STS 61 Flight (United States)

Discipline

Human Crew

Additional Information

Launch/Orbital information for STS 61 PDMP information for STS 61 Telecommunications information for STS 61

Experiments on STS 61

Data collections from STS 61

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

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The Hubble Space Telescope

Other Sources of STS 61 Information/Data

STS 61 information (NASA KSC) STS 61 Press Release images (NASA JSC)

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Endeavour (5)

USA

Launch, orbit and landing data

Launch date: 02.12.1993 Launch time: 09:27 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-B Altitude: 594 km Inclination: 28,45° Landing date: 13.12.1993 Landing time: 05:25 UT Landing site: Cape Canaveral (KSC)

Crew

No. Surname Given name Job Flight No. Duration Orbits

1 Covey Richard Oswalt CDR 4 10d 19h 58m 163

2 Bowersox Kenneth Dwane "Sox" PLT 2 10d 19h 58m 163

3 Thornton Kathryn Cordell Ryan MSP 3 10d 19h 58m 163

4 Nicollier Claude MSP 2 10d 19h 58m 163

5 Hoffman Jeffrey Alan MSP 4 10d 19h 58m 163

6 Musgrave Franklin Story MSP 5 10d 19h 58m 163

7 Akers Thomas Dale MSP 3 10d 19h 58m 163

Crew seating arrangement

Launch Landing 1 Covey 1 Covey 2 Bowersox 2 Bowersox 3 Thornton 3 Hoffman 4 Nicollier 4 Nicollier 5 Hoffman 5 Thornton 6 Musgrave 6 Musgrave 7 Akers 7 Akers

Backup Crew

No. Surname Given name Job

Harbaugh Gregory Jordan MSP

Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC).

First Hubble Space Telescope servicing mission; Hubble Space Telescope (HST) was successfully captured; first EVA by Hoffman and Musgrave on 05.12.1993 (7h 54m), replacing two sets of Remote Sensing Units (RSU) and a pair of electrical control units; after that the HST had a full set of six healthy gyroscopes.

Second EVA by Thornton and Akers on 06.12.1993 (6h 36m), in which two damaged solar arrays were replaced.

Third EVA by Hoffman and Musgrave on 07.12.1993 (6h 47m); this time the astronauts replaced two magnometers and the Wide Field Planetary Camera (WFPC); the new camera has a higher rating than the previous camera.

Fourth EVA again by Thornton and Akers on 08.12.1993 (6h 50m); the primary task of this EVA was to replace the High Speed Photometer (HSP) with a device called COSTAR (Corrective Optics Space telescope Axial Replacement), which corrects the problem with the main mirror.

Fifth and final EVA by Hoffman and Musgrave on 09.12.1993 (7h 21m); they replaced one of two Solar Array Drive Electronics (SADE), a very difficult work, because it was primary not planned to exchange des SADE; during this EVA the solar arrays were deployed after a few problems; they also fitted an electrical connection box on the Goddard High Resolution Spectrograph (GHRS) and installed some covers on the magnometers, produced onboard by Nicollier and Bowersox; after this spectacular and very difficult work, the HST was again released.

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Personnel TDRS-F

Publications NSSDC ID: 1993-003B Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events TDRS-F was the fifth successful launch of the Tracking and TDRS 6 Data Relay Satellite series. TDRS-F was used in combination Tracking and Data Relay with other TDRS spacecraft and a ground communications Satellite 6 system to form the Tracking and Data Relay Satellite System (TDRSS). The objective of the TDRSS program was to provide 22314 and maintain improved tracking and data acquisition services to spacecraft in low-Earth orbit. In order to fulfill this objective, Facts in Brief TDRSS required at least two fully operational TDRS in orbit with one or more additional spacecraft serving as system Launch Date: 1993-01- spares. Each TDRS was a three-axis, momentum-biased 13 satellite. The bus section of the spacecraft was hexagonal with Launch an approximate diameter of 3 m. Power was provided by two Vehicle: Shuttle opposing, three-section solar array panels, 4.0 x 3.8 m in Launch Site: Cape dimension, at the end of 3.25 m booms. Perpendicular to the Canaveral, United States TDRS-F solar arrays were the two 4.9 m diameter, K- and S-band, Mass: 2108.0 kg single-access (SA) antennae. With the solar panels and SA Nominal antennae deployed, TDRS measured 17.3 x 14.2 m. TDRS Power: 1700.0 W was comprised of three functional modules: payload, spacecraft, and antenna. The payload module consisted of two single-access compartments, the multiple access antenna Funding Agency platform, and a main payload module. The main payload NASA-Office of Tracking module had six panels which formed an integral part of the and Data Acquisition main bus structure and housed the principle elements of the (United States) TDRS payload. The spacecraft module contained the thermal control, electrical power, attitude control, propulsion, and tracking, telemetry, and command systems. The antenna Discipline module consisted of the two SA dish antennae, the 2.0 m K- band Space-to-Ground Link (SGL) antenna, and, on the bus of Communications the spacecraft, the 30 helical element, multiple access (MA) antenna array, a C-band antenna, and an S-band Additional omnidirectional SGL antenna. In addition to changes made to Information previous TDRS spacecraft subsequent to TDRS-A, TDRS-F had its S-band return parametric amplifiers replaced with solid- Launch/Orbital state, low-noise amplifiers. information for TDRS-F PDMP information for TDRS-F

Experiments on TDRS-F

Data collections from TDRS-F

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Personnel

Name Role Original Affiliation E-mail Mr. Charles Project NASA Goddard Space [email protected] S. Vanek Manager Flight Center

Related Information/Data at NSSDC

NSSDC TDRS page STS 54 DXS

Other Sources of TDRS Information/Data

TDRS program

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Personnel Telstar 401

Publications NSSDC ID: 1993-077A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Telstar 401 was an AT+T geostationary, communications 22927 spacecraft launched by an Atlas 2AS rocket from Cape Canaveral. It was the first of AT+T's next generation of broadcast video and data-communications satellites. In Facts in Brief addition to providing hybrid C- and Ku-band transmissions, the Launch Date: 1993-12- Telstar 4 satellites could support digital compression and 15 featured 50-state broadcast coverage, plus Puerto Rico and Launch Vehicle: Atlas- the US Virgin Islands. It was placed in a geosynchronous orbit 2 AS at 97 degrees W. Launch Site: Cape Canaveral, United States Telstar 401's telemetry and communications abruptly stopped Mass: 3375.0 kg early morning on January 11, 1997. AT+T petitioned the FCC to move Telstar 302 to Telstar 401's orbital slot to provide temporary transponder capacity for customers. Funding Agency

American Telephone and Telegraph Company (United States)

Discipline

Communications

Additional Information

Launch/Orbital information for Telstar 401

Experiments on Telstar 401

Data collections from Telstar 401

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Personnel TEMISAT

Publications NSSDC ID: 1993-055B Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events TEMISAT was an Italian micro-satellite released from Meteor 22783 2-21. It carried relaying instruments to uplink and downlink weather data from the Mediterranean and adjacent areas obtained by about 50 ground stations. The 32-kg satellite was Facts in Brief released into an orbit of 937 km by 969 km at an 82.5 degree Launch Date: 1993-08- inclination. The principal mission of TEMISAT was to collect 31 environmental data from numerous dispersed transmitters and Launch forward the information to special data collection centers in the Vehicle: Tsiklon-3 138-150 MHz band. It was expected to operate 3-5 years but Launch Site: Plesetsk, failed in the fall of 1994. Russia Mass: 42.0 kg

Funding Agency

Unknown (Italy)

Discipline

Earth Science

Additional Information

Launch/Orbital information for TEMISAT

Experiments on TEMISAT

Data collections from TEMISAT

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Personnel THAICOM 1A

Publications NSSDC ID: 1993-078B Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events THAICOM 1A, a Thailand geostationary communications 22931 spacecraft, was launched by an Ariane 44-L booster from Kourou, French Guiana and parked a little eastward of that country, at 120 degrees E. It contained twelve C-band Facts in Brief transponders with a footprint coverage including Thailand, Launch Date: 1993-12- Laos, Cambodia, Myanmar, Vietnam, Malaysia, The 17 Philippines, Korea, Japan and the East Coast of China, with a Launch Vehicle: Ariane nominal EIRP of 36 dBW. It also contained two KU-band 44L transponders that provided a high-powered spot beam for Launch Site: Kourou, Thailand with a nominal EIRP of 50 dBW which was ideally French Guiana suitable for direct broadcasting applications. Mass: 629.0 kg Nominal Power: 800.0 W

Funding Agency

Unknown (Thailand)

Discipline

Communications

Additional Information

Launch/Orbital information for THAICOM 1A

Experiments on THAICOM 1A

Data collections from THAICOM 1A

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Personnel UFO 1

Publications NSSDC ID: 1993-015A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events UFO 1 (UHF Follow On 1) was a US Navy satellite launched to UHF F/O 1 replace the FLTSATCOM and Leasat spacecraft currently UHF Follow On 1 sopporting the Navy's global communications network, serving ships at sea and a variety of other US military fixed and mobile 22563 terminals. It was compatible with ground- and sea-based terminals already in service. Facts in Brief

The UHF F/O satellites offered increased communications Launch Date: 1993-03- channel capacity over the same frequency spectrum used by 25 previous systems. Each spacecraft had 11 solid-state UHF Launch Vehicle: Atlas- amplifiers and 39 UHF channels with a total of 555 kHz Centaur bandwidth. The UHF payload compresed 21 narrow band Launch channels at 5 kHz each and 17 relay channels at 25 kHz. In Site: Vandenberg AFB, comparison, FLTSATCOM offered 22 channels. The F-1 United States through F-7 spacecraft included an SHF (super high frequency) Mass: 2866.0 kg subsystem, which provided command and ranging capabilities when the satellite was on station as well as the secure uplink for Fleet Broadcast service, which was downlinked at UHF. Funding Agency Department of Defense- Each satellite measured more than 60 feet long from the tip of Department of the Navy one three-panel solar array wing to the tip of the other. These (United States) arrays generated a combined 2500 watts of electrical power on the first three satellites, 2800 watts for F-4 through F-7, and 3800 watts for F-8 through F-10 with GBS. The arrays were Disciplines folded against the spacecraft bus for launch, forming a cube roughly 11 feet per side. Communications Surveillance and Other This satellite was placed in an unusable orbit. Military

Additional Information

Launch/Orbital information for UFO 1

Experiments on UFO 1

Data collections from UFO 1

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Personnel UFO 2

Publications NSSDC ID: 1993-056A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events UFO 2 (UHF Follow On 2) was a US Navy satellite launched to USA 95 replace the FLTSATCOM and Leasat spacecraft currently 22787 sopporting the Navy's global communications network, serving ships at sea and a variety of other US military fixed and mobile terminals. It was compatible with ground- and sea-based Facts in Brief terminals already in service. Launch Date: 1993-09- The UHF F/O satellites offered increased communications 03 channel capacity over the same frequency spectrum used by Launch Vehicle: Atlas previous systems. Each spacecraft had 11 solid-state UHF Launch Site: Cape amplifiers and 39 UHF channels with a total of 555 kHz Canaveral, United States bandwidth. The UHF payload compresed 21 narrow band Mass: 2844.0 kg channels at 5 kHz each and 17 relay channels at 25 kHz. In comparison, FLTSATCOM offered 22 channels. The F-1 Funding Agency through F-7 spacecraft included an SHF (super high frequency) subsystem, which provided command and ranging capabilities Department of Defense- when the satellite was on station as well as the secure uplink Department of the Navy for Fleet Broadcast service, which was downlinked at UHF. (United States)

Each satellite measured more than 60 feet long from the tip of one three-panel solar array wing to the tip of the other. These Disciplines arrays generated a combined 2500 watts of electrical power on Communications the first three satellites, 2800 watts for F-4 through F-7, and 3800 watts for F-8 through F-10 with GBS. The arrays were Surveillance and Other folded against the spacecraft bus for launch, forming a cube Military roughly 11 feet per side. Additional Information

Launch/Orbital information for UFO 2

Experiments on UFO 2

Data collections from UFO 2

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