Cronología de Lanzamientos Espaciales
Año 1996
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
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Publications There were 108 spacecraft returned.
Maps Spacecraft Name NSSDC ID Launch Date New/Updated Data ADEOS 1996-046A 1996-08-16
Lunar/Planetary Events AMOS 1 1996-030B 1996-05-15 Apstar 1A 1996-039A 1996-07-02 Arabsat 2A 1996-040A 1996-07-08 Arabsat 2B 1996-063A 1996-11-12 Astra 1F 1996-021A 1996-04-07 Bion 11 1996-073A 1996-12-23 Chinasat 7 1996-048A 1996-08-17 Cluster96 CLUSTR1 1996-06-03 Cosmos 2327 1996-004A 1996-01-15 Cosmos 2328 1996-009D 1996-02-18 Cosmos 2329 1996-009E 1996-02-18 Cosmos 2330 1996-009F 1996-02-18 Cosmos 2331 1996-016A 1996-03-13 Cosmos 2332 1996-025A 1996-04-23 Cosmos 2333 1996-051A 1996-09-03 Cosmos 2334 1996-052A 1996-09-04 Cosmos 2335 1996-069A 1996-12-10 Cosmos 2336 1996-071A 1996-12-19 Echostar 2 1996-055A 1996-09-10 Express 12 1996-058A 1996-09-25 FAST 1996-049A 1996-08-20 FSW-2 3 1996-059A 1996-10-19 Galaxy 9 1996-033A 1996-05-23 GE 1 1996-054A 1996-09-07 Gonets D1-1 1996-009A 1996-02-18 Gonets D1-2 1996-009B 1996-02-18 Gonets D1-3 1996-009C 1996-02-18 Gorizont 31 1996-005A 1996-01-24 Gorizont 32 1996-034A 1996-05-24 HETE 1 1996-061A 1996-11-03 Hot Bird 2 1996-067A 1996-11-20 IAE 1996-032C 1996-05-19 Inmarsat 3-F1 1996-020A 1996-04-02 Inmarsat 3-F2 1996-053A 1996-09-05 Inmarsat 3-F3 1996-070A 1996-12-17
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INTELSAT 7 F-7 1996-015A 1996-03-13 INTELSAT 709 1996-035A 1996-06-14 Interball Auroral Probe 1996-050C 1996-08-28 IRS-P3 1996-017A 1996-03-20 Italsat 2 1996-044A 1996-08-07 JAS 2 1996-046B 1996-08-16 KH 12-3 1996-072A 1996-12-19 Koreasat 2 1996-003A 1996-01-13 Magion 5 1996-050B 1996-08-28 Mars 96 Orbiter 1996-064A 1996-11-15 Mars 96 Penetrator MARS96D 1996-11-15 Mars 96 Penetrator MARS96E 1996-11-15 Mars 96 Surface Station MARS96B 1996-11-15 Mars 96 Surface Station MARS96C 1996-11-15 Mars Global Surveyor 1996-062A 1996-11-06 Mars Pathfinder 1996-068A 1996-12-03 Mars Pathfinder Rover MESURPR 1996-12-03 MEASAT 1 1996-002B 1996-01-11 MEASAT 2 1996-063B 1996-11-12 Microsat 1996-050A 1996-08-28 Molniya 1-89 1996-045A 1996-08-13 Molniya 3-48 1996-060A 1996-10-23 MSAT 1 1996-022A 1996-04-19 MSTI 3 1996-031A 1996-05-16 MSX 1996-024A 1996-04-23 N-Star-B 1996-007A 1996-02-04 Navstar 2A-16 1996-019A 1996-03-27 Navstar 2A-17 1996-041A 1996-07-15 Navstar 2A-18 1996-056A 1996-09-11 NEAR Shoemaker 1996-008A 1996-02-16 OAST Flyer 1996-001B 1996-01-10 ORFEUS-SPAS II 1996-065B 1996-11-19 OSL OSL 1995-12-31 Palapa C-1 1996-006A 1996-01-31 Palapa C-2 1996-030A 1996-05-15 PAMS-STU 1996-032D 1996-05-21 PANAMSAT 3R 1996-002A 1996-01-11 Polar 1996-013A 1996-02-23 Priroda 1996-023A 1996-04-22 Progress M-31 1996-028A 1996-05-04 Progress M-32 1996-043A 1996-07-30 Progress M-33 1996-066A 1996-11-18 Raduga 33 1996-010A 1996-02-18 REX 2 1996-014A 1996-03-08 SAC-B 1996-061B 1996-11-03 SAX 1996-027A 1996-04-29 Soyuz-TM 23 1996-011A 1996-02-20 Soyuz-TM 24 1996-047A 1996-08-17 Spartan 207 1996-032B 1996-05-19
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STS 72 1996-001A 1996-01-10 STS 75 1996-012A 1996-02-21 STS 76 1996-018A 1996-03-21 STS 77 1996-032A 1996-05-18 STS 78 1996-036A 1996-06-19 STS 79 1996-057A 1996-09-15 STS 80 1996-065A 1996-11-18 STS/SRL 3 SRL3 1996-01-31 TELECOM 2D 1996-044B 1996-08-07 TOMS-EP 1996-037A 1996-07-01 TSS-1R 1996-012B 1996-02-24 Turksat 1C 1996-040B 1996-07-08 UFO 7 1996-042A 1996-07-24 UNAMSAT-B 1996-052B 1996-09-04 USA 118 1996-026A 1996-04-23 USA 119 1996-029A 1996-05-11 USA 120 1996-029B 1996-05-11 USA 121 1996-029C 1996-05-11 USA 122 1996-029D 1996-05-11 USA 123 1996-029E 1996-05-11 USA 124 1996-029F 1996-05-11 USA 125 1996-038A 1996-07-02 WSF 3 1996-065C 1996-11-22
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Personnel ADEOS
Publications NSSDC ID: 1996-046A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The Japanese Advanced Earth Observing Satellite (ADEOS) Midori was developed to establish platform technology for Earth Advanced Earth Observing System (EOS) spacecraft and inter-orbit Observing Satellite communication technology for the transmission of Earth observation data. In addition, ADEOS contributed global 24277 observation of environmental change to the international community during the pre-EOS era. NASA's Mission to Planet Facts in Brief Earth (MTPE) program contributed two instruments for the ADEOS mission. Launch Date: 1996-08- 16 ADEOS was a sun-synchronous, morning equator-crossing (in Launch Vehicle: H-2 descending node at about 10:30 a.m.), polar orbiting Launch spacecraft. It had a modular type shape with a deployable one Site: Tanegashima, Japan wing solar paddle. The body measured 4 x 4 x 5 m and the Mass: 3500.0 kg solar paddle was 3 x 13 m in size. Nominal Power: 5000.0 W ADEOS was three-axis stabilized by a zero momentum strap- down attitude-control system. Attitude was maintained by four reaction wheels, two magnetometers, an inertial reference unit, Funding Agency and two hydrazine thrusters. Power was provided by a single National Space gallium arsenide flexible solar paddle and five 35 A-hr NiCd Development Agency batteries. Data was transmitted via direct transmission and (NASDA) (Japan) inter-orbit communication through ETS-6. A Mission Data Recorder system on-board ADEOS stored high data rate and low data rate data on separate tape recorders. Discipline
Eight experiments on ADEOS included: (1) Ocean Color and Earth Science Temperature Scanner (OCTS), a NASDA core instrument; (2) Advanced Visible and Near-Infrared Radiometer (AVNIR), a Additional NASDA core instrument; (3) NASA Scatterometer (NSCAT), a Information NASA/MTPE-provided instrument; (4) Total Ozone Mapping Spectrometer (TOMS), a NASA/MTPE provided instrument; (5) Launch/Orbital Polarization and Directionality of the Earth's Reflectances information for ADEOS (POLDER), provided by CNES of France; (6) Interferometric PDMP information for Monitor for Greenhouse Gases (IMG), provided by MITI of ADEOS Japan; (7) Improved Limb Atmospheric Spectrometer (ILAS), provided by Environmental Agency of Japan; and, (8) Telecommunications Retroreflector in Space (RIS), provided by the Environmental information for ADEOS Agency of Japan. Experiments on ADEOS The design lifetime for this mission was three years, but the spacecraft ceased operating on 30 June 1997 for as yet Data collections from unknown reasons. Subsequent flights of ADEOS are planned ADEOS during the EOS era.
Questions or comments about this spacecraft can be directed to: Coordinated
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Personnel
Name Role Original Affiliation E-mail Dr. Robert Project NASA Goddard Space Flight Douglas Scientist Center Hudson Dr. William Program NASA Headquarters [email protected] C. Patzert Scientist Dr. Robert T. Program NASA Headquarters Watson Scientist Mr. K. Project National Space Development Yoneyama Director Agency of Japan Dr. George Program NASA Headquarters F. Esenwein, Manager Jr. Dr. Firouz M. Project NASA Jet Propulsion [email protected] Naderi Manager Laboratory Mr. Donald Project NASA Goddard Space Flight [email protected] L. Margolies Manager Center General Laboratoire d'Etudes et de Contact Recherches en Teledetection Spatiale Mr. T. Program National Space Development Tanaka Manager Agency of Japan
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Personnel AMOS 1
Publications NSSDC ID: 1996-030B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events AMOS 1 was an Israeli 3-axis stabilized, geosynchronous 23865 communications satellite that was launched by an Ariane 44 L rocket along with Palapa C-2 from Kourou. It carried seven transponders in the Ku-band to enable voice and vision Facts in Brief communications to a large area centered in Israel. Launch Date: 1996-05- 15 Launch Vehicle: Ariane 44L Launch Site: Kourou, Israel Mass: 471.0 kg Nominal Power: 1150.0 W
Funding Agency
Unknown (Israel)
Discipline
Communications
Additional Information
Launch/Orbital information for AMOS 1
Experiments on AMOS 1
Data collections from AMOS 1
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Apstar 1A
Publications NSSDC ID: 1996-039A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events APSTAR 1A was a Chinese geosynchronous communications 23943 satellite launched by a Long March 3 rocket from the Xichang center in southeastern China. It provided TV coverage to the Asian-Pacific countries through its 24 C-band transponders. It Facts in Brief is expected to provide 10 years of service. It had two Launch Date: 1996-07- telescoping cylindrical solar panels and an antenna array that 03 folded down for launch. It measured 2.2 meters in diameter Launch Vehicle: Long and a compact 3.1 meters tall when stowed for launch. With March 3 the solar panels deployed and the antennas unfolded in orbit, it Launch Site: Xichang, measured 7.5 meters. The solar panels were covered with K-4 Peoples Republic of China 3/4 solar cells, which produced 1130 watts at beginning of life. Mass: 726.0 kg During eclipse, two super nickel cadmium batteries provided Nominal power for uninterrupted service. Power: 1130.0 W
Funding Agency
APT Satellite Company Ltd (Peoples Republic of China)
Discipline
Communications
Additional Information
Launch/Orbital information for Apstar 1A
Experiments on Apstar 1A
Data collections from Apstar 1A
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Arabsat 2A
Publications NSSDC ID: 1996-040A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Arabsat 2A was a geosynchronous communications satellite of 23948 the 21-nation ARABSAT consortium and was launched by an Ariane 44L rocket from the Kourou center in French Guiana. The spacecraft provided radio and TV communications to the Facts in Brief Middle East and neighboring countries. Launch Date: 1996-07- 09 Launch Vehicle: Ariane 44L Launch Site: Kourou, French Guiana Mass: 2100.0 kg
Funding Agency
Arabsat Satellite Communications (International)
Discipline
Communications
Additional Information
Launch/Orbital information for Arabsat 2A
Experiments on Arabsat 2A
Data collections from Arabsat 2A
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Arabsat 2B
Publications NSSDC ID: 1996-063A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Arabsat 2B was a geosynchronous communications satellite of 24652 the 21-nation ARABSAT consortium and was launched by an Ariane 44L rocket from the Kourou center in French Guiana. The spacecraft provided radio and TV communications to the Facts in Brief Middle East and neighboring countries. It was parked in a Launch Date: 1996-11- geostationary orbit at 21.9 deg E. 13 Launch Vehicle: Ariane 44L Launch Site: Kourou, French Guiana Mass: 2600.0 kg
Funding Agency
Arabsat Satellite Communications (International)
Discipline
Communications
Additional Information
Launch/Orbital information for Arabsat 2B
Experiments on Arabsat 2B
Data collections from Arabsat 2B
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Astra 1F
Publications NSSDC ID: 1996-021A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Astra 1F was a European (SES, Luxembourg) 23842 geosynchronous communications satellite launched by a Proton-K rocket from the Baykonur cosmodrome. It is parked over 19.2 deg E longitude and provides direct broadcast TV to Facts in Brief Europe through its 16 Ku-band transponders. Launch Date: 1996-04- 08 Launch Vehicle: Proton-K Launch Site: Tyuratam (Baikonur Cosmodrome), Kazakhstan Mass: 3010.0 kg
Funding Agency
Societe Europeenne des Satellites (Luxembourg) (Luxembourg)
Discipline
Communications
Additional Information
Launch/Orbital information for Astra 1F
Experiments on Astra 1F
Data collections from Astra 1F
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Bion 11
Publications NSSDC ID: 1996-073A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Bion 11 was a Russia biological research satellite launched 24701 from the Plesetsk cosmodrome aboard a Soyuz rocket. It carried two monkeys named Lalik and Multik. Facts in Brief
The spacecraft was based on the Zenit reconnaissance Launch Date: 1996-12- satellite and launches began in 1973 with primary emphasis on 24 the problems of radiation effects on human beings. Launches Launch in the program included Cosmos 110, 605, 670, 782, plus Vehicle: Soyuz-U Nauka modules flown on Zenit-2M reconnaissance satellites. Launch Site: Plesetsk, 90 kg of equipment could be contained in the external Nauka Russia module.
Funding Agency
Institute of Biomedical Problems, Moscow (Russia)
Disciplines
Life Science Microgravity
Additional Information
Launch/Orbital information for Bion 11
Experiments on Bion 11
Data collections from Bion 11
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Chinasat 7
Publications NSSDC ID: 1996-048A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Chinasat 7 was a geosynchronous communications spacecraft 24282 launched by the PRC from the Xichang space center aboard a Long March 3 rocket. A third stage rocket failure led to an almost useless orbit. Facts in Brief Launch Date: 1996-08- 18 Launch Vehicle: Long March 3 Launch Site: Xichang, Peoples Republic of China Mass: 734.0 kg Nominal Power: 1200.0 W
Funding Agency
Unknown (Peoples Republic of China)
Discipline
Communications
Additional Information
Launch/Orbital information for Chinasat 7
Experiments on Chinasat 7
Data collections from Chinasat 7
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cluster96
Publications NSSDC ID: CLUSTR1 Maps Description Facts in Brief New/Updated Data
Lunar/Planetary Events The original Cluster program of four spacecraft (all launched Launch Date: 1996-06- together on the same rocket) experienced a launch failure in 04 1996. Following that, a single replacement Cluster spacecraft Launch Vehicle: Ariane was authorized in July of 1996, and in April 1997 a further 5 three near-replicas of the original spacecraft were also Launch Site: Kourou, approved, thus completing the replication of the original four- French Guiana spacecraft Cluster mission. The following text describes one of Mass: 550.0 kg the original identical four Cluster spacecraft destroyed at Nominal launch. The spacecraft of the new replacement mission, Power: 224.0 W Cluster II, are described elsewhere, under the NSSDC IDs 2000-041A, 2000-041B, 2000-045A, and 2000-045B, and the names Cluster 2/FM5 (Rumba), Cluster 2/FM6 (Salsa), Cluster Funding Agencies 2/FM7 (Samba), and Cluster 2/FM8 (Tango). European Space Agency (International) Cluster-A, one of the four similar spacecraft of the Cluster mission, is part of ESA's and NASA's Solar-Terrestrial Science National Aeronautics and Program (STSP). The purpose of the mission is to study small- Space Administration scale structures in three dimensions in the Earth's plasma (United States) environment, such as those involved in the interaction between the solar wind and the magnetospheric plasma, in global Discipline magnetotail dynamics, in cross-tail currents, and in the formation and dynamics of the neutral line and of plasmoids. Space Physics The four spacecraft will orbit in a tetrahedral formation in 4 x 22 Re, near-polar orbits with relative separations of several hundred kilometers at periapsis. The tetrahedral formation is Additional essential for making three-dimensional measurements and for Information determining the curl of vectorial quantities such as the Launch/Orbital magnetic field. information for Cluster96 Each spacecraft will be spin-stabilized and cylindrical in shape, Telecommunications with a 2.9 m diameter and 0.9 m length. It will have two rigid 5 information for Cluster96 m magnetometer booms and two pairs of wire booms, with 100 m tip-to-tip lengths, for electric field measurements. Each Experiments on Cluster96 spacecraft will have AC and DC magnetometers, an electric fields and waves sensor, an electron emitter/detector, an Data collections from electron density sounder, electron and ion plasma analysers, Cluster96 an energetic particle detector, an ion emitter, and a data processing unit. Questions or comments Cluster operations will be performed by ESA with support from about this spacecraft can NASA's Deep Space Network. Cluster is also an IACG be directed to: Dr. Ramona mission. A more detailed description of the spacecraft and L. Kessel. experiments may be found in ``Cluster: Mission, payload and supporting activities,'' ESA SP-1159, March 1993.
Personnel
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Name Role Original Affiliation E-mail Dr. Melvyn L. Project NASA Goddard Space [email protected] Goldstein Scientist Flight Center Dr. Elden C. Program NASA Headquarters [email protected] Whipple Scientist Mr. Raymond Project NASA Goddard Space S. Tatum Manager Flight Center
Selected References
Cluster: Mission, payload and supporting activities, ESA SP-1159, Paris, France, Mar. 1993.
Other Cluster Information at NSSDC
Cluster96 (failed launch of four spacecraft) Samba Salsa Rumba Tango
Other Sources of Cluster Data/Information
Cluster home page (ESA) Cluster Active Archive (ESA/ESTEC)
Cluster Summary Parameters (CDAWeb) Cluster Prime Parameters (CDAWeb)
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Personnel Cosmos 2327
Publications NSSDC ID: 1996-004A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 2327 was part of a 6-satellite Russian military 23773 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: 1996-01- and 400 MHz) of the satellite position and orbital data. By 16 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
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 2327
Experiments on Cosmos 2327
Data collections from Cosmos 2327
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 2328
Publications NSSDC ID: 1996-009D Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 2328 was a Russian military spacecraft launched by a 23790 Cyclon-3 rocket from the Plesetsk Cosmodrome along with Cosmos 2329, 2330 and three Gonets spacecraft. It provided military data messaging and photo reconnaissance for the Facts in Brief Russian Federation Ministry of Defense. Launch Date: 1996-02- 18 Launch Vehicle: Tsiklon-3 Launch Site: Plesetsk, Russia Mass: 225.0 kg
Funding Agency
Unknown (Russia)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 2328
Experiments on Cosmos 2328
Data collections from Cosmos 2328
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 2329
Publications NSSDC ID: 1996-009E Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 2329 was a Russian military spacecraft launched by a 23791 Cyclon-3 rocket from the Plesetsk Cosmodrome along with Cosmos 2328, 2330 and three Gonets spacecraft. It provided military data messaging and photo reconnaissance for the Facts in Brief Russian Federation Ministry of Defense. Launch Date: 1996-02- 18 Launch Vehicle: Tsiklon-3 Launch Site: Plesetsk, Russia Mass: 225.0 kg
Funding Agency
Unknown (Russia)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 2329
Experiments on Cosmos 2329
Data collections from Cosmos 2329
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 2330
Publications NSSDC ID: 1996-009F Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 2330 was a Russian military spacecraft launched by a 23792 Cyclon-3 rocket from the Plesetsk Cosmodrome along with Cosmos 2328, 2329 and three Gonets spacecraft. It provided military data messaging and photo reconnoissance for the Facts in Brief Russian Federation Ministry of Defense. Launch Date: 1996-02- 18 Launch Vehicle: Tsiklon-3 Launch Site: Plesetsk, Russia Mass: 225.0 kg
Funding Agency
Unknown (Russia)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 2330
Experiments on Cosmos 2330
Data collections from Cosmos 2330
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 2331
Publications NSSDC ID: 1996-016A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 2331, a Russian high resolution photo 23818 reconnaissance spacecraft, was launched from the Plesetsk cosmodrome. It returned film in two small SpK capsules during the mission and with the main capsule at completion of the Facts in Brief mission. Launch Date: 1996-03- 14 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 2331
Experiments on Cosmos 2331
Data collections from Cosmos 2331
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 2332
Publications NSSDC ID: 1996-025A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events In 1969 KB Yuzhnoye introduced targets for exercise and test 23853 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: 1996-04- and the Ministry of Defence, completed the draft project. The 24 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 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 2332
Experiments on Cosmos 2332
Data collections from Cosmos 2332
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 2333
Publications NSSDC ID: 1996-051A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 2333 was a signals intelligence satellite of the Tselina 24297 2 series, built by KB Yuzhnoe of the Ukraine. It was launched on a Zenit 2 launch vehicle from the Baikonur cosmodrome and was operated by the Russian Ministry of Defense. Facts in Brief Launch Date: 1996-09- 04 Launch Vehicle: Zenit Launch Site: Tyuratam (Baikonur Cosmodrome), Kazakhstan
Funding Agency
Unknown (Russia)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 2333
Experiments on Cosmos 2333
Data collections from Cosmos 2333
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 2334
Publications NSSDC ID: 1996-052A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 2334 was part of a 6-satellite Russian military 24304 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: 1996-09- and 400 MHz) of the satellite position and orbital data. By 05 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 hours. Funding Agency
Unknown (Russia)
Discipline
Navigation & Global Positioning
Additional Information
Launch/Orbital information for Cosmos 2334
Experiments on Cosmos 2334
Data collections from Cosmos 2334
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 2335
Publications NSSDC ID: 1996-069A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 2335 was a Russian naval reconnaisance satellite 24670 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: 1996-12- radar, etc). 11 Launch Vehicle: Tsiklon-2 Launch Site: Tyuratam (Baikonur Cosmodrome), Kazakhstan Mass: 3150.0 kg
Funding Agency
Unknown (Russia)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 2335 Telecommunications information for Cosmos 2335
Experiments on Cosmos 2335
Data collections from Cosmos 2335
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 2336
Publications NSSDC ID: 1996-071A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 2336 was part of a 6-satellite Russian military 24677 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: 1996-12- and 400 MHz) of the satellite position and orbital data. By 20 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 hours. Funding Agency
Unknown (Russia)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 2336
Experiments on Cosmos 2336
Data collections from Cosmos 2336
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Echostar 2
Publications NSSDC ID: 1996-055A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Echostar 2, a Lockheed Martin satellite, was launched from the 24313 Kourou space center in French Guiana aboard an Ariane 42P rocket. This second in a series of DBS communications satellites, was positioned at 119 deg W and provided video, Facts in Brief audio and data services to the continental US, Southern Launch Date: 1996-09- Canada, and Northern Mexico. 10 Launch Vehicle: Ariane 42P Launch Site: Kourou, French Guiana Mass: 2885.0 kg Nominal Power: 7000.0 W
Funding Agency
Echostar Communications Corporation (United States)
Discipline
Communications
Additional Information
Launch/Orbital information for Echostar 2
Experiments on Echostar 2
Data collections from Echostar 2
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Express 12
Publications NSSDC ID: 1996-058A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Express 12 was a Russian geostationary communications 24435 satellite launched from the Baikonur cosmodrome aboard a Proton rocket. Express will replace the widely used Gorizont spacecraft, and current plans call for deployments at 13 Facts in Brief locations (40 degrees, 53 degrees, 80 degrees, 90 degrees, Launch Date: 1996-09- 96.5 degrees, 99 degrees, 103 degrees, 140 degrees, 145 26 degrees, 205 degrees, 322.5 degrees, 346 degrees, and 349 Launch Vehicle: Proton degrees, all East longitude) just for domestic needs and to Launch Site: Tyuratam support the Intersputnik Telecommunications Association. A (Baikonur Cosmodrome), typical Express payload will include 10 C-band and two Ku- Kazakhstan band transponders. Mass: 2500.0 kg
Funding Agency
Unknown (Russia)
Discipline
Communications
Additional Information
Launch/Orbital information for Express 12
Experiments on Express 12
Data collections from Express 12
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel FAST
Publications NSSDC ID: 1996-049A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The Fast Auroral SnapshoT Explorer (FAST) was successfully Small Explorer/FAST launched on 1996-08-21 into its intended orbit. FAST Explorer 70 investigates the plasma physics of auroral phenomena at extremely high time and spatial resolution using the full SMEX/FAST complement of particle and fields instruments. FAST is the Fast Auroral SnapshoT second spacecraft (SAMPEX was first) in the Small Explorer Explorer (SMEX) program at NASA-GSFC. SMEX was established to 24285 provide rapid (3 year development) low cost ($35M development) mission opportunities (1 per year) to the space science community using a single designated Principal Facts in Brief Investigator (PI). Launch Date: 1996-08- In order to capture the auroral phenomena over small time 21 (microseconds) and spatial scales, FAST utilizes high speed Launch data sampling, a large, fast-loading ("burst") memory, and a Vehicle: Pegasus XL smart, on-board software to trigger on the appearance of Launch various key phenomena. Using a 1 Gb solid-state memory and Site: Vandenberg AFB, a data acquisition rate of 8 Mbs (almost two orders of United States magnitude faster than previous satellites), FAST produces Mass: 187.0 kg high-resolution "snapshots" of auroral arcs and other Nominal Power: 60.0 W interesting auroral events. FAST flies in a highly eccentric, near-polar orbit precessing nominally one degree per day. Funding Agency Scientific investigations are operate in a campaign mode (about 60 days long) as apogee transitions through the NASA-Office of Space northern auroral zone and in less intense survey mode during Science Applications the rest of the orbit. (United States)
The FAST mission uses a unique (not a SAMPEX derivative), lightweight, orbit-normal spinner spacecraft developed by the Discipline SMEX project. The spacecraft has body-mounted solar arrays, Space Physics and is spin-stabilized, rotating at 12 rpm with the spin axis normal to the orbit plane ("cartwheel"). The four FAST experiments are: (1) the Electrostatic Analyzers (ESA) for Additional measuring the electron and ion distribution function, (2) the Information Time-of-flight Energy Angle Mass Spectrograph (TEAMS) for measuring the full 3-dimensional distribution function of the Launch/Orbital major ion species, (3) the Tri-Axial Fluxgate and Search-coil information for FAST Magnetometers for measuring magnetic field data, and (4) the PDMP information for Electric Field/Langmuir Probe Instrument for obtaining electric FAST field data and plasma density and temperature. The FAST Telecommunications electric field instrument stopped providing meaningful data information for FAST around 2002, all other instruments and systems continue to function nominally. Experiments on FAST
Data collections from FAST
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about this spacecraft can be directed to: Dr. Dieter K. Bilitza.
Personnel
Name Role Original Affiliation E-mail Dr. Robert F. Project Scientist NASA Goddard Space [email protected] Pfaff Flight Center Mr. Ronald E. Project Manager NASA Goddard Space Adkins Flight Center Dr. Charles Mission Principal University of California, [email protected] W. Carlson Investigator Berkeley
Other Sources of FAST Data/Information
Five-second Survey Data (CDAWeb) Orbit and conjunctions (SSCWeb) FAST Project page (U. California, Berkeley) Small Explorer Project page
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FSW-2 3
NSSDC ID: 1996-059A Description
FSW-2 3 was a People's Republic of China remote sensing satellite launched by a Long March 3 rocket from Xichuan. Alternate Names
24634
Facts in Brief
Launch Date: 1996-10-20 Launch Vehicle: Long March 3 Launch Site: Jiuquan, Peoples Republic of China Funding Agency
Unknown (Peoples Republic of China)
Discipline
Earth Science
Additional Information
Launch/Orbital information for FSW-2 3
Experiments on FSW-2 3
Data collections from FSW-2 3
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
NSSDC Master Catalog Search
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Personnel Galaxy 9
Publications NSSDC ID: 1996-033A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Galaxy 9 was a geosynchronous spacecraft launched by 23877 Hughes Communications Inc from Cape Canaveral aboard a Delta 2 rocket. It provided voice and vision communications to North America. Facts in Brief Launch Date: 1996-05- 23 Launch Vehicle: Delta II Launch Site: Cape Canaveral, United States
Funding Agency
Pan American Satellite (United States)
Discipline
Communications
Additional Information
Launch/Orbital information for Galaxy 9
Experiments on Galaxy 9
Data collections from Galaxy 9
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel GE 1
Publications NSSDC ID: 1996-054A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events GE 1 was an AMERICOM Corp communications satellite 24315 launched from Cape Canaveral aboard an Atlas 2A rocket. It was placed into a geostationary orbit at 103 deg W. Facts in Brief
Launch Date: 1996-09- 08 Launch Vehicle: Atlas 2A Launch Site: Cape Canaveral, United States
Funding Agency
GE American Communications, Inc. (United States)
Discipline
Communications
Additional Information
Launch/Orbital information for GE 1
Experiments on GE 1
Data collections from GE 1
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Gonets D1-1
Publications NSSDC ID: 1996-009A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Gonets D1-1 was a Russian communications/photo- 23787 reconnoissance spacecraft launched by a Cyclon-3 rocket, along with Gonets D1-2 and D1-3, and 3 Cosmos spacecraft. It will monitor disasters like oil spills, illicit transport of Facts in Brief radioactive cargo, and provide prompt alerts. Launch Date: 1996-02- 18 Launch Vehicle: Tsiklon-3 Launch Site: Plesetsk, Russia Mass: 250.0 kg
Funding Agency
Unknown (Russia)
Discipline
Communications
Additional Information
Launch/Orbital information for Gonets D1-1
Experiments on Gonets D1-1
Data collections from Gonets D1-1
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Gonets D1-2
Publications NSSDC ID: 1996-009B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Gonets D1-2 was a Russian communications/photo- 23788 reconnoissance spacecraft launched by a Cyclon-3 rocket along with Gonets D1-1, D1-3, and three Cosmos spacecraft. It will monitor disasters like oil spills, illicit transport of Facts in Brief radioactive cargo, and provide prompt alerts. Launch Date: 1996-02- 18 Launch Vehicle: Tsiklon-3 Launch Site: Plesetsk, Russia Mass: 250.0 kg
Funding Agency
Unknown (Russia)
Discipline
Communications
Additional Information
Launch/Orbital information for Gonets D1-2
Experiments on Gonets D1-2
Data collections from Gonets D1-2
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Gonets D1-3
Publications NSSDC ID: 1996-009C Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Gonets D1-3 was a Russian communications/photo- 23789 reconnoissance spacecraft launched by a Cyclon-3 rocket along with Gonets D1-1, D1-2, and three Cosmos spacecraft. It will monitor disasters like oil spills, illicit transport of Facts in Brief radioactive cargo, and provide prompt alerts. Launch Date: 1996-02- 18 Launch Vehicle: Tsiklon-3 Launch Site: Plesetsk, Russia Mass: 250.0 kg
Funding Agency
Unknown (Russia)
Discipline
Communications
Additional Information
Launch/Orbital information for Gonets D1-3
Experiments on Gonets D1-3
Data collections from Gonets D1-3
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Gorizont 31
Publications NSSDC ID: 1996-005A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Gorizont 31 was a Russian geosynchronous communications 23775 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 39 deg E. Launch Date: 1996-01- 25 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 31 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. 31
Data collections from Gorizont 31
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Gorizont 32
Publications NSSDC ID: 1996-034A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Gorizont 32 was a Russian geosynchronous communications 23880 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 53.2 deg E. Launch Date: 1996-05- 24 The Gorizont spacecraft possessed an initial mass in excess of Launch 2.1 metric tons and have demonstrated a lifetime of nearly 10 Vehicle: Proton-K years, although a 5-year service life was more common. The Launch Site: Tyuratam 3-axis stabilized satellite was approximately 2 m in diameter (Baikonur Cosmodrome), and 5 m long with two large solar arrays capable of generating Kazakhstan 1.3 kW of electrical power for the first 3 years. Seven separate Mass: 2125.0 kg transmission antennas allowed a variety of reception patterns for both broad and localized terrestrial regions. Funding Agency A typical Gorizont communications payload included six general purpose (TV, audio, facsimile) 6/4 GHz transponders Unknown (Russia) (five 12.5 W and one 60 W), one Luch 14/11 GHz transponder (15 W), and one Volna 1.6/1.5 GHz transponder (20 W). The Discipline Volna transponders were INMARSAT-compatible and were extensively used by the Russian merchant marine fleet via the Communications primary GEO television rebroadcasting system, supporting all five Federation time zones: Zone 1 from 140 deg E, Zone 2 from 90 deg E, Zone 3 from 80 deg E, Zone 4 from 53 deg E, Additional and Zone 5 from 14 deg W. These transmissions were handled Information by Orbita (12-m receiving antenna) and Moskva (2.5-m Launch/Orbital receiving antenna) ground stations in the 6/4 GHz band. The information for Gorizont Moskva Globalnaya system was inaugurated in 1989 using 4- 32 m receiving antennas and serviced by Gorizonts at 96.5 deg E and 11 deg W. Experiments on Gorizont 32
Data collections from Gorizont 32
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel HETE 1
Publications NSSDC ID: 1996-061A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The High Energy Transient Experiment (HETE) was to be an High Energy Transient international mission led by the Massachusetts Institute of Experiment Technology (MIT). Its prime objective was to carry out the first High-Energy Transient multiwavelength study of gamma-ray bursts (GRB) with UV, X- Explorer 1 ray and gamma ray instruments. A unique feature of the mission was its capability to localize bursts with several arc- 24645 second accuracy, in near real-time aboard the spacecraft. The spacecraft hardware and software was developed by Facts in Brief AeroAstro, Inc. (USA). The HETE spacecraft was sun-pointing with four solar panels connected to the bottom of the Launch Date: 1996-11- spacecraft bus. Spacecraft attitude was to be controlled by 04 magnetic torque coils and a momentum wheel. Launch Vehicle: Pegasus XL The HETE satellite was launched with the Argentine satellite Launch Site: Wallops SAC-B. HETE was trapped within the Dual Payload Island, United States Attachment Fitting due to a battery failure in the Pegasus XL Mass: 128.0 kg rocket third stage. Due to its inability to deploy the solar panels, HETE lost power several days after launch Funding Agency
NASA-Office of Space Science (United States)
Discipline
Astronomy
Additional Information
Launch/Orbital information for HETE 1
Experiments on HETE 1
Data collections from HETE 1
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
Personnel
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Name Role Original Affiliation E-mail
Related Information/Data at NSSDC
HETE 2
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Personnel Hot Bird 2
Publications NSSDC ID: 1996-067A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Hot Bird 2 was a geostationary communications spacecraft of Eurobird 9 the European EUTELSAT consortium. With a constellation of 5 24665 satellites, the Hot Bird family at 13 degrees E formed one of the largest broadcasting systems in the world. By fourth quarter 1998, the system was delivering over 320 analogue Facts in Brief and digital television channels, as well as radio and multimedia services, to more than 70 million homes connected to a cable Launch Date: 1996-11- network or equipped for satellite (direct-to-home or 21 community) reception. The Hot Bird satellites provided full Launch Vehicle: Atlas coverage of Europe and also took in parts of Africa and Asia, 2A including the entire Middle East. Launch Site: Cape Canaveral, United States Mass: 2800.0 kg
Funding Agency
European Telecommunications Satellite Consortium (International)
Discipline
Communications
Additional Information
Launch/Orbital information for Hot Bird 2
Experiments on Hot Bird 2
Data collections from Hot Bird 2
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel IAE
Publications NSSDC ID: 1996-032C Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events IAE (Inflatable Antenna Experiment) was a NASA inflatable Inflatable Antenna mylar antenna that was released from STS 77. It expanded to Experiment a diameter of 16 meters and retained its shape with the help of 23872 3 inflated 30-meter struts. It re-entered the atmosphere after several orbits. Facts in Brief
Launch Date: 1996-05- 20 Launch Vehicle: Shuttle Launch Site: Cape Canaveral, United States
Funding Agency
National Aeronautics and Space Administration (United States)
Discipline
Technology Applications
Additional Information
Launch/Orbital information for IAE
Experiments on IAE
Data collections from IAE
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Inmarsat 3-F1
Publications NSSDC ID: 1996-020A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Inmarsat 3-F1 was the first in a series of five third generation 23839 satellites. Launched from Cape Canaveral aboard an Atlas 2A rocket, it is currently in service over the Indian Ocean. It used the latest spot-beam technology and higher power to supply Facts in Brief voice and data communications services worldwide to mobile Launch Date: 1996-04- terminals as small as pocket-size messaging units on ships, 03 aricraft and vehicles. Launch Vehicle: Atlas 2A INMARSAT-3 development was carried out by prime contractor Launch Site: Cape Lockheed Martin and payload provider Matra Marconi Space. Canaveral, United States With an end-of-life power rating of 2,800 W, each INMARSAT- Mass: 2068.0 kg 3 could deliver an IERP of up to 48dBW - eight times the INMARSAT-2 level - in L-band. It could dynamically reallocate both RF power and bandwidth among a global beam and five Funding Agency spot beams, allowing greater reuse of the available spectrums. Simultaneous voice channel capacity was up to eight times the Inmarsat (International) INMARSAT-2 figure. Discipline Each INMARSAT-3 also carried a navigation transponder designed to enhance the accuracy, availability and integrity of Communications the GPS and Glonass satellite navigation systems.
Additional Information
Launch/Orbital information for Inmarsat 3-F1
Experiments on Inmarsat 3-F1
Data collections from Inmarsat 3-F1
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Personnel Inmarsat 3-F2
Publications NSSDC ID: 1996-053A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Inmarsat 3-F2 was the second in a series of five third 24307 generation satellites. Launched from the Baikonur cosmodrome aboard a Proton rocket, it is currently in service over the Atlantic Ocean. It used the latest spot-beam technology and Facts in Brief higher power to supply voice and data communications Launch Date: 1996-09- services worldwide to mobile terminals as small as pocket-size 06 messaging units on ships, aricraft and vehicles. Launch Vehicle: Proton Launch Site: Tyuratam INMARSAT-3 development was carried out by prime contractor (Baikonur Cosmodrome), Lockheed Martin and payload provider Matra Marconi Space. Kazakhstan With an end-of-life power rating of 2,800 W, each INMARSAT- 3 could deliver an IERP of up to 48dBW - eight times the INMARSAT-2 level - in L-band. It could dynamically reallocate Funding Agency both RF power and bandwidth among a global beam and five spot beams, allowing greater reuse of the available spectrums. International Simultaneous voice channel capacity was up to eight times the Telecommunications INMARSAT-2 figure. Satellite Corporation (International) Each INMARSAT-3 also carried a navigation transponder designed to enhance the accuracy, availability and integrity of Discipline the GPS and Glonass satellite navigation systems. Communications
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Launch/Orbital information for Inmarsat 3-F2
Experiments on Inmarsat 3-F2
Data collections from Inmarsat 3-F2
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Personnel Inmarsat 3-F3
Publications NSSDC ID: 1996-070A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Inmarsat 3-F3 was the third in a series of five third generation 24674 satellites. Launched from Cape Canaveral aboard an Atlas 2 rocket, it is currently in service over the Pacific Ocean. It used the latest spot-beam technology and higher power to supply Facts in Brief voice and data communications services worldwide to mobile Launch Date: 1996-12- terminals as small as pocket-size messaging units on ships, 17 aircraft and vehicles. Launch Vehicle: Atlas Launch Site: Cape INMARSAT-3 development was carried out by prime contractor Canaveral, United States Lockheed Martin and payload provider Matra Marconi Space. With an end-of-life power rating of 2,800 W, each INMARSAT- 3 could deliver an IERP of up to 48dBW - eight times the Funding Agency INMARSAT-2 level - in L-band. It could dynamically reallocate both RF power and bandwidth among a global beam and five International spot beams, allowing greater reuse of the available spectrums. Telecommunications Simultaneous voice channel capacity was up to eight times the Satellite Corporation INMARSAT-2 figure. (International)
Each INMARSAT-3 also carried a navigation transponder Discipline designed to enhance the accuracy, availability and integrity of the GPS and Glonass satellite navigation systems. Communications
Additional Information
Launch/Orbital information for Inmarsat 3-F3
Experiments on Inmarsat 3-F3
Data collections from Inmarsat 3-F3
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Personnel INTELSAT 7 F-7
Publications NSSDC ID: 1996-015A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Intelsat 7-F7 was a geostationary communications spacecraft 23816 for the Intelsat consortium that was launched by an Ariane 44LP rocket from the Kourou Space Center in French Guiana. The 4,175 kg spacecraft carried 26 C-band and 14 K-band Facts in Brief transponders to provide Europe and the Americas with 3 Launch Date: 1996-03- television channels and 22,500 telephone circuits after parking 14 over the eastern coast of Brazil. Launch Vehicle: Ariane 44LP Launch Site: Kourou, French Guiana Mass: 4175.0 kg
Funding Agency
International Telecommunications Satellite Corporation (International)
Discipline
Communications
Additional Information
Launch/Orbital information for INTELSAT 7 F-7
Experiments on INTELSAT 7 F-7
Data collections from INTELSAT 7 F-7
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Personnel INTELSAT 709
Publications NSSDC ID: 1996-035A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Intelsat 709 was a geosynchronous communications satellite of 23915 the INTELSAT consortium. It was launched by an Ariane 44P rocket from the Kourou site in French Guiana and carried 36 Ku- and C-band transponders to serve the Atlantic ocean Facts in Brief region. Launch Date: 1996-06- 15 Launch Vehicle: Ariane 44P Launch Site: Kourou, French Guiana
Funding Agency
International Telecommunications Satellite Corporation (International)
Discipline
Communications
Additional Information
Launch/Orbital information for INTELSAT 709
Experiments on INTELSAT 709
Data collections from INTELSAT 709
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Personnel Interball Auroral Probe
Publications NSSDC ID: 1996-050C Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The Interball Project is a multi-national effort that consists of Auroral Probe four spacecraft: two main spacecraft of the Prognoz series, Prognoz 2M made in Russia, each with a small subsatellite made in Czechoslovakia. The main objective is to study the physical Interball 2 mechanisms responsible for the transmission of solar wind Prognoz 12 energy to the magnetosphere, its storage there, and 24293 subsequent dissipation in the tail and auroral regions of the magnetosphere, ionosphere, and atmosphere during magnetospheric substorms. A ground-based support group will Facts in Brief provide coordinated and simultaneous ground-based data of many types, including observations from auroral and polar cap Launch Date: 1996-08- regions. Interball is an IACG-related mission. Key physical 29 parameters will be generated, and will be available for Launch exchange with other projects. Campaigns for intercomparison Vehicle: Molniya-M with the Wind and Geotail spacecraft are expected. One pair Launch Site: Plesetsk, of spacecraft, Tail Probe and its subsatellite S2-X (X for the Russia first letter of the Russian word for ``Tail''), will be launched into Mass: 1250.0 kg the magnetospheric tail. The second pair, Auroral Probe and S2-A (A for ``Auroral''), will have an orbit that crosses the Funding Agency auroral oval to observe the acceleration of auroral particles and the flow of electric currents that connect the Russian Space Agency magnetospheric tail with the conducting ionosphere. To study (Russia) the equilibrium tail structure, during about half of each year the Tail Probe pair will cross the main parts of the magnetotail every four days. The Auroral Probe pair will support the Tail Discipline Probe pair with auroral region measurements. Each main Space Physics spacecraft has more than twenty scientific instruments. The spacecraft is cylindrical, with spin axis toward the sun (within 10 degrees), and with spin period of ~120 s. The electric and Additional magnetic field sensors are on booms connected to the ends of Information the solar panels. The subsatellites are small, each with about ten scientific instruments. The spin axis will be directed within Launch/Orbital 10 degrees of the sun, with a spin period of ~120 s, as with the information for Interball main spacecraft. The subsatellites also carry gas-jet thrusters Auroral Probe for limited control of the orbit. Separation distance will range from hundreds of kilometers to several tens of thousands of Experiments on Interball kilometers for the Tail Probe pair. Separation distance will Auroral Probe range from hundreds of meters to hundreds of kilometers for the Auroral Probe pair. The Tail Probe has two telemetry Data collections from systems, at up to 32 Kbps in real-time, with a memory mode Interball Auroral Probe capacity of 30 Mb in the RTK telemetry system and 120 Mb in the SSNI system. The Auroral Probe has similar capability plus the additional real-time-only STO system, capable of 40 Kbps. Questions or comments Each subsatellite has only the STO real-time telemetry system. about this spacecraft can For S2-X the rate can be varied from 2--40 kbps. The Tail be directed to: Dr. H. Kent Probe has an adapting alert mode while in the memory mode, Hills. allowing time resolutions that are the same as in the real-time mode. The aim is to have the highest time resolution available at the thin borders of magnetospheric regions or the sharp Interball http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-050C[08/06/2011 23:00:56] NASA - NSSDC - Spacecraft - Details
borders of some features. In the alert mode (triggered by an Data/Information at on-board computer monitoring plasma and field parameters), NSSDC the bit rate is increased for plasma, field, and wave measurements. The duration of these alert periods is about 10 Interball Tail Probe minutes, and there can be 5--6 of them during one orbit. Interball S2-X Interball Auroral Probe Interball S2-A
Other Sources of Interball Data/Information
Interball project (IKI) Interball data archive (IKI)
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Personnel IRS-P3
Publications NSSDC ID: 1996-017A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events IRS-P3 is an Indian Remote Sensing spacecraft launched by a Indian Remote Sensing 4-stage PSLV-D3 developmental rocket from the Sriharikota Satellite P3 launch station on the southeast coast of India. The 930 kg 23827 spacecraft carried two remote sensing experiments and an astronomical x-ray detector. WIFS (WIde Field Sensor) was a scanner with visible light and infrared photometers to study Facts in Brief crop conditions, geology, and snow cover. The German Space Agency's (DLR's) modular opto-electronic scanner will monitor Launch Date: 1996-03- oceanic chlorophyll, sediment transport and ocean dynamics. 20 Data will be downlinked at 3 Indian stations, and stations in Launch Vehicle: PSLV Russia, Germany, and Mauritius. Launch Site: Sriharikota, India Mass: 930.0 kg
Funding Agency
Indian Space Research Organization (India)
Disciplines
Astronomy Earth Science
Additional Information
Launch/Orbital information for IRS-P3
Experiments on IRS-P3
Data collections from IRS- P3
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Italsat 2
Publications NSSDC ID: 1996-044A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Italy's second national communications satellite, ITALSAT 2 24208 was dual launched aboard an Ariane 44L booster from Kourou, French Guiana. Placed in geosynchronous orbit above 13.2 deg. e, the satellite served as a spaceborne telephone Facts in Brief switchboard, redirecting up to 12,000 calls at once. ITALSAT Launch Date: 1996-08- was experimental in nature, a pre-operational component of a 08 proposed digital satellite network for Italy. Built by Selenia Launch Vehicle: Ariane Spazio for Agenzia Spaziale Italiana (the Italian Space 44L Agency), ITALSAT 2 was box-shaped, measuring 2.72 by 2.22 Launch Site: Kourou, by 3.48 m. It was 6.1 m tall with its two 2-m reflector antennas French Guiana deployed. Solar arrays spanned 21 m and provided 1,600 W Mass: 2000.0 kg of power. Its communications package housed six 20/30 GHz multibeam transponders, three 20/30 GHz global beam transponders and a propagation experiment operating at 40/50 Funding Agency GHz. The multibeam system, using advanced time division multiple access (TDMA) techniques, was expected to undergo Unknown (Italy) two years of testing; the global beam system was considered operational from the start and was used to test new services. Discipline ITALSAT 2 had a 5-year design life. Communications
Additional Information
Launch/Orbital information for Italsat 2
Experiments on Italsat 2
Data collections from Italsat 2
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel JAS 2
Publications NSSDC ID: 1996-046B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events JAS-2 was a Japanese communications satellite launched from OSCAR 29 the Tanegashima Space Center for NASDA. It succeeded 24278 JAS-1b which was launched in February of 1990.
Facts in Brief
Launch Date: 1996-08- 16 Launch Vehicle: H-2 Launch Site: Tanegashima, Japan Mass: 50.0 kg
Funding Agency
Unknown (Japan)
Discipline
Communications
Additional Information
Launch/Orbital information for JAS 2
Experiments on JAS 2
Data collections from JAS 2
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel KH 12-3
Publications NSSDC ID: 1996-072A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events KH 12-3 was launched from Vandenberg AFB aboard a Titan 4 USA 129 rocket for the US Department of Defense. It was an electro- 24680 optical reconnaisance satellite that succeeded the KH-11 series. It was heavier and believed to include a signals intelligence payload, it had wider spectral band sensitivity, Facts in Brief perhaps "real time" television capability, and other improvements compared to the KH-11 satellites. Data were Launch Date: 1996-12- transmitted via the SDS military relay satellites. 20 Launch Vehicle: Titan IV Launch Site: Vandenberg AFB, United States Mass: 19600.0 kg
Funding Agency
Department of Defense- Department of the Air Force (United States)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for KH 12-3
Experiments on KH 12-3
Data collections from KH 12-3
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Koreasat 2
Publications NSSDC ID: 1996-003A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Koreasat 2, also known as Mugunghwa 2, was a South Korean Mugunghwa 2 geostationary communications spacecraft launched from Cape 23768 Canaveral by a Delta 2 rocket. It will be parked at 116 E longitude over Borneo island to provide broadcasting and telecommunications to South Korea beginning in July 1996. Facts in Brief
Launch Date: 1996-01- 14 Launch Vehicle: Delta II Launch Site: Cape Canaveral, United States
Funding Agency
Unknown (South Korea)
Discipline
Communications
Additional Information
Launch/Orbital information for Koreasat 2
Experiments on Koreasat 2
Data collections from Koreasat 2
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Magion 5
Publications NSSDC ID: 1996-050B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The Interball Project is a multi-national effort that consists of Auroral Subsatellite S2-A four spacecraft: two main spacecraft of the Prognoz series, Interball S2-A made in Russia, each with a small subsatellite made in Czechoslovakia. The main objective is to study the physical S2-A mechanisms responsible for the transmission of solar wind 24292 energy to the magnetosphere, its storage there, and subsequent dissipation in the tail and auroral regions of the magnetosphere, ionosphere, and atmosphere during Facts in Brief magnetospheric substorms. A ground-based support group will Launch Date: 1996-08- provide coordinated and simultaneous ground-based data of 29 many types, including observations from auroral and polar cap Launch regions. Interball is an IACG-related mission. Key physical Vehicle: Molniya-M parameters will be generated, and will be available for Launch Site: Plesetsk, exchange with other projects. Campaigns for intercomparison Russia with the Wind and Geotail spacecraft are expected. One pair Mass: 58.0 kg of spacecraft, Tail Probe and its subsatellite S2-X (X for the first letter of the Russian word for ``Tail''), will be launched into the magnetospheric tail. The second pair, Auroral Probe and Funding Agency S2-A (A for ``Auroral''), will have an orbit that crosses the auroral oval to observe the acceleration of auroral particles Unknown (Czech and the flow of electric currents that connect the Republic) magnetospheric tail with the conducting ionosphere. To study the equilibrium tail structure, during about half of each year the Discipline Tail Probe pair will cross the main parts of the magnetotail every four days. The Tail Probe, with approximately 30 earth Space Physics radii apogee, will cross the noon-midnight plane on December 1, so the measurements in the magnetotail will cover the period from October 1995 to February 1996. The Auroral Additional Probe pair will support the Tail Probe pair with auroral region Information measurements. Launch/Orbital information for Magion 5 Each main spacecraft has more than twenty scientific instruments. The spacecraft is cylindrical, with spin axis toward Experiments on Magion 5 the sun (within 10 degrees), and with spin period of ~120 s. The electric and magnetic field sensors are on booms Data collections from connected to the ends of the solar panels. Magion 5 The subsatellites are small, each with about ten scientific instruments. The spin axis will be directed within 10 degrees of the sun, with a spin period of ~120 s, as with the main Questions or comments spacecraft. The subsatellites also carry gas-jet thrusters for about this spacecraft can limited control of the orbit. Separation distance will range from be directed to: Dr. H. Kent hundreds of kilometers to several tens of thousands of Hills. kilometers for the Tail Probe pair. Separation distance will range from hundreds of meters to hundreds of kilometers for the Auroral Probe pair. The Tail Probe has two telemetry Interball systems, at up to 32 Kbps in real-time, with a memory mode Data/Information at capacity of 30 Mb in the RTK telemetry system and 120 Mb in NSSDC the SSNI system. The Auroral Probe has similar capability plus http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-050B[08/06/2011 23:03:56] NASA - NSSDC - Spacecraft - Details
Interball Tail Probe the additional real-time-only STO system, capable of 40 Kbps. Interball S2-X Each subsatellite has only the STO real-time telemetry system. Interball Auroral Probe For S2-X the rate can be varied from 2--40 kbps. Interball S2-A The Tail Probe has an adapting alert mode while in the memory mode, allowing time resolutions that are the same as Other Sources of in the real-time mode. The aim is to have the highest time Interball resolution available at the thin borders of magnetospheric Data/Information regions or the sharp borders of some features. In the alert mode (triggered by an on-board computer monitoring plasma Interball project (IKI) and field parameters), the bit rate is increased for plasma, Interball data archive (IKI) field, and wave measurements. The duration of these alert periods is about 10 minutes, and there can be 5--6 of them during one orbit.
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Personnel Mars 96 Orbiter
Publications NSSDC ID: 1996-064A Maps Description Facts in Brief New/Updated Data
Lunar/Planetary Events The Mars 96 spacecraft was launched into Earth orbit, but Launch Date: 1996-11- failed to achieve insertion into Mars cruise trajectory and re- 16 entered the Earth's atmosphere at about 00:45 to 01:30 UT on Launch 17 November 1996 and crashed within a presumed 320 km by Vehicle: Proton-K 80 km area which includes parts of the Pacific Ocean, Chile, Launch Site: Tyuratam and Bolivia. The cause of the crash is not known. (Baikonur Cosmodrome), Kazakhstan Mars 96 Orbiter The Russian Mars 96 mission was designed to send an orbiter, Mass: 3159.0 kg two small autonomous stations, and two surface penetrators to Mars to investigate the evolution and contemporary physics of the planet by studying the physical and chemical processes Funding Agency which took place in the past and which currently take place. Russian Space Agency The Mars 96 Orbiter was a 3-axis sun/star stabilized craft (Russia) based on the Phobos design with two platforms for pointing and stabilizing instruments. The propulsion units were mounted on the bottom and two large solar panels extended out from Discipline opposite sides of the craft. The two penetrators were mounted on the bottom by the propulsion system, the two small stations Planetary Science were connected on top of the spacecraft, and a dish antenna extended off one of the sides perpendicular to the solar Additional panels. The Mars 96 spacecraft had a launch mass (including Information propellant) of 6180 kg. Launch/Orbital Mars 96 was scheduled to arrive at Mars on 12 September information for Mars 96 1997, about 10 months after launch, on a direct trajectory. Orbiter About 4 to 5 days before arrival the small surface stations PDMP information for would have been released. The orbiter was to go into an Mars 96 Orbiter elliptical 3-day transfer orbit about Mars, and the two penetrators to descend to the surface during the first month of Telecommunications orbit. The final orbit would have been a 14.77 hour elliptical information for Mars 96 orbit with a periapsis of 300 km. Orbiter
The Mars 96 Orbiter carried 12 instruments to study the Experiments on Mars 96 surface and atmosphere of Mars, 7 instruments to study Orbiter plasma, fields, and particles, and 3 instruments for astrophysical studies. There were also radio science, a Data collections from Mars navigation TV camera, and a radiation and dosimetry control 96 Orbiter complex. The instruments were located directly on the sides of the craft, on one of the two platforms attached to the sides of the craft, or on the edges of the solar panels. Questions or comments about this spacecraft can be directed to: Dr. David R. Williams.
Personnel
Name Role Original Affiliation E-mail http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-064A[08/06/2011 23:04:20] NASA - NSSDC - Spacecraft - Details
Dr. Albert A. Galeev Program Russian Academy of [email protected] Scientist Sciences Dr. Alexander V. Project Russian Academy of [email protected] Zakharov Scientist Sciences
Selected References
Galeev, A. A., Russian program of planetary missions, Acta Astronautica, 39, No. 1-4, 9-14, 1996.
Other Mars 96 Information from NSSDC
Mars 96 Failure - Timeline from launch to re-entry Mars 96 Surface Station Mars 96 Penetrator
Other Sources of Mars 96 Information
Mars 96 Project (IKI)
Information about Mars
Mars Page
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Personnel Mars 96 Penetrator
Publications NSSDC ID: MARS96D Maps Description Facts in Brief New/Updated Data
Lunar/Planetary Events The Mars 96 spacecraft was launched into Earth orbit, but Launch Date: 1996-11- failed to achieve insertion into Mars cruise trajectory and re- 16 entered the Earth's atmosphere at about 00:45 to 01:30 UT on Launch Vehicle: Proton 17 November 1996 and crashed within a presumed 320 km by Launch Site: Tyuratam 80 km area which includes parts of the Pacific Ocean, Chile, (Baikonur Cosmodrome), and Bolivia. The cause of the crash is not known. Russia Mass: 45.0 kg The Russian Mars 96 mission was designed to send an orbiter, two small autonomous stations, and two surface penetrators to Mars to investigate the evolution and contemporary physics of Funding Agency the planet by studying the physical and chemical processes Russian Space Agency which took place in the past and which currently take place. (Russia) Mars 96 was scheduled to arrive at Mars on 12 September 1997, about 10 months after launch, on a direct trajectory. Discipline The two Mars 96 Penetrators were mounted on the bottom of the orbiter near the propulsion system. The penetrators were Planetary Science long thin cylinders, pointed at the bottom, or forebody, and with a widened, funnel-shaped top. Instruments were contained Additional inside throughout the length of the cylinder. The scientific Information objectives of the penetrator experiments were to obtain images Mars 96 Penetrator of the surface, study martian meteorology, examine the Launch/Orbital physical, chemical, magnetic, and mechanical properties of the information for Mars 96 martian regolith, including its water content, collect data on the Penetrator magnetic field, and record seismic activity. PDMP information for Mars 96 Penetrator After orbit insertion, adjustment to 300 km periapsis, and 7 to 28 days of orbital maneuvers, the orbiter would be properly Telecommunications oriented and the first penetrator would be spun about its long information for Mars 96 axis and released. When the penetrator had moved away from Penetrator the orbiter, its solid rocket motor was to ignite and put it into an atmospheric entry trajectory. Entry would occur 21 to 22 hours Experiments on Mars 96 later. The penetrator was to enter the atmosphere at about 4.9 Penetrator km/sec at an angle 10-14 degrees. The probe would first be slowed aerodynamically, followed by inflation of a braking Data collections from Mars device. The penetrator was to strike the surface at 96 Penetrator approximately 80 m/s. The forebody would separate on impact and can penetrate 5 to 6 meters into the ground, attached by wires to the aftbody, the top of the aftbody remaining above the Questions or comments surface. The plan called for the first penetrator to land near the about this spacecraft can site of one of the surface stations, and the second to land at be directed to: Dr. David R. least 90 degrees away. Both pentrators could have been Williams. released on the same orbit.
The penetrator was equipped with instruments in both the forebody and aftbody. The forebody held a seismometer, accelerometer, thermoprobe, neutron detector, and an alpha- proton-X-ray spectrometer. The aftbody contained a gamma- ray spectrometer and thermoprobe within the part of the http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=MARS96D[08/06/2011 23:04:42] NASA - NSSDC - Spacecraft - Details
cylinder underground, and meteorology sensors, a magnetometer, a television camera, and transmitter exposed at the top. The experiments were to begin after landing. Data was to be transmitted to the orbiter and then relayed to Earth. The penetrators have an expected lifetime of 1 year.
Personnel
Name Role Original Affiliation E-mail Dr. Albert A. Galeev Program Russian Academy of [email protected] Scientist Sciences Dr. Alexander V. Project Russian Academy of [email protected] Zakharov Scientist Sciences
Other Mars 96 Information from NSSDC
Mars 96 Failure - Timeline from launch to re-entry Mars 96 Orbiter Mars 96 Surface Station
Other Sources of Mars 96 Information
Mars 96 Project (IKI)
Information about Mars
Mars Page
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Personnel Mars 96 Penetrator
Publications NSSDC ID: MARS96E Maps Description Facts in Brief New/Updated Data
Lunar/Planetary Events The Mars 96 spacecraft was launched into Earth orbit, but Launch Date: 1996-11- failed to achieve insertion into Mars cruise trajectory and re- 16 entered the Earth's atmosphere at about 00:45 to 01:30 UT on Launch Vehicle: Proton 17 November 1996 and crashed within a presumed 320 km by Launch Site: Tyuratam 80 km area which includes parts of the Pacific Ocean, Chile, (Baikonur Cosmodrome), and Bolivia. The cause of the crash is not known. Russia Mass: 45.0 kg The Russian Mars 96 mission was designed to send an orbiter, two small autonomous stations, and two surface penetrators to Mars to investigate the evolution and contemporary physics of Funding Agency the planet by studying the physical and chemical processes Russian Space Agency which took place in the past and which currently take place. (Russia) Mars 96 was scheduled to arrive at Mars on 12 September 1997, about 10 months after launch, on a direct trajectory. Discipline The two Mars 96 Penetrators were mounted on the bottom of the orbiter near the propulsion system. The penetrators were Planetary Science long thin cylinders, pointed at the bottom, or forebody, and with a widened, funnel-shaped top. Instruments were contained Additional inside throughout the length of the cylinder. The scientific Information objectives of the penetrator experiments were to obtain images Mars 96 Penetrator of the surface, study martian meteorology, examine the Launch/Orbital physical, chemical, magnetic, and mechanical properties of the information for Mars 96 martian regolith, including its water content, collect data on the Penetrator magnetic field, and record seismic activity. PDMP information for Mars 96 Penetrator After orbit insertion, adjustment to 300 km periapsis, and 7 to 28 days of orbital maneuvers, the orbiter would be properly Telecommunications oriented and the first penetrator would be spun about its long information for Mars 96 axis and released. When the penetrator had moved away from Penetrator the orbiter, its solid rocket motor was to ignite and put it into an atmospheric entry trajectory. Entry would occur 21 to 22 hours Experiments on Mars 96 later. The penetrator was to enter the atmosphere at about 4.9 Penetrator km/sec at an angle 10-14 degrees. The probe would first be slowed aerodynamically, followed by inflation of a braking Data collections from Mars device. The penetrator was to strike the surface at 96 Penetrator approximately 80 m/s. The forebody would separate on impact and can penetrate 5 to 6 meters into the ground, attached by wires to the aftbody, the top of the aftbody remaining above the Questions or comments surface. The plan called for the first penetrator to land near the about this spacecraft can site of one of the surface stations, and the second to land at be directed to: Dr. David R. least 90 degrees away. Both penetrators could have been Williams. released on the same orbit.
The penetrator was equipped with instruments in both the forebody and aftbody. The forebody held a seismometer, accelerometer, thermoprobe, neutron detector, and an alpha- proton-X-ray spectrometer. The aftbody contained a gamma- ray spectrometer and thermoprobe within the part of the http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=MARS96E[08/06/2011 23:05:06] NASA - NSSDC - Spacecraft - Details
cylinder underground, and meteorology sensors, a magnetometer, a television camera, and transmitter exposed at the top. The experiments were to begin after landing. Data was to be transmitted to the orbiter and then relayed to Earth. The penetrators have an expected lifetime of 1 year.
Personnel
Name Role Original Affiliation E-mail Dr. Albert A. Galeev Program Russian Academy of [email protected] Scientist Sciences Dr. Alexander V. Project Russian Academy of [email protected] Zakharov Scientist Sciences
Other Mars 96 Information from NSSDC
Mars 96 Failure - Timeline from launch to re-entry Mars 96 Orbiter Mars 96 Surface Station
Other Sources of Mars 96 Information
Mars 96 Project (IKI)
Information about Mars
Mars Page
+ 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 Mars 96 Surface Station
Publications NSSDC ID: MARS96B Maps Description Facts in Brief New/Updated Data
Lunar/Planetary Events The Mars 96 spacecraft was launched into Earth orbit, but Launch Date: 1996-11- failed to achieve insertion into Mars cruise trajectory and re- 16 entered the Earth's atmosphere at about 00:45 to 01:30 UT on Launch Vehicle: Proton 17 November 1996 and crashed within a presumed 320 km by Launch Site: Tyuratam 80 km area which includes parts of the Pacific Ocean, Chile, (Baikonur Cosmodrome), and Bolivia. The cause of the crash is not known. Russia Mass: 8.0 kg The Russian Mars 96 mission was designed to send an orbiter, two small autonomous stations, and two surface penetrators to Mars to investigate the evolution and contemporary physics of Funding Agency the planet by studying the physical and chemical processes Mars 96 Surface Station Russian Space Agency which took place in the past and which currently take place. (Russia) Mars 96 was scheduled to arrive at Mars on 12 September 1997, about 10 months after launch, on a direct trajectory. About 4 to 5 days before arrival the small surface stations Discipline were to be released. Planetary Science The small station was contained inside a cylindrical aeroshell approximately 1 meter in diameter and 1 meter high with a Additional mass of 25.5 kg for a total mass (station plus aeroshell) of 33.5 Information kg. Each station was to enter the atmosphere at a velocity of less than 5.75 km/s at an entry angle between 10.5 and 20.5 Launch/Orbital degrees and an entry azimuth between 115 and 145 degrees. information for Mars 96 The aeroshells were to be shed before landing and parachutes Surface Station will be used to slow the descent. On landing the station PDMP information for covering would open into four triangular petals which extending Mars 96 Surface Station approximately 30 cm from the central base. Experiments on Mars 96 The primary landing sites were 41.31 N, 153.77 W and 32.48 Surface Station N, 169.32 W, with a backup site at 3.65 N, 193 W. Landing dispersion was to be 10 degrees along track and 2 degrees Data collections from Mars across track. All sites are in the Arcadia Planitia region in the 96 Surface Station northern hemisphere of Mars.
The station was to study the vertical structure of the atmosphere and take images during its descent. On the Questions or comments surface it would have a meteorology station mounted about this spacecraft can approximately 1 meter above the base of the station to study be directed to: Dr. David R. diurnal, seasonal, and annual variations in the atmosphere. A Williams. magnetometer would have extended from one of the petals to measure the planet's surface magnetic field and its variation with time. A seismometer would collect data on the seismic environment. An Alpha-Proton-X-Ray spectrometer would extend from one petal and measure the elemental composition of the surface. An oxidant sensor, extending from a third petal, was to measure oxidant abundances. A panoramic camera is mounted on a mast on the base of the station. The stations were planned to have an active lifetime of about 700 days (approximately 1 martian year) on the surface. http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=MARS96B[08/06/2011 23:05:34] NASA - NSSDC - Spacecraft - Details
The station was to be powered by two radio-isotope thermogenerators (RTG's), a battery, and a secondary power source. The surface station was equipped with a transmitter to radio data back to the orbiter for return to Earth, and a receiver to download commands from Earth via the orbiter.
Personnel
Name Role Original Affiliation E-mail Dr. Albert A. Galeev Program Russian Academy of [email protected] Scientist Sciences Dr. Alexander V. Project Russian Academy of [email protected] Zakharov Scientist Sciences
Other Mars 96 Information from NSSDC
Mars 96 Failure - Timeline from launch to re-entry Mars 96 Orbiter Mars 96 Penetrator
Other Sources of Mars 96 Information
Mars 96 Project (IKI)
Information about Mars
Mars Page
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Personnel Mars 96 Surface Station
Publications NSSDC ID: MARS96C Maps Description Facts in Brief New/Updated Data
Lunar/Planetary Events The Mars 96 spacecraft was launched into Earth orbit, but Launch Date: 1996-11- failed to achieve insertion into Mars cruise trajectory and re- 16 entered the Earth's atmosphere at about 00:45 to 01:30 UT on Launch Vehicle: Proton 17 November 1996 and crashed within a presumed 320 km by Launch Site: Tyuratam 80 km area which includes parts of the Pacific Ocean, Chile, (Baikonur Cosmodrome), and Bolivia. The cause of the crash is not known. Russia Mass: 8.0 kg The Russian Mars 96 mission was designed to send an orbiter, two small autonomous stations, and two surface penetrators to Mars to investigate the evolution and contemporary physics of Funding Agency the planet by studying the physical and chemical processes Mars 96 Surface Station Russian Space Agency which took place in the past and which currently take place. (Russia) Mars 96 was scheduled to arrive at Mars on 12 September 1997, about 10 months after launch, on a direct trajectory. About 4 to 5 days before arrival the small surface stations Discipline were to be released. Planetary Science The small station was contained inside a cylindrical aeroshell approximately 1 meter in diameter and 1 meter high with a Additional mass of 25.5 kg for a total mass (station plus aeroshell) of 33.5 Information kg. Each station was to enter the atmosphere at a velocity of less than 5.75 km/s at an entry angle between 10.5 and 20.5 Launch/Orbital degrees and an entry azimuth between 115 and 145 degrees. information for Mars 96 The aeroshells were to be shed before landing and parachutes Surface Station will be used to slow the descent. On landing the station PDMP information for covering would open into four triangular petals which extending Mars 96 Surface Station approximately 30 cm from the central base. Telecommunications The primary landing sites were 41.31 N, 153.77 W and 32.48 information for Mars 96 N, 169.32 W, with a backup site at 3.65 N, 193 W. Landing Surface Station dispersion was to be 10 degrees along track and 2 degrees across track. All sites are in the Arcadia Planitia region in the Experiments on Mars 96 northern hemisphere of Mars. Surface Station
The station was to study the vertical structure of the Data collections from Mars atmosphere and take images during its descent. On the 96 Surface Station surface it would have a meteorology station mounted approximately 1 meter above the base of the station to study diurnal, seasonal, and annual variations in the atmosphere. A Questions or comments magnetometer would have extended from one of the petals to about this spacecraft can measure the planet's surface magnetic field and its variation be directed to: Dr. David R. with time. A seismometer would collect data on the seismic Williams. environment. An Alpha-Proton-X-Ray spectrometer would extend from one petal and measure the elemental composition of the surface. An oxidant sensor, extending from a third petal, was to measure oxidant abundances. A panoramic camera is mounted on a mast on the base of the station. The stations were planned to have an active lifetime of about 700 days (approximately 1 martian year) on the surface. http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=MARS96C[08/06/2011 23:06:22] NASA - NSSDC - Spacecraft - Details
The station was to be powered by two radio-isotope thermogenerators (RTG's), a battery, and a secondary power source. The surface station was equipped with a transmitter to radio data back to the orbiter for return to Earth, and a receiver to download commands from Earth via the orbiter.
Personnel
Name Role Original Affiliation E-mail Dr. Albert A. Galeev Program Russian Academy of [email protected] Scientist Sciences Dr. Alexander V. Project Russian Academy of [email protected] Zakharov Scientist Sciences
Other Mars 96 Information from NSSDC
Mars 96 Failure - Timeline from launch to re-entry Mars 96 Orbiter Mars 96 Penetrator
Other Sources of Mars 96 Information
Mars 96 Project (IKI)
Information about Mars
Mars Page
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Personnel Mars Global Surveyor
Publications NSSDC ID: 1996-062A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The Mars Global Surveyor (MGS) orbited Mars over a seven MGS year period and collected data on the surface morphology, 24648 topography, composition, gravity, atmospheric dynamics, and magnetic field. This data will be used to investigate the surface processes, geology, distribution of material, internal properties, Facts in Brief evolution of the magnetic field, and the weather and climate of Mars. Launch Date: 1996-11- 07 Spacecraft and Subsystems Launch Vehicle: Delta The spacecraft itself is a rectangular box approximately 1.17 x II 7925 1.17 x 1.7 meters in size, made up of two parts, the equipment Launch Site: Cape module and the propulsion module. All instruments except the Canaveral, United States magnetometer are stored on the nadir equipment deck, on one Mass: 1030.5 kg of the 1.17 x 1.17 meter surfaces. This is the top of the Nominal equipment module, which is 0.735 m high. The main thruster Power: 980.0 W Mars Global Surveyor and propulsion tanks are on the opposite side from the instruments, on the propulsion module, which is approximately Funding Agency 1 meter high. Two solar panels, each 3.5 x 1.9 m in size, extend out from opposite sides of the craft. A 1.5 meter NASA-Office of Space diameter parabolic high gain dish antenna is mounted on an Science (United States) adjacent side, and attached to a 2 meter boom, which is extended for mapping operations so the antenna is held away from the body of the spacecraft. Discipline Planetary Science The spacecraft is three-axis stabilized with no scan platform. The main 596 N thruster wil use hydrazine and N2O4 propellant. Control is through 12 4.45 N hydrazine thrusters, Additional mounted in four groups of three (two aft facing and one roll Information control thruster). The initial propellant load was 216.5 kg of hydrazine and 144 kg of N2O4. Four solar array panels (2 Launch/Orbital GaAs, 2 SI) provide 980 W of power to the spacecraft. Energy information for Mars is stored in two 20 Amp-hr nickel hydrogen batteries, and Global Surveyor supplied at 28 V DC. Temperature control is primarily passive PDMP information for with multilayer insulation, thermal radiators, and louvers, Mars Global Surveyor augmented by electrical heaters. Communications is achieved Telecommunications via the deep space network using the high gain antenna and information for Mars two low gain antennas, one mounted on the high gain antenna Global Surveyor and one on the equipment module. Uplink is in the X-band, downlink in the X and Ka bands. Minimum downlink rate is Experiments on Mars 21.33 kbps, 2 kbps engineering data downlink, and 10 bps Global Surveyor emergency downlink. Data collections from Mars The instruments on the nadir equipment deck consist of a Global Surveyor camera, thermal emission spectrometer, laser altimeter, and a radio transmission relay. A magnetometer/electron reflectometer sensor is attached to the end of each solar array, and an ultra-stable oscillator is used for tracking and Questions or comments gravity determination. An 8086 processor is used for the about this spacecraft can payload data subsystem, and 1750A processors for the be directed to: Dr. David R. http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-062A[08/06/2011 23:07:27] NASA - NSSDC - Spacecraft - Details
standard controls processor and the engineering data Williams. formatter. Data is stored on four 0.75 Gb solid state recorders.
Mission Profile After launch on a Delta 7925 (a Delta II Lite launch vehicle with nine strap-on solid-rocket boosters and a Star 48 (PAM-D) third stage) and a 10 month cruise phase, the Mars Global Surveyor was inserted into an elliptical capture orbit at 01:17 UT 12 September 1997. Over the next four months, it was intended that aerobraking maneuvers and thrusters would be used to lower the orbit to the final circular mapping orbit. However, one of the solar panels failed to latch properly when it was deployed and subsequently showed unexpected motion and moved past its fully deployed position when aerobraking began (thought to be due to the fracture of a damper arm and subsequent structural damage). A new aerobraking schedule was employed, which involved slower aerobraking putting less pressure on the solar panels through April 1998, at which time an 11.6 hour science phasing orbit with a 171 km periapsis was achieved and aerobraking was halted. After a 5 month hiatus, aerobraking was resumed on 23 September 1998. Science observations were made periodically during these maneuvers.
After aerobraking ended in February 1999, MGS was in a 118 minute circular polar science mapping orbit with an index altitude of 378 km. The orbit is sun-synchronous (2 a.m./2 p.m.) and maps over the 2 p.m. crossing from south to north (instead of north to south as originally planned). The orbit has a 7 day near-repeat cycle so Mars will be mapped in 26 day cycles. Science mapping began in mid-March 1999, which was summer in the northern hemisphere on Mars. The primary mission lasted one martian year (687 Earth days) through January, 2001. An extended mission took place until April 2002, further extensions were added until contact with the spacecraft was lost on 2 November 2006.
The Mars Global Surveyor mission cost about $154 million to develop and build and $65 million to launch. Mission operations and data analysis cost approximately $20 million/year.
Personnel
Name Role Original Affiliation E-mail Dr. Mary K. Program NASA Headquarters [email protected] Olsen Manager Dr. Arden L. Project California Institute of [email protected] Albee Scientist Technology Mr. Glenn F. Project NASA Jet Propulsion [email protected] Cunningham Manager Laboratory Ms. Patricia G. Program NASA Headquarters Rogers Scientist
Selected References
Albee, A. L., et al., Mars Global Surveyor mission: Overview and status, Science, 279, No. 5357, 1671-1672, Mar. 1998.
Albee, A. L., et al., Overview of the Mars Global Surveyor mission, J. Geophys. Res., 106, No. E10, 23291-23316, Oct. 2001.
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-062A[08/06/2011 23:07:27] NASA - NSSDC - Spacecraft - Details
Mars Global Surveyor NSSDC Home Page Mars Home Page Mars Fact Sheet
Mars Global Surveyor Sampler CD-ROM
Preliminary Report on Loss of MGS Released
Science Press Releases
Mars Global Surveyor Project Home Page
Mars Pathfinder Mission Information Viking Mission Information
+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.16, 26 April 2011
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-062A[08/06/2011 23:07:27] Mars Global Surveyor
DESCRIPCIÓN: Esta misión ha sido la primera en 20 años en llegar con éxito al planeta rojo. Durante su primer año y medio se dedicó a la fase de aerofrenado consistente en ir adquiriendo la órbita definitiva a base de pasar por las capas superiores de la atmósfera marciana y así ir frenando su velocidad hasta conseguir una órbita adecuada. Este periodo fue más largo de lo previsto para no dañar los paneles solares en exceso. Ahora sigue una órbita polar cercana a la superficie y desde allí nos manda las fotos con mayor resolución de la exploración de Marte y nos ha mandado más datos que todas las misiones anteriores juntas.
FECHAS PRINCIPALES: Lanzamiento: 7 noviembre 1.996 Llegada Marte: 12 septiembre 1.997 Comienzo misión primaria: marzo 1.999 Comienzo misión extendida: enero 2.001
Camino recorrido y fases de la misión
LA NAVE: Tiene forma de caja de 1.7x1.17x1.17 metros con 2 partes bien diferenciadas, una para los instrumentos y otra para la propulsión. Los paneles solares tienen una envergadura de 3.5x1.9 metros y proporcionan 980W de potencia para los instrumentos. La parabólica tiene un diámetro de 1.5 metros y un brazo extensible de 2 metros.
INSTRUMENTOS:
Vista frontal de los instrumentos
Vista posterior del resto de equipos.
- Mars Orbital Camera (MOC): Es la encargada de tomar las imágenes de alta resolución del planeta así como otras de menor calidad para tener una visión general de la atmósfera y el clima en todo el planeta. - Thermal Emission Spectrometer (TES):Es un interferómetro que mide la cantidad de luz infrarroja emitida por la superficie de Marte. - Mars Orbital Laser Altimeter (MOLA):Su misión es construir un mapa topográfico de Marte con un rayo laser lanzado a la superficie. - Radio Science Investigations (RS):Mide las variaciones de la señal enviada desde la Tierra para medir las desviaciones gravitatorias. - Magnetic Fields Investigation (MAG/ER):Magnetómetro dedicado al estudio del campo magnético de Marte y su intensidad. - Mars Relay:Antena de apoyo a otras misiones de la NASA, Japón y la ESA.
ORGANISMOS: La misión está financiada por la NASA y será controlada desde el JPL y por Lockheed Martin Astronautics. La cámara MOC está controlada por Malin Space Science Systems (MSSS
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Personnel Mars Pathfinder
Publications NSSDC ID: 1996-068A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The Mars Pathfinder was the second of NASA's low-cost MESUR Pathfinder planetary Discovery missions to be launched. The mission Carl Sagan Memorial consists of a stationary lander and a surface rover. The Station mission had the primary objective of demonstrating the feasibility of low-cost landings on and exploration of the Pathfinder Martian surface. This objective was met by tests of 24667 communications between the rover and lander, and the lander Mars Pathfinder and Earth, tests of the imaging devices and sensors, and tests of the maneuverability and systems of the rover on the Facts in Brief surface. The scientific objectives include atmospheric entry Launch Date: 1996-12- science, long-range and close-up surface imaging, rock and 04 soil composition and material properties experiments, and Launch Vehicle: Delta meteorology, with the general objective being to characterize II 7925 the Martian environment for further exploration. (Mars Launch Site: Cape Pathfinder was formerly known as the Mars Environmental Canaveral, United States Survey (MESUR) Pathfinder.) Mass: 463.0 kg Nominal Power: 35.0 W Mars Pathfinder was launched on a Delta 7925 (a Delta II Lite launch vehicle with nine strap-on solid-rocket boosters and a Star 48 (PAM-D) third stage) at 6:58:00 UT (1:58 a.m. EST) on Funding Agency 4 December 1996. The spacecraft entered the Martian atmosphere on 4 July 1997 directly from its approach NASA-Office of Space hyperbola at about 7300 m/s without going into orbit around Science (United States) the planet. The cruise stage was jettisoned 30 minutes before atmospheric entry. The lander took atmospheric Discipline measurements as it descended. The entry vehicle's heat shield slowed the craft to 400 m/s in about 160 seconds. A 12.5 Planetary Science meter parachute was deployed at this time, slowing the craft to about 70 m/s. The heat shield was released 20 seconds after parachute deployment, and the bridle, a 20 meter long braided Additional Kevlar tether, deployed below the spacecraft. The lander Information separated from the backshell and slid down to the bottom of Launch/Orbital the bridle over about 25 seconds. At an altitude of about 1.6 information for Mars km, the radar altimeter acquired the ground, and about 10 Pathfinder seconds before landing four air bags inflated in about 0.3 seconds forming a 5.2 meter diameter protective 'ball' around PDMP information for the lander. Four seconds later at an altitude of 98 m the three Mars Pathfinder solid rockets, mounted in the backshell, fired to slow the Telecommunications descent, and about 2 seconds later the bridle was cut 21.5 m information for Mars above the ground, releasing the airbag-encased lander. The Pathfinder lander dropped to the ground in 3.8 seconds and impacted at 16:56:55 UT (12:56:55 p.m. EDT) on 4 July 1997 at a velocity Experiments on Mars of 18 m/s - approximately 14 m/s vertical and 12 m/s horizontal Pathfinder - and bounced about 12 meters (40 feet) into the air, bouncing at least another 15 times and rolling before coming to rest Data collections from Mars approximately 2.5 minutes after impact and about 1 km from Pathfinder the initial impact site.
After landing, the airbags deflated and were retracted. http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-068A[08/06/2011 23:08:27] NASA - NSSDC - Spacecraft - Details
Pathfinder opened its three metallic triangular solar panels Questions or comments (petals) 87 minutes after landing. The lander first transmitted about this spacecraft can the engineering and atmospheric science data collected during be directed to: Dr. David R. entry and landing, the first signal being received at Earth at Williams. 18:34 UT (2:34 p.m. EDT). The imaging system obtained views of the rover and immediate surroundings and a panoramic view of the landing area and transmitted it to Earth at 23:30 UT. After some maneuvers to clear an airbag out of the way, ramps were deployed and the rover, stowed against one of the petals, rolled onto the surface on 6 July at about 05:40 UT (1:40 a.m. EDT).
The bulk of the lander's task was to support the rover by imaging rover operations and relaying data from the rover to Earth. The lander was also equipped with a meteorology station. Over 2.5 meters of solar cells on the lander petals, in combination with rechargeable batteries, powered the lander. The lander on-board computer is based on 32-bit architecture with 4 million bytes of static random access memory and 64 million bytes of mass memory for storing images. The main lander components are held in a tetrahedral shaped unit in the center of the three petals, with three low-gain antennas extending from three corners of the box and a camera extending up from the center on a 0.8 meter high pop-up mast. Images were taken and experiments performed by the lander and rover until 27 September 1997 when communications were lost for unknown reasons.
The landing site in the Ares Vallis region of Mars is at 19.33 N, 33.55 W. The lander has been named the Sagan Memorial Station. The Ares Vallis region of Mars is a large outwash plain near Chryse Planitia. This region is one of the largest outflow channels on Mars, the result of a huge flood (possibly an amount of water equivalent to the volume of all five Great Lakes) over a short period of time flowing into the martian northern lowlands.
The Mars Pathfinder mission cost approximately $265 million including launch and operations. Development and construction of the lander cost $150 million and the rover about $25 million.
Personnel
Name Role Original Affiliation E-mail Dr. Mark A. Project NASA Headquarters Saunders Manager Dr. Matthew Project NASA Jet Propulsion [email protected] Golombek Scientist Laboratory Dr. Joseph M. Program NASA Headquarters [email protected] Boyce Scientist Mr. Anthony J. Project NASA Jet Propulsion [email protected] Spear Manager Laboratory Mr. Donald T. Program NASA Headquarters [email protected] Ketterer Manager
Selected References
Golombek, M. P., The Mars Pathfinder mission, J. Geophys. Res., 102, No. E2, 3953-3965, Feb. 1997.
Golombek, M. P., et al., Overview of the Mars Pathfinder Mission: Launch through landing, surface operations, data sets, and science results, J. Geophys. Res., 104, No. E4, 8523-8553, Apr. 1999.
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-068A[08/06/2011 23:08:27] NASA - NSSDC - Spacecraft - Details
Mars Pathfinder Page Mars Pathfinder Rover - NSSDC Master Catalog.
Mars Pathfinder Flight Status Report
Information on the entry and landing strategy Information on the landing site Information on post-landing itinerary - operations and image availability
Mars Pathfinder Project Home Page
Mars Fact Sheet Mars Home Page
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La sonda Mars Pathfinder fue la segunda misión del programa Discovery de la NASA, una iniciativa para la exploración del Sistema Solar con desarrollos cortos del proyectos y bajo coste. Esta misión fue dirigida por el JPL de la NASA y su objetivo principal era la realización de una demostración de tecnologías y conceptos clave que serían usados en futuras misiones a Marte empleando aterrizadores.
INTRODUCCIÓN Además la misión llevaba instrumentos científicos hasta la superficie del planeta rojo para investigar la estructura de la atmósfera marciana, la meteorología, la geología y la composición elemental de las rocas y el suelo. Por último un rover llamado Sojourner sería desplegado para realizar experimentos tecnológicos y para estudiar las rocas del entorno, convirtiéndose en el primer rover marciano de la historia.
Lanzamiento de la misión Pathfinder LANZAMIENTO Y VIAJE La nave de crucero fue lanzada en un cohete Delta II - 7925 que llevaba acoplado una etapa superior PAM-D (Payload Assist Module), desde Cabo Cañaveral (Torre 17B) en una ventana de lanzamiento de 29 días que comenzaba el 2 de diciembre de 1.996. La nave salió disparada al espacio el 4 de diciembre de 1.996 a las 06:58 GMT. Tras el lanzamiento la nave requiere unos 7 meses de viaje de crucero para llegar a Marte. En esta fase se programaron 4 maniobras de corrección de trayectoria (TCM) para ajustar el recorrido de la etapa de crucero de la sonda los días 10 de enero, 3 de febrero, 6 de mayo y 25 de junio. El seguimiento, la telemetría y los comandos son enviados usando las antenas de la Deep Space Network de la NASA.
Etapa de crucero con el aterrizador en su interior El objetivo para la nave era entrar en la atmósfera marciana, desplegar un paracaidas de frenado que la llevara hasta cerca de la superficie de Marte. Allí unos retro-cohetes y varios airbags protegerían al aterrizador del impacto contra el suelo. Tras esto comenzaría la fase primaria de toma de datos con una duración estimada de 30 días marcianos o soles. Además el microrover debía moverse por la superficie al menos durante 7 soles. Si pasado este periodo ambos funcionaran correctamente, la NASA ampliaría la misión del aterrizador hasta 1 año y la del microrover durante un mes. LUGAR DE ATERRIZAJE El lugar de aterrizaje de Pathfinder pasó una serie de rigurosos estudios de ingeniería para determinar la seguridad del lugar: suficiente luz solar, pendientes aceptables, poca rugosidad del suelo, baja elevación del polvo para tener la suficiente densidad atmosférica, poco potencial para tormentas, etc. Además debía proporcionar un buen retorno de datos científicos. Finalmente se seleccionó un lugar cerca de la boca de un canal donde se produjo un desbordamiento catastrófico en el pasado en Ares Vallis y que además permitía tener rocas de diferentes tipos en el mismo lugar. Aunque era imposible saber durante la misión el lugar de procedencia de cada roca, el uso de los datos de los orbitadores posteriores pudo ser usado para determinar el camino que siguieron la rocas estudiadas por Pathfinder. La zona de aterrizaje para la nave tenía forma de elipse con una dimensiones de 200 x 70 kilómetros.
Elipse de aterrizaje en Ares Vallis. 19,33º N y 33,55º O ENTRADA, DESCENSO Y ATERRIZAJE La etapa de entrada, descenso y aterrizaje (EDL) para Mars Pathfinder comenzó varios días antes de la llegada a Marte cuando los controladores del JPL enviaron comandos a la nave para decirle cuando y como debía ejecutar las complejas maniobras de la secuencia para llegar a la superficie marciana de una pieza. Este proceso se repite hasta unas horas antes de la llegada para aumentar la precisión del recorrido y los datos enviados, ya que la gravedad marciana sólo es perceptible para la nave las 48 horas previas a la llegada. Desde una hora y media antes del aterrizaje hasta 3 horas y media después, la nave está bajo el control del programa autónomo de abordo que dirige los eventos que ocurrirán. La primera tarea de la nave es hacer circular el líquido de enfriamiento por toda la nave unos 90 minutos antes de la llegada. Este fluido circuló por el perímetro de la etapa de crucero y dentro del aterrizador para mantener los fríos durante los 7 meses de la etapa de crucero. Con su misión cumplida, la etapa de crucero es expulsada media hora antes de la llegada a 8.500 kilómetros de la superficie de Marte. Esta etapa de crucero usaba como combustible para la propulsión hidrazina monopropelante, que hacía funcionar 8 toberas de 4,4 N y proporcionando un delta-V (diferencia de velocidad) de 130 m/s.
Algunos minutos antes de la llegada, la nave comienza a sentir las capas exteriores de la atmósfera a unos 125 kilómetros de altura y quedando ya tan sólo 4 minutos para llegar al suelo. Con el giro estabilizado a 2 revoluciones por minuto y a 7,5 km/s de velocidad, la nave entra en la atmósfera con un ángulo de 14,8º. El escudo térmico derivado de los Viking protege la nave del intenso calor de la reentrada. En el momento de máximo calor, el escudo absorbe más de 100 megavatios de energía termal, de tal manera que la nave baja su velocidad hasta los 400 m/s. La deceleración es superior a los 20 G's y es detectada por los acelerómetros de abordo, lo que provoca que una secuencia de eventos programados comience a funcionar en una rápida sucesión.
Fase completa de entrada y descenso (EDL) El despliegue del paracaidas de 7,5 metros ocurre a los 2 minutos y medio tras la entrada atmosférica a una altura de entre 5 y 11 kilómetros de la superficie bajando la velocidad hasta los 65 m/s. El escudo térmico es separado pirotécnicamente unos 20 segundos más tarde y cae desde una altura entre los 2 y los 9 kilómetros. El aterrizador comienza a separarse del escudo trasero descendiendo en una cuerda de Kevlar de 20 metros de longitud, lo que deja espacio para el inflado de los airbags, una distancia prudente para el encendido de los motores y una estabilidad adicional. Una vez que el aterrizador está en posición se activa el radar altímetro y ayuda en la secuencia de eventos que llegan a continuación (inflado de airbags, encendido de motores del escudo trasero y corte del cable de Kevlar). El radar del aterrizador comenzará a detectar la superficie unos 32 segundos antes del aterrizaje a una altura de 1,5 kilómetros. Los airbags se inflan 8 segundos antes del aterrizaje a 300 metros de altura. Los airbags tienen dos dispositivos explosivos, el primero de los cuales corta los cables y libera las bolsas para que puedan ser infladas. El segundo explosivo se enciende 0,25 segundos después y 4 segundos antes de que se enciendan los cohetes, para activar tres generadores de gas que inflan en 0,3 segundos las tres bolsas de 5,2 metros de diámetro a una presión de poco menos de 1 psi.
Primeras etapas de la entrada El escudo cónico trasero sobre el aterrizador contiene los tres motores de combustible sólido que provocan una fuerza de una tonelada durante dos segundos. El ordenador enciende los motores por unos instantes a una altura de entre 80 y 100 metros del suelo, para que la velocidad sea nula a una altura de 12 metros de la superficie. En ese instante se corta el cable de tal forma que el escudo junto con el paracaidas es lanzado lejos de la zona y el aterrizador envuelto en los airbags cae al suelo. El último impulso de los cohetes debería provocar una gran velocidad lateral al aterrizador, de hasta 25 m/s y un ángulo de 30º para evitar que el paracaidas y el escudo le caigan encima. Tras esto el aterrizador comenzará a botar hasta a 12 metros de altura y recorriendo más de 100 metros entre los botes.
Los retrocohetes frenan la caída y se suelta el airbag que comienza a botar
Tras pararse en la superficie, se activan dispositivos pirotécnicos en los pétalos para que puedan ser abiertos y permitan al aterrizador que comienze su actividad. El aterrizaje ocurrió sobre las 03:00 de la hora local marciana, las 17:07:25 GMT del viernes 4 de julio de 1.997. RETRO-COHETES Los motores de Pathfinder eran esenciales para un aterrizaje seguro. Al ser la atmósfera marciana tan delgada, el paracaidas no podría frenar lo suficiente la nave para evitar que se estrellara. Sin estos cohetes la velocidad de impacto contra el suelo habría sido de 62 m/s y los airbags hubieran reventados junto con la nave. Construidos por la empresa Thiokol, los cohetes apenas tienen una longitud de 90 centímetros pero poseen una gran potencia. De esta forma, en tan sólo 2,4 segundos eran capaces de frenar el descenso y dejar a Pathfinder sin velocidad de caída Durante el instante que son encendidos, podrían generar la suficiente electricidad como para abastecer a una localidad de 15.000 personas. Los gases expulsados llegan a una temperatura de 3.000º C (la mitad de la temperatura de la superficie solar) y una velocidad de 2,6 km/s (10 veces más rápido que un avión de pasajeros). Los tres cohetes son anclados en un estructura que va insertada en el escudo trasero.
Un test de los retrocohetes RETRACCIÓN DE LOS AIRBAGS Y ORIENTACIÓN DEL ROVER Una vez que Mars Pathfinder ha aterrizado en la superficie, se activan los sistemas pirotécnicos en los petalos del aterrizador, de tal manera que permitan su apertura. Las juntas que unen los pétalos laterales son necesarias debido a las fuerzas ejercidas en los pétalos del aterrizador por el sistema de airbags desplegado.
En paralelo con la apertura de los pétalos, un sistema de retracción comenzará a recoger los airbags hacia el aterrizador, practicando una apertura en el lateral de cada bolsa para facilitar el proceso de desinflado a través de un filtro. Los airbags son traídos hacia los pétalos por cables internos que se extienden por las uniones entre los airbags y las pequeñas aberturas en cada una de las caras del aterrizador. El proceso dura unos 64 minutos en desinflar y retraer completamente los airbags.
Hay un motor de giro en cada una de las bisagras de los 3 pétalos. Si el lander aterriza sobre uno de los laterales, será colocado en la posición correcta por la apertura de un pétalo lateral con un motor que colocará el aterrizador en posición vertical. Una vez colocado correctamente se abren los otros dos pétalos.
El proceso de retraer los airbags y desplegar los pétalos del aterrizador dura unas 3 horas en total. Mientras tanto el sistema de radio en banda X del aterrizador es desconectado por primera vez desde el lanzamiento el 4 de diciembre de 1.996. Esto ahorra baterías y permite al sistema electrónico enfriarse tras haberse calentado durante la entrada al no disponer de sistema de enfriamiento. Tras este periodo la Tierra ya es visible bien alta sobre el horizonte y estará en buena posición para comunicarse con el aterrizador a través de la antena de baja ganancia a última hora de la mañana. LA NAVE. EL ATERRIZADOR Y EL ROVER.
El rover Sojourner La masa total del microrover era de 11,5 kilogramos incluyendo el mecanismo de despliegue del APXS y el propio instrumento. Otros 6 kilogramos están situados en el aterrizador como parte del sistema de comunicaciones UHF con el rover, los sistemas de despliegue y de soporte estructural durante el viaje. La altura es de 28 centímetros con una elevación inferior de 13 centímetros sobre el suelo. El espacio dentro del aterrizador para el rover era de tan sólo 20 centímetros por lo que debía viajar con las ruedas plegadas con una altura de tan sólo 18 centímetros. Su longitud total es de 63 centímetros y su anchura de 48 cm.
Esquema del rover. Imagen: Wikipedia Todo el rover es un experimento de tecnología en si mismo, para determinar el rendimiento de los microrovers en el por entonces poco conocido terreno marciano, de forma que permita a las siguientes generaciones de rovers una navegación y movimiento más efectivo en Marte.
El rover Sojourner Tiene tres objetivos principales: 1. Experimentos tecnológicos 2. Experimentos de ciencia con el rover 3. Experimentos de la misión del lander El rover tenía libertad de movimientos respecto al aterrizador y tenía un sistema básico de navegación autónoma usando dos lásers para la detección de obstáculos. Para desplazarse contaba con 6 ruedas autónomas y un sistema de suspensión que permitía sortear pequeñas rocas, viajando a una velocidad máxima de 1 centímetro por segundo. Los datos los enviaba y recibía a través de una antena UHF que conectaba con el aterrizador. Su carga científica constaba de: - Cámara fotográfica trasera a color y doble cámara delantera para imágenes en 3D - Mecanismo de despliegue del APXS - Espectrómetro APXS Para funcionar portaba sobre él un panel solar de 0,25 m2 que proporcionaba un pico de energía de 16 W-hora y una batería con capacidad para 50 W-hora. La temperatura era mantenida en unos límites aceptables gracias a 3 calentadores de radio-isótopos o RHU. El ordenador era un 80C85, con 0,1 MIPS y 0,5 MB de RAM para almacenar datos, todo ello con un peso de 500 gramos y un consumo de 1,5 W. Debido a las limitaciones energéticas, el rover podía funcionar entre las 10 de la mañana y las 2 de la tarde (4 horas en total), de cada sol.
El aterrizador. Carl Sagan Memorial Station. La masa total del conjunto de la misión en el lanzamiento era de 890 kilogramos incluyendo el combustible para el viaje. La masa de entrada en la atmósfera del planeta (sin el módulo de crucero) era de 570 kilogramos y la masa del aterrizador era de 360 kilogramos, incluyendo airbags, paneles y rover. Los objetivos de la Estación Aterrizadora eran varios:
- Permitir al rover llegar hasta la superficie mediante dos rampas de descenso. - Recibir los datos del rover para reenviarlos a la Tierra y enviarle al rover las órdenes de los controladores. - Obtener datos científicos con la estación meteorológica y las cámaras del mástil. El ordenador del aterrizador era un R6000 con un bus VME, con 22 millones de instrucciones por segundo (MIPS) y 128 MB de memoria de almacenamiento. El aterrizador estaba alimentado por paneles solares y las comunicaciones de telemetría se enviaban por la antena de Alta Ganancia (HGA) de banda-X a un ritmo de 6 kb/s a las antenas de 70 metros de la DSN. Para los comandos de operaciones en superficie se usaba la HGA a un ritmo de 250 b/s.
Esquema del aterrizador rebautizado 'Carl Sagan Memorial Station'. Imagen: Wikipedia
Realización de pruebas de movimiento y comunicaciones en el aterrizador y el rover
El mástil, las antenas y las cámaras SISTEMA DE TELECOMUNICACIONES DEL ROVER El sistema de telecomunicaciones del rover es un sistema en dos direcciones en UHF entre el lander y el rover, usado para enviar comandos desde la Tierra al rover y recibir los datos e imágenes obtenidas. Debido a que el alcance es similar al de un walkie-talkie no es posible la comunicación directa con el rover. Todas las comunicaciones del rover se realizan con la ayuda del sistema de comunicaciones del aterrizador. Está formado por dos radios UHF y dos antenas UHF. La radio está localizada dentro del WEB (Warm Electronic Box) del rover, donde está protegida del frío extremo del ambiente marciano. La radio está conectada a la antena usando un cable coaxial.
Enlaces de comunicación SISTEMA ELÉCTRICO DEL ROVER Panel Solar Toda la energía del rover es proporcionada por un ligero panel solar colocado como un panel plano en la parte superior del rover. El panel es una red de varios cientos de celdas solares muy ligeras y frágiles. La producción al medio día es de unos 16 W, el equivalente a una luz de un horno, pero que permite al rover realizar todas sus actividades científicas.
El panel solar antes de ser instalado Baterías Durante los momentos en los cuales hay muy poca luz solar o ninguna, el rover usaba la electricidad almacenada en las baterías de forma moderada ya que si se descargan por completo ya no hubieran podido ser cargadas de nuevo. Se utilizaron sobretodo para experimentos nocturnos y operaciones a primera hora de la mañana, así como para los chequeos de salud a los que fue sometido durante los 7 meses de crucero hasta la Tierra. INSTRUMENTOS La misión llevaba 3 instrumentos científicos entre el rover y la base:
· Cámara de Mars Pathfinder - Imager For Mars Pathfinder (IMP) · Espectrómetro de Rayos-X Protones Alfa - Alpha Proton X-Ray Spectrometer (APXS) con un Mecanismo de despliegue del APXS. · Instrumentos de Estructura Atmosférica y Meteorología - Atmospheric Structure Instrument/Meteorology Package (ASI/MET)
Imager For Mars Pathfinder (IMP)
La cámara IMP (Imager for Mars Pathfinder) es un sistema de obtención de imágenes en estereo con la posibilidad añadida de captar imágenes en color usando filtros seleccionables en cada una de dos cámaras de las que consta el instrumento. Fue desarrollado por la Universidad de Arizona. El sistema está formado por la cabeza de la cámara (óptica estereo, rueda de filtros, CCDs, preamplificadores y motores de movimiento), el mástil extensible con el cableado y dos tarjetas electrónicas (tarjeta de los datos de CCD y tarjeta de los motores). Tenía un peso de 5,2 kilogramos y gastaba 2,6 Watios.
La cámara IMP Los movimientos en azimut y elevación para la cámara están proporcionados por motores de paso que permiten un movimiento de ±180 grados en azimut y +83/-72 grados en elevación. La cámara está situada en lo más alto del mástil desplegable con una elevación de un metro sobre la superficie del lander. Las imágenes adquiridas son de 256x256 píxeles y es idéntica a la cámara DISR de Huygens. Las dos ruedas llevaban cada una 12 filtros que eran combinados de hasta 30 formas diferentes para obtener las imágenes para observar la atmósfera, elementos geológicos o en estereo. Uno de los filtros era una lente que permitía algunos aumentos para fotografiar imágenes de los imanes que acumulaban el polvo del viento durante la misión y situados en la plataforma de la IMP.
Durante la misión se adquirieron varios panoramas completos de la zona de aterrizaje en color y en estereo. Antes del despliegue del mástil se obtuvo un panorama de 360 grados para luego comparar las distintas perspectivas a las dos alturas.
La cámara en el mástil desplegado Usando las imágenes obtenidas por la cámara se llevaron a cabo investigaciones atmosféricas. La opacidad de los aerosoles se mide realizando fotos del Sol en dos bandas estrechas con dos filtros distintos. Las partículas de polvo en la atmósfera se caracterizaron observando Phobos durante la noche. Además se estudió la abundancia de vapor de agua en la atmósfera con imágenes del Sol en varios filtros en la banda de absorción del agua. Durante algunos soles se fotografiaron los sensores de viento a varias alturas para conocer su dirección y velocidad.
Otra parte de las investigaciones estuvo centrada en las propiedades magnéticas del polvo marciano. Se colocaron imanes de diferente fuerza en una placa acoplada al aterrizador y durante la misión se obtuvieron imágenes para determinar la acumulación de los componentes magnéticos llevados por el polvo marciano. Además las imágenes se obtuvieron con varios filtros para diferenciar los diversos minerales encontrados. Las observaciones también se centraron en un objetivo de referencia para la calibración de las imágenes que portaba un pequeño sensor de viento. Alpha Proton X-Ray Spectrometer
Este instrumento es un derivado directo de los espectrómetros de rayos X que volaron en las misiones rusas Vega y Phobos y es idéntico al que fue usado en la misión Mars 96. Con la movilidad proporcionada por el rover y el sistema de despliegue, el espectrómetro APX no sólo adquirió el espectro del polvo marciano, sino que por primera vez permitió el análisis de distintas rocas de la superficie marciana. El espectrómetro alfa y de protones ha sido proporcionado por el Instituto Max Planck de Alemania y el de rayos X por la Universidad de Chicago. Pesaba 0,74 kilogramos y gastaba 0,8 W.
El APXS en el frontal del rover El instrumento permite conocer la composición elemental de los materiales de las rocas y el suelo utilizando para ello una fuente radiactiva de partículas alfa y detectores de estas partículas, de protones y rayos X que analizaron la energía del espectro devuelto por las muestras. De esta manera se dedujo la composición química elemental de las rocas en todos sus elementos menos el hidrógeno.
Sensores del instrumento El sensor del APXS va montado externo al chasis del rover en un sistema desplegable. Este sistema coloca al APXS en contacto con la roca y el suelo. El resto de la electrónica va en el rover en un sistema de temperatura controlada.
APXS Deployment Mechanism
El sistema de despliegue soporta al APXS bajo las condiciones del lanzamiento y aterrizaje y proporciona los medios necesarios para colocar al APXS en su objetivo con un solo movimiento. El mecanismo es lo bastante flexible como para permitir la colocación del APXS a diversas alturas y orientaciones. Varios mecanismos de contacto en el anillo frontal permiten al rover saber que el aparato se encuentra ya bien posicionado, terminando los movimientos del mecanismo.
El mini-brazo con el APXS en el extremo Atmospheric Structure Instrument/Meterology Package
El ASI/MET es un subsistema de ingeniería que adquiere información atmosférica durante el descenso del aterrizador a través de la atmósfera y durante la misión. Está diseñado por el JPL de sistemas heredados de las misiones Viking. Los datos adquiridos durante la entrada y descenso permitieron la reconstrucción de perfiles de densidad atmosférica, temperatura y presión desde los 100 kilómetros de altura hasta la superficie. Pesaba 2 kilogramos y gastaba 3,2 W.
El ASI consiste en un acelerómetro con sensores en los 3 ejes que permiten conocer los movimientos y fuerzas de aceleración durante la entrada y los eventos del aterrizaje, hasta los 50 G's. Entre los instrumentos se encuentran sensores de temperatura, presión y viento, así como la electrónica necesaria para los sensores y el tratamiento digital de los datos obtenidos. La temperatura es medida por termopares montados en un mástil que se despliega tras el aterrizaje. Uno de ellos permite conocer la temperatura durante el descenso y otros tres están colocados a 25, 50 y 100 cm del suelo en la misión.
ASI/MET con los sensores de temperatura y viento Tres sensores de viento están colocados a varias alturas del mástil para determinar las velocidades y direcciones del viento en la zona de aterrizaje. Este sensor fue muy fotografiado por la cámara IMP durante la misión. De esta manera es posible conocer la orientación de los alerones para determinar la dirección y velocidad del viento a las 3 alturas, permitiendo la obtención de perfiles verticales del viento.
NASA - NSSDC - Spacecraft - Details
Wednesday, 08 June 2011
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Personnel Mars Pathfinder Rover
Publications NSSDC ID: MESURPR Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The Mars Pathfinder was the second of NASA's low-cost Rocky IV planetary Discovery missions to be launched. The mission MFEX consists of a stationary lander and a surface rover. The mission had the primary objective of demonstrating the Microrover Flight feasibility of low-cost landings on and exploration of the Experiment Martian surface. This objective was met by tests of MESUR Pathfinder Rover communications between the rover and lander, and the lander Sojourner and Earth, tests of the imaging devices and sensors, and tests of the maneuverability and systems of the rover on the surface. The scientific objectives include atmospheric entry Facts in Brief science, long-range and close-up surface imaging, rock and soil composition and material properties experiments, and Launch Date: 1996-12- meteorology, with the general objective being to characterize 04 Launch Vehicle: Delta Mars Pathfinder Rover the Martian environment for further exploration. (Mars Pathfinder was formerly known as the Mars Environmental II Survey (MESUR) Pathfinder.) Launch Site: Cape Canaveral, United States The rover, which has been named "Sojourner" is a six-wheeled Mass: 10.5 kg vehicle, 280 mm high, 630 mm long, and 480 mm wide with a Nominal Power: 13.0 W ground clearance of 130 mm, mounted on a "rocker-bogie" suspension. The rover was stowed on the lander at a height of Funding Agency 180 mm. At deployment, the rover extended to its full height and rolled down a deployment ramp at about 05:40 UT on 6 NASA-Office of Space July 1997 (1:40 a.m. EDT). The rover was controlled by an Science (United States) Earth-based operator who used images obtained by both the rover and lander systems. Note that the time delay was between 10 and 15 minutes depending on the relative position Discipline of Earth and Mars over the course of the mission, requiring Planetary Science some autonomous control, provided by a hazard avoidance system on the rover. The on-board control system is an Intel 80C85 8-bit processor which runs about 100,000 instructions Additional per second. The computer is capable of compressing and Information storing a single image on-board. The rover is powered by 0.2 square meters of solar cells, which will provide energy for Launch/Orbital several hours of operations per sol (1 Martian day = 24.6 Earth information for Mars hours). Non-rechargeable lithium thionyl chloride (LiSOCl2) D- Pathfinder Rover cell batteries provide backup. All rover communications were PDMP information for done through the lander. Mars Pathfinder Rover Telecommunications The rover is equipped with black and white and color imaging information for Mars systems which were used to image the lander in order to Pathfinder Rover assess its condition after touchdown. The goal was to acquire three black and white images spaced 120 degrees apart of the Experiments on Mars lander. Images of the surrounding terrain were also acquired Pathfinder Rover to study size and distribution of soils and rocks, as well as locations of larger features. Imaging of the rover wheel tracks Data collections from Mars will be used to estimate soil properties. Imaging of the rover by Pathfinder Rover the lander was also done to assess rover performance and soil and site properties. The rover's performance was monitored to http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=MESURPR[08/06/2011 23:10:00] NASA - NSSDC - Spacecraft - Details
determine tracking capabilities, drive performance, thermal behavior, and sensor performance. UHF Communications Questions or comments between the rover and lander were studied to determine the about this spacecraft can effectiveness of the link between the rover and lander. be directed to: Dr. David R. Assessments of rock and soil mechanics will be made based Williams. on abrasion of the wheels and adherence of dust. An alpha- proton-X-ray spectrometer (APXS) is on-board the rover to assess the composition of rocks and soil. Images of all samples tested are transmitted to Earth. The primary objectives were scheduled for the first seven sols, all within about 10 meters of the lander. The extended mission included slightly longer trips away from the lander, and even longer journeys were planned. Images were taken and experiments performed by the lander and rover until 27 September 1997 when communications were lost for unknown reasons.
The landing site in the Ares Vallis region of Mars is at 19.33 N, 33.55 W. The lander has been named the Sagan Memorial Station. The Ares Vallis region of Mars is a large outwash plain near Chryse Planitia. This region is one of the largest outflow channels on Mars, the result of a huge flood (possibly an amount of water equivalent to the volume of all five Great Lakes) over a short period of time flowing into the martian northern lowlands.
The Mars Pathfinder mission cost approximately $265 million including launch and operations. Development and construction of the lander cost $150 million and the rover about $25 million.
Personnel
Name Role Original Affiliation E-mail Dr. Mark A. Project NASA Headquarters Saunders Manager Dr. Matthew Project NASA Jet Propulsion [email protected] Golombek Scientist Laboratory Dr. Joseph M. Program NASA Headquarters [email protected] Boyce Scientist Mr. Anthony J. Project NASA Jet Propulsion [email protected] Spear Manager Laboratory Mr. Donald T. Project NASA Headquarters [email protected] Ketterer Manager
Selected References
The Rover Team, The Pathfinder microrover, J. Geophys. Res., 102, No. E2, 3989-4001, Feb. 1997.
Matijevic, J., Sojourner: The Mars Pathfinder microrover flight experiment, Space Technol., 17, No. 3/4, 143-149, 1997.
Golombek, M. P., et al., Overview of the Mars Pathfinder Mission: Launch through landing, surface operations, data sets, and science results, J. Geophys. Res., 104, No. E4, 8523-8553, Apr. 1999.
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Mars Pathfinder Page Mars Pathfinder Lander - NSSDC Master Catalog.
Mars Pathfinder Flight Status Report
Information on the entry and landing strategy Information on the landing site Information on post-landing itinerary - operations and image availability
Mars Pathfinder Project Home Page
Mars Fact Sheet Mars Home Page
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Personnel MEASAT 1
Publications NSSDC ID: 1996-002B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events MEASAT 1 was a Malaysian geostationary communications Malaysia East Asia Sat 1 spacecraft launched by an Ariane 44L rocket from the Kourou 23765 Space Center in French Guiana. After parking at 91.5 E longitude, the 1,450 kg spacecraft will provide communications and direct-to-home television services to Malaysia and Facts in Brief neighboring countires through its 4 Ku-band and 12 C-band transponders. Launch Date: 1996-01- 12 Launch Vehicle: Ariane 44L Launch Site: Kourou, French Guiana Mass: 886.0 kg
Funding Agency
Binariang Sdn Bhd, Malaysia (Malaysia)
Discipline
Communications
Additional Information
Launch/Orbital information for MEASAT 1
Experiments on MEASAT 1
Data collections from MEASAT 1
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel MEASAT 2
Publications NSSDC ID: 1996-063B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events MEASAT 2 (Malaysia East Asia Satellite 2) was a Malaysia East Asia Sat 2 geostationary communications satellite designed to provide 12 24653 years of both direct-to-user television service in Malaysia and general communications services in the region from Malaysia to the Philippines and from Beijing to Indonesia. It had 11 Facts in Brief active transponders in Ku-band (uplink 13.75 - 14.45 GHz, downlink 10.960-11.700 GHz). Eight of these used 95-watt Launch Date: 1996-11- traveling-wave amplifiers, and three had 62 watts. There were 13 also six active transponders in C-band (uplink 5.925-6.425 Launch Vehicle: Ariane GHz, downlink 3.700-4.200 GHz), powered by 12-watt solid- 44L state amplifiers. It was located at 148 degrees E. Launch Site: Kourou, French Guiana Mass: 886.0 kg
Funding Agency
Binariang Sdn Bhd, Malaysia (Malaysia)
Discipline
Communications
Additional Information
Launch/Orbital information for MEASAT 2
Experiments on MEASAT 2
Data collections from MEASAT 2
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Microsat
Publications NSSDC ID: 1996-050A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events MICROSAT, also known as MuSat, is an Argentine 33 kg MuSat microsatellite that was launched by a Molniya-M booster from 24291 Plesetsk cosmodrome at 05:22 UT. It carries instruments to photograph natural resources. Facts in Brief
Launch Date: 1996-08- 29 Launch Vehicle: Molniya-M Launch Site: Plesetsk, Russia Mass: 33.0 kg
Funding Agency
Unknown (Argentina)
Discipline
Earth Science
Additional Information
Launch/Orbital information for Microsat
Experiments on Microsat
Data collections from Microsat
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Molniya 1-89
Publications NSSDC ID: 1996-045A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Molniya 1/89 was a first-generation Russian communications Molniya 1T satellite orbited to test and perfect a system of radio 24273 communications and television broadcasting using earth satellites as active transponders and to experiment with the system in practical use. The basic function of the satellite was Facts in Brief to relay television programs and long-distance two-way multichannel telephone, phototelephone, and telegraph links Launch Date: 1996-08- from Moscow to the various standard ground receiving stations 14 in the 'Orbita' system. The satellite was in the form of a Launch hermetically sealed cylinder with conical ends -- one end Vehicle: Molniya-M contained the orbital correcting engine and a system of Launch Site: Plesetsk, microjets, and the other end contained externally mounted Russia 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 around the central cylinder were six large solar battery panels Discipline 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 provided in a frequency range of 3.4 to 4.1 GHz at 40 w. Launch/Orbital Molniya 1/89, whose cylindrical body was 3.4 m long and 1.6 m information for Molniya 1- in diameter, was much heavier than corresponding U.S. 89 COMSATs, and it had about 10 times the power output of the Early Bird COMSAT. In addition, it did not employ a Experiments on Molniya 1- geosynchronous equatorial orbit as have most U.S. COMSATs 89 because such an orbit would not provide coverage for areas north of 70 deg n latitude. Instead, the satellite was boosted Data collections from from a low-altitude parking orbit into a highly elliptical orbit with Molniya 1-89 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 1/89 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 3-48
Publications NSSDC ID: 1996-060A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The Molniya-3 Russian communications satellites were used to 24640 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: 1996-10- enhanced electrical power system and a communications 24 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-M 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 Communications System. Trials of this version began in the 1980's, with the system being accepted by the Russian military Funding Agency in 1983-1985. Unknown (Russia)
Discipline
Communications
Additional Information
Launch/Orbital information for Molniya 3- 48
Experiments on Molniya 3- 48
Data collections from Molniya 3-48
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel MSAT 1
Publications NSSDC ID: 1996-022A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events M-SAT 1 was a Canadian geostationary mobile telephone 23846 communications satellite launched by an Ariane 42P rocket from the Kourou Space Center to serve the North American continent. The spacecraft and its transponders are very similar Facts in Brief to those of the American AMSC 1. It had the capability to Launch Date: 1996-04- support 2000 radio channels in L-band. The footprint covered 20 the entire continental US and Canada, as well as Alaska, Launch Vehicle: Ariane Hawaii, Puerto Rico, the Virgin Islands, and 200 mile of US 42P and Canadian coastal waters. It was one of the first satellites Launch Site: Kourou, to use Hughes' springback antennas, flexible 17-foot-by-22- French Guiana foot ovals made of graphite.
Funding Agency
TMI Communications and Co. Ltd (Canada)
Discipline
Communications
Additional Information
Launch/Orbital information for MSAT 1
Experiments on MSAT 1
Data collections from MSAT 1
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel MSTI 3
Publications NSSDC ID: 1996-031A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events MSTI 3 is the third satellite developed by the MSTI (Miniature Miniature Sensor Sensor Technology Integration) Program within the US Air Technology Integration 3 Force. The satellite carries three sensors: a medium 23868 wavelength infrared (MWIR) camera, a short wavelength infrared (SWIR) camera, and a visible imaging spectrometer. It's primary mission, to last for one year, is intended to gather Facts in Brief extensive background clutter statistics at medium wavelengths in the infrared at sufficient resolution to resolve whether Launch Date: 1996-05- tracking theater ballistic missiles (TBMs) in the coast phase 16 against a warm earth background is achievable. The visible Launch imaging spectrometer will gather environmental data of similar Vehicle: Pegasus quality to the Land-Remote Sensing Satellite to support Launch environmental and ecological studies. Site: Vandenberg AFB, United States Mass: 175.0 kg
Funding Agency
Department of Defense- Department of the Air Force (United States)
Disciplines
Earth Science Surveillance and Other Military
Additional Information
Launch/Orbital information for MSTI 3
Experiments on MSTI 3
Data collections from MSTI 3
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel MSX
Publications NSSDC ID: 1996-024A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The Midcourse Space Experiment (MSX) was a test project of Midcourse Space the Ballistic Missile Defense Organization (BMDO). Its primary eXperiment purpose was to gather data over a wide-wavelength interval to 23851 demonstrate the feasibility of identifying and tracking ballistic missiles during their midcourse flight phase. Its multispectral instruments were capable of obtaining wide band and spectral Facts in Brief images in the range of ultraviolet to infrared wavelengths (110 nm to 28,000 nm). The instruments were also utilized for Launch Date: 1996-04- civilian aeronomic and auroral studies. 24 Launch Vehicle: Delta The 5.1 m spacecraft consisted of three sections each of 1.5 m II x 1.5 m cross-section to house three payload components: an Launch MSX electronics section, an 8.5 K frozen hydrogen section, and an Site: Vandenberg AFB, instruments section. The three instruments were: SPIRIT III United States (Space Infrared Imaging Telescope), a five-color, high-spatial Mass: 2700.0 kg resolution scanning radiometer and a six-channel, high- Nominal spectral resolution, Fourier-transform spectrometer; UVISI Power: 1200.0 W (Ultraviolet and Visible Imagers and Spectrographic Imagers), five spectrographic imagers and four UV/visible imagers with Funding Agencies capabilities from the far ultraviolet through visible wavelengths; and, Space-Based Visible (SBV), a visible band telescope with Department of Defense- a six-inch aperturn, a charge-coupled device, and image Department of the Navy processing electronics. Also on-board were the On-board (United States) Signal and Data Processor (OSDP), which provided real-time Air Force Ballistic Missile signal processing for target detection and tracking for data Defense Organization generated by SPIRIT III, sensors for monitoring and measuring (United States) instrument contamination and degradation of performance largely due to outgassing, and a number of small (2.0 cm) reference spheres, deployed as reference objects from MSX Disciplines for instrument calibration. Astronomy Engineering Earth Science Planetary Science Space Physics
Additional Information
Launch/Orbital information for MSX PDMP information for MSX Telecommunications information for MSX
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Experiments on MSX
Data collections from MSX
Questions or comments about this spacecraft can be directed to: Dr. Dieter K. Bilitza.
Personnel
Name Role Original Affiliation E-mail Dr. John D. Mill Project Environmental Research [email protected] Scientist Institute of Michigan(ERIM) Dr. Max R. Program Applied Physics Laboratory [email protected] Peterson Manager Lcol Bruce D. Program USAF Ballistic Missile [email protected] Guilmain, Manager Defense Organization USAF
Other Sources of MSX Information/Data
MSX information (Applied Physics Laboratory)
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Personnel N-Star-B
Publications NSSDC ID: 1996-007A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events N-Star-B as a Japanese geosynchronous spacecraft launched 23781 by an Ariane rocket from the Kourou Space Center in French Guiana. The 3,400 kg spacecraft is expected to provide voice and TV broadcasts to Japan and neighboring regions. Facts in Brief Launch Date: 1996-02- 05 Launch Vehicle: Ariane Launch Site: Kourou, French Guiana Mass: 3400.0 kg
Funding Agency
Unknown (Japan)
Discipline
Communications
Additional Information
Launch/Orbital information for N-Star-B
Experiments on N-Star-B
Data collections from N- Star-B
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Navstar 2A-16
Publications NSSDC ID: 1996-019A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Global Positioning System (GPS) was developed by the US USA 117 Department of Defense to provide all-weather round-the-clock GPS 2-25 navigation capabilities for military ground, sea, and air forces. Since its implementation, GPS has also become an integral 23833 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: 1996-03- 55 degrees. These vehicles are placed in 6 orbit planes with 27 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-16
Experiments on Navstar 2A-16
Data collections from Navstar 2A-16
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Request and User Support Office.
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Personnel Navstar 2A-17
Publications NSSDC ID: 1996-041A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Global Positioning System (GPS) was developed by the US GPS 2-26 Department of Defense to provide all-weather round-the-clock USA 126 navigation capabilities for military ground, sea, and air forces. Since its implementation, GPS has also become an integral 23953 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: 1996-07- 55 degrees. These vehicles are placed in 6 orbit planes with 15 four operational satellites in each plane. Launch Vehicle: Delta II 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-17
Experiments on Navstar 2A-17
Data collections from Navstar 2A-17
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Navstar 2A-18
Publications NSSDC ID: 1996-056A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Global Positioning System (GPS) was developed by the US USA 128 Department of Defense to provide all-weather round-the-clock GPS 2-27 navigation capabilities for military ground, sea, and air forces. Since its implementation, GPS has also become an integral 24320 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: 1996-09- 55 degrees. These vehicles are placed in 6 orbit planes with 12 four operational satellites in each plane. Launch Vehicle: Delta II 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-18
Experiments on Navstar 2A-18
Data collections from Navstar 2A-18
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Request and User Support Office.
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Personnel NEAR Shoemaker
Publications NSSDC ID: 1996-008A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The Near Earth Asteroid Rendezvous - Shoemaker (NEAR Near Earth Asteroid Shoemaker), renamed in honor of Gene Shoemaker, was Rendezvous designed to study the near Earth asteroid Eros from close orbit NEAR over a period of a year. The mission was the first-ever to orbit an asteroid and to touch down on the surface of an asteroid. 23784 The primary scientific objectives of NEAR were to return data on the bulk properties, composition, mineralogy, morphology, Facts in Brief internal mass distribution and magnetic field of Eros. Secondary objectives include studies of regolith properties, Launch Date: 1996-02- interactions with the solar wind, possible current activity as 17 indicated by dust or gas, and the asteroid spin state. This data Launch Vehicle: Delta NEAR Shoemaker will be used to help understand the characteristics of asteroids II 7925 in general, their relationship to meteorites and comets, and the Launch Site: Cape conditions in the early solar system. To accomplish these Canaveral, United States goals, the spacecraft is equipped with an X-ray/gamma ray Mass: 487.0 kg spectrometer, a near infrared imaging spectrograph, a multi- Nominal spectral camera fitted with a CCD imaging detector, a laser Power: 1800.0 W rangefinder, and a magnetometer. A radio science experiment was also performed using the NEAR tracking system to estimate the gravity field of the asteroid. The total mass of the Funding Agency instruments is 56 kg, and they require 81 W power. NASA-Office of Space Science Applications Mission Profile (United States) The ultimate goal of the mission was to study the near Earth asteroid 433 Eros from orbit for approximately one year. Eros is an S-class asteroid approximately 13 x 13 x 33 km in size, Disciplines the second largest near-Earth asteroid. Initially the orbit was circular with a radius of 200 km. The radius of the orbit was Planetary Science brought down in stages to a 50 x 50 km orbit on 30 April 2000 Space Physics and decreased to 35 x 35 km on 14 July 2000. The orbit was raised over succeeding months to a 200 x 200 km orbit and then slowly decreased and altered to a 35 x 35 km retrograde Additional orbit on 13 December 2000. The mission ended with a Information touchdown in the "saddle" region of Eros on 12 February 2001. Launch/Orbital information for NEAR After launch on a Delta 7925-8 (a Delta II Lite launch vehicle Shoemaker with nine strap-on solid-rocket boosters and a Star 48 (PAM-D) third stage) and exit from Earth orbit, NEAR entered the first PDMP information for part of its cruise phase. It spent most of this phase in a NEAR Shoemaker minimal activity "hibernation" state, which ended a few days Telecommunications before the flyby of the 61 km diameter asteroid 253 Mathilde information for NEAR on June 27, 1997. The spacecraft flew within 1200 km of Shoemaker Mathilde at 12:56 UT at 9.93 km/sec, returning imaging and other instrument data. On July 3, 1997 NEAR executed the Experiments on NEAR first major deep space maneuver, a two-part burn of the main Shoemaker 450 Newton thruster. This decreased the velocity by 279 m/sec and lowered perihelion from 0.99 AU to 0.95 AU. The Data collections from Earth gravity assist swingby occurred on January 23, 1998 at NEAR Shoemaker 7:23 UT. The closest approach was 540 km, altering the orbital http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-008A[08/06/2011 23:25:37] NASA - NSSDC - Spacecraft - Details
inclination from 0.5 to 10.2 degrees, and the aphelion distance from 2.17 to 1.77 AU, nearly matching those of Eros. Instrumentation was active at this time. Questions or comments about this spacecraft can The first of four scheduled rendezvous burns on 20 December be directed to: Dr. David R. 1998 at 22:00 UT aborted due to a software problem. Contact Williams. was lost immediately after this and was not re-established for over 24 hours. The original mission plan called for these four burns to be followed by an orbit insertion burn on 10 January 1999, but the abort of the first burn and loss of communication made this impossible. A new plan was put into effect in which NEAR flew by Eros on 23 December 1998 at 18:41:23 UT at a speed of 0.965 km/s and a distance of 3827 km from the center of mass of Eros. Images of Eros were taken by the camera, data was collected by the near IR spectrograph, and radio tracking was performed during the flyby. A rendezvous maneuver was performed on 3 January 1999 involving a thruster burn to match NEAR's orbital speed to that of Eros. A hydrazine thruster burn took place on 20 January to fine-tune the trajectory. On 12 August a 2 minute thruster burn slowed the spacecraft velocity relative to Eros to 300 km/hr.
Orbit insertion around Eros occurred on 14 February 2000 at 15:33 UT (10:33 AM EST) after NEAR completed a 13 month heliocentric orbit which closely matched the orbit of Eros. A rendezvous maneuver was completed on 3 February at 17:00 UT, slowing the spacecraft from 19.3 to 8.1 m/s relative to Eros. Another maneuver took place on 8 February increasing the relative velocity slightly to 9.9 m/s. Searches for satellites of Eros took place on 28 January, and 4 and 9 February, none were found. The scans were for for scientific purposes and to mitigate any chances of collision with a satellite. NEAR went into a 321 x 366 km orbit around Eros on 14 February. The orbit was slowly decreased to a 35 km circular polar orbit by 14 July. NEAR remained in this orbit for 10 days and then was backed out in stages to a 100 km circular orbit by 5 September 2000. Maneuvers in mid-October led to a flyby of Eros within 5.3 km of the surface at 07:00 UT on 26 October.
Following the flyby NEAR moved to a 200 km circular orbit and shifted the orbit from prograde near-polar to a retrograde near- equatorial orbit. By 13 December 2000 the orbit was be shifted back to a circular 35 km low orbit. where NEAR will remain until the nominal end of mission on 12 February 2001. Starting on 24 January 2001 the spacecraft began a series of close passes (5 to 6 km) to the surface and on 28 January passed 2 to 3 km from the asteroid. The spacecraft made a slow controlled descent to the surface of Eros ending with a touchdown in the "saddle" region of Eros on 12 February 2001 at 20:01:52 UT (3:01:52 p.m. EST). This was the first spacecraft touchdown on an asteroid. After landing, the spacecraft continued to operate until the final contact was made on 28 February. The gamma-ray spectrometer collected data from the asteroid's surface over this time. A later attempt to contact the spacecraft on 10 December 2002 was unsuccessful.
Spacecraft and Subsystems The spacecraft has the shape of an octagonal prism, approximately 1.7 m on a side, with four fixed gallium arsenide solar panels in a windmill arrangement, a fixed 1.5 m X-band high-gain radio antenna with a magnetometer mounted on the antenna feed, and an X-ray solar monitor on one end (the forward deck), with the other instruments fixed on the opposite end (the aft deck). Most electronics are mounted on the inside of the decks. The propulsion module is contained in the interior.
The craft is three-axis stabilized and uses a single bipropellant
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(hydrazine / nitrogen tetroxide) 450 Newton (N) main thruster, and four 21 N and seven 3.5 N hydrazine thrusters for propulsion, for a total delta-V potential of 1450 m/s. Attitude control is achieved using the hydrazine thrusters and 4 reaction wheels. The propulsion system carries 209 kilograms of hydrazine and 109 kilograms of NTO oxidizer in two oxidizer and three fuel tanks.
Power is provided by four 1.8 by 1.2 meter gallium arsenide solar panels which can produce 400 W at 2.2 AU (NEAR's maximum distance from the Sun) and 1800 W at 1 AU. Power is stored in a 9 amp-hour, 22-cell rechargeable super nickel- cadmium battery.
Spacecraft guidance is achieved through the use of a sensor suite of five digital solar attitude detectors, an inertial measurement unit, (IMU) and a star tracker camera pointed opposite the instrument pointing direction. The IMU contains hemispherical resonator gyros and accelerometers. Four reaction wheels (arranged so that any three can provide complete three-axis control) are used for normal attitude control. The thrusters are used to dump angular momentum from the reaction wheels, as well as for rapid slew and propulsive maneuvers. Attitude control is to 0.1 degree, line-of- sight pointing stability is within 50 microradians over 1 second, and post-processing attitude knowledge is to 50 microradians.
The command and data handling subsytem is composed of two redundant command and telemetry processors and solid state recorders, a power switching unit, and an interface to two redundant 1553 standard data buses for communications with other subsystems. The solid state recorders are constructed from 16 Mbit IBM Luna-C DRAMs. One recorder has 1.1 Gbits of storage, the other has 0.67 Gbits.
The NEAR mission was the first launch of NASA's Discovery program, a series of small-scale spacecraft designed to proceed from development to flight in under three years for a cost of less than $150 million. The total cost of the mission was $220.5 million, which included $43.5 million for the launch vehicle and $60.8 million for mission operations after launch.
Personnel
Name Role Original Affiliation E-mail Dr. John Kerridge Program NASA Headquarters Scientist Mr. Thomas B. Project Applied Physics [email protected] Coughlin Manager Laboratory Dr. Robert W. Mission Applied Physics [email protected] Farquhar Manager Laboratory Dr. Elizabeth E. Program NASA Headquarters [email protected] Beyer Manager Dr. Andrew F. Project Applied Physics [email protected] Cheng Scientist Laboratory
Selected References
Cheng, A. F., Near Earth Asteroid Rendezvous: Mission overview, Space Sci. Rev., 82, No. 1-2, 3-29, 1997.
Cheng, A. F., et al., Near-Earth Asteroid Rendezvous: Mission overview, J. Geophys. Res., 102, No. E10, 23695-23708, Oct. 1997.
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Dunham, D. W., et al., Implementation of the first asteroid landing, Icarus, 159, No. 2, 433-438, Oct. 2002.
Prockter, L., et al., The NEAR Shoemaker mission to asteroid 433 Eros, Acta Astronaut., 51, No. 1-9, 491-500, 2002.
NEAR data is currently being validated and prepared for archive. The preliminary data sets can be found at the PDS Small Bodies Node Archive.
Diagram showing location of NEAR science instruments
NSSDC NEAR Home Page - Links to further information on NEAR Images of Eros
Images from the Earth Flyby Images from the Eros and Mathilde Flybys
Asteroid Fact Sheet NSSDC Asteroid Home Page Information on NASA's Discovery program
NEAR project home page Low-cost innovation in spaceflight - The NEAR Shoemaker mission (3.3 Mb PDF)
Information on the NEAR Mission Profile and Trajectory
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-008A[08/06/2011 23:25:37] NEAR (Discovery 2, Shoemaker)
NEAR (Near Earth Asteroid Rendezvous) was a mission to rendezvous and orbit around an near earth asteroid (433 Eros). On the cruise to Eros, it flew by asteroid 253 Mathilde on 27 Jun 1997 and flew by earth on 23 January 1998. After failing to insert itself into Eros' orbit in January 1999, NEAR finally inserted itself into orbit around the asteroid on the second try on 14 February NEAR [NASA] 2000. Initially in a 323 km x 370 km orbit, it lowered its altitude during observation. After reaching orbit, NEAR was renamed NEAR-Shoemaker.
After completing its one year mission, NEAR Shoemaker gently landed on the tips of two solar panels and its bottom edge on February 12, 2001. The spacecraft snapped 69 detailed pictures during the final 5 km of its descent, the highest resolution images ever obtained of an asteroid, showing features as small as one centimeter across. The slow touchdown speed left the spacecraft intact and still sending a signal back to Earth. NASA decided to extend the mission to February 28th, to get "bonus science" from the spacecraft, which had already collected 10 times more data than originally planned. This allowed the gamma-ray spectrometer to collect data from an ideal vantage point about four inches (10 cm) from the surface
The primary scientific goals were to measure the asteroid's:
bulk properties (size, shape, volume, mass, gravity field, and spin state); surface properties (elemental and mineral composition, geology, morphology, and texture); internal properties (mass distribution and magnetic field).
Science instruments:
MultiSpectral Imager (MSI) - a refractive telescope with passively cooled Si CCD array (244 x 537) that will determine the overall size, shape, and spin characteristics of the asteroid, map the morphology and composition of the surface, and search for satellites of Eros.2.25 x 2.9 deg FOV, 10-16 meter resolution from 100 km altitude, sensitive between 400 and 1100 nm. X-Ray/Gamma-Ray Spectrometer (XGRS) - containing two sensors (an X-ray fluorescence spectrometer and a gamma-ray spectrometer), XGRS will be used to determining the surface/near-surface elemental composition of the asteroid. Near-Infrared Spectrograph (NIS) - a spectrometer covering 800-2700 nm, NIS is designed to map the mineralogical composition of Eros. Magnetometer - a three-axis fluxgate sensor that will be used to measure Eros' magnetic field. These measurements will help determine the internal composition of the asteroid. NEAR Laser Rangefinder (NLR) - an altimeter that uses a solid-state pulsed laser to measure the distance between the spacecraft and the surface of the asteroid. It will be used to make will make accurate measurements of the asteroid's shape and detailed surface structure. Nd-YAG laser operating at 1.064 mm wavelength, 6 meter resolution, 50 km range. Radio Science - uses the satellite's telemetry system to map Eros' gravity field.
Nation: USA Type / Application: Asteroid Orbiter / Lander Operator: NASA Contractors: Johns Hopkins University Applied Physics Laboratory (APL) Equipment: MSI, XGRS, NIS, NLR Configuration: Octagonal Prism, 1.5 m dish antenna, 4 deployed fixed solar arrays Propulsion: LEROS-1 Lifetime: Mass: 818 kg Orbit: Heliocentric, later orbit around Asteroid 433 Eros, finally landed on Eros
Satellite Date LS Launcher Remarks: NEAR (Discovery 2, Shoemaker) 17.02.1996 CC LC-17B Delta-7925-8
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Personnel OAST Flyer
Publications NSSDC ID: 1996-001B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events OAST Flyer (NASA's Office of Aeronautical and Space 23763 Technology Flyer) is an American minispacecraft that was released from the shuttle STS 72. It carried 4 experimental packages: to measure spacecraft contamination levels at low- Facts in Brief earth orbits, to test GPS equipment, to test amateur radio Launch Date: 1996-01- gear, and finally to determine the effects of solar radiation on 11 the explosives aboard satellite systems. Launch Vehicle: Shuttle Launch Site: Cape Canaveral, United States
Funding Agency
NASA-Office of Aeronautics and Space Technology (United States)
Disciplines
Communications Navigation & Global Positioning Solar Physics
Additional Information
Launch/Orbital information for OAST Flyer
Experiments on OAST Flyer
Data collections from OAST Flyer
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel ORFEUS-SPAS II
Publications NSSDC ID: 1996-065B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The ORFEUS-SPAS II mission followed the ORFEUS-SPAS I STS 80/ ORFEUS mission flown in 1993, motivated by improvements in ORFEUS II instrument performance and the critical need for additional observation time. The purpose of the ORFEUS-SPAS II 24661 mission was to conduct investigations of celestial sources in the far and extreme ultraviolet spectral range, and to increase Facts in Brief understanding of the evolution of stars, the structure of galaxies, and the nature of the interstellar medium. ORFEUS- Launch Date: 1996-11- SPAS II was one of a series of planned joint DARA (German 20 Space Agency) /NASA missions. The name arises from the Launch reusable Astro-Shuttle Pallet Satellite (Astro-SPAS), and the Vehicle: Shuttle Orbiting Retrievable Far and Extreme Ultraviolet Launch Site: Cape Spectrometers (ORFEUS) Telescope carried on Astro-SPAS. Canaveral, United States Mass: 3500.0 kg ORFEUS-SPAS was a free-flying platform designed to be deployed and retrieved from the space shuttle. The Astro- SPAS carrier was powered by batteries, and data from the Funding Agencies instruments were stored on tape. Absolute pointing was NASA-Office of Space accurate to within a few arc seconds. ORFEUS-SPAS is 4.5m Science Applications in length and has a 2.5m width base. Operation of ORFEUS- (United States) SPAS was approximately 40km from the shuttle. German Space Agency ORFEUS-SPAS II carried the same three spectrometers, (Federal Republic of operating over the wavelength range 400 - 1250 Angstroms, as Germany) was carried on ORFEUS-SPAS I. The Tubingen Ultraviolet Echelle Spectrometer (TUES) and the Berkeley Extreme and Discipline Far-UV Spectrometer (BEFS) were housed on the primary instrument - the ORFEUS 1-m telescope. The Interstellar Astronomy Medium Absorption Profile Spectrograph (IMAPS) was operated independently from ORFEUS. Additional The ORFEUS-SPAS II mission was flown in November- Information December 1996. The mission acquired spectra of numerous Launch/Orbital celestial objects during 14 days of observations. Efficiency of information for ORFEUS- 62.5% for all instruments was achieved. SPAS II
Experiments on ORFEUS- SPAS II
Data collections from ORFEUS-SPAS II
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Personnel OSL
Publications NSSDC ID: OSL Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The main objective of the Orbiting Solar Laboratory (OSL) is to Orbiting Solar Lab acquire images of the solar surface with the high spatial resolution required for the determination of density, temperature, magnetic field, and non-thermal velocity field in Facts in Brief solar features on the scale at which many basic physical Launch Date: 1995-12- processes occur -- less than 0.2 arcsec. In addition, high- 31 resolution spectroscopy is performed. OSL consists of five Launch Vehicle: Delta instruments. The main telescope uses an f/24 on-axis II Gregorian configuration with primary mirror 1.1 m in diameter, Launch Site: Cape useful throughout the 220 - 1000 nm range and providing a 3.9 Canaveral, United States arcmin field of view with 0.15 arcsec resolution. Three Mass: 3364.0 kg instruments make up the Coordinated Instrument Package (CIP) and share the focal plane at the Gregorian focus. These instruments obtain narrow-band and broad-band filtergrams as Funding Agencies well as high-resolution spectrograms. Charge-coupled Device (CCD) cameras are employed in each instrument in the CIP NASA-Office of Space while the remaining instrument packages use self-contained Science (United States) telescopes and acquire high-resolution UV spectra and XUV NASA-Office of Space and X-ray images. A finder telescope provides a continuous Science Applications full-Sun image for reference by users of the other, limited field- (United States) of-view instruments. The OSL spacecraft is three-axis stabilized, with pointing accuracy of 9 arcsec in pitch/yaw and 30 arcmin in roll; image motion compensation is carried out Discipline within the individual instruments to achieve better than 0.2 Solar Physics arcsec stability. A polar, Sun-synchronous orbit is used to achieve more than 250 full-Sun days per year. Solar arrays provide power. The Tracking and Data Relay Satellite System Additional (TDRSS) contact provides 2E7 bit/s telemetry for eight Information hours/day on average. The mission is planned for three years or longer and mission operations are to include near-realtime Launch/Orbital targeting during TDRSS contacts. Further information may be information for OSL obtained through D. F. Spicer (NASA-GSFC), Project Scientist. Experiments on OSL
Data collections from OSL
Questions or comments about this spacecraft can be directed to: Dr. H. Kent Hills.
Personnel
Name Role Original Affiliation E-mail Ms. Maureen C. Project NASA Headquarters mlocke@hst-
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Locke Manager popb8.gsfc.nasa.gov Dr. J. David Program NASA Headquarters Bohlin Scientist Dr. Daniel S. Project NASA Goddard Space [email protected] Spicer Scientist Flight Center Mr. Roger A. Project NASA Goddard Space Mattson Manager Flight Center
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Personnel Palapa C-1
Publications NSSDC ID: 1996-006A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Palapa C-1 was an Indonesian geosynchronous spacecraft 23779 launched from Cape Canaveral by an Atlas 2AS rocket. It will provide voice and TV communications to the 17,000 islands of Indonesia, and the nearby Asian-Pacific region. It carried 24 C- Facts in Brief band, 6 extended C-band, and 4 Ku-band transponders, most Launch Date: 1996-01- of which were leased to several countries. 31 Launch Vehicle: Atlas- 2 AS Launch Site: Cape Canaveral, United States
Funding Agency
Unknown (Indonesia)
Discipline
Communications
Additional Information
Launch/Orbital information for Palapa C- 1
Experiments on Palapa C- 1
Data collections from Palapa C-1
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Palapa C-2
Publications NSSDC ID: 1996-030A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Palapa C-2 was an Indonesian geosynchronous 23864 communications satellite that was launched from Kourou, French Guiana, by an Ariane 44L rocket. With its 34 transponders and parked at 113 E longitude, it is expected to Facts in Brief provide voice and vision communications to a large area Launch Date: 1996-05- bounded by Iran, Vlodivostok, Australia and New Zealand. 15 Launch Vehicle: Ariane 44LP Launch Site: Kourou, French Guiana
Funding Agency
Unknown (Indonesia)
Discipline
Communications
Additional Information
Launch/Orbital information for Palapa C- 2
Experiments on Palapa C- 2
Data collections from Palapa C-2
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel PAMS-STU
Publications NSSDC ID: 1996-032D Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events PAMS-STU was a NASA experimental spacecraft launched 23876 from STS 77 to test an attitude stabilization design. It had an unbalanced mass distribution and two magnetic rods. The interaction of the rods with Earth's magnetic field was expected Facts in Brief to damp any wobble or spin. There were some problems in Launch Date: 1996-05- ascertaining the success fully because of the malfunction of 22 the laser ranger. It reentered the atmosphere on October 26. Launch Vehicle: Shuttle Launch Site: Cape Canaveral, United States Mass: 35.0 kg
Funding Agency
National Aeronautics and Space Administration (United States)
Discipline
Technology Applications
Additional Information
Launch/Orbital information for PAMS- STU
Experiments on PAMS- STU
Data collections from PAMS-STU
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel PANAMSAT 3R
Publications NSSDC ID: 1996-002A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events PAS 3R, also known as PANAMSAT 3R, as an American PAS 3R geostationary communications spacecraft launched by an Intelsat 3R Ariane 44L rocket from the Kourou Space Center in French Guiana. After parking at 43.0 W longitude, the 2,900 kg IS-3R spacecraft will provide TV and communications services to 23764 North and South American countries through its 16 C-band transponders. Facts in Brief
Launch Date: 1996-01- 12 Launch Vehicle: Ariane 44L Launch Site: Kourou, French Guiana Mass: 2900.0 kg
Funding Agencies
Pan American Satellite (United States) International Telecommunications Satellite Corporation (International)
Discipline
Communications
Additional Information
Launch/Orbital information for PANAMSAT 3R
Experiments on PANAMSAT 3R
Data collections from PANAMSAT 3R
Questions or comments about this spacecraft can be directed to: Coordinated
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Request and User Support Office.
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Personnel Polar
Publications NSSDC ID: 1996-013A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events POLAR is one of four spacecraft in the Global Geospace Polar Plasma Laboratory Science (GGS) program. These are among the six spacecraft GGS/Polar in the International Solar Terrestrial Physics (ISTP) program. POLAR provides multi-wavelength imaging of the aurora, ISTP/Polar measuring plasma entry into the polar magnetosphere and 23802 geomagnetic tail, the flow of plasmas to and from the ionosphere, and the deposition of particle energy in the ionosphere and upper atmosphere. POLAR has on-board Facts in Brief propulsion systems and a design lifetime of three to five years, Launch Date: 1996-02- with redundant subsystems. POLAR is cylindrical, 24 approximately 2.8 m in diameter by 1.25 m high (plus 1.25 m Launch Vehicle: Delta for its two despun platforms), with body-mounted solar cells, II weighs 1250 kg and uses 333 W of power. The spin rate is 10 Launch rpm around an axis approximately normal to the orbital plane. It Site: Vandenberg AFB, has long wire spin-plane antennas, inertial booms, and spin- United States plane appendages to support sensors. POLAR has two Mass: 1300.0 kg despun gimbaled instrument platforms, and booms are deployed along both Z axes. Data are stored using on-board tape recorders and are relayed to the Deep Space Network at Funding Agency 600 kbps maximum (250 kbps nominal) although the average NASA-Office of Space Polar real-time data rate for POLAR is 41.6 kbps. POLAR has a 22.6-h polar orbit (90 deg inclination), with perigee and apogee Science Applications of 11,500 and 57,000 km. Polar was launched to observe the (United States) polar magnetosphere and, as its orbit has precessed with time, has observed the equatorial inner magnetosphere and is now Discipline carrying out an extended period of southern hemisphere coverage. Details on the POLAR mission and instrumentation Space Physics are provided in Space Science Reviews (Vol. 71, Nos. 1-4, 1995) and reprinted in The Global Geospace Mission, edited by C. T. Russell (Kluwer, 1995). Additional Information
Launch/Orbital information for Polar PDMP information for Polar
Experiments on Polar
Data collections from Polar
Questions or comments about this spacecraft can be directed to: Dr. Timothy E. Eastman.
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Personnel
Name Role Original Affiliation E-mail Dr. Keith W. Mission Principal NASA Goddard Space [email protected] Ogilvie Investigator Flight Center Dr. John B. Project Scientist NASA Goddard Space Sigwarth Flight Center Dr. Charles Program Scientist NASA Headquarters [email protected] P. Holmes
Other Sources of Polar Data/Information
ISTP Home Page
Charge and Mass Magnetospheric Ion Composition Experiment (CAMMICE) and Comprehensive Energetic Particle and Pitch Angle Distribution (CEPPAD) teams Electric Fields Investigation (EFI) team Hot Plasma Analyzer (Hydra) team Magnetic Fields Experiment (MFE) team Polar Ionospheric X-ray Imaging Experiment (PIXIE) team Plasma and Radio Waves Instrument (PWI) team Thermal Ion Dynamics Experiment (TIDE) team Toroidal Imaging Mass-Angle Spectrograph (TIMAS) team Ultraviolet Imager (UVI) team Visible Imaging System (VIS) team
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Personnel Priroda
Publications NSSDC ID: 1996-023A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Priroda was the last of the scheduled 5 Russian modules of Mir 23848 and was launched from the Baykonur cosmodrome by a Proton-K rocket to dock after 3 days rather than the usual 9 days. The launch itself was 3 days earlier than the planned Facts in Brief date in order to facilitate an American microbiology program. Launch Date: 1996-04- Priroda carried 900 kg of American equipment to be delivered 23 to the American astronaut on Mir. Other cargo on board Launch included several remote sensing Russian instruments. It is Vehicle: Proton-K likely that Priroda may later be attached to the planned Launch Site: Tyuratam international space station, Alpha. (Baikonur Cosmodrome), Kazakhstan Mass: 19000.0 kg
Funding Agency
Unknown (Russia)
Disciplines
Earth Science Resupply/Refurbishment/Repair
Additional Information
Launch/Orbital information for Priroda
Experiments on Priroda
Data collections from Priroda
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Progress M-31
Publications NSSDC ID: 1996-028A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events An improved version of cargo freighters used to supply the Mir 23860 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: 1996-05- Spare propellent in Progress M's tanks can be transferred to 05 Mir before it is consigned to burn up in reentry. In the past, Launch extra fuel was abandoned with the craft. Future Progress Vehicle: Soyuz-U vehicles will carry a recoverable reentry capsule for the speedy Launch Site: Tyuratam return of up to 150 kg of material from Mir to earth. (Baikonur Cosmodrome), Kazakhstan Progress M-31 was launched by a Soyuz U rocket from the Mass: 7250.0 kg Baykonur cosmodrome. It docked with Mir and delivered 3000 kg of food, fuel and water. It undocked on August 1 at 16:45 UT and was deorbited over the south Pacific later that day. Funding Agency
Unknown (Russia)
Discipline
Resupply/Refurbishment/Repair
Additional Information
Launch/Orbital information for Progress M-31
Experiments on Progress M-31
Data collections from Progress M-31
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Progress M-32
Publications NSSDC ID: 1996-043A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events An improved version of cargo freighters used to supply the Mir 24071 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: 1996-07- Spare propellent in Progress M's tanks can be transferred to 31 Mir before it is consigned to burn up in reentry. In the past, Launch extra fuel was abandoned with the craft. Future Progress Vehicle: Soyuz-U vehicles will carry a recoverable reentry capsule for the speedy Launch Site: Tyuratam return of up to 150 kg of material from Mir to earth. (Baikonur Cosmodrome), Kazakhstan Progress M-32 was launched from the Baikonur cosmodrome Mass: 2500.0 kg aboard a Soyuz-U rocket. It delivered 2,500 kg of supplies and equipment to the Mir space station. Funding Agency
Unknown (Russia)
Discipline
Resupply/Refurbishment/Repair
Additional Information
Launch/Orbital information for Progress M-32
Experiments on Progress M-32
Data collections from Progress M-32
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Progress M-33
Publications NSSDC ID: 1996-066A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events An improved version of cargo freighters used to supply the Mir 24633 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: 1996-11- Spare propellent in Progress M's tanks can be transferred to 19 Mir before it is consigned to burn up in reentry. In the past, Launch extra fuel was abandoned with the craft. Future Progress Vehicle: Soyuz-Y vehicles will carry a recoverable reentry capsule for the speedy Launch Site: Tyuratam return of up to 150 kg of material from Mir to earth. (Baikonur Cosmodrome), Kazakhstan Progress M-33 was launched by a Soyuz-Y rocket from the Baykonur cosmodrome. It delivered 2,400 kg of food, fuel and equipment. Funding Agency
Unknown (Russia)
Discipline
Resupply/Refurbishment/Repair
Additional Information
Launch/Orbital information for Progress M-33
Experiments on Progress M-33
Data collections from Progress M-33
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Raduga 33
Publications NSSDC ID: 1996-010A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Raduga 33 was a Russian communications spacecraft 23794 launched by a Proton-K rocket from the Baykonur Cosmodrome. It was intended to be geostationary but it turned out to be a failed launch due to the explosion of the fourth Facts in Brief stage just prior to the final maneuver. Launch Date: 1996-02- 19 Launch Vehicle: Proton-K Launch Site: Tyuratam (Baikonur Cosmodrome), Kazakhstan Mass: 1965.0 kg
Funding Agency
Russian Space Agency (Russia)
Discipline
Communications
Additional Information
Launch/Orbital information for Raduga 33
Experiments on Raduga 33
Data collections from Raduga 33
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel REX 2
Publications NSSDC ID: 1996-014A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events REX 2 (Radiation EXperiment 2) was an American military 23814 minispacecraft launched from Vandenberg AFB by a Pegasus XL rocket. The rocket was carried aloft in the belly of a L-1011 aircraft to 12 km altitude before release and ignition. It is an Air Facts in Brief Force Rome Laboratory ionospheric research satellite which Launch Date: 1996-03- will test the effects of the atmosphere on radio transmissions, 08 and will employ GPS for on-board navigation and attitude Launch control. Vehicle: Pegasus XL Launch Site: Vandenberg AFB, United States Mass: 110.0 kg
Funding Agency
Unknown (United States)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for REX 2
Experiments on REX 2
Data collections from REX 2
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel SAC-B
Publications NSSDC ID: 1996-061B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Satellite de Aplicaciones Cientifico-B (SAC-B) was a small Satelite de Aplicaciones satellite built by the Argentinean National Commission of Cientificas - B Space Activities (CoNAE). SAC-B was designed to advance 24645 the study of solar physics and astrophysics through the examination of solar flares, gamma ray bursts, diffuse X-ray cosmic background, and energetic neutral atoms. The satellite Facts in Brief was also designed to test and characterize the performance of new equipment and technologies which may be used in future Launch Date: 1996-11- operational or scientific missions. The satellite payload 04 included three astronomical instruments - the Hard X-ray Launch Spectrometer (HXRS), the Goddard X-ray Experiment (GXRE), Vehicle: Pegasus XL and the Cosmic Unresolved X-ray Background Instrument Launch Site: Wallops (CUBIC). Also flying was an Italian instrument called ISENA Island, United States which plans to measure energetic netral atoms. The spacecraft Mass: 181.0 kg body was a 62 x 62 cm wide by 80 cm high rectangular parallelepiped wotj 4 extended solar panels 62 cm wide by 76 Funding Agencies cm long. NASA-Office of Space SAC-B satellite was launched with the NASA satellite HETE 1. Science (United States) The SAC-B solar arrays did not automatically deploy due to a National Commission of battery failure in the Pegasus XL rocket third stage. The solar Space Activities arrays were deployed via ground commands, however (Argentina) because of spacecraft tumbling and shadowing of the Pegasus XL third stage, they were unable to generate enough power to keep the satellite's batteries charged. Disciplines
Astronomy Solar Physics Space Physics
Additional Information
Launch/Orbital information for SAC-B
Experiments on SAC-B
Data collections from SAC- B
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
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Personnel SAX
Publications NSSDC ID: 1996-027A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events SAX is the X-Ray Astronomy Satellite selected by the Italian Satellite for X-Ray National Space Plan for inclusion in the Science Plan. The Astronomy objective of the mission is to perform spectroscopic and time Beppo-SAX variability studies of celestial X-ray sources in the energy band from 1 to 200 keV, including an all-sky monitoring investigation 23857 of transients in the 2-30 keV energy range. The payload includes the following narrow-field detectors coaligned to a Facts in Brief common pointing axis: (1) four X-ray imaging concentrators sensitive from 1 to 10 keV (one of them extending down to 0.1 Launch Date: 1996-04- keV), (2) one gas scintillation proportional counter sensitive 30 from 3 to 12 keV, and (3) a sodium iodide scintillator crystal in Launch Vehicle: Atlas- phoswich configuration operating from 15 to 200 keV. At 90 Centaur deg to the axis of the narrow field instruments is an array of Launch Site: Cape three identical wide field camera units sensitive from 2 to 30 Canaveral, United States keV. The SAX mission payload and science program is under Mass: 900.0 kg the responsibility of a consortium of Italian institutes together with institutes from Holland. The participation of the Space Science Department of ESA is also foreseen. A listing of the Funding Agency SAX Consortium of Institutes is given in Appendix B8. Agenzia Spaziale Italiana (Italy)
Discipline
Astronomy
Additional Information
Launch/Orbital information for SAX
Experiments on SAX
Data collections from SAX
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
US Active Arvhive for Beppo-SAX Information/Data
The Beppo-SAX Data Archive at HEASARC
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Other Sources of SAX Information/Data
Beppo-SAX home page (Italian Space Agency)
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Personnel Soyuz-TM 23
Publications NSSDC ID: 1996-011A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Soyuz TM-33 was a Russian transportation spacecraft that 23798 was launched from the Baykonur Cosmodrome carrying 2 cosmonauts. It docked with the Mir space station on February 23rd. Facts in Brief Launch Date: 1996-02- Designed and manufactured by RKK Energiya, the Soyuz TM 21 was capable of carrying three cosmonauts and had a gross Launch Vehicle: Soyuz weight of just over seven metric tons, a length of seven Launch Site: Tyuratam meters, and a maximum diameter of 2.7 m. The spacecraft (Baikonur Cosmodrome), consisted of three main sections: the orbital module, the Kazakhstan command and reentry module, and the service module. Two Mass: 7150.0 kg solar arrays (10.6 m span) provided electrical power for the typical 50-hour journey to Mir and could be interconnected with the space station's electrical system to furnish additional 1.3 Funding Agency kW. The nominal flight time for Soyuz TM spaceship was 5-6 months. Unknown (Russia)
Discipline
Human Crew
Additional Information
Launch/Orbital information for Soyuz-TM 23
Experiments on Soyuz-TM 23
Data collections from Soyuz-TM 23
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-011A[08/06/2011 23:34:47] Soyuz TM-23
Launch, orbit and landing data
Launch date: 21.02.1996 Launch time: 12:34 UT Launch site: Baikonur Launch pad: 1 Altitude: 201 - 246 km Inclination: 51,6° Landing date: 02.09.1996 Landing time: 07:41 UT Landing site: 50° 17' N, 70° 50' E
Crew No Orbit Surname Given name Job Flight No. Duration . s Onufriyenk 1 Yuri Ivanovich Commander 1 193d 19h 07m 3066 o Yuri Flight 2 Usachyov 2 193d 19h 07m 3066 Vladimirovich Engineer Crew seating arrangement
Launch Landing 1 Onufriyenko 1 Onufriyenko 2 Usachyov 2 Usachyov 3 3 André-Deshays
Double Crew
No Surname Given name Job . Tsibliye Vasili Commande 1 v Vasiliyevich r Aleksandr Flight 2 Lazutkin Ivanovich Engineer
Flight Launch from Baikonur; landing 107 km southwest of Akmola.
Docking on MIR spacestation; both cosmonauts became the 21st resident crew after crew exchanging; both cosmonauts performed six EVA`s on 15.03.1996 (5h 51m), 20.05.1996 (5h 20m), 24.05.1996 (5h 43m), 30.05.1996 (4h 20m), 06.06.1996 (3h 34m) and 13.06.1996 (5h 42m) carrying out following work: installation of the telescopic boom, the MSCA solar array, the multi-spectral scanner, exchanging materials samples and deploying of a radar antenna; protein crystal growth experiments; more experiments in materials science using high temperture melting oven "Optizon"; module "Priroda" arrived on 26.04.1996; supplies arrived with cargo spacecraft Progress M-31.
Crew was visited by crew of STS-76; since that time (24.03.1996) U.S. astronaut Shannon Lucid completed resident crew.
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Personnel Soyuz-TM 24
Publications NSSDC ID: 1996-047A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Soyuz TM-24 carried a crew of three to the Mir space station. 24280 The crew consisted of Cosmonauts Valery Korzun and Alexander Kalery, and the first French woman in space, Claudie Andre-Deshays. They joined American astronaut Facts in Brief Shannon Lucid and Mir 21 crewmates Yuri Onufriyenko and Launch Date: 1996-08- Yuri Usachev. Andre-Deshays carried out biological and 18 medical experiments on Mir for 16 days before returning to Launch Earth with Onufriyenko and Usachev. Vehicle: Soyuz-U Launch Site: Tyuratam (Baikonur Cosmodrome), Kazakhstan
Funding Agency
Unknown (Russia)
Discipline
Human Crew
Additional Information
Launch/Orbital information for Soyuz-TM 24
Experiments on Soyuz-TM 24
Data collections from Soyuz-TM 24
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-047A[08/06/2011 23:35:09] Soyuz TM-24
Launch, orbit and landing data
Launch date: 17.08.1996 Launch time: 13:18 UT Launch site: Baikonur Launch pad: 1 Altitude: 195,8 - 242,8 km Inclination: 51,63° Landing date: 02.03.1997 Landing time: 06:44 UT Landing site: 47° 49' N, 69° 24' E
Crew No Orbi Surname Given name Job Flight No. Duration . ts Valeri 196d 17h 3113 1 Korzun Commander 1 Grigoriyevich 26m Aleksandr 196d 17h 3113 2 Kaleri Flight Engineer 2 Yuriyevich 26m André- Research 3 Claudie 1 15d 18h 23m 249 Deshays Cosmonaut Crew seating arrangement
Launch Landing 1 Korzun 1 Korzun 2 Kaleri 2 Kaleri 3 André-Deshays 3 Ewald
Double Crew
Given No. Surname Job name Research 3 Eyharts Léopold Cosmonaut
Flight Launch from Baikonur; landing 128 km east of Dzheskasgan.
Former prime crew (Manakov and Vinogradov) was exchanged five days before launch due of medical problems of Manakov.
Docking on MIR spacestation; 22nd resident crew (first together with Shannon Lucid, later John Blaha/Jerry Linenger); French mission CASSIOPÈE; physiological and neurological experiments; crew was visited by STS-79, MIR97 and STS-81-crews; EVA`s by Korzun and Kaleri on 02.12.1996 (5h 57m) and 09.12.1996 (6h 36m), (external cable installation of the MSCA solar array).
Note André-Deshays returned to Earth on 02.09.1996 at 07:41 UT with Soyuz TM-23-spacecraft. Photos / Drawings
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Personnel Spartan 207
Publications NSSDC ID: 1996-032B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Spartan 207 was an 850 kg module released from STS 77 as 23871 a platform from which to launch an inflatable antenna (IAE). It was captured back into the shuttle soon after the antenna release. Facts in Brief Launch Date: 1996-05- 20 Launch Vehicle: Shuttle Launch Site: Cape Canaveral, United States Mass: 850.0 kg
Funding Agency
National Aeronautics and Space Administration (United States)
Discipline
Astronomy
Additional Information
Launch/Orbital information for Spartan 207
Experiments on Spartan 207
Data collections from Spartan 207
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel STS 72
Publications NSSDC ID: 1996-001A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events STS 72 was a US shuttle spacecraft launched from Cape 23762 Canaveral. It carried, released, and retrieved the OAST Flyer. It also retrieved a long orbiting Japanese reusable spacecraft, SFU, that had amassed astronomical data and material Facts in Brief science products since March 1995. Launch Date: 1996-01- 11 The primary objective of the STS-72 mission was to capture Launch and return to Earth a Japanese microgravity research Vehicle: Shuttle spacecraft known as Space Flyer Unit (SFU). The 7,885lbs Launch Site: Cape SFU spacecraft was launched by Japan's National Space Canaveral, United States Development Agency (NASDA) from Tanegashima Space Mass: 6510.0 kg Center in Japan at 8:01 UT on March 18, 1995 aboard a Japanese H-II rocket (HII-3). Funding Agency The STS-72 mission also deployed (for about 50 hours) and then retrieved the Office of Aeronautics and Space Technology NASA-Office of Space Flyer (OAST-Flyer) spacecraft. OAST-Flyer was the seventh in Flight (United States) a series of missions aboard reuseable free-flying Spartan carriers. It consisted of four experiments: Return Flux Discipline Experiment (REFLEX), Global Positioning System Attitude Determination and Control Experiment (GADACS), Solar Human Crew Exposure to Laser Ordnance Device (SELODE) and the University of Maryland Spartan Packet Radio Experiment (SPRE). Additional Information Other experiments onboard STS-72 included the Shuttle Solar Launch/Orbital Backscatter Ultraviolet Experiment (SSBUV-8) (previously information for STS 72 flown on STS-34, STS-41, STS-43, STS-45, STS-56, STS-62 and STS-66), EDFT-03, Shuttle Laser Altimeter Payload (SLA- Experiments on STS 72 01/GAS(5)), VDA-2, National Institutes of Health NIH-R3 Experiment, Space Tissue Loss Experiment (STL/NIH-C), Pool Data collections from STS Boiling Experiment (PBE) (hardware previously flown on STS- 72 47, STS-57 and STS-60) and the Thermal Energy Storage (TES-2) experiment (previously flown on STS-69).
Get Away Special payloads included the United States Air Questions or comments Force Academy G-342 Flexible Beam Experiment about this spacecraft can (FLEXBEAM-2), Society of Japanese Aerospace Companies' be directed to: Coordinated G-459 - Protein Crystal Growth Experiment and the Jet Request and User Support Propulsion Laboratory GAS Ballast Can with Sample Return Office. Experiment.
Endeavour's 10th flight also included two 6.5 hour spacewalks by three astronauts to test hardware and tools that will be used in the assembly of the International Space Station starting in late 1997. EVA-1 on flight day five consists of Crewmembers Leroy Chiao (EV1) and Dan Barry (EV2) while EVA-2 on Flight Day 7 consists of Leroy Chiao (EV1) and Winston Scott (EV2). http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-001A[08/06/2011 23:35:55] STS-72
Endeavour (10)
USA
Launch, orbit and landing data
Launch date: 11.01.1996 Launch time: 09:41 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-B Altitude: 463 km Inclination: 28,45° Landing date: 20.01.1996 Landing time: 07:41 UT Landing site: Cape Canaveral (KSC)
Crew
No. Surname Given name Job Flight No. Duration Orbits
1 Duffy Brian CDR 3 8d 22h 01m 142
2 Jett Brent Ward, Jr. PLT 1 8d 22h 01m 142
3 Chiao Leroy MSP 2 8d 22h 01m 142
4 Scott Winston Elliott MSP 1 8d 22h 01m 142
5 Wakata Koichi MSP 1 8d 22h 01m 142
6 Barry Daniel Thomas MSP 1 8d 22h 01m 142
Crew seating arrangement
Launch Landing 1 Duffy 1 Duffy 2 Jett 2 Jett 3 Chiao 3 Wakata 4 Scott 4 Scott 5 Wakata 5 Chiao 6 Barry 6 Barry
Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC).
Space Flyer Unit from Japan was captured and brought to Earth; EVA by Chiao and Barry on 15.01.1996 (6h 9m) and by Chiao and Scott on 17.01.1996 (6h 41m) to test tools and hardware that will be used in the assembly of the ISS; crew also deployed and retrieved the OAST-Flyer.
Photos / Drawings
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Personnel STS 75
Publications NSSDC ID: 1996-012A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The STS 75 mission was the 75th shuttle mission and the 19th 23801 flight of the Columbia orbiter. The primary tasks of this shuttle flight were to conduct experiments as part of the third flight of the United States Microgravity Payload (USMP-3) and to Facts in Brief deploy the joint Italian-US Tethered Satellite System (TSS- Launch Date: 1996-02- 1R). 22 Launch The TSS-1R mission was a reflight of TSS-1 which was flown Vehicle: Shuttle onboard Space Shuttle Atlantis on STS-46 in July/August of Launch Site: Cape 1992. During that flight, the tether was deployed a distance of Canaveral, United States 860 feet. STS-75 mission scientist hope to deploy the tether to Mass: 10592.0 kg a distance of over 12 miles (20.7km).
The Tether Satellite System circled the Earth at an altitude of Funding Agency 296 kilometers which placed the tether system within the rarefied electrically charged layer of the atmosphere known as NASA-Office of Space the ionosphere. The conducting tether generated high voltage Flight (United States) and electrical currents as it moved through the ionosphere STS 75 across the magnetic field lines of the earth. Scientists were Disciplines able to learn more about the electrodynamics of a conducting tether system to deepen our understanding of physical Human Crew processes in the near-Earth space environment. These studies Space Physics will help provide explanations for events such as the formation and behavior of comet tails and bursts of radio "noise" detected from other planets. Additional Information The specific TSS1-R mission objectives were: characterize the current-voltage response of the TSS-orbiter system, Launch/Orbital characterize the satellites high-voltage sheath structure and information for STS 75 current collection process, demonstrate electric power generation, verify tether control laws and basic tether Experiments on STS 75 dynamics, demonstrate the effect of neutral gas on the plasma sheath and current collection, characterize the TSS radio Data collections from STS frequency and plasma wave emissions and characterize the 75 TSS dynamic-electrodynamic coupling.
TSS-1R Science Investigations include: TSS Deployer Core Questions or comments Equipment and Satellite Core Equipment (DCORE/SCORE), about this spacecraft can Research on Orbital Plasma Electrodynamics (ROPE), be directed to: Coordinated Research on Electrodynamic Tether Effects (RETE), Magnetic Request and User Support Field Experiment for TSS Missions (TEMAG), Shuttle Office. Electrodynamic Tether System (SETS), Shuttle Potential and Return Electron Experiment (SPREE), Tether Optical Phenomena Experiment (TOP), Investigation of Electromagnetic Emissions by the Electrodynamic Tether (EMET), Observations at the Earth's Surface of Electromagnetic Emissions by TSS (OESSE), Investigation and Measurement of Dynamic Noise in the TSS (IMDN), Theoretical and Experimental Investigation of TSS Dynamics http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-012A[08/06/2011 23:36:55] NASA - NSSDC - Spacecraft - Details
(TEID) and the Theory and Modeling in Support of Tethered Satellite Applications (TMST).
The USMP-3 payload consisted of four major experiments mounted on two Mission Peculiar Experiment Support Structures (MPESS) and three Shuttle Mid-deck experiments. The experiments are: Advanced Automated Directional Solidification Furnace (AADSF), Material pour l'Etude des Phenomenes Interessant la Solidification sur Terre et en Orbite (MEPHISTO), Space Acceleration Measurement System (SAMS), Orbital Acceleration Research Experiment (OARE), Critical Fluid Light Scattering Experiment (ZENO) and Isothermal Dendritic Growth Experiment (IDGE).
During this flight, the tether on TSS-1R broke after the satellite had been deployed to a distance of 19.7 km. The shuttle ended its mission after 251 orbits and a total mission duration of 15 days, 17 hours, 41 minutes, and 25 seconds.
Related Information/Data at NSSDC
TSS-1R
Other Sources of STS 75 Information/Data
STS 75 information (NASA KSC) STS 75 Electronic Photo File (NASA KSC) STS 75 Press Release images (NASA JSC)
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Columbia (19)
USA
Sour
Launch, orbit and landing data
Launch date: 22.02.1996 Launch time: 20:18 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-B Altitude: 296 km Inclination: 28,45° Landing date: 09.03.1996 Landing time: 13:58 UT Landing site: Cape Canaveral (KSC)
Crew
No. Surname Given name Job Flight No. Duration Orbits 1 Allen Andrew Michael "Andy" CDR 3 15d 17h 41m 251
2 Horowitz Scott Jay "Doc" PLT 1 15d 17h 41m 251
3 Hoffman Jeffrey Alan MSP 5 15d 17h 41m 251
4 Cheli Maurizio MSP 1 15d 17h 41m 251
5 Nicollier Claude MSP 3 15d 17h 41m 251
6 Chang-Diaz Franklin Ramon MSP 5 15d 17h 41m 251
7 Guidoni Umberto MSP 1 15d 17h 41m 251
Crew seating arrangement
Launch Landing 1 Allen 1 Allen 2 Horowitz 2 Horowitz 3 Hoffman 3 Nicollier 4 Cheli 4 Cheli 5 Nicollier 5 Hoffman 6 Chang-Diaz 6 Chang-Diaz 7 Guidoni 7 Guidoni
Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC).
Mission "US Microgravity Payload-3" with several experiment in different sientific fields; deploying of Italian Tethered Satellite System-1 failed, because the tether has broken after a distance of 19 km; satellite was lost; mission was extended one day due of bad weather on Cape Canaveral (KSC). Photos / Drawings
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Personnel STS 76
Publications NSSDC ID: 1996-018A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events STS 76 was a US shuttle mission launched from Cape 23831 Canaveral. The primary mission objective was the third docking between the Space Shuttle Atlantis and the Russian Space Station Mir. It included a crew transfer, an Facts in Brief extravehicular activity (EVA), logistics operations and scientific Launch Date: 1996-03- research. 22 Launch Rendezvous and docking with Mir was scheduled to occur on Vehicle: Shuttle flight day three using the same approach as previously used Launch Site: Cape during STS-74. Docking occured between the Orbiter Docking Canaveral, United States System in the forward area of Atlantis' payload bay and the Mass: 6753.0 kg Docking Module installed during STS-74 on Mir's Kristall module docking port. Funding Agency The mission also featured a SPACEHAB module, middeck experiments, a Get Away Special (GAS) canister and a 6-hour NASA-Office of Space EVA. Over 1,900 pounds (862 kilograms) of equipment are Flight (United States) being transfered from Atlantis to Mir including a gyrodyne, transformer, batteries, food, water, film and clothing. Discipline
Planned Experiments included the Mir Electric Field Human Crew Characterization (MEFC) experiment, numerious European Space Agency's (ESA) Biorack life sciences experiments, the Queen's University Experiment in Liquid Diffusion (QUELD) Additional experiment, the Optizone Liquid Phase Sintering Experiment Information (OLIPSE) and a Naval Research Laboratory (NRL) Get Away Launch/Orbital Special (GAS) payload Trapped Ions in Space (TRIS) information for STS 76 experiment. TRIS measured low-energy particle radiation in the inner magnetosphere. Another experiment conducted on Experiments on STS 76 Mir during STS-76 was the Mir Wireless Network Experiment (WNE) which was launched on STS-74 in November 1995. It Data collections from STS tested the first wireless client-server network in the space 76 environment.
The mission also included KidSat, a prototype of Earth viewing cameras and instruments that allows students in grades Questions or comments Kindergarden to Grade 12 (K-12) to see and direct the capture about this spacecraft can of pictures from space. be directed to: Coordinated Request and User Support Mission Specialists Godwin and Clifford perform a six-hour Office. spacewalk on flight day six. They attached four experiments, known collectively as the Mir Environmental Effects Payload MEEP, onto handrails located on the Mir Docking Module. These experiments include the Polished Plate Micrometeoroid Debris (PPMD) experiment, the Orbital Debris Collector (ODC) experiment, and the Passive Optical Samples (POSA) I and II experiments.
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-018A[08/06/2011 23:38:05] STS-76
Atlantis (16)
Launch, orbit and landing data
Launch date: 22.03.1996 Launch time: 08:13 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-B Altitude: 296 km Inclination: 51,6° Landing date: 31.03.1996 Landing time: 13:28 UT Landing site: Edwards AFB
Crew No Orbit Surname Given name Job Flight No. Duration . s CD 1 Chilton Kevin Patrick "Chily" 3 9d 05h 16m 144 R Searfos 2 Richard Alan PLT 2 9d 05h 16m 144 s MS 3 Sega Ronald Michael 2 9d 05h 16m 144 P Michael Richard Uram MS 4 Clifford 3 9d 05h 16m 144 "Rich" P MS 5 Godwin Linda Maxine 3 9d 05h 16m 144 P MS 6 Lucid Matilda Shannon Wells 5 188d 04h 00m 2977 P
Crew seating arrangement
Launch Landing 1 Chilton 1 Chilton 2 Searfoss 2 Searfoss 3 Sega 3 Godwin 4 Clifford 4 Clifford 5 Godwin 5 Sega 6 Lucid 6
Backup Crew
No. Surname Given name Job
6 Blaha John Elmer MSP
Flight Launch from Cape Canaveral (KSC); landing on Edwards AFB; small leak of hydraulic fluid from the hydraulic system, but no Minimum Duration Flight was necessary.
Docking on MIR spacestation; Shannon Lucid became member of the 21st resident crew onboard the MIR (as research cosmonaut); during the common-flight of STS-76 and MIR Godwin and Clifford performed an EVA on 27.03.1996 (6h 2m) to attach the Mir Environmental Effects Payload (MEEP), including 4 different experiments, onto handrails located on the Mir Docking Module; after 5 days of common flight separation.
Note Lucid landed on 26.09.1996 at 12:13 UT with STS-79.
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Personnel STS 77
Publications NSSDC ID: 1996-032A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events STS 77 was a Shuttle Endeavour mission launched from Cape 23870 Canaveral. The main mission was to release an inflatable antenna, IAE. The release occurred from a platform called Spartan 207 which in turn was released from the shuttle a few Facts in Brief hours later. The third object released was an experimental 35 Launch Date: 1996-05- kg minispacecraft, PAMS-STU. STS 77 carried the usual 19 complement of crystal, metal, and biomedical experimental Launch gear along with 32,000 sea urchin eggs and a supply of sperm Vehicle: Shuttle to squirt on them, all in the Spacelab module. A new fizzy Launch Site: Cape Coca-Cola delivering experimental device failed to perform Canaveral, United States satisfactorily. Mass: 12233.0 kg
Funding Agency
NASA-Office of Space Flight (United States)
Disciplines
Human Crew Life Science
Additional Information
Launch/Orbital information for STS 77 Telecommunications information for STS 77
Experiments on STS 77
Data collections from STS 77
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-032A[08/06/2011 23:39:05] STS-77
Endeavour (11)
USA
Launch, orbit and landing data
Launch date: 19.05.1996 Launch time: 10:30 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-B Altitude: 283 km Inclination: 39° Landing date: 29.05.1996 Landing time: 11:09 UT Landing site: Cape Canaveral (KSC)
Crew
No. Surname Given name Job Flight No. Duration Orbits
1 Casper John Howard CDR 4 10d 00h 40m 161
2 Brown Curtis Lee, Jr. "Curt" PLT 3 10d 00h 40m 161
3 Thomas Andrew Sydney Withiel MSP 1 10d 00h 40m 161
4 Bursch Daniel Wheeler MSP 3 10d 00h 40m 161
5 Runco Mario, Jr. "Trooper" MSP 3 10d 00h 40m 161
6 Garneau Joseph Jean-Marie Marc MSP 2 10d 00h 40m 161
Crew seating arrangement
Launch Landing 1 Casper 1 Casper 2 Brown 2 Brown 3 Thomas 3 Runco 4 Bursch 4 Bursch 5 Runco 5 Thomas 6 Garneau 6 Garneau
Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC).
Mission "Spacehab-4"; deploying and retrieval of a SPARTAN-satellite and deploying of a PAMS/STU-satellite; several rendezvous-maneuvers with both satellites; various additional experiments in different fields.
Photos / Drawings
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Personnel STS 78
Publications NSSDC ID: 1996-036A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events STS 78 was a NASA shuttle spacecraft launched from Cape 23931 Canaveral for a 17 day mission. It carried a Spacelab (LMS-1) with many supplies and instruments for 41 microgravity experiments involving fish embryos, rats, Bonzai plants, fluid Facts in Brief dynamics, metallurgy, protein crystal growth, etc. Launch Date: 1996-06- 20 Five space agencies (NASA/USA; European Space Launch Agency/Europe; French Space Agency/France; Canadian Vehicle: Shuttle Space Agency/Canada; and Italian Space Agency/Italy) and Launch Site: Cape research scientists from 10 countries worked together on the Canaveral, United States primary payload of STS-78, the Life and Microgravity Spacelab (LMS). More than 40 experiments flown were grouped into two areas: life sciences, which included human physiology and Funding Agency space biology, and microgravity science, which included basic fluid physics investigations, advanced semiconductor and NASA-Office of Space metal alloy materials processing, and medical research in Flight (United States) protein crystal growth. Discipline LMS investigations were conducted via the most extensive telescience to date. Investigators were located at four remote Human Crew European and four remote U.S. locations, similar to what will happen with the International Space Station. The mission also made extensive use of video imaging to help crew members Additional perform inflight maintenance procedures on the experiment Information hardware. Launch/Orbital information for STS 78 Previous life science investigations have delved into what physiological changes take place in microgravity environment; Experiments on STS 78 the integrated LMS experiments explored why these changes occur. The most extensive studies ever were conducted on Data collections from STS bone and muscle loss in space. STS-78 marked the first time 78 researchers collected muscle tissue biopsy samples both before and after flight. Crew members also were scheduled to undergo Magnetic Resonance Imaging (MRI) scans almost immediately after landing. Findings from comparison of the Questions or comments biopsy samples, along with various musculoskeletal tests about this spacecraft can conducted during mission, could lead to effective be directed to: Coordinated countermeasures to reduce inflight muscle atrophy. Request and User Support Office. Other life science investigations included: First ever comprehensive study of sleep cycles, 24-hour circadian rhythms and task performance in microgravity. Spacecraft orbiting Earth pass through 16 sunrises and sunsets in single 24-hour period, which could disrupt normal body rhythms. During two 72-hour time blocks, crew members completed questionnaires and measured such functions as eye movement and muscle activity during sleep. In the Performance Assessment Work Station, crew members performed a series of drills involving math problems and other http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-036A[08/06/2011 23:40:15] NASA - NSSDC - Spacecraft - Details
mental tests to measure the microgravity effects on cognitive, or thinking, skills.
The microgravity science investigations included Advanced Gradient Heating Facility, in which samples of pure aluminum containing zirconia particles were solidified. This could lead to more inexpensive ways to make mixtures of metals and ceramics, particularly useful to the metal casting industry. The Advanced Protein Crystallization Facility is the first ever designed to use three methods for growing protein crystals. In Electrohydrodynamics of Liquid Bridges, which focused on changes that occur in a fluid bridge suspended between two electrodes. This research could finds applications in industrial processes where control of a liquid column or spray is used, including in ink-jet printing.
The crew performed in-flight fixes to problem hardware on the Bubble, Drop and Particle Unit (BDPU), designed to study fluid physics.
The orbiter itself played a key part in a test that could help raise the Hubble Space Telescope to a higher orbit in 1997 during the second servicing mission. Columbia's vernier Reaction Control System jets were gently pulsed to boost the orbiter's altitude without jarring payloads. The same exercise could be conducted with orbiter Discovery during Mission STS- 82 to raise HST's orbit without impacting its solar arrays.
No significant in-flight problems were experienced with orbiter.
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Columbia (20)
USA
Launch, orbit and landing data
Launch date: 20.06.1996 Launch time: 14:49 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-B Altitude: 278 km Inclination: 39° Landing date: 07.07.1996 Landing time: 12:37 UT Landing site: Cape Canaveral (KSC)
Crew
No. Surname Given name Job Flight No. Duration Orbits
1 Henricks Terence Thomas "Tom" CDR 4 16d 21h 48m 271
2 Kregel Kevin Richard PLT 2 16d 21h 48m 271
3 Linnehan Richard Michael MSP 1 16d 21h 48m 271
4 Helms Susan Jane MSP 3 16d 21h 48m 271
5 Brady Charles Eldon, Jr. MSP 1 16d 21h 48m 271
6 Favier Jean-Jacques PSP 1 16d 21h 48m 271
7 Thirsk Robert Brent PSP 1 16d 21h 48m 271
Crew seating arrangement
Launch Landing 1 Henricks 1 Henricks 2 Kregel 2 Kregel 3 Linnehan 3 Brady 4 Helms 4 Helms 5 Brady 5 Linnehan 6 Favier 6 Favier 7 Thirsk 7 Thirsk
Backup Crew
No. Surname Given name Job
6 Duque Pedro Francisco PSP
7 Urbani Luca PSP
Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC).
Mission "Life and Microgravity Spacelab"; experiments in the areas of life science and materials science; experiments for planned long-duration mission onboard the ISS; longest Shuttle-flight to date. Photos / Drawings
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Personnel STS 79
Publications NSSDC ID: 1996-057A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events STS 79 was the 79th Shuttle mission, the 4th Shuttle-Mir 24324 docking, the 1st US crew exchange, and the 32nd KSC landing. The mission was highlighted by the return to Earth of US astronaut Shannon Lucid after 188 days in space which Facts in Brief set a new US record for long-duration as well as a world Launch Date: 1996-09- record for a woman. Succeeding her on Mir for an 16 approximately four-month stay was Mission Specialist John E. Launch Blaha who returned with the STS 81 crew. Vehicle: Shuttle Launch Site: Cape STS 79 marked the second flight of the SPACEHAB module in Canaveral, United States support of the Shuttle-Mir activities and first flight of the SPACEHAB Double Module configuration. During 5 days of mated operations, two crews transferred more than 4,000 Funding Agency pounds (1,814 kg) of supplies to Mir, including logistics, food and water generated by orbiter fuel cells. Three experiments NASA-Office of Space also were transferred: Biotechnology System (BTS) for study Flight (United States) of cartilage development; Material in Devices as Superconductors (MIDAS) to measure electrical properties of Discipline high- temperature superconductor materials; and Commercial Generic Bioprocessing Apparatus (CGBA), containing several Human Crew smaller experiments, including self- contained aquatic systems.
About 2,000 pounds (907 kg) of experiment samples and Additional equipment were transferred from Mir to Atlantis. During her Information approximately six-month stay on Mir, Lucid conducted research Launch/Orbital in the following fields: advanced technology, Earth sciences, information for STS 79 fundamental biology, human life sciences, microgravity research and space sciences. Specific experiments included: Experiments on STS 79 Environmental Radiation Measurements to ascertain ionizing radiation levels aboard Mir; Greenhouse- Integrated Plant Data collections from STS Experiments, to study the effects of microgravity on plants, 79 specifically dwarf wheat; and Assessment of Humoral Immune Function During Long-Duration Space flight, to gather data on the effect of long-term spaceflight on the human immune system and involving the collection of blood serum and saliva Questions or comments samples. Some research was conducted in the newest and about this spacecraft can final Mir module, Priroda, which arrived at the space station be directed to: Coordinated during Lucid's stay. Request and User Support Office. Three experiments remained on Atlantis: Extreme Temperature Translation Furnace (ETTF), a new furnace design allowing space-based processing up to 871 degrees F (1,600 degrees C) and above; Commercial Protein Crystal Growth (CPCG) complement of 128 individual samples involving 12 different proteins; and Mechanics of Granular Materials, designed to further understanding of behavior of cohesionless granular materials, which could in turn lead to better understanding of how the Earth's surface responds during earthquakes and landslides. http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-057A[08/06/2011 23:40:57] NASA - NSSDC - Spacecraft - Details
STS 79's crew consisted of the following: Commander : Willaim F. Readdy (3rd Shuttle flight) Pilot : Terrence W. Wilcutt (2) Mission Specialist : Tom Akers (4) Mission Specialist : Jay Apt (4) Mission Specialist : Carl E. Walz (3) Mission Specialist : John E. Blaha (5)
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Atlantis (17)
USA
Launch, orbit and landing data
Launch date: 16.09.1996 Launch time: 08:54 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-A Altitude: 315 - 394 km Inclination: 51,6° Landing date: 26.09.1996 Landing time: 12:13 UT Landing site: Cape Canaveral (KSC)
Crew
No. Surname Given name Job Flight No. Duration Orbits
1 Readdy William Francis "Bill" CDR 3 10d 03h 19m 160
2 Wilcutt Terrence Wade PLT 2 10d 03h 19m 160
3 Apt Jerome "Jay" MSP 4 10d 03h 19m 160
4 Akers Thomas Dale MSP 4 10d 03h 19m 160
5 Walz Carl Erwin MSP 3 10d 03h 19m 160
6 Blaha John Elmer MSP 5 128d 05h 28m 2027
Crew seating arrangement
Launch Landing 1 Readdy 1 Readdy 2 Wilcutt 2 Wilcutt 3 Apt 3 Walz 4 Akers 4 Akers 5 Walz 5 Apt 6 Blaha 6 Lucid
Backup Crew
No. Surname Given name Job
6 Linenger Jerry Michael MSP
hi res version (880 KB)
Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC).
Fourth docking with MIR space station; common mission with the 22. MIR resident crew (19. - 24.09.1996); partly crew exchange with MIR resident crew (Shannon Lucid returned to Earth, Blaha remained on MIR); supplies and equipment were also transferred between the MIR and the Shuttle including an IMAX-camera.
Note Blaha returned to Earth on 22.01.1997 at 14:23 UT with STS-81. Photos / Drawings
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Personnel STS 80
Publications NSSDC ID: 1996-065A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The final shuttle flight of 1996 was highlighted by the 24660 successful deployment, operation and retrieval of two free- flying research spacecraft. Two planned extravehicular activities (EVAs) were cancelled. Facts in Brief Launch Date: 1996-11- Orbiting and Retrievable Far and Extreme Ultraviolet 19 Spectrometer-Shuttle Pallet Satellite II (ORFEUS-SPAS-II) Launch was deployed on flight day one and began approximately two Vehicle: Shuttle weeks of data gathering. It featured three primary scientific Launch Site: Cape instruments: the ORFEUS-Telescope with the Far Ultraviolet Canaveral, United States (FUV) Spectrometer and Extreme Ultraviolet (EUV) Spectrograph. A secondary but highly complementary payload was the Interstellar Medium Absorption Profile Spectrograph Funding Agency (IMAPS). Non-astronomy payloads included the Surface Effects Sample Monitor (SESAM), the ATV Rendezvous Pre- NASA-Office of Space Development Project (ARP) and the Student Experiment on Flight (United States) ASTRO-SPACE (SEAS). Discipline The Wake Shield Facility-3 (WSF-3) was deployed on flight day 4. It was a 12-foot diameter, free-flying stainless steel disk Human Crew designed to generate an ultravacuum environment in which to grow semiconductor then films for use in advanced electronics. This third flight was successful, with a maximum of seven film Additional growths of semiconductor materials achieved and the satellite Information hardware performing nearly flawlessly. It was retrieved after Launch/Orbital three days of free-flight. information for STS 80 Two planned six-hour EVAs by astronauts Jernigan and Jones Experiments on STS 80 were designed to evaluate equipment and procedures that would be used during construction and maintenance of the Data collections from STS International Space Station. However, the crew could not open 80 the outer airlock hatch and when troubleshooting did not reveal the cause, mission managers concluded that it would not be prudent to attempt the two EVAs and risk unnecessary damage to the hatch or seals. Questions or comments about this spacecraft can Other experiments included the Space Experiment Module be directed to: Coordinated (SEM) which provided increased educational access to space; Request and User Support NIH-R4, the fourth in a series of collaborative experiments Office. developed by NASA and the National Institutes of Health, to investigate the role of calcium in blood pressure regulation; NASA/CCM-A, one of a series of shuttle bone cell experiments; Biological Research in Canister (BRIC)-09 experiment to study the influence of microgravity on genetically-altered tomato and tobacco seedlings; Commercial MDA ITA experiment (CMIX-5), the last in a series of shuttle experiments; and Visualization in an Experimental Water Capillary Pumped Loop (VIEW-CPL), a middeck experiment to investigate the method for spacecraft thermal management. http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-065A[08/06/2011 23:41:53] NASA - NSSDC - Spacecraft - Details
The crew consisted of the following: Kenneth D. Cockrell - Commander Kent V. Rominger - Pilot Tamara E. Jernigan - Mission Specialist Thomas D. Jones - Mission Specialist Story Musgrave - Mission Specialist
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Columbia (21)
USA
Launch, orbit and landing data
Launch date: 19.11.1996 Launch time: 19:55 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-B Altitude: 351 km Inclination: 28,45° Landing date: 07.12.1996 Landing time: 11:49 UT Landing site: Cape Canaveral (KSC)
Crew No Orbit Surname Given name Job Flight No. Duration . s CD 1 Cockrell Kenneth Dale "Taco" 3 17d 15h 53m 279 R Rominge 2 Kent Vernon PLT 2 17d 15h 53m 279 r Tamara Elizabeth MS 3 Jernigan 4 17d 15h 53m 279 "Tammy" P MS 4 Jones Thomas David 3 17d 15h 53m 279 P Musgrav MS 5 Franklin Story 6 17d 15h 53m 279 e P
Crew seating arrangement
Launch Landing 1 Cockrell 1 Cockrell 2 Rominger 2 Rominger 3 Jernigan 3 Musgrave 4 Jones 4 Jones 5 Musgrave 5 Jernigan
Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC).
Mission ORFEUS-SPAS-02; two planned EVA's were cancelled, because a hatch couldn't be opened; deploying and retrieval of German built astronomy-satellite ORFEUS-SPAS-02 and of the Wake Shield Facility (WSF 03); several secondary experiments; longest Shuttle- mission to date, landing was postponed due of bad weather at landing site; Musgrave became the oldest astronaut to date flying into space.
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Personnel STS/SRL 3
Publications NSSDC ID: SRL3 Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The Space Radar Laboratory 3 (SRL 3) was the third in a SRL 3/STS series of flights of this payload which was designed to (1) Shuttle Radar Lab 3 acquire radar imagery of the Earth's surface for studies in geology, geography, hydrology, oceanography, agronomy, and Space Radar Lab 3 botony; (2) gather data for future space-borne radar systems SIR-C/X-SAR including Earth Observing System (EOS); and (3) provide measurements of the global distribution of carbon dioxide (CO2) in the troposphere. Instruments on board included the Facts in Brief Shuttle Imaging Radar-C (SIR-C) with multi-frequency (C- and Launch Date: 1996-01- L-Bands), multi-polarization (HH, VV, HV, VH), and multi- 31 incidence angle (15 to 55 degrees) capabilities thus lending Launch itself to a wide range of earth surface applications; the X-band Vehicle: Shuttle Synthetic Aperture Radar (X-SAR), an X-band, VV-polarized Launch Site: Cape imaging radar system, built by Dornier (Germany) and Alenia Canaveral, United States (Italy) for the German Space Agency (DARA)/German Mass: 12094.0 kg Aerospace Research Establishment (DLR) and the Italian Space Agency (ASI); and, the Mapping Air Pollution from Space (MAPS) for the study of global air pollution. Also, on- Funding Agencies board the SRL, was an ocean wave spectra processor, designed and built by Johns Hopkins Applied Physics Agenzia Spaziale Italiana Laboratory, which collected data on ocean surface wave (Italy) length, direction, and height. Four 45-Mbps data channels NASA-Office of Space were recorded on special high data rate tape recorders and Science Applications real-time data was transmitted to ground stations. About 50 (United States) hours each of SIR-C and X-SAR data were recorded during Bundesministerium fuer the mission. The combined SIR-C/X-SAR Science Team was Forschung und made up of 49 members and 3 associates representing 13 Tecnnologie (Federal countries. SIR-C/X-SAR data collection was focused on Republic of Germany) several worldwide supersites and correlated with ground and aircraft measurements. Radar data was also calibrated to allow comparisons with other operating spaceborne radars (ERS-1 Discipline SAR, JERS-1 SAR). Earth Science
Additional Information
Launch/Orbital information for STS/SRL 3 PDMP information for STS/SRL 3 Telecommunications information for STS/SRL 3
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Data collections from STS/SRL 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. Richard M. Program NASA Headquarters Monson Manager Dr. Paulo Project Consiglio Nazionale delle [email protected] Pampaloni Scientist Ricerche Dr. Diane L. Project NASA Jet Propulsion [email protected] Evans Scientist Laboratory Dr. Manfred Project Deutsche Agentur fur [email protected] Wahl Manager Ramfahrt-Angelegenheiten Dr. Herwig Ottl Project Deutsche Forschungsenstalt [email protected] Scientist fuer Luft-und Raumfahrt Dr. Paulo Deputy Italian Space Agency [email protected] Ammendola Project Manager Dr. George F. Program NASA Headquarters Esenwein, Jr. Manager Mr. R. Wayne Program NASA Headquarters Richie Manager Dr. Robert J. Program NASA Headquarters McNeal Scientist Mr. Michael J. Project NASA Jet Propulsion Sander Manager Laboratory
Selected References
Jordan, R. L., et al., SIR-C/X-SAR synthetic aperture radar system, IEEE Proc., 79, No. 6, 827- 838, June 1991.
Evans, D. L., et al., The Shuttle Imaging Radar-C and X-SAR mission, EOS, 74, No. 13, Mar. 1993.
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Personnel TELECOM 2D
Publications NSSDC ID: 1996-044B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events TELECOM 2D was a French geosynchronous satellite 24209 launched from the Kourou space center in French Guiana aboard an Ariane 44L rocket. It provided voice and video communications to western Europe. Facts in Brief Launch Date: 1996-08- 08 Launch Vehicle: Ariane 44L Launch Site: Kourou, French Guiana
Funding Agency
France Telecom (France)
Discipline
Communications
Additional Information
Launch/Orbital information for TELECOM 2D
Experiments on TELECOM 2D
Data collections from TELECOM 2D
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel TOMS-EP
Publications NSSDC ID: 1996-037A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The goal of the Total Ozone Mapping Spectrometer (TOMS) SMEX/TOMS-Earth Earth Probe mission (part of NASA's Mission To Planet Earth Probe (MTPE) Phase I program) was to continue the high-resolution Small Explorer/TOMS- global mapping of total ozone on a daily basis (begun with the Earth Probe Nimbus 7 SBUV/TOMS) as well as to detect global ozone trends to verify depletion predicted by atmospheric chemistry TOMS-EP96 models. TOMS-Earth Probe 23940 The TOMS-Earth Probe (TOMS-EP), the first of a series of NASA Earth Probe missions, was one of three TOMS missions which included METEOR 3/TOMS2 (launched 1991) and Facts in Brief ADEOS/TOMS (launched 1995). The TOMS-EP carried only one instrument: the Total Ozone Mapping Spectrometer Launch Date: 1996-07- (TOMS). 02 Launch The TOMS-EP spacecraft was based on the TRW/DSI Eagle Vehicle: Pegasus XL bus developed under the USAF STEP program. The Launch spacecraft was three-axis stabilized so that the TOMS Site: Vandenberg AFB, instrument was nadir-pointed with about 0.5 degree control United States and about 0.1 degree knowledge from measured altitude data. Mass: 248.0 kg The TOMS-EP spacecraft bus was designed to accomodate all of the TOMS instrument requirements to support a two-year Funding Agency lifetime with a three-year lifetime goal. NASA-Office of Space Science Applications (United States)
Discipline
Earth Science
Additional Information
Launch/Orbital information for TOMS-EP PDMP information for TOMS-EP Telecommunications information for TOMS-EP
Experiments on TOMS-EP
Data collections from TOMS-EP
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Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
Personnel
Name Role Original Affiliation E-mail Dr. Robert Project NASA Goddard Space Douglas Scientist Flight Center Hudson Dr. George F. Program NASA Headquarters Esenwein, Jr. Manager Mr. Donald L. Project NASA Goddard Space [email protected] Margolies Manager Flight Center
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Personnel TSS-1R
Publications NSSDC ID: 1996-012B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The TSS-1R mission is a reflight of the Tethered Satellite TSS- Tethered Satellite System 1 that had been flown on the Space Shuttle mission STS-46 in 1R July of 1992. A protruding bolt had prevented full release of 23805 the tether during the TSS-1 mission. The TSS mission equipment consists of the deployer system, the Italian-build satellite, the electrically conductive tether (22km total length) Facts in Brief and 6 science instruments. The TSS-1 is to be deployed from a reel in the orbiter payload bay upward (away from Earth) to up Launch Date: 1996-02- to 20 Km (12.5 miles) above the Orbiter. The objectives of this 25 mission are: (1) to verify engineering performance of the Launch Tethered Satellite System (TSS); (2) to determine and to Vehicle: Shuttle understand the electro-magnetic interaction between the Launch Site: Cape tether/satellite/orbiter system and the ambient space plasma; Canaveral, United States (3) to investigate and to understand the dynamical forces Mass: 518.0 kg acting upon a tethered satellite; (4) to demonstrate electrical power generation; and, (5) to develop the capability for future Funding Agencies tether applications on the Shuttle and Space Station. The deploying system consists of a motor- driven tether storage Piano Spaziale Nazionale reel and level wind system. A separate multipurpose of CNR (Italy) equipment support structure (MPESS) carries all science NASA-Office of Space instruments not integrated on the satellite, with the exception Science Applications of the Tethered Optical Phenomena (TOP) equipment, which is (United States) carried in the crew compartment. The spherical satellite is 1.6 meters in diameter and 6.5 meters in length. The S-band antenna, magnetometers, and Research on Orbital Plasma Disciplines Electrodynamics (ROPE) equipment are mounted on stationary booms, and the Research on Electrodynamic Tether Effects Engineering (RETE) Langmuir probe and dipole field antenna are mounted Space Physics on 2.5 meter deployable/retractable booms. At the base of the satellite, a swivel joint and a bayonet pin attache the tether to the satellite. A connector routes the tether conductor to an Additional ammeter and then to the satellite's skin. The satellite contained Information cold gas (nitrogen) thrusters used for deployment, retrieval, Launch/Orbital and attitude control. The 2.54 mm diameter conducting tether information for TSS-1R was constructed using Kevlar and Nomex with 10 strands of 34 AWG copper wire and a Teflon sheath. NASA is reponsible PDMP information for for the TSS deployer and systems integration, and Italy for TSS-1R building the satellite. Five hours after deployment began on Telecommunications February 25, 1996, with 19.7 km (of 20.7 planned) of tether information for TSS-1R released, the tether cable suddenly snapped near the top of the deployment boom. The TSS satellite shot away into a Experiments on TSS-1R higher orbit. TSS instruments could be re-actived and produced science data for three days until battery power ran Data collections from TSS- out. An independent review panel was formed to review the 1R TSS-1R failure.
Questions or comments about this spacecraft can
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be directed to: Dr. Dieter K. Bilitza.
Personnel
Name Role Original Affiliation E-mail Mr. Robert O. Project NASA Marshall Space McBrayer Manager Flight Center Prof. Franco Program Consiglio Nazionale delle [email protected] Mariani Scientist Ricerche Dr. Michael A. Program NASA Headquarters [email protected] Calabrese Manager Mr. Nobie H. Project NASA Marshall Space Stone Scientist Flight Center Mr. James M. Mission NASA Marshall Space Sisson Manager Flight Center Dr. Robert A. Program NASA Goddard Space [email protected] Hoffman Scientist Flight Center Prof. Marino Program Consiglio Nazionale delle [email protected] Dobrowolny Scientist Ricerche Dr. G. Manarini Program Consiglio Nazionale delle Manager Ricerche Dr. Stanley D. Program NASA Headquarters Shawhan Scientist
Other TSS-1R Data/Information at NSSDC
Independant panel formed to review TSS-1R loss (02/26/96) Early results from TSS-1R may cause revision to theory (05/23/96) Report on TSS-1R tether failure released (06/04/96)
Related Information/Data at NSSDC
STS 75 TSS-1
Other Sources of TSS-1R Information/Data
TSS home page
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Personnel Turksat 1C
Publications NSSDC ID: 1996-040B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Turksat 1C was a Turkish geosynchronous communications 23949 satellite that was launched by an Ariane 44L rocket from the Kourou site in French Guiana. After parking at 42 deg E, the spacecraft provided radio and TV communications to Turkey Facts in Brief and neighboring countries. Launch Date: 1996-07- 09 Launch Vehicle: Ariane 44L Launch Site: Kourou, French Guiana Mass: 2100.0 kg
Funding Agency
Unknown (Turkey)
Discipline
Communications
Additional Information
Launch/Orbital information for Turksat 1C
Experiments on Turksat 1C
Data collections from Turksat 1C
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel UFO 7
Publications NSSDC ID: 1996-042A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events UFO 7 (UHF Follow On 7) was a US Navy satellite launched to USA 127 replace the FLTSATCOM and Leasat spacecraft currently UHF Follow On 7 supporting the Navy's global communications network, serving ships at sea and a variety of other US military fixed and mobile 23967 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: 1996-07- channel capacity over the same frequency spectrum used by 25 previous systems. Each spacecraft had 11 solid-state UHF Launch Vehicle: Atlas 2 amplifiers and 39 UHF channels with a total of 555 kHz Launch Site: Cape bandwidth. The UHF payload compresed 21 narrow band Canaveral, United States channels at 5 kHz each and 17 relay channels at 25 kHz. In Mass: 3015.0 kg comparison, FLTSATCOM offered 22 channels. The F-1 through F-7 spacecraft included an SHF (super high frequency) subsystem, which provided command and ranging capabilities Funding Agency when the satellite was on station as well as the secure uplink Department of Defense- for Fleet Broadcast service, which was downlinked at UHF. Department of the Navy (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 arrays generated a combined 2500 watts of electrical power on Disciplines 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 Communications folded against the spacecraft bus for launch, forming a cube Surveillance and Other roughly 11 feet per side. Military
Additional Information
Launch/Orbital information for UFO 7
Experiments on UFO 7
Data collections from UFO 7
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
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-042A[08/06/2011 23:47:20] NASA - NSSDC - Spacecraft - Details
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Personnel UNAMSAT-B
Publications NSSDC ID: 1996-052B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events A secondary payload launched with Cosmos 2334 was the OSCAR 30 UNAMSAT-B small satellite, for the Automonous University of 24305 Mexico (UNAM). It repaced a satellite lost in a launch failure in 1995. It used the 25 cm AMSAT Microsat bus and carried an experiment to determine the velocity of meteors using radio Facts in Brief doppler echo, and a communications data relay for environmental sensors in remote locations. Launch Date: 1996-09- 05 Launch Vehicle: Cosmos Launch Site: Plesetsk, Russia Mass: 10.0 kg
Funding Agency
Automonous University of Mexico (Mexico)
Disciplines
Communications Space Physics
Additional Information
Launch/Orbital information for UNAMSAT-B
Experiments on UNAMSAT-B
Data collections from UNAMSAT-B
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
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-052B[08/06/2011 23:48:06] NASA - NSSDC - Spacecraft - Details
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Personnel USA 118
Publications NSSDC ID: 1996-026A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events USA 118 was an American military (USAF) electronic 23855 inteligence satellite launched from Cape Canaveral aboard a Titan 4 rocket. Facts in Brief
Launch Date: 1996-04- 24 Launch Vehicle: Titan IV Launch Site: Cape Canaveral, United States
Funding Agency
Department of Defense- Department of the Air Force (United States)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for USA 118
Experiments on USA 118
Data collections from USA 118
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
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-026A[08/06/2011 23:48:27] NASA - NSSDC - Spacecraft - Details
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Personnel USA 119
Publications NSSDC ID: 1996-029A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events This US Navy Ocean Surveillance Satellite (NOSS) was SDS-2 launched from Vandenberg AFB aboard an Atlas E/F rocket. It 23893 placed a cluster of one primary satellite and three smaller sub- satellites (that trailed along at distances of several hundred kilometers) into low polar orbit. This satellite array determined Facts in Brief the location of radio and radars transmitters, using triangulation, and the identity of naval units, by analysis of the Launch Date: 1996-05- operating frequencies and transmission patterns. 12 Launch Vehicle: Titan IV Launch Site: Cape Canaveral, United States Mass: 700.0 kg
Funding Agency
Department of Defense- Department of the Air Force (United States)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for USA 119
Experiments on USA 119
Data collections from USA 119
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
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-029A[08/06/2011 23:48:47] NASA - NSSDC - Spacecraft - Details
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Personnel USA 120
Publications NSSDC ID: 1996-029B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events USA 120 was a naval reconnaisance, electronic intelligence 23907 satellite launched from Vandenberg AFB aboard a Titan 4 rocket along with USA 119, 121 - 124. Facts in Brief
Launch Date: 1996-05- 12 Launch Vehicle: Titan IV Launch Site: Cape Canaveral, United States
Funding Agency
Unknown (United States)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for USA 120
Experiments on USA 120
Data collections from USA 120
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
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-029B[08/06/2011 23:49:09] NASA - NSSDC - Spacecraft - Details
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Personnel USA 121
Publications NSSDC ID: 1996-029C Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events USA 121 was a US Naval reconnaisance satellite, part of the 23908 NOSS 2 series, launched from Vandenberg AFB aboard a Titan 4 rocket along with USA 119, 120, 122 - 124. Facts in Brief
Launch Date: 1996-05- 12 Launch Vehicle: Titan IV Launch Site: Cape Canaveral, United States
Funding Agency
Department of Defense- Department of the Navy (United States)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for USA 121
Experiments on USA 121
Data collections from USA 121
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
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-029C[08/06/2011 23:49:30] NASA - NSSDC - Spacecraft - Details
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Personnel USA 122
Publications NSSDC ID: 1996-029D Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events USA 122 was a US naval reconnaisance satellite, part of the 23862 NOSS 2 series, launched from Vandenberg AFB aboard a Titan 4 rocket along with USA 119 - 121, 123 and 124. Facts in Brief
Launch Date: 1996-05- 12 Launch Vehicle: Titan IV Launch Site: Cape Canaveral, United States
Funding Agency
Department of Defense- Department of the Navy (United States)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for USA 122
Experiments on USA 122
Data collections from USA 122
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
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-029D[08/06/2011 23:49:51] NASA - NSSDC - Spacecraft - Details
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Personnel USA 123
Publications NSSDC ID: 1996-029E Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events USA 123 was a naval tether spacecraft launched from 23936 Vandenberg AFB aboard a Titan 4 rocket along with USA 119 - 122 and 124. Facts in Brief
Launch Date: 1996-05- 12 Launch Vehicle: Titan IV Launch Site: Cape Canaveral, United States
Funding Agency
Department of Defense- Department of the Navy (United States)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for USA 123
Experiments on USA 123
Data collections from USA 123
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
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-029E[08/06/2011 23:50:12] NASA - NSSDC - Spacecraft - Details
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Personnel USA 124
Publications NSSDC ID: 1996-029F Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events USA 124 was a naval reconnaisance satellite, part of the 23937 NOSS 2 series, launched from Vandenberg AFB aboard a Titan 4 rocket along with USA 119 - 123. Facts in Brief
Launch Date: 1996-05- 12 Launch Vehicle: Titan IV Launch Site: Cape Canaveral, United States
Funding Agency
Department of Defense- Department of the Navy (United States)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for USA 124
Experiments on USA 124
Data collections from USA 124
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
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-029F[08/06/2011 23:50:33] NASA - NSSDC - Spacecraft - Details
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Personnel USA 125
Publications NSSDC ID: 1996-038A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events USA 125 was an Air Force surveillance satellite launched by a 23945 Titan 4 rocket from Cape Canaveral. It was part of the NOSS program. Facts in Brief
Launch Date: 1996-07- 02 Launch Vehicle: Titan IV Launch Site: Cape Canaveral, United States Mass: 700.0 kg
Funding Agency
Department of Defense- Department of the Air Force (United States)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for USA 125
Experiments on USA 125
Data collections from USA 125
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
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-038A[08/06/2011 23:50:53] NASA - NSSDC - Spacecraft - Details
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Personnel WSF 3
Publications NSSDC ID: 1996-065C Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events WSF 3 (Wake Field Facility 3) is an American microgravity Wake Shield Facility 3 module that was released from STS 80. The four-meter 24662 diameter, 2,000 kg steel saucer was to grow ultra-purity semiconductors on its rear side where the module's wake is an ultra-vacuum. Its orbital parameters were very close to those Facts in Brief of STS 80. It was recaptured by the shuttle on the 26 November 1996. Launch Date: 1996-11- 23 Launch Vehicle: Shuttle Launch Site: Cape Canaveral, United States Mass: 2000.0 kg
Funding Agency
Unknown (United States)
Discipline
Microgravity
Additional Information
Launch/Orbital information for WSF 3
Experiments on WSF 3
Data collections from WSF 3
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
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-065C[08/06/2011 23:51:14]