Cronología de Lanzamientos Espaciales
Año 2003
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 89 spacecraft returned.
Maps Spacecraft Name NSSDC ID Launch Date New/Updated Data AAU Cubesat 2003-031G 2003-06-30
Lunar/Planetary Events AMC 9 2003-024A 2003-06-06 Amos 2 2003-059A 2003-12-27 Asiasat 4 2003-014A 2003-04-12 B-Sat 2C 2003-028A 2003-06-11 Beagle 2 2003-022C 2003-06-02 Beidou 1C 2003-021A 2003-05-24 Bilsat 1 2003-042E 2003-09-27 BNSCSAT 2003-042D 2003-09-27 CANX 1 2003-031H 2003-06-30 CBERS 2003-049A 2003-10-21 CHIPS 2003-002B 2003-01-13 Columbus Orbital Facility COLMBUS 2003-01-01 Coriolis 2003-001A 2003-01-06 Cosmos 2397 2003-015A 2003-04-24 Cosmos 2398 2003-023A 2003-06-04 Cosmos 2399 2003-035A 2003-08-12 Cosmos 2400 2003-037A 2003-08-19 Cosmos 2401 2003-037B 2003-08-19 Cosmos 2402 2003-056B 2003-12-10 Cosmos 2403 2003-056C 2003-12-10 Cosmos 2404 2003-056A 2003-12-10 Cubesat XI-IV 2003-031J 2003-06-30 Cute 1 2003-031E 2003-06-30 DMSP 5D-3/F16 2003-048A 2003-10-18 Double Star 1 2003-061A 2003-12-29 Dtusat 2003-031C 2003-06-30 Echostar 9 2003-034A 2003-08-08 Eurobird 3 2003-043A 2003-09-27 Express AM22 2003-060A 2003-12-28 FSW-3 1 2003-051C 2003-11-03 Galaxy 12 2003-013B 2003-04-09 GALEX 2003-017A 2003-04-28 Gruzomaket 2003-055A 2003-12-05 GSAT 2 2003-018A 2003-05-08 Hayabusa 2003-019A 2003-05-09
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Hellas-Sat 2003-020A 2003-05-13 Horizons 1 2003-044A 2003-10-01 ICESat 2003-002A 2003-01-13 IGS 1A 2003-009A 2003-03-28 IGS 1B 2003-009B 2003-03-28 Innovation 1 2003-049B 2003-10-21 Insat 3A 2003-013A 2003-04-09 INSAT 3E 2003-043E 2003-09-27 Intelsat 907 2003-007A 2003-02-15 IRS P6 2003-046A 2003-10-17 Kaistsat 4 2003-042G 2003-09-27 Larets 2003-042F 2003-09-27 Mars Express 2003-022A 2003-06-02 MILSTAR 6 2003-012A 2003-04-08 Mimosa 2003-031B 2003-06-30 Molniya 1-92 2003-011A 2003-04-02 Molniya 3-53 2003-029A 2003-06-19 Monitor-E/Breeze 2003-031A 2003-06-30 Most 2003-031D 2003-06-30 Mozhayets 4 2003-042A 2003-09-27 Navstar 51 2003-005A 2003-01-29 Navstar 52 2003-010A 2003-03-31 Navstar 53 2003-058A 2003-12-21 Nigeriasat 1 2003-042C 2003-09-27 Opportunity 2003-032A 2003-07-08 Optus 1C 2003-028B 2003-06-11 Orbview 3 2003-030A 2003-06-26 Progress M-47 2003-006A 2003-02-02 Progress M-48 2003-039A 2003-08-29 Progress M1-10 2003-025A 2003-06-08 Quakesat 2003-031F 2003-06-30 Rainbow 1 2003-033A 2003-07-17 Rubin 4 2003-042B 2003-09-27 Scisat 1 2003-036A 2003-08-13 SERVIS 1 2003-050A 2003-10-30 Shenzhou 5 2003-045A 2003-10-15 SMART 1 2003-043C 2003-09-27 SORCE 2003-004A 2003-01-25 SOYUZ TMA 3 2003-047A 2003-10-18 Soyuz TMA-2 2003-016A 2003-04-26 Spirit 2003-027A 2003-06-10 Spitzer Space Telescope 2003-038A 2003-08-25 STS 107 2003-003A 2003-01-16 Thuraya 2 2003-026A 2003-06-10 UFO 11 2003-057A 2003-12-18 USA 167 2003-008A 2003-03-11 USA 170 2003-040A 2003-08-29 USA 171 2003-041A 2003-09-09 USA 173 2003-054A 2003-12-02
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XSS 10 2003-005B 2003-01-29 Yamal 201 2003-053B 2003-11-24 Yamal 202 2003-053A 2003-11-24 Zhongxing 20 2003-052A 2003-11-14
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Personnel AAU Cubesat
Publications NSSDC ID: 2003-031G Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events AAU CUBESAT is a Danish (Aalborg University) students-built 27846 photo -imaging nanosatellite that was launched by a Rokot rocket from Plesetsk at 14:15 UT on 30 June 2003. Facts in Brief
Launch Date: 2003-06- 30 Launch Vehicle: Rokot Launch Site: Plesetsk, Russia
Funding Agency
Unknown (Denmark)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for AAU Cubesat
Experiments on AAU Cubesat
Data collections from AAU Cubesat
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=2003-031G[13/10/2010 23:25:00]
Cronología de Lanzamientos Espaciales
Año 2003
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 - Details
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Personnel AMC 9
Publications NSSDC ID: 2003-024A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events AMC 9 is an American geostationary communications 27820 spacecraft that was launched by a Proton-K rocket from Baikonur at 22:15 UT on 6 June 2003. the 4.1 tonne satellite will provide direct-to-home digital TV, and data transfer in USA Facts in Brief and Canada, through its 24 C-, and 24 Ku-band transponders Launch Date: 2003-06- after parking at 85 deg-W longitude. 06 Launch Vehicle: Proton-K Launch Site: Tyuratam (Baikonur Cosmodrome), Kazakhstan
Funding Agency
Unknown (United States)
Discipline
Communications
Additional Information
Launch/Orbital information for AMC 9
Experiments on AMC 9
Data collections from AMC 9
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Amos 2
Publications NSSDC ID: 2003-059A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Amos 2 is an Israeli geostationary communcations satellite that 28132 was launched by a Soyuz-Fregat rocket from Baikonur at 21:30 UT on 27 December 2003. The 1.4 tonne satellite carries 11 Ku-band transponders to provide direct-to-home television, Facts in Brief internet and data transmissions to the West Asia, Europe and Launch Date: 2003-12- eastern United States after parking over 4.0 deg-W longitude. 27 Launch Vehicle: Soyuz-Fregat Launch Site: Tyuratam (Baikonur Cosmodrome), Kazakhstan
Funding Agency
Unknown (Israel)
Discipline
Communications
Additional Information
Launch/Orbital information for Amos 2
Experiments on Amos 2
Data collections from Amos 2
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Asiasat 4
Publications NSSDC ID: 2003-014A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Asiasat 4 is an American geostationary communications 27718 spacecraft that was launched by an Atlas 3B rocket from Cape Canaveral at 01:47 UT on 12 April 2003. The 9.5 kW satellite will provide direct-to-home voice and video and video Facts in Brief broadcast to about 40 countries from Middle East to New Launch Date: 2003-04- Zealand through its 28 C-band, and 20 ku-band transponders 12 after parking over 122 deg-E longitude. Launch Vehicle: Atlas 3B Launch Site: Cape Canaveral, United States
Funding Agency
Unknown (United States)
Discipline
Communications
Additional Information
Launch/Orbital information for Asiasat 4
Experiments on Asiasat 4
Data collections from Asiasat 4
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel B-Sat 2C
Publications NSSDC ID: 2003-028A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events B-Sat 2C is a Japanese geostationary communications 27830 spacecraft that was launched by an Ariane 5 rocket from Kourou at 22:38 UT on 11 June 2003. It will provide direct digital broadcasts to homes in Japan and neighboring Facts in Brief countries through its Ku-band transponders. Launch Date: 2003-06- 11 Launch Vehicle: Ariane 5 Launch Site: Kourou, French Guiana
Funding Agency
Unknown (Japan)
Discipline
Communications
Additional Information
Launch/Orbital information for B-Sat 2C
Experiments on B-Sat 2C
Data collections from B- Sat 2C
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Beagle 2
Publications NSSDC ID: 2003-022C Maps Description Facts in Brief New/Updated Data
Lunar/Planetary Events Beagle 2 was declared lost after no communications were Launch Date: 2003-06- received following the scheduled landing on Mars. Attempts at 02 contact were made for over a month after the expected landing Launch Vehicle: Soyuz at 2:54 UT December 25. A board of inquiry was appointed to Launch Site: Tyuratam look into the reason for the failure and released its report on 24 (Baikonur Cosmodrome), August 2004. No concrete reason for the probe's failure was Kazakhstan determined. Factors that were considered as plausible causes Mass: 33.2 kg of the failure were unusually thin atmosphere over the landing site, electronic glitches, a gas bag puncture, damage to a heat shield, a broken communications antenna, and collision with an Funding Agency unforeseen object. Unknown (United Kingdom) The Beagle 2 is a Mars lander initially mounted on the top deck of the Mars Express Orbiter. It was released from the Orbiter Beagle 2 on 19 December 2003 on a course to land on Mars at 2:54 UT Discipline on 25 December. A point at 10.6 N, 270 W in Isidis Planitia, a large flat region that overlies the boundary between the ancient Planetary Science highlands and the northern plains of Mars, was chosen as the landing site. No signals were received following the scheduled Additional landing and after over a month of attempts at contact the Information mission was declared lost. A board of inquiry has been appointed to look into the reason for the failure. The lander Launch/Orbital was expected to operate for about 180 days and an extended information for Beagle 2 mission of up to one martian year (687 Earth days) was PDMP information for considered possible. The Beagle 2 lander objectives were to Beagle 2 characterize the landing site geology, mineralogy, geochemistry and oxidation state, the physical properties of Experiments on Beagle 2 the atmosphere and surface layers, collect data on martian meteorology and climatology, and search for signatures of life. Data collections from Beagle 2 Spacecraft and Subsystems Beagle 2 is equipped with a robot sampling arm and a small "mole" (Planetary Undersurface Tool, or PLUTO) which can be deployed by the arm and is capable of moving across the Questions or comments surface at a rate of about 1 cm every 5 seconds using a about this spacecraft can compressed spring mechanism. This mechanism can also be directed to: Dr. David R. allow the mole to burrow into the ground and collect a Williams. subsurface sample in a cavity in its tip. The mole is attached to the lander by a power cable which can be used as a winch to bring the sample back to the lander. The lander will be equipped with instruments for gas chromatography and mass spectroscopy (the Gas Analysis Package, or GAP), a microscope, panoramic and wide-angle cameras, Mossbauer and X-ray flourescence spectrometers and environmental sensors.
The robot arm is equipped with a grinder and corer, a device to collect a core sample from inside any rocks within reach of the robot arm. The Mossbauer and X-ray spectrometers and the http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2003-022C[13/10/2010 23:29:02] NASA - NSSDC - Spacecraft - Details
microscope are also held in a package on the end of the arm called the position adjustable workbench, or PAW. The stereo camera system is also mounted on the arm. The lander has the shape of a shallow bowl with a diameter of 0.65 m and a depth of 0.25 m. The cover of the lander is hinged and folds open to reveal the interior of the craft which holds a UHF antenna, the 0.75 m long robot arm, and the scientific equipment. The main body also contains the battery, telecommunications, electronics, and central processor, and the heaters. The lid itself further unfolds to expose four disk- shaped solar arrays. The lander package has a mass of 69 kg at launch but the actual lander is only 33.2 kg at touchdown.
Mission Profile Beagle 2 was launched with the Mars Express orbiter and was released on a ballistic trajectory towards Mars on 19 December 2003 at 8:31 UT. Beagle 2 coasted for five days after release and entered the martian atmosphere at over 20,000 km/hr on the morning of 25 December. As no signals were received after separation from Mars Express it is not known what happened during the landing sequence After initial deceleration in the martian atmosphere from simple friction, parachutes were to be deployed and about 1 km above the surface large gas bags would have inflated around the lander to protect it when it hit the surface. Landing was expected to occur at about 02:54 UT on 25 December (9:54 p.m. EST 24 December). After landing the bags would deflate and the top of the lander would open. The top would unfold to expose the four solar array disks. Within the body of the lander a UHF antenna would have been deployed. A panoramic image of the landing area would be taken using the stereo camera and a pop-up mirror. A signal was scheduled to be sent after landing (and possibly an image) to Mars Odyssey at about 5:30 UT and another the next (local) morning to confirm that Beagle 2 survived the landing and the first night on Mars. No signal was received at this time nor at any of the subsequent opportunities. Nothing further is known about the lander. If the landing had been successful instructions would be sent to Beagle 2. The lander arm would be released and be used to maneuver the scientific package located on the end of the arm and to dig up samples to be deposited in the Gas Analysis Package for study. The "mole" would be deployed by the arm, crawling across the surface to a distance of about three meters from the lander and capable of burrowing under rocks to collect soil samples for analysis.
The Beagle 2 is a British-led effort as part of the European Space Agency's Mars Express mission. It is named after the HMS Beagle, the ship which carried Charles Darwin on the voyage which led to his discovery of natural selection and evolution. The exact cost of Beagle 2 is not known, but most estimates give a range 40 to 50 million British pounds (roughly $65 million to $80 million U.S.)
Personnel
Name Role Original Affiliation E-mail Dr. Colin T. Pillinger Mission Scientist Open University [email protected]
Selected References
Wright, I. P., et al., Scientific objectives of the Beagle 2 lander, Acta Astronaut., 52, No. 2-6, 219-225, 2003.
Sims, M. R., et al., Beagle 2: A proposed exobiology lander for ESA's 2003 Mars Express mission, Adv. Space Res., 23, No. 11, 1925-1928, 1999.
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Beagle 2 after separating from Mars Express All images courtesy Beagle 2 and ESA, all rights reserved. Mars Express
Beagle 2 Declared Lost - ESA Press Release (11 February 2004) Mars Express Releases Beagle 2 - ESA Press Release (19 December 2003) Beagle 2 Set For Christmas Day Landing - ESA Press Release (23 December 2003)
Mars Home Page Chronology of Mars Exploration
Beagle 2 Home Page - The Open University Mars Express Home Page - ESA
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Personnel Beidou 1C
Publications NSSDC ID: 2003-021A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Beidou 1C was a Chinese (PRC) geostationary navigational Beidou 3 satellite that was launched by a Long March 3A rocket from 27813 Xichang launching center in Sichuan province at 16:34 UT on 24 May 2003. It joined two others, Beidou 1A and Beidou 1B, that were launched in 2000 and enabled a viable global Facts in Brief positioning constellation. Besides enabling positioning, it was to be used in weather monitoring and telecommunications. Launch Date: 2003-05- 24 Launch Vehicle: Long March 3A Launch Site: Xichang, Peoples Republic of China
Funding Agency
Unknown (Peoples Republic of China)
Discipline
Navigation & Global Positioning
Additional Information
Launch/Orbital information for Beidou 1C
Experiments on Beidou 1C
Data collections from Beidou 1C
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Bilsat 1
Publications NSSDC ID: 2003-042E Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Bilsat 1 is a Turkish DMC (multinational Diaster Monitoring 27943 Constellation) satellite that was launched by a Kosmos 3M rocket at 06:12 UT on 27 September 2003 from Plesetsk Cosmodrome. The 130 kg satellite carries five imaging Facts in Brief cameras to monitor natural disasters at a resolution of 26 m in Launch Date: 2003-09- color by four cameras (operating in red, green, blue, and 27 infrared colors) and another at 4-m resolution in black-and- Launch white. The DMC is run by an organization of seven countries Vehicle: Kosmos-3M (UK, Algeria, China, Nigeria, Thailand, Turkey, and Vietnam) Launch Site: Plesetsk, with the satelllites built at Surrey, UK. BILSAT 1 will also help Russia in agriculture and urban planing.
Funding Agency
Unknown (Turkey)
Discipline
Other
Additional Information
Launch/Orbital information for Bilsat 1
Experiments on Bilsat 1
Data collections from Bilsat 1
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel BNSCSAT
Publications NSSDC ID: 2003-042D Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events BNSCSAT (British National Science Center SATellite, also British National Science known as UK-DMC) is a British DMC (multinational Disaster Center Satellite Monitoring Constellation) satellite that was launched by a UK-DMC Kosmos 3M rocket from Plesetsk at 06:12 UT on 27 September 2003. Besides disaster monitoring, it will help in 27942 urban planning and agriculture surveys. Facts in Brief
Launch Date: 2003-09- 27 Launch Vehicle: Kosmos-3M Launch Site: Plesetsk, Russia
Funding Agency
Unknown (Brazil)
Discipline
Other
Additional Information
Launch/Orbital information for BNSCSAT
Experiments on BNSCSAT
Data collections from BNSCSAT
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel CANX 1
Publications NSSDC ID: 2003-031H Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events CANX 1 is a Canadian (University of Toronto) students-built, 27847 photo-imaging nanosatellite that was launched by a Rokot rocket from Plesetsk at 14:15 UT on 30 June 2003. Facts in Brief
Launch Date: 2003-06- 30 Launch Vehicle: Rokot Launch Site: Plesetsk, Russia
Funding Agency
Canadian Space Agency (Canada)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for CANX 1
Experiments on CANX 1
Data collections from CANX 1
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel CBERS
Publications NSSDC ID: 2003-049A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events CBERS (China Brazil Earth Resources Satellite) is a Sino- China Brazil Earth Brazilian remote sensing satellite that was launched by a Long Resources Satellite March 4B rocket from Taiyuan Satellite Launch Center is 28057 Shanxi province on 21 October 2003. The 1.6 tonne satellite will collect data relevant to environment, agriculture, urban planning and water pollution, under Chinese control for 18 Facts in Brief months, and later under Brazilian control during the remaining lifetime (of six or more months). Launch Date: 2003-10- 21 Launch Vehicle: Long March 4B Launch Site: Taiyuan, Peoples Republic of China
Funding Agency
Unknown (Brazil)
Discipline
Earth Science
Additional Information
Launch/Orbital information for CBERS
Experiments on CBERS
Data collections from CBERS
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel CHIPS
Publications NSSDC ID: 2003-002B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events CHIPS (Cosmic Hot Interstellar Plasma Spectrometer) is an UNEX/CHIPS American (NASA) astrophysics spacecraft that was launched Explorer 82 by a Delta 2 rocket from Vandenberg AFB at 00:45 UT on 13 January 2003. The 60 kg, triaxially-stabilized spacecraft has a Cosmic Hot Interstellar spectrograph covering the 9-26 nm wavelength band at a Plasma Spectrometer resolution of 0.1 nm, scanning the entire sky in chunks of 5 27643 degree x 27 degree segments during each orbit. The targets are the hot and diffuse nebulae at about a million degrees temperature. The band covers several strong emission lines. Facts in Brief Launch Date: 2003-01- 13 Launch Vehicle: Delta II Launch Site: Vandenberg AFB, United States Mass: 60.0 kg
Funding Agency
National Aeronautics and Space Administration (United States)
Discipline
Astronomy
Additional Information
Launch/Orbital information for CHIPS
Experiments on CHIPS
Data collections from CHIPS
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Other Sources of CHIPS Information/Data
CHIPS Project (U. California, Berkeley)
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Personnel Columbus Orbital Facility
Publications NSSDC ID: COLMBUS Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The ESA laboratory module known as the Columbus Orbital ISS Facility (COF) will be launched and attached to Node 2 of the COF orbiting International Space Station sometime after the year 2002. The Columbus Polar Platform, Columbus Attached Lab, Space Station and Columbus Free-Flying Platform were early proposed ESA MKS spacecraft to be coordinated with the proposed U.S. Space International Space Station. Just as the early U.S. Space Station plans went Station through a series of re-scoping, downsizing, and internationalizing steps before eventually receiving budget approval as the U.S.-led International Space Station (ISS), Facts in Brief these proposed Columbus plans similarly evolved into the current COF module. Launch Date: 2003-01- 01 The COF is a pressurized, habitable module whose structure is Launch derived from the Italian Mini-Pressurized Logistics Module Vehicle: Shuttle (MPLM). It is designed as a general purpose laboratory that Launch Site: Cape can support any foreseen user discipline, including materials Canaveral, United States and fluid sciences, life sciences and technology development. Funding Agency For more information, see the following ESA and NASA WWW pages: http://www.estec.esa.int/spaceflight/index.htm European Space Agency (International) (ISS) http://www.estec.esa.int/spaceflight/zarya.htm
(Columbus) http://www.estec.esa.nl/spaceflight/cof.htm Disciplines Earth Science http://spaceflight.nasa.gov/ (ISS) http://spaceflight.nasa.gov/station/ Human Crew (An ISS search page) Life Science http://station.nasa.gov/station/assembly/index.html Microgravity (Zarya) http://station.nasa.gov/station/assembly/elements/fgb/ Additional Information (Unity) http://station.nasa.gov/station/assembly/elements/node1/ Launch/Orbital information for Columbus Orbital Facility PDMP information for Columbus Orbital Facility Telecommunications information for Columbus Orbital Facility
Experiments on Columbus Orbital Facility
Data collections from
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Columbus Orbital Facility
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Coriolis
Publications NSSDC ID: 2003-001A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Coriolis is an American (DOD) spacecraft that was launched by 27640 a Titan 2 rocket from Vandenberg AFB at 14:19 UT on January 2003. The 395 kg, 1,174 W, 3.0 m diameter, 6.9 m high, triaxially-stabilized spacecraft carried 82 kg of fuel and 340 kg Facts in Brief of instruments. The two instruments are WindSat to monitor Launch Date: 2003-01- ocean surface winds, and SMEI to image Solar Mass Ejections 06 (SME). Data will be stored onboard and downlinked to Launch Vehicle: Titan II dedicated ground stations in x-band. Launch Site: Vandenberg AFB, United States Nominal Power: 1174.0 W
Funding Agency
Department of Defense (United States)
Disciplines
Earth Science Solar Physics Space Physics
Additional Information
Launch/Orbital information for Coriolis
Experiments on Coriolis
Data collections from Coriolis
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
Personnel
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2003-001A[13/10/2010 23:34:44] NASA - NSSDC - Spacecraft - Details
Name Role Original Affiliation E-mail Ms. Janet Johnson Program Manager
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Personnel Cosmos 2397
Publications NSSDC ID: 2003-015A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 2397 is a Russian geostationary military satellite that 27775 was launched by a Proton-K rocket from Baikonur at 04:23 UT on 24 April 2003. It was inserted into geostationary orbit at 11:00 UT on the same day. The Moscow Kommersat uses the Facts in Brief name US-KMO for the series of four such spacecraft in Launch Date: 2003-04- geostationary orbit, and US-KS for the older eight in highly 24 elliptical orbit, all of which are for early warning of missile Launch launches. It also reports that Cosmos 2397 will ensure total Vehicle: Proton-K global coverage of missile launches, filling out a gap over the Launch Site: Tyuratam Pacific region. (Baikonur Cosmodrome), Kazakhstan
Funding Agency
Unknown (Russia)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 2397
Experiments on Cosmos 2397
Data collections from Cosmos 2397
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 2398
Publications NSSDC ID: 2003-023A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 2398 is a Russian military satellite that was launched 27818 by a Cosmos-3M rocket from Plesetsk at 19:23 UT on 4 June 2003. Facts in Brief
Launch Date: 2003-06- 04 Launch Vehicle: Cosmos Launch Site: Plesetsk, Russia
Funding Agency
Unknown (Russia)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 2398
Experiments on Cosmos 2398
Data collections from Cosmos 2398
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 2399
Publications NSSDC ID: 2003-035A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 2399, also named NEMAN, is a Russian military Neman photo- reconnaissance satellite that was launched by a Soyuz- 27856 U rocket from Baikonur at 14:20 UT on 12 August 2003.
Facts in Brief
Launch Date: 2003-08- 12 Launch Vehicle: Soyuz-U Launch Site: Tyuratam (Baikonur Cosmodrome), Kazakhstan
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 2399
Experiments on Cosmos 2399
Data collections from Cosmos 2399
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 2400
Publications NSSDC ID: 2003-037A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 2400 is a Russian military communications satellite 27868 that was launched by a Cosmos 3M rocket from Plesetsk at 10:50 UT on 19 August 2003. Facts in Brief
Launch Date: 2003-08- 19 Launch Vehicle: Cosmos Launch Site: Plesetsk, Russia
Funding Agency
Unknown (Russia)
Disciplines
Communications Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 2400
Experiments on Cosmos 2400
Data collections from Cosmos 2400
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 2401
Publications NSSDC ID: 2003-037B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 2401is a Russian military communications satellite 27869 that was launched by a Cosmos 3M rocket from Plesetsk at 10:50 UT on 19 August 2003. Facts in Brief
Launch Date: 2003-08- 19 Launch Vehicle: Cosmos Launch Site: Plesetsk, Russia
Funding Agency
Unknown (Russia)
Disciplines
Communications Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 2401
Experiments on Cosmos 2401
Data collections from Cosmos 2401
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 2402
Publications NSSDC ID: 2003-056B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 2403 is one of the latest additions to the Russian fleet Glonass 794 of Glonass navigational satellites. One of the good websites 28113 for the Glonass fleet is
http://gge.unb.ca/Resources/GLONASSConstellationStatus.txt Facts in Brief
Launch Date: 2003-12- 10 Launch Vehicle: null Launch Site: null
Funding Agency
Unknown (Russia)
Discipline
Navigation & Global Positioning
Additional Information
Launch/Orbital information for Cosmos 2402
Experiments on Cosmos 2402
Data collections from Cosmos 2402
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 2403
Publications NSSDC ID: 2003-056C Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 2404 is one of the latest additions to the Russian fleet Glonass 795 of Glonass navigational satellites. One of the good websites 28114 for the Glonass fleet is
http://gge.unb.ca/Resources/GLONASSConstellationStatus.txt Facts in Brief
Launch Date: 2003-12- 10 Launch Vehicle: null Launch Site: null
Funding Agency
Unknown (Russia)
Discipline
Navigation & Global Positioning
Additional Information
Launch/Orbital information for Cosmos 2403
Experiments on Cosmos 2403
Data collections from Cosmos 2403
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 2404
Publications NSSDC ID: 2003-056A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 2402 is one of the latest additions to the Russian fleet Glonass 701 of Glonass navigational satellites. One of the good websites 28112 for the Glonass fleet is
http://gge.unb.ca/Resources/GLONASSConstellationStatus.txt Facts in Brief
Launch Date: 2003-12- 10 Launch Vehicle: null Launch Site: null
Funding Agency
Unknown (Russia)
Discipline
Navigation & Global Positioning
Additional Information
Launch/Orbital information for Cosmos 2404
Experiments on Cosmos 2404
Data collections from Cosmos 2404
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cubesat XI-IV
Publications NSSDC ID: 2003-031J Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events CUBESAT XI-IV is a Japanese nanosatellite that was launched OSCAR 57 by a Rokot rocket from Plesetsk at 14:15 UT on 30 June 2003. 27848 With a mass of one kilogram, it carries an 80 mW beacon at 436.8475 MHz. Facts in Brief
Launch Date: 2003-06- 30 Launch Vehicle: Rokot Launch Site: Plesetsk, Russia Mass: 1.0 kg
Funding Agency
Unknown (Japan)
Disciplines
Communications Technology Applications
Additional Information
Launch/Orbital information for Cubesat XI-IV
Experiments on Cubesat XI-IV
Data collections from Cubesat XI-IV
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cute 1
Publications NSSDC ID: 2003-031E Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events CUTE 1 is a Japanese (Tokyo Institute of Technology) one CubeSat kilogram nanosatellite that was launched by a Rokot rocket OSCAR 55 from Plesetsk at 14:15 UT on 30 June 2003. It carries a 100 mW beacon at 436.8375 MHz. 27844
Facts in Brief
Launch Date: 2003-06- 30 Launch Vehicle: Rokot Launch Site: Plesetsk, Russia Mass: 1.0 kg
Funding Agency
Tokyo Institute of Technology (Japan)
Disciplines
Communications Technology Applications
Additional Information
Launch/Orbital information for Cute 1
Experiments on Cute 1
Data collections from Cute 1
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel DMSP 5D-3/F16
Publications NSSDC ID: 2003-048A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events DMSP F16 (USA 172) was launched by a Titan 2 rocket from DMSP-F16 Vandenberg AFB at 16:17 UT on 18 October 2003. The USA 172 Defense Meteorological Satellite Program (DMSP) is a Department of Defense (DoD) program run by the Air Force 28054 Space and Missle Systems Center (SMC). The program designs, builds, launches, and maintains satellites monitoring Facts in Brief the meteorological, oceanographic, and solar-terrestrial physics environments. Each DMSP satellite has a 101 minute, Launch Date: 2003-10- sun-synchronous near-polar orbit at an altitude of 830km 18 above the surface of the earth. The visible and infrared Launch Vehicle: Titan II sensors (OLS) collect images across a 3000 km swath, Launch providing global coverage twice per day. The combination of Site: Vandenberg AFB, day/night and dawn/dusk satellites allows monitoring of global United States information such as clouds every 6 hours. The microwave imager (SSMI) and sounders (SSMT1, SSMT2) cover one half the width of the visible and infrared swath. These instruments Funding Agency cover polar regions at least twice and the equatorial region Unknown (United States) once per day. The space environment sensors (SSJ, SSM, SSIES) record along-track plasma densities, velocities, composition and drifts (SS stands for Special Sensor). Disciplines
DMSP F16 carries two new experiments: the limb scanning Earth Science ultraviolet imager/spectrometer SSULI built by the Naval Surveillance and Other Research Laboratory and the nadir scanning ultaviolet Military imager/spectrometer and photometer SSUSI built by the Space Physics Applied Physics Laboratory at Johns Hopkins University. It also carried new versions of the Special Sensor for Ions, Electrons and Scintillations (SSIES-13) and of the precipitating Additional ion and electron monitor (SSJ-5) Information
The data from the DMSP satellites are received and used at Launch/Orbital operational centers continuously. The data are sent to the information for DMSP 5D- National Geophysical Data Center's Solar Terrestrial Physics 3/F16 Division (NGDC/STP) by the Air Force Weather Agency (AFWA) for creation of an archive. Experiments on DMSP 5D- 3/F16
Data collections from DMSP 5D-3/F16
Questions or comments about this spacecraft can be directed to: Dr. Dieter K. Bilitza.
Other Sources of DMSP Data/Information
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2003-048A[13/10/2010 23:47:43] NASA - NSSDC - Spacecraft - Details
DMSP data (National Geophysical Data Center)
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Personnel Double Star 1
Publications NSSDC ID: 2003-061A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Double Star 1 (also known as Tan Ce 1, and TC 1) is a Sino- Tan Ce 1 European (CSNA-ESA) satellite that was launched by a Long TC 1 March 2C/SM rocket from Xichang Satellite Launch Center in the Sichuan province of China (PRC) at 19:06 UT on 29 28140 December 2003. The 330 kg, 260 W satellite is cylindrical, with a diameter of 2.1 m, a height of 1.4 m, and spins at a rate of Facts in Brief 15 rpm. It carries eight instruments to probe Earth's magnetosphere, five from ESA and three from CNSA. (The Launch Date: 2003-12- ESA instruments are legacies from ESA's Cluster mission.) 29 The data from all instruments will be stored on-board and Launch Vehicle: Long dumped over three grounds stations: Shanghai and Beifing in March 2C/SM China, and Villafranca in Spain. There will be coordination Launch Site: Xichang, between the Cluster and Double Star missions. For more Peoples Republic of China information, see Mass: 330.0 kg http://www.esa.int/export/esaSC/120381_index_0_m.html Nominal Power: 260.0 W In the early morning on 14 October 2007, the satellite re- entered the Earth's atmosphere and disintegrated during its descent. Funding Agencies China National Space Administration (Peoples Republic of China) European Space Agency (International)
Discipline
Space Physics
Additional Information
Launch/Orbital information for Double Star 1
Experiments on Double Star 1
Data collections from Double Star 1
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Office.
Personnel
Name Role Original Affiliation E-mail Dr. Christophe Project ESA-European Space Research [email protected] Philippe Escoubet Scientist and Technology Centre
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Personnel Dtusat
Publications NSSDC ID: 2003-031C Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events DTUSAT is a Danish (Danish Technological University) 27842 nanosatellite that was launched by a Rokot rocket from Plesetsk at 14:15 UT on 30 June 2003. It will image stars. Facts in Brief
Launch Date: 2003-06- 30 Launch Vehicle: Rokot Launch Site: Plesetsk, Russia
Funding Agency
Unknown (Denmark)
Discipline
Astronomy
Additional Information
Launch/Orbital information for Dtusat
Experiments on Dtusat
Data collections from Dtusat
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Echostar 9
Publications NSSDC ID: 2003-034A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events ECHOSTAR 9, also known as TELSTAR 13, is an American Galaxy 23 geostationary communications satellite that was launched by a G-23 Zenit 3SL rocket from the floating Odyssey platform on the equatorial Pacific at 154 deg-W longitude at 03:31 UT on 8 Telstar 13 August 2003. The 4.7 tonne satellite carries 24 C-band, and a 27854 few Ku- and Ka- band transponders to provide direct-to-home and cable-fed high definition television programs to all regions of North America after parking over 121 deg-W longitude. Facts in Brief Launch Date: 2003-08- 08 Launch Vehicle: Zenit 3SL Launch Site: Odyssey (Sea Launch Platform), null
Funding Agency
International Telecommunications Satellite Corporation (International)
Discipline
Communications
Additional Information
Launch/Orbital information for Echostar 9
Experiments on Echostar 9
Data collections from Echostar 9
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Eurobird 3
Publications NSSDC ID: 2003-043A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events E-Bird is a European geostationary communications spacecraft E-bird that was launched by an Ariane 5 rocket from Kourou at 23:14 27948 UT on 27 September 2003. The 888 kg, 1.6 kW satellite carries 20 Ku-band transponders to provide video and data transmissions to Europe and Turkey through four antenna Facts in Brief beams, after parking over 33 deg-E longitude. Launch Date: 2003-09- 27 Launch Vehicle: Ariane 5 Launch Site: Kourou, French Guiana
Funding Agency
European Telecommunications Satellite Consortium (International)
Discipline
Communications
Additional Information
Launch/Orbital information for Eurobird 3
Experiments on Eurobird 3
Data collections from Eurobird 3
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Express AM22
Publications NSSDC ID: 2003-060A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Express AM-22 is a Russian geostationary communications SESAT 2 satellite that was launched by a Proton-K rocket from Baikonur 28134 at 23:00 UT on 28 December 2003. The 2.6 tonne, 6 kW satellite will provide television, internet and data transmissions to Russia and bordering countries through its 24 Ku-band Facts in Brief transponders, after parking over 53 degrees E longitude. Launch Date: 2003-12- 28 Launch Vehicle: Proton-K Launch Site: Tyuratam (Baikonur Cosmodrome), Kazakhstan Mass: 590.0 kg Nominal Power: 6000.0 W
Funding Agency
Russian Satellite Communications Company (Russia)
Discipline
Communications
Additional Information
Launch/Orbital information for Express AM22
Experiments on Express AM22
Data collections from Express AM22
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel FSW-3 1
Publications NSSDC ID: 2003-051C Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events FSW-3 1 is a Chinese (PRC) recoverable satellite that was 28078 launched at 07:20 on 3 November 2003, by a Long March 2-D rocket. During the few weeks of orbiting, it was to collect "scientific and other" data through its imaging instruments. It Facts in Brief reentered on 25 November 2003, probably as soft-landing. Launch Date: 2003-11- 03 Launch Vehicle: Long March 2D Launch Site: Peoples Republic of China
Funding Agency
Unknown (Peoples Republic of China)
Disciplines
Earth Science Microgravity
Additional Information
Launch/Orbital information for FSW-3 1
Experiments on FSW-3 1
Data collections from FSW- 3 1
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Galaxy 12
Publications NSSDC ID: 2003-013B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Galaxy 12 is an American (PanAmSat Corp.) geostationary 27715 communications spacecraft that was launched by an Ariane 5 rocket from Kourou on 9 April 2003. The 1.8 tonne satellite carries 24 -band transponders to provide voice, video and data Facts in Brief transmissions to North and South Americas, after parking over Launch Date: 2003-04- 72 deg-W longitude. 09 Launch Vehicle: Ariane 5 Launch Site: Kourou, French Guiana
Funding Agency
Unknown (United States)
Discipline
Communications
Additional Information
Launch/Orbital information for Galaxy 12
Experiments on Galaxy 12
Data collections from Galaxy 12
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel GALEX
Publications NSSDC ID: 2003-017A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The Galaxy Evolution Explorer (GALEX) is an orbiting space Galaxy Evolution Explorer ultraviolet telescope, which explores the origin and evolution of Small Explorer/GALEX galaxies, and the origins of stars and heavy elements over the redshift range of z between 0 and 2. GALEX will conduct an SMEX/GALEX all-sky imaging survey, a deep imaging survey, and a survey of Explorer 83 200 galaxies nearest to the Milky Way Galaxy. As well, 27783 GALEX will perform three spectroscopic surveys over the 135- 300 nanometer band. GALEX has a planned 29 month mission, and is a part of the Small Explorers (SMEX) program. Facts in Brief
The spacecraft will be three-axis stabilized, with power coming Launch Date: 2003-04- from four fixed solar panels. The spacecraft bus is from Orbital 28 Sciences Corporation based on OrbView 4. The telescope is a Launch 50-cm Modified Ritchey-Chretien with a rotating grism. GALEX Vehicle: Pegasus XL uses the first ever UV light dichroic beam-splitter flown in Launch Site: Cape space to direct photons to the Near UV (175-280 nanometers) Canaveral, United States and Far UV (135-174 nanometers) microchannel plate Mass: 280.0 kg detectors. Each of the two detectors has a 65 millimeter Nominal diameter. The target orbit is 670 km circular and inclined at Power: 290.0 W 28.5 degrees to the equator. Funding Agency
NASA-Office of Space Science (United States)
Discipline
Astronomy
Additional Information
Launch/Orbital information for GALEX PDMP information for GALEX Telecommunications information for GALEX
Experiments on GALEX
Data collections from GALEX
Questions or comments about this spacecraft can http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2003-017A[13/10/2010 23:55:55] NASA - NSSDC - Spacecraft - Details
be directed to: Coordinated Request and User Support Office.
Personnel
Name Role Original Affiliation E-mail Dr. Peter Project Scientist California Institute of [email protected] Friedman Technology Dr. Christopher Mission Principal California Institute of [email protected] R. Martin Investigator Technology Dr. James L. Project Manager NASA Jet Propulsion [email protected] Fanson Laboratory
US Active Archive for GALEX Information/Data
The GALEX Archive at MAST (STScI)
Other Sources of GALEX Information/Data
GALEX Home Page
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Personnel Gruzomaket
Publications NSSDC ID: 2003-055A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Gruzomaket is a Russian satellite that was launched by a 28098 Strela rocket (a modified SS-19 ICBM) from Baikonur. No further information could be ascertained except that the Russian Interfax news agency calls the payload as a mock-up Facts in Brief (and the name can be so translated also). Launch Date: 2003-12- 05 Launch Vehicle: null Launch Site: Tyuratam (Baikonur Cosmodrome), Kazakhstan
Funding Agency
Unknown (Russia)
Discipline
Other
Additional Information
Launch/Orbital information for Gruzomaket
Experiments on Gruzomaket
Data collections from Gruzomaket
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel GSAT 2
Publications NSSDC ID: 2003-018A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events GSAT 2 is an Indian (ISRO) geostationary communications 27807 and space monitoring spacecraft that was launched by a 414 tonne GSLV-D2 rocket from Satish Dhawan Space Center in Sriharikota on the southeastern coast of India at 11:28 UT on 8 Facts in Brief May 2003. The main mission was to test for the second time Launch Date: 2003-05- the rocket configuration, with the proven PSLV lower stages 08 and a cryogenic third stage that uses a Russian motor. The 1.9 Launch Vehicle: GSLV- tonne, 1.4 kW GSAT 2 carries four C-band and two Ku-band D2 transponders to provide voice and video transmissions to India Launch Site: Sriharikota, and neighboring countries. It was maneuvered into the India designated parking lot at 48 deg-E longitude on 19 May 2003. For more details, see Funding Agency http://www.isro.org/ Unknown (India)
Discipline
Communications
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Launch/Orbital information for GSAT 2
Experiments on GSAT 2
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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=2003-018A[13/10/2010 23:58:40] Muses-C / Hayabusa
DESCRIPCIÓN: Esta nave es un proyecto de la Agencia Espacial Japonesa y su principal objetivo es el asteroide de nombre (por decir algo) 1998SF36 (nº 25143- Tipo Apollo) (Se le ha rebautizado como 'Itokawa', nombre del creador de los primeros cohetes japoneses). Su diámetro es de unos 500 metros. Fue descubierto el 26 de septiembre de 1.998 por el programa LINEAR del M.I.T. La gran novedad de esta misión es que descenderá sobre la superficie de la roca y tomará muestras para traerlas de nuevo a la Tierra, siendo la primera sonda que lo haga.
Esta misión tiene gran importancia puesto que el conocimiento de la composición de los asteroides nos puede ayudar a conocer el origen de nuestro Sistema Solar. Fue lanzada por el cohete japonés M-V en mayo de 2.003 y llegará a su destino en el verano de 2.005. Durante 5 meses orbitará el asteroide y tomará muestras de él para retornar a la Tierra en el 2.007, aterrizando en paracaídas en Woomera, Australia. Otra novedad es que usará un sistema de propulsión eléctrica de calentamiento por microondas de gas xenón.
En esta nave se encuentran inscritos los nombres de todos los que se apuntaron a través de esta web. (Ver noticia 27.06.02)
FECHAS PRINCIPALES:
- Lanzamiento: 9 de mayo de 2.003 - Sobrevuelo de la Tierra: junio de 2.004 - Llegada y toma de muestras: verano de 2.005 - Retorno muestras a Tierra: verano de 2.007
ATERRIZAJE: La sonda cartografiará y estudiará durante varios meses el asteroide para conocer su forma y composición. Una vez decidida una zona de aterrizaje, al llegar a una altitud de 100m. soltará el llamado 'Target Market' que es un pequeño objeto con marcas para poder calibrar las distancias de aproximamiento por los distintos medidores de distancia de la sonda. Cuando falten unos centímetros, la sonda disminuirá su velocidad y el cono de muestras quedará muy cerca de la superficie. En ese momento disparará un pequeño proyectil que levantará el polvo de la superficie para ser recogido por el propio cono. Apenas un par de segundos después la sonda se levantará y volverá a su órbita.
LA NAVE: Su peso es de unos 500kg. y se alimenta de energía solar. Posee un sistema de navegación autónoma que le permite la toma de decisiones por ejemplo en el aterrizaje. Sus dimensiones son de 1.5x1.5x1.2m. y la antena tiene un diámetro de 1.5m.
INSTRUMENTOS:
- Optical Navegacion Cámera (ONC): Cámara para la toma de fotografías. - Light Detection And Ranging (LIDAR): Medirá la distancia a los objetos. - Laser Range Finder (LRF): Láser para medidas - Espectrómetro Rayos X e infrarrojo: Análisis de la superficie del asteroide. - Minerva: Pequeño robot autónomo que volará por la superficie del asteroide.
ORGANISMOS: Toda la sonda ha sido construida, diseñada y financiada por la Agencia Espacial Japonesa ISAS.
La cámara ONC-T de Hayabusa posee una CCD que tiene una resolución de 1024 x 1000 píxeles. En el pasado acercamiento del día 12, esta cámara ha realizado la mejor imagen disponible hasta la fecha de la superficie de un asteroide. Desde una distancia de 5 kilómetros puede captar objetos con una resolución de hasta 50 centímetros. Mientras más desciende Hayabusa, la resolución espacial aumenta hasta distinguir minúsculas estructuras en la superficie de Itokawa.
En el descenso del día 12, la sonda Hayabusa logró bajar hasta unos 55 metros de la superficie del asteroide. Si la sonda se acerca a menos de 60 a 75 metros, la cámara ONC-T ya no consigue enfocarse correctamente por lo que esa es la mejor distancia posible para realizar las imágenes. A esa distancia la resolución espacial es de unos 6 milímetros por píxel lo que permite ver hasta los más pequeños guijarros del suelo.
Parte de la imagen de alta resolución y el entorno
Los trozos de rocas que conocemos como meteoritos, ahora ya pueden ser vistos en su estado original y apreciar su naturaleza y estructura. En la imagen dada a conocer la resolución es de 2 centímetros por píxel y está realizada desde una altura de 160 metros. La imagen de la derecha muestra el entorno de la zona ampliada y está tomada en el mismo momento con la cámara de campo ancho ONC-W1. La segunda imagen muestra una comparación con la última fotografía adquirida por la sonda NEAR en el asteroide Eros.
Comparación con la imagen de NEAR
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did not collect a sample. This was the first ever controlled of the Hayabusa spacecraft at landing on an asteroid and first ascent from any other solar the Muses Sea on Itokawa, sytem body except the Moon. Science, 312, No. 5578, 1350-1353, June 2006. A second touchdown and sampling run was made on 25 November, early telemetry indicates the spacecraft touched down at 10 cm/sec and two sampling bullets were fired 0.2 Kawaguchi, J., et al., MUSES- seconds apart at 22:07 UT 24 November (7:07 a.m. JST 25 C, Its launch and early orbit November) but examination of later telemetry indicates it is not operations, Acta Astronaut., clear that the bullets were fired. On 9 December contact was 59, No. 8-11, 669-678, Dec. lost with the spacecraft, presumably because of torques 2006. caused by a thruster leak which altered the pointing of the antenna. Communications with the spacecraft were regained in Spacecraft image at top of page early March 2006. It appears that the chemical fuel has been by James Garry lost due to the leak, two of three reaction wheels are also inoperable and 4 of the 11 lithium-ion battery cells are not functioning. Ground controllers are using the solar batteries to run the ion engine, which will be used in place of the chemical thrusters to maintain attitude control. The ion engine ran until November 2007, at which time it was turned off and the spacecraft went into hibernation mode and continue on a ballistic trajectory. There is still a large margin of xenon left to run the thrusters for propulsion and attitude control. Earth return is scheduled for 13 June 2010.
The samples, if any were collected, will have a total mass of less than one gram. It is hoped that even if the projectiles did not fire that a small number of particles may have been kicked up into the collection area during the touchdown due to the extremely low surface gravity. They are held inside a separate re-entry capsule. The re-entry capsule will be detached from the main spacecraft at a distance of about 300,000 to 400,000 km from the Earth, and the capsule will coast on a ballistic Hayabusa Project Home trajectory, re-entering the Earth's atmosphere on 13 June Page - ISAS, Japan 2010. The capsule will experience peak decellerations of about Hayabusa Project Science 25 G and heating rates approximately 30 times those Data Archive experienced by the Apollo spacecraft. It will land via parachute near Woomera, Australia. (This scenario is a change from the Public Release of Hayabusa original plan to launch in July 2002 to the asteroid Nereus.) Data Archives - 24 April 2007 More detail on the recovery Spacecraft and Subsystems plan - 14 December 2005 The Hayabusa spacecraft has a box-shaped main body 1.5 m Hayabusa Status Report - 12 along each side and 1.05 m high. The launch mass is 530 kg, December 2005 including 50 kg of chemical propellant and 65 kg of xenon gas. Hayabusa Status Report - 12 Two solar panel wings with a total array area of 12 square December 2005 meters protrude from the side and a 1.5 m diameter high-gain Hayabusa's Practice Descent parabolic antenna is mounted on top on a two-axis gimbal. A (Rehearsal) - 04 November cylindrical sampler horn, deployed shortly after launch, 2005 JAXA Report protrudes from the bottom of the spacecraft. The Minerva MUSES-C Testing Status lander was also mounted on th spacecraft near the bottom Report - 06 August 2002 panel. Hayabusa is propelled during cruise phases by two MUSES-C Rover Cancelled - microwave ion thruster engines, which use a microwave 03 November 2000 NASA discharge to ionize xenon gas. The ionized plasma is Press Release accelerated by high-voltage electrodes through four thruster Change in MUSES-C Target heads which protrude from one side of the spacecraft body to and Launch Date - 07 August provide a peak thrust of 20 mN using 1 kW power. A nitrogen 2000 NASA Press Release tetroxide/hydrazine propulsion system with a peak thrust of 22 N will be used for maneuvering. The spacecraft is powered by gallium-arsenide solar cells and a 15 A-hr rechargeable nickel- metal hydride (Ni-MH) battery. Communications are via X- and S-band low gain antennas and the high gain dish antenna (X- band) with a transmitted power of 20 W. The mission is also be equipped with a camera, used for imaging, visible-polarimetry studies, and optical navigation near the asteroid, a laser ranging device (LIDAR), and near-IR and X-ray spectrometers. The insulated and cushioned re-entry capsule, 40 cm in diameter and 25 cm deep with a mass of about 20 kg, is attached to the body of the spacecraft near the sample collection horn. The capsule has a convex nose covered with a 3 cm thick ablative heat shield to protect the samples from the high velocity (~13 km/s) re-entry. Cost of the Hayabusa spacecraft is roughly 12 billion yen ($100 million U.S.)
Surface Sample Collection The lander will be equipped with a universal sample collection Image of asteroid Itokawa device which will gather roughly one gram of surface samples taken by Hayabusa (Copyright taken from the landings at 3 different locations. The device ISAS, JAXA) consists of a funnel-shaped collection horn, 40 cm in diameter at the end, which is to be placed over the sampling area. A Other NSSDC Resources pyrotechnic device fires a 10 gram metal projectile down the Asteroid Page barrel of the horn at 200 - 300 m/sec. The projectile strikes the Asteroid Fact Sheet surface producing a small impact crater in the surface of the May 1997 Press Release - NASA asteroid and propelling ejecta fragments back up the horn, Rover and involvement with the where some of it is funnelled into a sample collection chamber. mission. Prior to each sampling run, the spacecraft will drop a small target plate onto the surface from about 30 m altitude to use as JAXA Resources a landmark to ensure the relative horizontal velocity between Hayabusa Now - Current the spacecraft and asteroid surface is zero during the Position of Hayabusa sampling. After sampling the samples will be stored in the re- Hayabusa Description - ISAS, entry capsule for return to Earth. Japan Hayabusa Project News - JAXA, Minerva Japan The Minerva lander is a small (591 gram) cylinder about the Hayabusa Home Page - ISAS, size of a coffee can, designed to be released from the Japan spacecraft on the first rehearsal touchdown run. It has the ISAS Home Page ability to "hop" on the surface of the asteroid and has full autonomy. It is equipped with an imaging system comprising
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three miniature cameras and temperature measuring devices. Data will be relayed to Hayabusa and then to Earth.
SSV Rover The rover, or Small Science Vehicle (SSV), was to have been a NASA contribution to the mission but was cancelled due to budget contraints. The SSV would have been dropped onto the surface of the asteroid by the Hayabusa spacecraft. The rover goals were to make texture, composition and morphology measurements of the surface layer at scales smaller than 1 cm, investigations of lateral heterogeneity at small scales, investigation of vertical regolith structure by taking advantage of disturbances of the surface layer by microrover operations, and to measure constraints on the mechanical and thermal properties of the surface layer. The rover would weigh about 1 kg and would be capable of rolling, climbing, or hopping around on the surface of the asteroid. It would have run on solar power and carry a multi-band imaging camera, a near- infrared point spectrometer, and an alpha/X-ray spectrometer (AXS).
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Personnel Hellas-Sat
Publications NSSDC ID: 2003-020A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Hellas-Sat is a joint Greece-Cyprus geostationary 27811 communications spacecraft that was launched by an Atlas 5 rocket (fitted with a Russian RD-180 motor) from Cape Canaveral at 22:10 UT on 13 May 2003. The 3.45 tonne Facts in Brief satellite carries 30 Ku-band transponders to provide direct-to- Launch Date: 2003-05- home voice and video transmissions to much of Europe, North 13 Africa and the Middle East, after parking over 39 deg-E Launch Vehicle: Atlas longitude. V Launch Site: Cape Canaveral, United States
Funding Agencies
Hellas-Sat Consortium (Greece) Hellas-Sat Consortium (Cyprus)
Discipline
Communications
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Launch/Orbital information for Hellas-Sat
Experiments on Hellas-Sat
Data collections from Hellas-Sat
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Horizons 1
Publications NSSDC ID: 2003-044A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events HORIZONS 1 (GALAXY 13) is a joint American-Japanese (i.e, Galaxy 13 PanAmSat- JSAT corporations) geostationary communications 27954 spacecraft that was launched by a Zenit 3 rocket from the floating platform Odessey in equatorial Pacific ocean on 1 October 2003. The 2.6 tonne (4.06, including the fuel), 9.9 kW Facts in Brief satellite carries 24 transponders each in the C- and Ku-bands to provide digital video, internet, and data services to the Launch Date: 2003-10- countries on either side of the Pacific ocean after parking over 01 127 deg-W longitude. The alternative designation of GALAXY Launch Vehicle: Zenit 3 13 is adopted from the fact that the C-band component is a Launch Site: Odyssey legacy of the GALAXY series and its co-owner PanAmSat who (Sea Launch Platform), null will control it, not the JSAT. Funding Agencies
PANAMSAT - JSAT (United States) PANAMSAT - JSAT (Japan)
Discipline
Communications
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Launch/Orbital information for Horizons 1
Experiments on Horizons 1
Data collections from Horizons 1
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel ICESat
Publications NSSDC ID: 2003-002A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events ICESat is a part of NASA's Earth Observing System. Its Ice, Cloud, and Land primary objectives are to determine the mass balance of the Elevation Satellite polar ice sheets and their contributions to global sea level 27642 change and to obtain essential data for prediction of future changes in ice volume and sea-level. Secondary objectives are to measure cloud heights and the vertical stucture of Facts in Brief clouds and aerosols in the atmosphere, to map the topography of land surfaces, and to measure roughness, reflectivity, Launch Date: 2003-01- vegetation heights, snow-cover, and sea-ice surface 13 characteristics. Launch Vehicle: Delta II To achieve these goals, ICESat will utilize its sole instrument, Launch the Geoscience Laser Altimeter System, or GLAS. Site: Vandenberg AFB, United States Nominal Power: 350.0 W
Funding Agency
National Aeronautics and Space Administration (United States)
Discipline
Earth Science
Additional Information
Launch/Orbital information for ICESat Telecommunications information for ICESat
Experiments on ICESat
Data collections from ICESat
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Other sources of ICESat information
ICESat project (NASA GSFC)
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Personnel IGS 1A
Publications NSSDC ID: 2003-009A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events IGS 1A (Informaton Gathering Satellite 1A) and IGS 1B are two Information Gathering Japanese reconnaissance satellites that were launched by a Satellite 1A H-2A rocket from Tanegashima Space Center at 01:27 UT on 27698 28 March 2003. They may be tasked to watch for nuclear explosions and missile launches in nearby countries, in addition to global natural disasters and hurricanes. As such, Facts in Brief according to the Japanese Defence Ministry, the launch is not in violation of the Japan-N. Korea declaration of September Launch Date: 2003-03- 2002. One of the two spacecraft uses optical cameras with a 28 resolution of one meter; the other uses synthetic aperture Launch Vehicle: H-2A radar to provide images at a resolution of a few meters. No Launch information is available as to which satellite carries which Site: Tanegashima, Japan instrument. Funding Agency
Unknown (Japan)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for IGS 1A
Experiments on IGS 1A
Data collections from IGS 1A
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel IGS 1B
Publications NSSDC ID: 2003-009B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events IGS 1B (Information Gathering Satellite 1B) and IGS 1A are Information Gathering two Japanese reconnaissance satellites that were launched by Satellite 1B a H-2A rocket from Tanegashima Space Center at 01:27 UT 27699 on 28 March 2003. They may be tasked to watch for nuclear explosions and missile launches in nearby countries, in addition to global natural disasters and hurricanes. As such, Facts in Brief according to the Japanese Defence Ministry, the launch is not in violation of the Japan-N. Korea declaration of September Launch Date: 2003-03- 2002. One of the two spacecraft uses optical cameras with a 28 resolution of one meter; the other uses synthetic aperture Launch Vehicle: H-2A radar to provide images at a resolution of a few meters. No Launch information is available as to which satellite carries which Site: Tanegashima, Japan instrument. Funding Agency
Unknown (Japan)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for IGS 1B
Experiments on IGS 1B
Data collections from IGS 1B
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Innovation 1
Publications NSSDC ID: 2003-049B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Innovation 1, also known as Chuangxin 1, is a Chinese (PRC) Chuangxin 1 prototype of an advanced telecommunication satellite with 29058 potentials for environmental protection, oil and gas transportation, flood prevention and earthquake monitoring. The 100 kg satellite was launched by a Long March 4B rocket Facts in Brief from Taiyuan Satellite Launch Center in Shanxi province on 21 October 2003. Launch Date: 2003-10- 21 Launch Vehicle: Long March 4B Launch Site: Taiyuan, Peoples Republic of China
Funding Agency
Unknown (Peoples Republic of China)
Discipline
Communications
Additional Information
Launch/Orbital information for Innovation 1
Experiments on Innovation 1
Data collections from Innovation 1
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Insat 3A
Publications NSSDC ID: 2003-013A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Insat 3A is an Indian (ISRO) geostationary communications 27714 and weather-monitoring satellite that was launched by an Ariane 5 rocket from Kourou at 22:52 UT on 9 April 2003. The 3-tonne satellite carries 12 C-band, six Extended C-band, and Facts in Brief six Ku-band transponders to provide voice, video and data Launch Date: 2003-04- transmission to West Asia, East Asia, and India, after parking 09 over 93.5 deg-E longitude. Insat 3A carries also the usual Launch Vehicle: Ariane Insat package of sensors in visual, infrared and water vapor 5 bands to monitor clouds and storms. The spatial resolution at Launch Site: Kourou, visual wavelengths is 2 km, and at infrared 1 km. The satellite French Guiana also carries a separate transponder for the international search and rescue program. Funding Agency
Indian Space Research Organization (India)
Disciplines
Communications Earth Science
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Launch/Orbital information for Insat 3A
Experiments on Insat 3A
Data collections from Insat 3A
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel INSAT 3E
Publications NSSDC ID: 2003-043E Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events INSAT 3E is an Indian geostationary communications satellite 27951 that was launched by an Ariane 5 rocket from Kourou at 23:14 UT on 27 September 2003. It joins the currently operational fleet of four such INSATs (2E, 3A, 3B, and 3C). The 2.8 tonne, Facts in Brief triaxially stabilized satellite carries 24 C-band, and 12 Launch Date: 2003-09- extended C-band transponders to provide communications and 27 television services to the Indian subcontinent, after parking Launch Vehicle: Ariane over 55 deg-E longitude. 5 Launch Site: Kourou, French Guiana
Funding Agency
Unknown (India)
Discipline
Communications
Additional Information
Launch/Orbital information for INSAT 3E
Experiments on INSAT 3E
Data collections from INSAT 3E
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Intelsat 907
Publications NSSDC ID: 2003-007A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Intelsat 907 is a geostationary communications spacecraft of 27683 the Intelsat corporation which had been a global, multigovernment-owned consortium that was privatized in 2002. It was launched by an Ariane 44L rocket from Kourou at Facts in Brief 07:00 UT on 15 February 2003. The 4.7 tonne spacecraft will Launch Date: 2003-02- provide data-relay among installations in North America, South 15 America, Western Europe and Africa through its array of C- Launch Vehicle: Ariane and K-band transponders after parking over 27.5 deg-W 44L longitude. It replaces the aging Intelsat 605. This was the last Launch Site: Kourou, and 116th launch of the Ariane-4 series which will be replaced French Guiana by the Ariane-5 series.
Funding Agency
International Telecommunications Satellite Corporation (International)
Discipline
Communications
Additional Information
Launch/Orbital information for Intelsat 907
Experiments on Intelsat 907
Data collections from Intelsat 907
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel IRS P6
Publications NSSDC ID: 2003-046A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events IRS P6, also known as Resourcesat 1, is an Indian remote Resourcesat 1 sensing and photo-imaging spacecraft that was launched by a 28050 PSLV-C5 rocket from Sriharikota in southeast India at 04:54 UT on 17 October 2003. The 1,360 kg satellite carries carries high resolution imaging instruments to monitor agricultural, Facts in Brief land, and water resources. Launch Date: 2003-10- 17 Launch Vehicle: PSLV Launch Site: Sriharikota, India
Funding Agency
Unknown (India)
Discipline
Earth Science
Additional Information
Launch/Orbital information for IRS P6
Experiments on IRS P6
Data collections from IRS P6
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Kaistsat 4
Publications NSSDC ID: 2003-042G Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Kaistsat 4 (Korea Advanced Institute of Science and Korea Advanced Institute Technology SATellite 4) is a S-Korean astrophysical satellite of Science and that was launched by a Kosmos 3M rocket from Plesetsk at Technology Satellite 4 06:12 UT on 27 September 2003. The 120 kg satellite carries a 27945 spcial UV imaging spectrograph to monitor gas clouds in the Galaxy. It will complete a full sky mapping in about a year, by scanning a one-degree strip every day. Additionally, it may Facts in Brief also aim the telescope downward to image auroral displays. Launch Date: 2003-09- 27 Launch Vehicle: Kosmos-3M Launch Site: Plesetsk, Russia
Funding Agency
Unknown (South Korea)
Discipline
Astronomy
Additional Information
Launch/Orbital information for Kaistsat 4
Experiments on Kaistsat 4
Data collections from Kaistsat 4
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Personnel Larets
Publications NSSDC ID: 2003-042F Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Larets is a Russian satelite that was launched by a Kosmos 27944 3M rocket from Plesetsk at 06:12 UT on 27 September 2003. It will help "tuning ground radars". It carries reflectors for ground based laser rangers. Facts in Brief Launch Date: 2003-09- 27 Launch Vehicle: Kosmos-3M Launch Site: Plesetsk, Russia
Funding Agency
Unknown (Russia)
Discipline
Other
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Personnel Mars Express
Publications NSSDC ID: 2003-022A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Mars Express is a European Space Agency (ESA) mission to Mars Express Orbiter Mars. It consists of an orbiter, the Mars Express Orbiter, and a Beagle 2 lander, Beagle 2. The scientific objectives of the Mars Express Orbiter are to obtain global high-resolution photo-geology (10 m resolution), mineralogical mapping (100 m resolution) and Facts in Brief mapping of the atmospheric composition, study the subsurface structure, the global atmospheric circulation, and the Launch Date: 2003-06- interaction between the atmosphere and the subsurface, and 02 the atmosphere and the interplanetary medium. The Beagle 2 Launch Vehicle: Soyuz lander objectives are to characterize the landing site geology, Launch Site: Tyuratam mineralogy, and geochemistry, the physical properties of the (Baikonur Cosmodrome), atmosphere and surface layers, collect data on martian Kazakhstan Mass: 666.0 kg Mars Express meteorology and climatology, and search for possible signatures of life. Nominal Power: 460.0 W Spacecraft and Subsystems The Mars Express Orbiter is a cube-shaped spacecraft with Discipline two solar panel wings extending from opposite sides. The launch mass of 1123 kg includes a main bus with a 113 kg of Planetary Science payload, the 60 kg lander, and 457 kg of propellant. The main body is 1.5 m x 1.8 m x 1.4 m in size, with an aluminum honeycomb strucure covered by an aluminum skin. The solar Additional panels measure about 12 m tip-to-tip. A 1.8 m diameter high- Information gain antenna is mounted on one face, pointing in the same Launch/Orbital direction as the solar panels. Two 20 m long wire dipole information for Mars antennas extend from opposite side faces perpendicular to the Express solar panels as part of the radar sounder. A 4 m tubular monopole low-gain antenna extends from the upper face. The PDMP information for body is built around the main propulsion system, which Mars Express consists of a bi-propellant 400 N main engine. The two 267- liter propellant tanks have a total capacity of 595 kg. Experiments on Mars Approximately 370 kg are needed for the nominal mission. Express Pressurized helium from a 35 liter tank is used to force fuel into the engine. Trajectory corrections will be made using a set of Data collections from Mars eight 10 N thrusters, one attached to each corner of the Express spacecraft bus. Attitude control (3-axis stabilization) is achieved using two 3-axis inertial measurement units, a set of two star cameras and two Sun sensors, gyroscopes, Questions or comments accelerometers, and four 12-Nms reaction wheels. Pointing about this spacecraft can accuracy is .04 degrees with respect to the inertial reference be directed to: Dr. David R. frame and 0.8 degrees with respect to the Mars orbital frame. Williams. Thermal control is maintained through the use of radiators, multi-layer insulation, and actively controlled heaters. The spacecraft configuration is optimized for a Soyuz/Fregat, but is fully compatible with a Delta II launch vehicle if necessary.
Spacecraft power is provided by the solar panels which contain 11.42 square meters of silicon cells. The originally planned power was to be 660 W at 1.5 AU but a faulty connection has http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2003-022A[14/10/2010 0:21:37] NASA - NSSDC - Spacecraft - Details
reduced the amount of power available by 30%, to about 460 W. This loss of power is not expected to significantly impact the science return of the mission. Power is stored in three lithium-ion batteries with a total capacity of 64.8 Ah for use during eclipses. The power is fully regulated at 28 V, the peak power requirement at Mars is 450 W. Telecommunications are via the high-gain parabolic antenna and two omnidirectional low-gain S-band antennas. These provide X-band (7.1 GHz) and S-band (2.1 GHz) uplink and downlink. Two Mars lander relay UHF antennas are mounted on the top face for communication with the Beagle 2. The spacecraft is run by two Control and Data management Units with a 10 gigabit solid state mass memory for storage of data and housekeeping information for transmission.
The science payload consists of seven experiments. The high resolution stereoscopic camera (HRSC) is mounted inside the spacecraft body, aimed through the top face of the spacecraft, which is nadir pointing during Mars operations. A visible and near-infrared spectrometer (OMEGA), infrared spectrometer (PFS) and ultraviolet spectrometer (SPICAM) are also mounted inside pointing out the top face. The neutral and charged particle sensors (ASPERA) are mounted on the top face. The subsurface radar and altimeter is mounted in the body and is nadir pointing, and also incorporates the two 20 m antennas. The radio science experiment (MaRS) uses the communications subsystem. The total mass budgeted for the science payload is 116 kg.
Beagle 2 The Beagle 2 is a lander initially mounted on the top deck of the Mars Express Orbiter. It was released from Mars Express on 19 December and reached Mars on 25 December. However no signals have been received from the lander and the mission has been declared lost. For more information on the Beagle 2 lander, see:
http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=2003- 022C
Mission profile Launch took place on a Soyuz/Fregat from Baikonur Cosmodrome on 2 June 2003 at 23:45 local time (17:45 UT, 1:45 p.m. EDT), with the Mars Express and Fregat booster put into a 200 km Earth parking orbit. The Fregat was fired again at 19:14 UT to put the spacecraft into a Mars transfer orbit, and the Fregat and Mars Express separated at approximately 19:17 UT. The solar panels have been deployed and a trajectory correction maneuver will be performed on 4 June to aim Mars Express towards Mars and allow the Fregat booster to coast into interplanetary space. Mars Express arrived at Mars after a 400 million km journey and a course correction in September, in December 2003. The Beagle 2 lander was released on 19 December at 8:31 UTC (9:31 CET) on a ballistic cruise towards the surface. On 20 December, Mars Express fired a short thruster burst to put it into position to orbit the planet. The Mars Express Orbiter fired its main engine for 37 minutes on 25 December at 2:47 UT (9:47 p.m. EST, 24 December) and went into a highly elliptical 250 km x 150,000 km initial capture orbit with an inclination of 25 degrees. The orbit will be adjusted by four more main engine firings starting on 30 December to the desired 258 km x 11,560 km near polar (86.3 degree inclination) orbit with a period of 7.5 hours. Near periapsis the top deck will be pointed down towards the martian surface and near apoapsis the high gain antenna will be pointed towards Earth for uplink and downlink. After 440 days the apoapsis will be lowered to 10,107 km and periapsis will be raised to 298 km to give an orbital period of 6.7 hours. Aerobraking can be used to modify the orbit if there are any
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problems with the main engine. Nominal mission duration is planned to be 1 martian year (687 Earth days).
The Beagle 2 coasted for five days after release and entered the martian atmosphere on the morning of 25 December. Landing was expected to occur at about 02:54 UT on 25 December (9:54 p.m. EST 24 December). No signals have been received and the lander was declared lost
The overall Mars Express budget excluding the lander is 150 million Euros (roughly $150 million U.S.)
Personnel
Name Role Original Affiliation E-mail Mr. Augustin Project ESA-European Space Research and Chicarro Scientist Technology Centre Dr. Rudolf J. Project ESA-European Space Research and [email protected] Schmidt Manager Technology Centre
Selected References
Bridges, J. C., et al., Selection of the landing site in Isidis Planitia of Mars probe Beagle 2, J. Geophys. Res., 108, No. E1, Jan. 2003.
Schmidt, R., Mars Express - ESA's first mission to planet Mars, Space Technol., 20, No. 5-6, 219-224, 2001.
Wright, I. P., et al., Scientific objectives of the Beagle 2 lander, Acta Astronaut., 52, No. 2-6, 219-225, 2003.
Beagle 2 after separating from Mars Express
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Beagle 2 lander (image © Beagle 2 Project)
Mars Express Launches Successfully - ESA Press Release
Beagle 2 Information Mars Home Page Chronology of Mars Exploration
Mars Express Home Page - ESA Beagle 2 Home Page - The Open University
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Esta misión es la primera de la Agencia Espacial Europea hacia Marte y será una de las cuatro que lleguen a las inmediaciones del planeta entre finales de 2.003 y principios de 2.004, sumándose a las dos que ya están en órbita. La sonda portará una pequeña nave de descenso denominada Beagle-2. El lanzamiento fue llevado a cabo por un cohete ruso Soyuz/Fregat el 2 de junio de 2.003, para llegar a Marte seis meses después, a finales de año. El objetivo principal de la misión es la búsqueda de agua en el subsuelo desde la órbita y de restos pasado o presentes de vida desde la superficie. El orbitador posee siete instrumentos científicos que buscarán la localización y el estado del agua en Marte y la sonda de descenso se centrará en la búsqueda de elementos químicos y biológicos.
FECHAS PRINCIPALES:
Lanzamiento: 2 de junio de 2.003. 17:45 GMT Llegada a Marte: 19 de diciembre 2.003 Suelta de la sonda de descenso y aterrizaje en Marte: 25 de diciembre de 2.003 - 02:54 GMT Fin de la misión: diciembre 2.005
EL ORBITADOR MARS EXPRESS:
Esta misión nació tras el fracaso de Mars'96, una misión rusa a Marte no logró llegar ni siquiera a la órbita de la Tierra y en ella iban muchos experimentos europeos que se perdieron. De este modo, la Agencia Espacial Europea decidió revivir algunos de esos experimentos en una nueva misión y añadir algunos más, con las mejoras técnicas del paso del tiempo. La nave permanecerá en órbita durante un año marciano (687 días o dos años terrestres) pero puede ser extensible a dos años más y aparte de sus propios objetivos como misión, llevará consigo un pequeño módulo de descenso y servirá como repetidor para las futuras misiones europeas y americanas a Marte. Un mes antes de llegar a Marte, se activará la sonda Beagle-2 y sólo 5 días antes del encuentro, la sonda será soltada para iniciar una caída libre hacia el Planeta Rojo. En esos momentos Mars Express encenderá por primera vez su motor principal que le dará la dirección necesaria para ponerse días después en órbita del planeta.
Una vez llegado a Marte adquirirá un órbita elíptica a una altitud entre 1.000 y 11.500 km. con un periodo de 7,5 horas que le permitirá adquirir datos del módulo Beagle-2 y tomar datos con sus equipos cuando se encuentre en la parte más cercana de la órbita y transmitirlos a la Tierra cuando se encuentre en la parte más alejada de Marte. Las antenas de Guayana y Perth serán las encargadas de mantener el contacto con la nave.
Las dimensiones totales de la nave son de 1,5x1,8x1,4 metros y su peso total con el Beagle-2 y el combustible incluido no llegan a los 1.100 kg. La electricidad la proveen dos paneles solares con una superficie de 11 m2. Durante el recorrido se harán ajustes a la órbita con unas pequeñas toberas que posee la sonda a su alrededor y el motor principal es capaz de desarrollar una fuerza de 400N y posee dos tanques con 267 litros de propelentes impulsados por helio. La antena principal de comunicaciones tiene un diámetro de 1,8 metros y la secundaria una longitud de 40 cm. La velocidad de transmisión puede llegar a 230kbps. El disco duro de la nave tiene una capacidad de 12 Gb. donde los datos serán almacenados antes de ser transmitidos a la Tierra. INSTRUMENTOS MARS EXPRESS:
Mars Express lleva cuatro instrumentos dedicados al estudio de la superficie. - High Resolution Stereo Camera (HRSC): Cámara de altísima resolución que realizará mapas topográficos y tomará imágenes con una resolución de hasta 2 metros. - IR Mapping Spectrometer (OMEGA): espectrómetro infrarrojo para el suelo y las rocas. - Radio Science Experiment (MaRS): experimentos de radio que analizarán el interior de Marte y su geodesia. - Sub-surface Sounding Radar / Altimeter (MARSIS): Radar que medirá la profundidad y composición del suelo marciano. Se espera que este aparato determine hasta una profundidad de 3 kilómetros la cantidad de agua que hay actualmente en Marte. Y otros tres instrumentos se dedicarán al estudio de la atmósfera. - Energetic Neutral Atoms Analyser (or ASPERA): estudiará la atmósfera superior y examinará los efectos del viento solar sobre ella, midiendo los gases neutros y los cargados eléctricamente. - Planetary Fourier Spectrometer (PFS): estudiará la atmósfera en infrarrojos creando mapas en tres dimensiones de temperaturas y presiones. - UV and IR Atmospheric Spectrometer (SPICAM): medirá la composición y estructura de la atmósfera. LA SONDA DE DESCENSO - BEAGLE 2:
El Beagle-2 es una sonda de descenso a Marte diseñada y construida por completo por un consorcio de universidades británicas, que llegará al planeta rojo a bordo de la sonda de la Agencia Espacial Europea Mars Express. Su misión fundamental será la búsqueda de indicios biológicos y experimentos atmosféricos y geoquímicos. La sonda fue aprobada en noviembre de 1.999 con un peso inicial de 108kg. pero este peso ha sido reducido hasta los 30 kg. debido a la miniaturización y los recortes presupuestarios. Es hasta este momento la sonda con mayor carga de instrumentos en relación a su peso.
Se espera que su vida útil en la superficie sea de seis meses extensibles hasta 24 meses en total. Como sitio de aterrizaje se elegirá un lugar en el cual hayan acontecido inundaciones en el pasado para que la superficie sea lo más lisa posible y aumente la posibilidad de encontrar restos orgánicos. Cinco días después de entrar en órbita, Mars Express soltará al módulo de descenso, siendo este un momento crítico ya que si no se soltara ninguna de las dos partes podría seguir su misión. La sonda va metida en una cápsula que la protege de la contaminación biológica en la Tierra, de las radiaciones del espacio durante el viaje y del calor de la entrada en la atmósfera marciana. Una vez frenada en la atmósfera la mayor parte de la velocidad, se despliega un paracaídas hasta las cercanías de la superficie donde este se soltará y se abrirán los airbags que protegen a Beagle-2 del impacto contra el suelo hasta que el conjunto quede inmovilizado por completo.
INSTRUMENTOS BEAGLE 2:
- Espectrómetro de masas: analizará muestras del suelo en busca de restos biológicos. Contiene el GAP - Gas Analysis Package, aparato encargado de calentar las muestras en presencia de oxígeno e introducirlas en el espectrómetro. Las muestras calentadas desprenderán dióxido de carbono y el espectrómetro medirá la abundancia de dos isótopos del carbono y ver la relación existente entre ellos (12C y 13C). Otros gases como el metano también serán analizados. Las muestras serán analizadas en un amplio intervalo de temperaturas, pero las muestras orgánicas deben de descomponerse en temperaturas entre los 200 y 500ºC. También estudiará componentes de la atmósfera que nos informarán sobre la historia climática de Marte.
- Cámaras: la sonda de descenso llevará tres cámaras, dos de ellas formarán un sistema de visión estéreo y estará montadas en el brazo robótico. Una de ellas está provista de un espejo y nos dará la primera imagen de Marte antes incluso de que el brazo esté desplegado. La tercera cámara está acoplada a un microscopio en el brazo robótico y nos servirá para analizar las rocas del entorno de la nave con una resolución de cuatro micrones y en varias longitudes de onda.
- Recogida de muestras: Llamado Pluto, es un mecanismo de penetración en el suelo marciano para tomar muestras sin contaminar y analizarlas en el espectrómetro. Todo el aparato se encuentra al final de un cable de tres metros de longitud que será la distancia a la cual podrá ser lanzador el recogedor de las muestras.
- Espectrómetro Mossbauer: nos dará información acerca de las muestras de terreno y su composición en mineral de hierro midiendo la velocidad de los rayos gamma emitidos por las rocas y el análisis de un detector de rayos-X.
- Equipo de sensores medioambientales: En total habrá un conjunto de 7 sensores entre los que tenemos un sensor ultravioleta para detectar el flujo de radiación solar en los 200-400 nm., MAOS que es un instrumento capaz de identificar y cuantificar las moléculas oxidantes de la atmósfera, un sensor de radiaciones de protones solares y rayos cósmicos de alta energía, termómetros que medirán variaciones de hasta 0.05ºC, sensores de presión atmosférica con sensibilidad de hasta 0,1mBar, una veleta para medir la velocidad de los vientos y su dirección, detectores de impacto de polvo para medir la fuerza de impacto de los granos de arena en Marte y un acelerómetro triple que medirá las condiciones en las que se encuentra la nave durante el descenso y datos sobre las capas altas de la atmósfera. WEBS:
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Personnel MILSTAR 6
Publications NSSDC ID: 2003-012A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events USA 169 is an American military geostationary, super-secure USA 169 communications satellite that was launched by a Titan 4 rocket 27711 from Cape Canaveral AFS at 13:43 UT on 8 April 2003. The 4.5 tonne satellite is also known as MILSTAR 6 (MILitary Strategic and TActical Relay satellite 6). With the end of the Facts in Brief cold war, MILSTARs are no longer engineered for "heroic survivability". No further details are available. Launch Date: 2003-04- 08 Launch Vehicle: Titan IV Launch Site: Cape Canaveral, United States
Funding Agency
Department of Defense (United States)
Discipline
Surveillance and Other Military
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Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Mimosa
Publications NSSDC ID: 2003-031B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events MIMOSA is a Czech minisatellite that was launched by a Rokot 27841 rocket from Plesetsk at 14:15 UT on 30 June 2003. The 66 kg satellite is nearly spherical with 28 sides and carries a microaccelerometer to monitor atmospheric density profile by Facts in Brief sensing the atmospheric drag. Launch Date: 2003-06- 30 Launch Vehicle: Rokot Launch Site: Plesetsk, Russia
Funding Agency
Czechoslovakia Academy of Sciences (Czech Republic)
Discipline
Earth Science
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Personnel Molniya 1-92
Publications NSSDC ID: 2003-011A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Molniya 1-92 is a Russian military communications spacecraft 27707 that was launched from Plesetsk by a Molniya-M rocket at 01:53 UT on 2 April 2003. Facts in Brief
Launch Date: 2003-04- 02 Launch Vehicle: Molniya-M Launch Site: Plesetsk, Russia
Funding Agency
Unknown (Russia)
Discipline
Surveillance and Other Military
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Personnel Molniya 3-53
Publications NSSDC ID: 2003-029A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Molniya 3-53 is a two-tonne Russian military communications 27834 spacecraft that was launched into a highly elliptical orbit by a Molniya-M rocket from Plesetsk at 20:00 UT on 19 June 2003. It will be the last in the Molniya 3 series. Facts in Brief Launch Date: 2003-06- 19 Launch Vehicle: Molniya-M Launch Site: Plesetsk, Russia
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Unknown (Russia)
Disciplines
Communications Surveillance and Other Military
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Personnel Monitor-E/Breeze
Publications NSSDC ID: 2003-031A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events MONITOR-E/Breeze is a Russian mockup of a MONITOR- 27840 E(arth) satellite that remained unseparated from the Breeze- KM upper stage. Facts in Brief
Launch Date: 2003-06- 30 Launch Vehicle: Rokot Launch Site: Plesetsk, Russia
Funding Agency
Unknown (Russia)
Discipline
Earth Science
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Publications NSSDC ID: 2003-031D Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events MOST is a Canadian (CSA) astronomy satellite that was 27843 launched by a Rokot rocket from Plesetsk at 14:15 UT on 30 June 2003. The 65 x 65 x 30 cm, 51 kg satellite carries a 60 cm aperture reflecting telescope to monitor the brightness Facts in Brief variations in a star caused by soundwaves on its surface, or Launch Date: 2003-06- from reflections from an orbiting planet. Because of its light 30 weight and low cost, it has been dubbed as Humble Launch Vehicle: Rokot Telescope. Launch Site: Plesetsk, Russia
Funding Agency
Canadian Space Agency (Canada)
Discipline
Astronomy
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Personnel
Name Role Original Affiliation E-mail Dr. Jaymie Mission Principal University of British [email protected] Matthews Investigator Columbia
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Personnel Mozhayets 4
Publications NSSDC ID: 2003-042A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Mozhayets 4 is a Russian cadets' training satelite that was 27939 launched by a Kosmos 3M rocket from Plesetsk at 06:12 UT on 27 September 2003. It will help in laser-assisted geodesic measurements via its optical reflectors. Facts in Brief Launch Date: 2003-09- 27 Launch Vehicle: Kosmos-3M Launch Site: Plesetsk, Russia
Funding Agency
Unknown (Russia)
Discipline
Other
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Personnel Navstar 51
Publications NSSDC ID: 2003-005A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Navstar 51 (also known as USA 166, and as GPS 2R-8) is the USA 166 latest to join the American (DoD) fleet of Global Positioning GPS 2-R-8 Satellites. It was launched by a Delta 2 rocket from Cape Canaveral at 18:06 UT on January 29 2003. The fleet is 27663 operating in full capacity with 24 spacecraft (in six planes, with four satellites in each). GPS 2R-8 will replace the aging GPS Facts in Brief 2A-18, which will be shifted away in its Plane-B and then retired. Launch Date: 2003-01- 29 Launch Vehicle: Delta II Launch Site: Cape Canaveral, United States
Funding Agency
Department of Defense (United States)
Discipline
Navigation & Global Positioning
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Personnel Navstar 52
Publications NSSDC ID: 2003-010A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Navstar 52, also known as USA 168 and as GPS 2R-9, is an USA 168 American Global Positioning Satellite that was launched by a 27704 Delta 2 rocket from Cape Canaveral AFS at 22:09 UT on 31 March 2003. It will replace the aging GPS 2-5 in the fleet (of 28 satellites). Facts in Brief
Launch Date: 2003-03- 31 Launch Vehicle: Delta II Launch Site: Cape Canaveral, United States
Funding Agency
Unknown (United States)
Discipline
Navigation & Global Positioning
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Personnel Navstar 53
Publications NSSDC ID: 2003-058A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Navstar 53, also known as USA 175, as GPS 2R-10, and as USA 175 SVN-47, is an American navigational satellite in the GPS fleet. GPS 2R-10 It was launched by a Delta 2 rocket from Cape Canaveral AFS at 07:50 UT on 21 December 2003. It will replace the aging but SVN-47 still operational GPS 2A-10 craft in Plane-E and Slot-2. The 28129 GPS constellation consists of 24 satellites split into six orbital planes with four in each plane, all in circular orbits of altitude 20,200 km, and inclination of 55 degrees. There are also four Facts in Brief additional satellites orbiting as reserves. The full list is available Launch Date: 2003-12- at 21 Launch Vehicle: Delta http://leonardo.jpl.nasa.gov/msl/Programs/gps.html II Launch Site: Cape Canaveral, United States
Funding Agency
Unknown (United States)
Discipline
Navigation & Global Positioning
Additional Information
Launch/Orbital information for Navstar 53
Experiments on Navstar 53
Data collections from Navstar 53
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Nigeriasat 1
Publications NSSDC ID: 2003-042C Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Nigeriasat 1 is a Nigerian DMC (multinational Disaster 27941 Monitoring Constellation) satellite that was launched by a Kosmos 3M rocket from Plesetsk at 06:12 UT on 27 September 2003. It carries imaging cameras for disaster Facts in Brief monitoring, urban planning and agriculture. Launch Date: 2003-09- 27 Launch Vehicle: Kosmos-3M Launch Site: Plesetsk, Russia
Funding Agency
Unknown (Nigeria)
Discipline
Other
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Launch/Orbital information for Nigeriasat 1
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Personnel Opportunity
Publications NSSDC ID: 2003-032A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events "Opportunity" (Mars Exploration Rover B or MER-1) is one of MER 1 the two rovers launched to Mars in mid-2003. The rovers Mars Exploration Rover 1 arrived at Mars in January of 2004 equipped with a battery of scientific instruments and will be able to traverse 100 meters a Mars Exploration Rover B day. The nominal plan calls for the missions to last for 90 days, MER-B until April 2004, but it is likely the mission will last beyond this 27849 time. The scientific goals of the rover missions are to gather data to help determine if life ever arose on Mars, characterize the climate of Mars, characterize the geology of Mars, and Facts in Brief prepare for human exploration of Mars. To achieve these goals, seven science objectives are called for: 1) search for Launch Date: 2003-07- and characterize a variety of rocks and soils that hold clues to 08 Launch Vehicle: Delta Opportunity past water activity, 2) determine the distribution and composition of minerals, rocks, and soils surrounding the II 7925 landing sites, 3) determine what geologic processes have Launch Site: Cape shaped the local terrain and influenced the chemistry 4) Canaveral, United States perform "ground truth" of surface observations made by Mars Mass: 185.0 kg orbiter instruments, 5) search for iron-bearing minerals, identify and quantify relative amounts of specific mineral types Funding Agency tha contain water or were formed in water, 6) characterize the mineralogy and textures of rocks and soils and determine the NOAA National processes that created them, and 7) search for geological Environmental Satellite clues to the environmental conditions that existed when liquid Service (United States) water was present and assess whether those environments were conducive to life. Discipline Spacecraft and Subsystems Planetary Science The Mars Exploration Rover consists of a box-like chassis mounted on six wheels. The chassis contains the warm electronics box (WEB). On top of the WEB is the triangular Additional rover equipment deck, on which is mounted the Pancam mast Information assembly, high gain, low gain, and UHF antennas, and a camera calibration target. Attached to the two forward sides of Launch/Orbital the equipment deck are solar arrays which are level with the information for deck and extend outward with the appearance of a pair of Opportunity swept-back wings. Attached to the lower front of the WEB is PDMP information for the instrument deployment device, a long hinged arm which Opportunity protrudes in front of the rover. Telecommunications information for The wheels are attached to a rocker-bogie suspension system. Opportunity Each wheel has its own motor and the two front and two rear wheels are independently steerable. The rover has a top speed Experiments on of 5 cm per second, but the average speed over time on flat Opportunity hard ground would be 1 cm/sec or less due to the hazard avoidance protocols. The rover is designed to withstand a tilt of Data collections from 45 degrees without falling over, but is programmed to avoid Opportunity exceeding tilts of 30 degrees. The warm electronics box houses the computer, batteries, and other electronic components. The box is designed to protect these components http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2003-032A[14/10/2010 0:36:26] NASA - NSSDC - Spacecraft - Details
and control their temperature. Thermal control is achieved Questions or comments through the use of gold paint, aerogel insulation, heaters, about this spacecraft can thermostats, and radiators. be directed to: Dr. David R. Williams. Power is provided by the solar arrays, generating up to 140 W of power under full Sun conditions. The energy is stored in two rechargeable batteries. Communications with Earth are in X- band via the high gain directional dish antenna and the low gain omni-directional antenna. Communications with orbiting spacecraft are through the UHF antenna. The onboard computer has 128 Mb RAM. An inertial measurement unit provides 3-axis information on position.
The rover carries a suite of instruments for science and navigation. The panoramic camera (Pancam) and navigation cameras are mounted on top of the Pancam mast assembly, at a height of about 1.4 meters from the base of the wheels. The mast, mounted at the front of the equipment deck, also acts as a periscope for the Miniature Thermal Emission Spectrometer (Mini-TES). Attached to the end of the instrument deployment device are the Alpha Particle X-Ray Spectrometer (APXS), Mossbauer Spectrometer (MB), Microscopic Imager (MI), and Rock Abrasion Tool (RAT). A magnet array is attached to the front of the equipment deck. Two hazard avoidance cameras are mounted on the front of the rover and two on the rear. The group of science instruments (Pancam, Mini-TES, APXS, MB, MI, and RAT) is known as the Athena science package.
The rover will be compactly stowed in a tetrahedron shaped landing platform and encased in an aeroshell consisting of a heat shield and a backshell for launch, cruise, and atmospheric entry. The lander platform has a mass of 348 kg, the backshell and parachute 209 kg, and the heat shield 78 kg. The cruise stage mass is 193 kg and propellant mass is 50 kg.
Mission Profile Opportunity was launched on a heavy Delta II 7925H on 8 July 2003 at 03:18:15 UT (July 7, 11:18:15 p.m. EDT). After insertion into a circular Earth parking orbit, the spacecraft third stage reignited and put the craft on a trajectory to Mars, after which the aeroshell, lander, and rover separated from the third stage. The cruise phase to Mars ended on 11 December 2003, 45 days before Mars entry. The approach phase lasted from this date until martian atmospheric entry on 25 January 2004. On entry the lander and components had a mass of 827 kg and were travelling at 19,300 km/hr. The aeroshell decelerated the lander in the upper martian atmosphere for about four minutes to a velocity of 1600 km/hr, followed by deployment of a parachute. The parachute slowed the spacecraft to about 300 km/hr. A series of tones transmitted by the spacecraft during entry and after landing indicated the successful completion of each phase. Just prior to impact, at an altitude of about 100 m, retrorockets slowed the descent and airbags inflated to cushion the impact. The craft hit at roughly 50 km/hr and bounced and rolled along the surface, stopping in a small crater. The airbags deflated and retracted, the petals opened, and the rover deployed its solar arrays. The landing took place at 5:05 UT (Earth received time), 12:05 a.m. EST or approximately 1:15 p.m. local time, about two and a half hours before Earth set at Terra Meridiani. On Mars it was the latter half of southern summer. The landing ellipse is centered at 2.07 S, 6.08 W and is roughly 119 by 17 km oriented at 88 degrees. Terra Meridiani is also known as the "Hematite Site" because it displays evidence of coarse-grained hematite, an iron-rich mineral which typically forms in water. It also appears to be one of the smoothest and therefore safest areas for a landing.
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An egress phase took place over the first 4 days, involving deployment of the Pancam mast and high gain antenna, rover stand up, imaging and calibration, selection of proper egress path, and finally driving of the rover off the lander deck onto the martian surface. Over three years of surface operations, involving driving the rover, imaging, and use of the science instruments has already been achieved, the Opportunity rover has covered over 10 km and continues to operate.
Personnel
Name Role Original Affiliation E-mail Ms. Joy Anne Project NASA Jet Propulsion [email protected] Crisp Scientist Laboratory Mr. Peter C Project NASA Jet Propulsion [email protected] Theisinger Manager Laboratory Dr. James B. Program NASA Headquarters [email protected] Garvin Scientist Dr. Firouz M. Program NASA Jet Propulsion [email protected] Naderi Manager Laboratory
Selected References
Crisp, J. A., et al., Mars Exploration Rover mission, J. Geophys. Res., 108, No. E12, 8061, doi:10.1029/2002JE002038, 2003.
Squyres, S. W., et al., Athena Mars rover science investigation, J. Geophys. Res., 108, No. E12, 8062, doi:10.1029/2003JE002121, 2003.
Squyres, S. W., et al., The Opportunity Rover's Athena Science Investigation at Meridiani Planum, Mars, Science, 306, No. 5702, 1698-1703, Dec. 2004.
Cook, R. A., The Mars exploration rover project, Acta Astronaut., 57, No. 2-8, 116-120, 2005.
Squyres, S. W., et al., Two years at Meridiani Planum: Results from the Opportunity Rover, Science, 313, No. 5792, 1403-1407, Sept. 2006.
Squyres, S. W., et al., Overview of the Opportunity Mars Exploration Rover Mission to Meridiani Planum: Eagle Crater to Purgatory Ripple, J. Geophys. Res., 111, E12S12, doi:10.1029/2006JE002771, 2006.
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"Opportunity" images from Meridiani Planum
Mars Exploration Rover "Spirit" Page
Labelled Diagram of the Mars Exploration Rover
NASA Mars Rovers Braving Severe Dust Storms - NASA Press Release 20 July 2007 Durable Mars Rovers Sent Into Third Overtime Period - NASA Press Release 5 April 2005 Opportunity Rover Finds Strong Evidence Meridiani Planum Was Wet - NASA Press Release 2 March 2004 Mars Rovers Head for Exciting Landings in January - NASA Press Release 2 December 2003 NASA Selects 28 Participating Scientists for Mars Rover Mission - NASA Press Release 29 May 2002 NASA Plans to Send Rover Twins to Mars in 2003 - NASA Press Release 10 August 2000 Announcement of Rover Option - NASA Press Release 27 July 2000 Mars Pathfinder Rover
Mars Exploration Rover Home Page - NASA JPL Athena Science Package Site - Cornell University
Mars Home Page Mars Fact Sheet
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Personnel Optus 1C
Publications NSSDC ID: 2003-028B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Optus 1C is an Australian dual-use (civil-military) geostationary 27831 satellite that was launched by an Ariane 5 rocket from Kourou at 22:38 UT on 11 June 2003. The 4.7 tonne satellite carries 24 Ku-band civilian transponders and eight military Facts in Brief transponders. The civilian part of the payload will enable video Launch Date: 2003-06- and internet links to Australia, New Zealand and East Asia, 11 after parking over 156 deg-E longitude. Launch Vehicle: Ariane 5 Launch Site: Kourou, French Guiana
Funding Agency
Unknown (Australia)
Discipline
Communications
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Launch/Orbital information for Optus 1C
Experiments on Optus 1C
Data collections from Optus 1C
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Orbview 3
Publications NSSDC ID: 2003-030A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Orbview 3 is an American photo-imaging minisatellite that was 27838 launched at 18:55 UT on 26 June 2003 by a Pegasus rocket that was released from an L-1011 cargo plane flying out of Vandenberg AFB. The 304 kg satellite carries high-resolution Facts in Brief cameras to enable black-and-white images at 1.0 meter Launch Date: 2003-06- resolution and color images at 4.0 meter resolution. 26 Launch Vehicle: Pegasus Launch Site: Vandenberg AFB, United States
Funding Agency
Unknown (United States)
Discipline
Surveillance and Other Military
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Launch/Orbital information for Orbview 3
Experiments on Orbview 3
Data collections from Orbview 3
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Progress M-47
Publications NSSDC ID: 2003-006A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Progress M-47 is a Russian automatic cargo carrier that was 27681 launched by a Soyuz-U rocket from Baikonur at 12:59 UT on 2 February 2003. It was the 100th launch of the Progress craft series (with 43 Progress, 46 Progress-M, nine Progress M1, Facts in Brief and one Progress M-SO1). It transported food, fuel, and Launch Date: 2003-02- equipment to the ISS and docked automatically with the 02 Zvezda module of the ISS at 14:49 UT on 4 February. The Launch previously docked Progress M1-9 had been undocked and Vehicle: Soyuz-U deorbited in advance. Launch Site: Tyuratam (Baikonur Cosmodrome), Kazakhstan
Funding Agency
Unknown (Russia)
Discipline
Resupply/Refurbishment/Repair
Additional Information
Launch/Orbital information for Progress M-47
Experiments on Progress M-47
Data collections from Progress M-47
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Progress M-48
Publications NSSDC ID: 2003-039A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Progress M-48 is a Russian automatic cargo carrier that was 27873 launched by a Soyuz-FG rocket from Baikonur at 01.47 UT on 29 August 2003. It carried 2.6 tonne of food, fuel, water, and equipment to be delivered to the International Space Station Facts in Brief (ISS). It docked automatically with the Zvezda module of the Launch Date: 2003-08- ISS at 3:45 UT on 31 August 2003. In anticipation, the 29 previous carrier, PROGRESS M-47, containing the trash from Launch Vehicle: Soyuz the ISS was undocked and deorbited on 27 August. FG Launch Site: Tyuratam (Baikonur Cosmodrome), Kazakhstan
Funding Agency
Unknown (Russia)
Discipline
Resupply/Refurbishment/Repair
Additional Information
Launch/Orbital information for Progress M-48
Experiments on Progress M-48
Data collections from Progress M-48
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Progress M1-10
Publications NSSDC ID: 2003-025A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Progress M1-10 is a Russian automatic cargo carrier that was 27823 launched by a Soyuz-U rocket form Baikonur at 10:34 UT on 8 June 2003. It docked at 11:15 UT on 11 June with the PIRS module of the International Space Station (ISS) automatically Facts in Brief and delivered 2.3 tonnes of food, fuel, water, and Launch Date: 2003-06- scientific/engineering equipment. 08 Launch Vehicle: Soyuz-U Launch Site: Tyuratam (Baikonur Cosmodrome), Kazakhstan
Funding Agency
Unknown (Russia)
Discipline
Resupply/Refurbishment/Repair
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Launch/Orbital information for Progress M1-10
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Data collections from Progress M1-10
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Quakesat
Publications NSSDC ID: 2003-031F Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Quakesat is an American photo-imaging nanosatellite that was 27845 launched by a Rokot rocket at 14:15 UT on 30 June 2003. It is equipped with an earthquake detection instrument. Facts in Brief
Launch Date: 2003-06- 30 Launch Vehicle: Rokot Launch Site: Plesetsk, Russia
Funding Agency
Unknown (United States)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Quakesat
Experiments on Quakesat
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Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Rainbow 1
Publications NSSDC ID: 2003-033A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events RAINBOW 1 is an American geostationary communications 27852 satellite that was launched by an Atlas 5 rocket from Cape Canaveral at 23:45 UT on 17 July 2003. The 4.3 tonne satellite will provide direct-to- home television services in the Facts in Brief contiguous United States through its several transponders. Launch Date: 2003-07- Parking longitude is not available. 17 Launch Vehicle: Atlas V Launch Site: Cape Canaveral, United States
Funding Agency
Unknown (United States)
Discipline
Communications
Additional Information
Launch/Orbital information for Rainbow 1
Experiments on Rainbow 1
Data collections from Rainbow 1
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Personnel Rubin 4
Publications NSSDC ID: 2003-042B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Rubin 4 is a German satellite that was launched by a Kosmos 27940 3M rocket from Plesetsk at 06:12 UT on 27 September 2003. It remained attached to the upper stage of the rocket so as to monitor its position, velocity, and acceleration. Facts in Brief Launch Date: 2003-09- 27 Launch Vehicle: Kosmos-3M Launch Site: Plesetsk, Russia
Funding Agency
Unknown (Federal Republic of Germany)
Discipline
Communications
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Personnel Scisat 1
Publications NSSDC ID: 2003-036A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events SCISAT 1 is a Canadian (CSA) atmospheric research satellite Atmospheric Chemistry that was launched at 02:10 UT by a Pegasus XL rocket Experiment (ACE) released from a an L-1011 cargo plane flying out of ACE Vandenberg AFB on 13 August 2003. The 152 kg, 70 W, "bias momentum stabilized" spacecraft points to the Sun at one 27858 degree accuracy, and carries two instruments, FTS and MAESTRO, to monitor the atmospheric ozone and dust Facts in Brief composition in the 4-100 km altitude range. More details of the mission and the instruments are available via Launch Date: 2003-08- 13 http://www.space.gc.ca/asc/eng/ Launch Vehicle: Pegasus XL Launch Site: Vandenberg AFB, United States
Funding Agency
Canadian Space Agency (Canada)
Discipline
Earth Science
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Launch/Orbital information for Scisat 1
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Personnel
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Name Role Original Affiliation E-mail Dr. Peter F. Bernath Mission Scientist [email protected]
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Personnel SERVIS 1
Publications NSSDC ID: 2003-050A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events SERVIS 1 (Space Environment Reliability Verification Space Environment Integrated System) is Japanese test satellite that was Reliability Verification launched by a Rokot rocket from Plesetsk at 13:43 UT on 30 Integrated System October. The 900 kg, 1.4 x 1.4 x 2.3 m, 1.2 kW satellite carries 28060 mostly commercially available off-the-shelf household items like PCs and cell phones so as to ascertain the viability of such inexpensive satellites. It carries parts evaluation monitors also Facts in Brief to measure the degradation due to gamma rays and energetic particles. Launch Date: 2003-10- 30 Launch Vehicle: Rokot Launch Site: Plesetsk, Russia
Funding Agency
Unknown (Japan)
Discipline
Other
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Personnel Shenzhou 5
Publications NSSDC ID: 2003-045A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Shenzhou 5 was the fifth spacecraft in a series of launches Divine Vessel 5 which was designed to demonstrate the feasibility of sending a 28043 human into space by the People's Republic of China and the first to contain a human presence. The spacecraft was manned by Lt. Col. Yang Liwei, who orbited the Earth for nearly 21.5 Facts in Brief hours before landing in the grasslands of Inner Mongolia at 22:23 UTC (6:23 a.m. local time). While in orbit the taikonaut Launch Date: 2003-10- dined on specially prepared versions of Chinese food, talked 15 with his wife and son, and took a three hour nap in addition to Launch Vehicle: Long performing various planned activities. A total of 14 orbits were March 2F made. Launch Site: Jiuquan, Peoples Republic of China The Shenzhou spacecraft is based on the three-seat Russian Soyuz capsule, although extensive modifications have been Funding Agency made. China National Space Although the budget for China's space program was a closely- Administration (Peoples held secret, the government announced that it had spent $2.18 Republic of China) billion up to the point of this launch.
Discipline Shenzhou 5 Human Crew
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ESPECIAL MISIÓN SHENZHOU 5. PRIMERA MISIÓN TRIPULADA DE CHINA Lanzamiento: miércoles 15 de octubre - 01:00 GMT Aterrizaje: miércoles 15 de octubre - 22:23 GMT
El primer chino que ha sido puesto en el espacio regresó satisfactoriamente a la Tierra este miércoles 15 de octubre. Con este retorno, China se une a la Unión Soviética y a Estados Unidos en el exclusivo club de las naciones que han conquistado el espacio.
Suspendida en el aire con un gran paracaídas, la cápsula espacial en la que viajaba Yang Liwei aterrizó en las praderas del interior de Mongolia hacia las 6.23 a.m (hora local), tras 21 horas de odisea que le llevó a dar 14 vueltas alrededor de la Tierra. Yang apareció unos quince minutos después del aterrizaje, saludando y con aspecto cansado.
Apenas pronunció tres frases antes de volar hacia Pekín: “ La nave operó suavemente; me siento bien; estoy orgulloso de mi patria.”
Su retorno ha supuesto el final feliz para el primer viaje espacial chino, que tiene lugar cuadro décadas después de que el cosmonauta soviético Yuri Gagarin y el americano Alan Shepard se convirtieran en los primeros tripulantes de vuelos espaciales en 1961. Esta misión culmina el programa espacial iniciado por Mao Zedong en 1958, aunque éste fue inmediatamente abandonado durante la guerra fría. Un año después, China lanzó su primer satélite a bordo del cohete Long March, difundiendo el himno de la Revolución Cultural “El Este es Rojo.” La hazaña refleja el poder emergente de China, miembro permanente del Consejo de Seguridad de la ONU y una de las economías con mayor crecimiento. También ha sido elegida como sede de los Juegos Olímpicos de 2.008.
“Nuestro héroe espacial Yang Liwei salió de la cápsula por su pie. Nuestro primer vuelo tripulado ha sido un completo éxito”, afirmó el comandante de la misión Li Jinai. En una misión que parece contrarreloj, un cohete Long March 2F chino despegó hacia un despejado cielo azul sobre el desierto del Gobi (01:00 GMT del miércoles), alcanzando su órbita predeterminada diez minutos después. Yang realizó varias actualizaciones de sus condiciones a lo largo del viaje. La última de ellas, cuando la cápsula flotaba sobre el campo tras la re-entrada. También contactó con su mujer cuando el Shenzou V, también llamada “Nave Divina V” comenzaba su octava vuelta a la Tierra, asegurándole desde el espacio: “Me siento bien, no te preocupes.”
Yang, un teniente coronel del Ejército de Liberación del Pueblo, fue elegido entre catorce aspirantes. Es originario de la provincia china de Liaoning. Los medios estatales afirmaron que la cápsula de Yang portaba una pistola, un cuchillo y una tienda de campaña para el caso de que aterrizase en un lugar equivocado. Esta misión ha recibido muchas felicitaciones. En los Estados Unidos, el director de la NASA, Sean O’Keefe, describió el lanzamiento como un acontecimiento muy importante. El Secretario General de la ONU, Kofi Annan, afirmó que “cuando la exploración espacial no conoce límites nacionales, la misión del Shenzou-V es un paso adelante para toda la humanidad.” La tripulación que está a punto de despegar hacia la Estación Espacial Internacional afirmó que China es un serio competidor en la carrera por la supremacía en el espacio. “¿Es China una potencia rival? Naturalmente, no sólo en el espacio, sino en aspectos comerciales, económicos, incluso militares,” afirmó el astronauta norteamericano Michael Foale, comandante de la 8ª Expedición a la ISS.
Un tupido velo de secreto ha cubierto todo el programa espacial chino. El Estado retrasó la transmisión de televisión, tanto la del lanzamiento como la del aterrizaje.
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Publications NSSDC ID: 2003-043C Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The SMART-1 (Small Missions for Advanced Research in Small Missions for Technology 1) is a lunar orbiter designed to test spacecraft Advanced Research in technologies for future missions. It entered initial lunar orbit on Technology 1 13 November 2004. The primary technology being tested is a solar-powered ion drive. It will also carry an experimental deep-space telecommunications system and an instrument Facts in Brief payload to monitor the ion drive and study the Moon. The Launch Date: 2003-09- primary scientific objectives of the mission are to return data 27 on the geology, morphology, topography, mineralogy, Launch Vehicle: Ariane geochemistry, and exospheric environment of the Moon in 5 order to answer questions about planetary formation Launch Site: SMART 1 Kourou, accretional processes, origin of the Earth-Moon system, the French Guiana lunar near/far side dichotomy, long-term volcanic and tectonic Mass: 305.0 kg activity, thermal and dynamical processes involved in lunar evolution, and water ice and external processes on the surface. Discipline
Spacecraft and Subsystems Planetary Science SMART-1 is a box-shaped spacecraft roughly a meter on a side with two large solar panel wings spanning 14 meters Additional extending from opposite sides. The launch mass, including Information fuel, is 366.5 kg, the mass at the time it reaches the Moon should be about 305 kg. A solar-electric propulsion system (a Launch/Orbital Stationary Plasma Hall-effect thruster, PPS-1350) uses xenon information for SMART 1 gas as a propellant by ionizing the xenon and accelerating and PDMP information for discharging the plasma from the spacecraft at high speed. SMART 1 Electrons are also released into the flow to maintain a neutral charge on the spacecraft. A thrust of 70 milliNewtons and a Experiments on SMART 1 specific impulse of 1600 s is produced. 82 kg of supercritical xenon propellant will be carried aboard SMART-1 in a tank Data collections from mounted in the center of the structure above the thruster. The SMART 1 spacecraft is three-axis stabilized using four skewed reaction wheels and eight 1-N hydrazine thrusters mounted on the corners of the spacecraft bus. Attitude knowledge is provided by a star tracker, sun sensor, and angular rate sensors. Questions or comments about this spacecraft can 1850 W of power is produced from an array of gallium-indium- be directed to: Dr. David R. phosphide gallium arsenide germanium (GaInP/GaAs/Ge) Williams. solar cells covering an active surface on the wings of about 10 square meters. Solar array power is regulated to 50 V in the power control and distribution unit and distributed via solid- state power controllers. Power is stored in five 130-Whr lithium ion battery cells. Roughly 75% of the power is used to run the propulsion system during flight. Thermal control is achieved through the use of radiators, heat pipes, multilayer insulation blankets, thermistor controlled heaters, and high emissivity optical properties. Communication takes place via a medium gain and two low gain S-band antennas as well as the antenna for the experimental Ka/X system. The medium gain antenna http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2003-043C[15/10/2010 22:28:53] NASA - NSSDC - Spacecraft - Details
provides a telemetry rate of 65 kb/s. The two low gain antennas provide omin-directional ground coverage at 2 kb/s. The medium gain, Ka/X band, and one low gain antenna are mounted on one side panel of the spacecraft bus and the other low gain antenna is mounted on the opposite panel.
The spacecraft will carry a suite of science and technology instruments with a total mass of 19 kg. The science instruments include a pan-chromatic camera (AMIE) for lunar imaging, Langmuir probes mounted on booms (SPEDE) to measure the plasma environment, and radio science experiments (RSIS). Science instruments which are being tested as part of the technology verification are a miniaturized visible/near-infrared spectrometer (SIR) for lunar crustal studies, a miniature X-ray spectrometer for astronomy and lunar chemistry (D-CIXS), and an X-ray spectrometer to calibrate D-CIXS and to study the Sun (XSM). The Electric Propulsion Diagnostic package (EPDP) is a multi-sensor suite designed specifically to monitor the ion propulsion system, it also works in concert with the SPEDE to study the space plasma environment. The RSIS is also used to monitor the ion propulsion system. Finally an experimental telecommunication and tracking system, the Ka/X-band TTC (Telemetry and Telecommand) Experiment (KaTE) is included in the payload for technology assessment. The AMIE camera will also be used to support a test of an image-based On-Board Autonomous Navigation (OBAN) system. OBAN is designed to minimize the amount of ground intervention required for the mission.
Mission Profile The SMART-1 spacecraft launched on 27 September 2003 from Kourou, French Guiana as an auxiliary passenger on an Ariane-5 Cyclade which launched two other large satellites as its primary payload. It was put into a geostationary transfer orbit, 742 x 36,016 km, inclined at 7 degrees to the equator. The spacecraft used its ion drive over a period of 14 months to elongate its Earth orbit and utilized three lunar resonance maneuvers in August, September, and October 2004 to minimize propellant use. Its final continuous thrust maneuver took place over 100 hours from 10 to 14 October 2004. Lunar orbit capture occurred on 13 November 2004 at a distance of 60,000 km from the lunar surface. The ion engine began firing in orbit at 05:24 UT (12:24 a.m. EST) on 15 November to start a 4.5 day period of thrust to lower the orbit. The first perilune took place on 15 November at 17:48 UTC (12:48 p.m. EST) at an altitude of about 5000 km above the lunar surface. The engine was then used to lower the initial 4962 x 51477 km altitude, 5 day, 9 hour period, 81 degree inclination orbit, putting SMART-1 into a 300 x 3000 km polar orbit. Lunar commissioning began in mid-January 2005 and lunar science operations in February 2005. The mission has been extended from its originally planned 6-month lifetime by a year, so it will now conduct mapping of the Moon's surface and evaluating the new technologies onboard from lunar orbit until August 2006. The xenon-ion engine was shut down in September 2005 after exhausting its fuel supply. It operated for almost 5000 hours and underwent 843 starts and stops. SMART-1 performed a controlled crash into the Moon at about 2 km/sec on 3 September 2006, at 5:42 UT in the mid-southern region of the near side of the Moon in Lacus Excellentiae (Lake of Excellence) at 34.4 S, 46.2 W. The total cost of the spacecraft is estimated at 100 million euros in 2001 economic conditions (~$90 million U.S.).
Personnel
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Name Role Original Affiliation E-mail Dr. Guiseppe Project ESA-European Space Research and [email protected] D. Racca Manager Technology Centre Dr. Bernard Project ESA-European Space Research and [email protected] Foing Scientist Technology Centre
Selected References
Foing, B. H., et al., SMART-1 mission to the Moon: Technology and science goals, Adv. Space Res., 31, No. 11, 2323-2333, 2003.
Racca, G. D., et al., SMART-1 mission description and development status, Planet. Space Sci., 50, 1323-1337, 2002.
Foing, B. H., et al., The ESA SMART-1 mission to the Moon with solar electric propulsion, Adv. Space Res., 23, No. 11, 1865-1870, 1999.
Rathsman, P., et al., SMART-1: Development and lessons learnt, Acta Astronaut., 57, No. 2-8, 455-468, 2005.
Foing, B. H., et al., SMART-1 after lunar capture: First results and perspectives, J. Earth Syst. Sci., 114, No. 6, 689-697, Dec. 2005.
Foing, B. H., et al., SMART-1 mission to the Moon: Status, first results and goals, Adv. Space Res., 37, No. 1, 6-13, 2006.
SMART 1 Stationary Plasma Thruster (Credit ESA) SMART 1 Status Reports Impact landing ends SMART-1 mission to the Moon - ESA Press Release, 3 September 2006 Europe rediscovers the Moon with SMART-1 - ESA Press Release, 17 August 2006 Europe Reaches the Moon - ESA Press Release, 16 November 2004 SMART 1 leaves Earth on a long journey to the Moon - ESA Press Release (28 September 2003)
SMART 1 Home Page - ESA SMART 1 Mission Review - ESA ESA Home Page - Italy
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SMART 1 image of Pythagoras Crater (Credit ESA)
Moon Home Page
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DESCRIPCIÓN DE LA MISIÓN:
La Agencia Espacial Europea (ESA) posee un programa de pequeñas sondas de bajo coste denominadas genéricamente SMART (Small Missions for Advanced Research in Technology) que permiten probar nuevas tecnologías de comunicaciones y navegación que serán luego aplicadas a otras misiones de mayor tamaño.
La sonda SMART-1 cuyo destino es La Luna, es la primera en ver la luz de todo el proyecto y su objetivo primario es probar un nuevo sistema de propulsión llamado 'solar eléctrico' o 'propulsión iónica' que será usado posteriormente en la misión BepiColombo a Mercurio entre otras. Hasta ahora la única sonda en usar este sistema ha sido la Deep Space 1 de la NASA en 1.998. Además de este sistema de propulsión llevará varios instrumentos científicos para estudiar la Luna.
Esta nave con un peso total de 350kg. es la primera que la ESA envía a nuestro satélite y se espera que lo orbite durante al menos 6 meses. Será enviada al espacio desde la Guayana Francesa, como carga secundaria en un Ariane 5 en septiembre de 2.003. La sonda será controlada desde el Centro Europeo de Operaciones Espaciales (European Space Operations Centre, ESOC, en Darmstadt, Alemania).
SISTEMA DE PROPULSIÓN:
Ha sido desarrollado por la empresa SNECMA de Francia y utiliza el sistema conocido como 'propulsión eléctrica por iones', basado en el uso del gas xenón como propelente y los paneles solares como fuente de energía eléctrica, proporcionando una fuerza de empuje total de 70 miliNewtons, que la sonda utilizará para ir aumentando progresivamente su órbita en forma de espiral hasta alcanzar la Luna. Además de la propulsión, la sonda utilizará las técnicas de sobrevuelo y de los puntos de Lagrange lunares para ahorrar combustible y completar su recorrido hasta nuestro satélite que será de unos 16 meses. Otros dos instrumentos llamados SPEDE y EPDP medirán los datos y comportamientos del sistema de propulsión durante el viaje.
La misión usa un sistema electrostático conocido como motor de efecto Hall. El modelo para la misión llamado PSS-1350 desarrollado por SNECMA usa el gas xenón como propelente. Es un aparato muy compacto construido alrededor de una cámara de cerámica de forma anular de 10 cms de diámetro rodeada de imanes. En un lado se sitúa el cátodo que es un aparato que crea electrones. Estos electrones atraviesan una cámara anular y son atrapados por campos magnéticos, los electrones chocan con el gas xenón que entra en la cámara y forma iones de xenón cargados positivamente y más electrones. Esos electrones son usados otra vez para acelerar los iones, los cuales salen disparados de la cámara acelerados por el campo eléctrico creado por los electrones del cátodo. Estos iones brillan con una característica luz azul.
El empuje producido por el motor del SMART-1 es apenas perceptible, el equivalente al ejercido por un trozo de papel en la palma de la mano, pero tiene la ventaja de que funciona por largos periodos de tiempo (lo que no ocurre en los motores químicos), por lo que a la larga la sonda adquiere una mayor velocidad. Para las misiones interplanetarias, a pesar de tener un impulso bajo, al acumularse durante largos periodos de tiempo de manera continua, la nave alcanzará su destino antes que otra dotada con un motor químico.
ÓRBITAS DE LA MISIÓN:
De la Tierra a La Luna
Órbita de acercamiento a La Luna
FECHAS PRINCIPALES:
Lanzamiento: 27 de septiembre 2.003 Llegada a La Luna: diciembre 2.004 Fin de la misión: junio 2.005 - diciembre 2.006
INSTRUMENTOS SMART-1: De los siete instrumentos de a bordo, tres están destinados a la monitorización de los sistemas de propulsión eléctrica y los otros son para telecomunicaciones experimentales y tres para investigaciones lunares. - AMIE, Asteroid-Moon Micro-Imager Experiment: Es una cámara miniaturizada de alta resolución para fotografiar la superficie lunar, desarrollada por el Centre Suisse d'Electronique et de Microtechnique (CSEM) en Neuchatel, Suiza. Su peso total es de sólo 450 gramos y está diseñada para tomar imágenes en color, almacenarlas en memoria propia, comprimir las imágenes y enviarlas a la computadora de la nave. Posee un CCD de 1.024x1.024 pixeles con un campo de visión de 5,3 grados, alcanzando una resolución de 50 metros/pixel. Puede funcionar en luz visible, infrarrojo y ultravioleta gracias a los filtros que lleva incorporados.
- SIR: Espectrómetro de infrarrojo cercano entre los 900 y los 2.400 nm, para investigar los minerales de la superficie de la Luna desarrollado por el Max Planck Institute für Aeronomie (MPAe) en Garching, Alemania. Podrá distinguir entre varios componentes de la superficie como los piroxenos, olivinos y feldespatos.
- D-CIXS: Espectrómetro de Rayos-X miniaturizado para determinar la composición de la superficie lunar. Funciona analizando los rayos-X reflejados en la superficie lunar y que provienen del Sol. Como cada elemento tiene su propia huella, el espectrómetro podrá determinar la composición del terreno. Posee un sub-instrumento llamado XSM que es un sensor de rayos-X que medirá la radiación X del Sol para calibrar al D-CIXS. De camino a la Luna estudiarán otras fuentes de rayos-X de nuestro sistema solar y la galaxia. Se ha desarrollado en el Rutherford Appleton Laboratory del Reino Unido, la Universidad Politécnica de Catalunya y el Instituto de Estudios Espaciales. Nos dará un mapa global de la composición y distribución de los minerales (magnesio, aluminio, silicio, hierro...).
- KaTE: Demostrador tecnológico de telemetría y comunicaciones digitales en el espacio profundo en las bandas X y Ka. De esta manera en el futuro se usarán sistemas de comunicación con las sondas más efectivos y menos costosos. Se realizará un experimento de radio (RSIS) que observará el comportamiento del sistema de propulsión. Servirá como test para la futura misión a Mercurio que utilizará este medio junto a la cámara de imágenes para medir la libración del planeta y su estructura interna.
- Laser Link Experiment: Usando la Estación Óptica de Seguimiento de Tenerife se realizará este experimento que servirá estudiar las comunicaciones ópticas entre la Tierra y la nave y además probará el sistema autónomo de navegación. Este sistema de comunicaciones por láser permitirá a futuras sondas enviar muchísima más cantidad de información en menos tiempo.
- OBAN, Onboard Autonomous Navigation: Desarrolla un sistema experimental que permite a la sonda actuar de forma autónoma sin tener que esperar los comandos y órdenes que le llegan desde la Tierra y actuar de forma independiente. Estos sistemas de navegación fueron probados con gran éxito en la sonda Deep Space 1 de la NASA y permite que en situaciones de emergencia, la nave decida que es lo que tiene que hacer en cada momento. Esto no implica que la sonda pueda cambiar su rumbo, sino simplemente ajustar la trayectoria y actuar en el caso de que se produzca una llamarada solar.
- SPEDE/EPDP: Medirá los efectos que produce el motor iónico sobre el resto de la sonda y su funcionamiento. Estos efectos serán físicos, mecánicos, térmicos y eléctricos.
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Publications NSSDC ID: 2003-004A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events SORCE (SOlar Radiation and Climate Experiment) is an SOlar Radiation and American (NASA) Sun-Earth Connection satellite that was Climate Experiment launched at 20:13 UT by a Pegasus XL rocket released from a 27651 L-1011 cargo aircraft flying out of Cape Canaveral. It is to measure solar irradiance in a number of wavelength-bands through three spectrometers and a photometer. Facts in Brief
The URL http://lasp.colorado.edu/sorce/ provides much Launch Date: 2003-01- detailed descriptions of the experiments and data availability. 25 The PI is Gary J. Rottman of LASP, University of Colorado, Launch Boulder, with many co-investigators. Vehicle: Pegasus XL Launch Site: Cape Canaveral, United States
Funding Agency
National Aeronautics and Space Administration (United States)
Discipline
Solar Physics
Additional Information
Launch/Orbital information for SORCE
Experiments on SORCE
Data collections from SORCE
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
Personnel
Name Role Original Affiliation E-mail
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Dr. Thomas P. Program University of Colorado [email protected] Sparn Manager
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Personnel SOYUZ TMA 3
Publications NSSDC ID: 2003-047A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Soyuz TMA 3 is a Russian passenger-transporting satellite that 28052 was launched by a Soyuz-FG rocket from Baikonur at 05:38 UT on 18 October 2003. It carried three astronauts (a Russian, an American and a Spanish) to the International Space Station Facts in Brief (ISS). It docked automatically with the ZARYA module 20 Launch Date: 2003-10- October 2003 and the crew moved into the ISS. The Spanish 18 astronaut will conduct some microgravity life science Launch Vehicle: Soyuz experiments, code named Cervantes (the author of Don FG Quixote novel) while in the ISS for about 10 days. The other Launch Site: Tyuratam two crew members will remain in the ISS for a six-month stay, (Baikonur Cosmodrome), relieving the two astronauts from the previous mission. The two Kazakhstan astronauts that had stayed on ISS for six months, plus the Cervantes astronaut returned to Earth in the SOYUZ TMA 2 module (that had remained docked with the ISS) at 02:41 UT Funding Agency on 28 October 2003, soft-landing at the precisely planned location in Kazakhstan. Unknown (Russia)
Disciplines
Human Crew Resupply/Refurbishment/Repair
Additional Information
Launch/Orbital information for SOYUZ TMA 3
Experiments on SOYUZ TMA 3
Data collections from SOYUZ TMA 3
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Launch, orbit and landing data
Launch date: 18.10.2003 Launch time: 05:38 UT Launch site: Baikonur Launch pad: 1 Altitude: 376 - 385 km Inclination: 51,63° Landing date: 30.04.2004 Landing time: 00:12 UT 50° 39' N, 67° 27' Landing site: E
Crew No Surnam Orbit Given name Job Flight No. Duration . e s Aleksandr 1 Kaleri Commander 4 194d 18h 34m 3054 Yuriyevich Flight 2 Duque Pedro Francisco 2 9d 21h 02m 155 Engineer Flight 3 Foale Colin Michael 6 194d 18h 34m 3054 Engineer Crew seating arrangement
Launch Landing 1 Kaleri 1 Kaleri 2 Duque 2 Kuipers 3 Foale 3 Foale
Flight Launch from Baikonur; landing 59 km NE of Arkalyk; ISS-expedition 8; "caretaker" crew; docking to ISS; crew replaced expedition 7 crew.
Note Duque landed on 28.10.2003 at 02:40 UT with Soyuz TMA-2-spacecraft.
Photos / Drawings
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Publications NSSDC ID: 2003-016A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Soyuz TMA-2 is a Russian passenger transport craft that was 27781 launched by a Soyuz-U rocket from Baikonur at 03:54 UT on 26 April 2003. It carried two astronauts, one Russian and one American, for a six-month stay at the International Space Facts in Brief Station (ISS), performing microgravity biology experiments. It Launch Date: 2003-04- docked with the ISS at about 07:00 UT on 28 April 2003. The 26 previous three-man crew in ISS will leave the station on 4 May Launch 2003 on the earlier Soyuz TMA-1 that has remained docked. Vehicle: Soyuz-U Launch Site: Tyuratam (Baikonur Cosmodrome), Kazakhstan
Funding Agency
Unknown (Russia)
Discipline
Human Crew
Additional Information
Launch/Orbital information for Soyuz TMA-2
Experiments on Soyuz TMA-2
Data collections from Soyuz TMA-2
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Launch, orbit and landing data
Launch date: 26.04.2003 Launch time: 03:54 UT Launch site: Baikonur Launch pad: 1 Altitude: 388,2 - 413,2 km Inclination: 51,67° Landing date: 28.10.2003 Landing time: 02:40 UT 49° 57' 06" N, 67° Landing site: 02' 15" E
Crew No Orbit Surname Given name Job Flight No. Duration . s Malenchenk Yuri 1 Commander 3 184d 22h 46m 2890 o Ivanovich Edward Flight 2 Lu 3 184d 22h 46m 2890 Tsang Engineer Crew seating arrangement
Launch Landing 1 Malenchenko 1 Malenchenko 2 Lu 2 Duque 3 3 Lu
Flight Launch from Baikonur; landing 42 km south of Arkalyk in Kazakhstan; ISS-expedition 7; "caretaker" crew; docking to ISS; crew replaced expedition 6 crew.
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Publications NSSDC ID: 2003-027A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The "Spirit" rover (Mars Exploration Rover A or MER-2) is one MER 2 of the two rovers launched to Mars in mid-2003. The rovers MER-A arrived at Mars in January of 2004 equipped with a battery of scientific instruments and will be able to traverse 100 meters a Mars Exploration Rover A day. The nominal plan calls for the missions to last for 90 days, Mars Exploration Rover 2 until April 2004, but it is likely the mission will last beyond this time. The scientific goals of the rover missions are to gather data to help determine if life ever arose on Mars, characterize Facts in Brief the climate of Mars, characterize the geology of Mars, and Launch Date: 2003-06- prepare for human exploration of Mars. To achieve these 10 goals, seven science objectives are called for: 1) search for Launch Vehicle: Delta and characterize a variety of rocks and soils that hold clues to II 7925 Spirit past water activity, 2) determine the distribution and Launch Site: Cape composition of minerals, rocks, and soils surrounding the Canaveral, United States landing sites, 3) determine what geologic processes have Mass: 185.0 kg shaped the local terrain and influenced the chemistry 4) perform "ground truth" of surface observations made by Mars orbiter instruments, 5) search for iron-bearing minerals, Funding Agency identify and quantify relative amounts of specific mineral types tha contain water or were formed in water, 6) characterize the National Aeronautics and mineralogy and textures of rocks and soils and determine the Space Administration processes that created them, and 7) search for geological (United States) clues to the environmental conditions that existed when liquid water was present and assess whether those environments Discipline were conducive to life. Planetary Science Spacecraft and Subsystems The Mars Exploration Rover consists of a box-like chassis mounted on six wheels. The chassis contains the warm Additional electronics box (WEB). On top of the WEB is the triangular Information rover equipment deck, on which is mounted the Pancam mast Launch/Orbital assembly, high gain, low gain, and UHF antennas, and a information for Spirit camera calibration target. Attached to the two forward sides of the equipment deck are solar arrays which are level with the PDMP information for deck and extend outward with the appearance of a pair of Spirit swept-back wings. Attached to the lower front of the WEB is Telecommunications the instrument deployment device, a long hinged arm which information for Spirit protrudes in front of the rover. Experiments on Spirit The wheels are attached to a rocker-bogie suspension system. Each wheel has its own motor and the two front and two rear Data collections from Spirit wheels are independently steerable. The rover has a top speed of 5 cm per second, but the average speed over time on flat hard ground would be 1 cm/sec or less due to the hazard avoidance protocols. The rover is designed to withstand a tilt of Questions or comments 45 degrees without falling over, but is programmed to avoid about this spacecraft can exceeding tilts of 30 degrees. The warm electronics box be directed to: Dr. David R. http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2003-027A[15/10/2010 22:33:36] NASA - NSSDC - Spacecraft - Details
houses the computer, batteries, and other electronic Williams. components. The box is designed to protect these components and control their temperature. Thermal control is achieved through the use of gold paint, aerogel insulation, heaters, thermostats, and radiators.
Power is provided by the solar arrays, generating up to 140 W of power under full Sun conditions. The energy is stored in two rechargeable batteries. Communications with Earth are in X- band via the high gain directional dish antenna and the low gain omni-directional antenna. Communications with orbiting spacecraft are through the UHF antenna. The onboard computer has 128 Mb RAM. An inertial measurement unit provides 3-axis information on position.
The rover carries a suite of instruments for science and navigation. The panoramic camera (Pancam) and navigation cameras are mounted on top of the Pancam mast assembly, at a height of about 1.4 meters from the base of the wheels. The mast, mounted at the front of the equipment deck, also acts as a periscope for the Miniature Thermal Emission Spectrometer (Mini-TES). Attached to the end of the instrument deployment device are the Alpha Particle X-Ray Spectrometer (APXS), Mossbauer Spectrometer (MB), Microscopic Imager (MI), and Rock Abrasion Tool (RAT). A magnet array is attached to the front of the equipment deck. Two hazard avoidance cameras are mounted on the front of the rover and two on the rear. The group of science instruments (Pancam, Mini-TES, APXS, MB, MI, and RAT) is known as the Athena science package.
The rover will be compactly stowed in a tetrahedron shaped landing platform and encased in an aeroshell consisting of a heat shield and a backshell for launch, cruise, and atmospheric entry. The lander platform has a mass of 348 kg, the backshell and parachute 209 kg, and the heat shield 78 kg. The cruise stage mass is 193 kg and propellant mass is 50 kg.
Mission Profile Spirit was launched on a standard Delta II 7925 on 10 June 2003 at 17:58:46.773 UT. After insertion into a circular Earth parking orbit, the spacecraft was despun and the third stage was reignited to put the craft on a trajectory to Mars, after which the aeroshell, lander, and rover separated from the third stage. The cruise phase to Mars ended on 20 November 2003, 45 days before Mars entry. The approach phase lasted from this date until martian atmospheric entry on 4 January 2004. On entry the lander and components had a mass of 827 kg and were travelling at 19,300 km/hr. The aeroshell decelerated the lander in the upper martian atmosphere for about four minutes to a velocity of 1600 km/hr, followed by deployment of a parachute. The parachute slowed the spacecraft to about 300 km/hr. A series of tones was transmitted by the spacecraft during entry and after landing to indicate the successful completion of each phase. Just prior to impact, at an altitude of about 100 m, retrorockets slowed the descent and airbags were inflated to cushion the impact. The craft hit at roughly 50 km/hr and bounced and rolled along the surface. After it stopped the airbags deflated and retracted, the petals opened, and the rover deployed its solar arrays. The landing took place at 04:35 UT on 4 January 2004 (Earth received time), (11:35 p.m. Jan. 3 EST) approximately 2:00 p.m. local time, about one hour before Earth set, in Gusev Crater, roughly 15 degrees south of the equator. On Mars it is the latter half of southern summer. The landing ellipse is centered at 14.82 S, 184.85 W and is 96 km by 19 km oriented at 76 degrees. http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2003-027A[15/10/2010 22:33:36] NASA - NSSDC - Spacecraft - Details About three hours after landing the first images were returned to Earth, showing a flat plain littered with small rocks. Gusev Crater was chosen as a landing site because it has the appearance of a crater lakebed. If Gusev was at one time filled with water, the bottom of the crater may contain sedimentary deposits laid down in the submarine environment.
An egress phase took place over the first few days, involving deployment of the Pancam mast and high gain antenna, rover stand up, imaging and calibration, and selection of proper egress path. The rover drove off the platform onto the surface of Mars on 15 January at 8:41 UT (3:41 a.m. EST). Over three years of surface operations, involving driving the rover, imaging, and use of the science instruments has already been achieved, and the Spirit rover continues to operate, although it has lost the use of one of its six wheels. It has covered a total of about 7 km.
Personnel
Name Role Original Affiliation E-mail Ms. Joy Anne Project NASA Jet Propulsion [email protected] Crisp Scientist Laboratory Mr. Peter C Project NASA Jet Propulsion [email protected] Theisinger Manager Laboratory Dr. James B. Program NASA Headquarters [email protected] Garvin Scientist Dr. Firouz M. Program NASA Jet Propulsion [email protected] Naderi Manager Laboratory
Selected References
Crisp, J. A., et al., Mars Exploration Rover mission, J. Geophys. Res., 108, No. E12, 8061, doi:10.1029/2002JE002038, 2003.
Squyres, S. W., et al., Athena Mars rover science investigation, J. Geophys. Res., 108, No. E12, 8062, doi:10.1029/2003JE002121, 2003.
Squyres, S. W., et al., The Spirit Rover's Athena science investigation at Gusev crater, Mars, Science, 305, No. 5685, 794-799, Aug. 2004.
Cook, R. A., The Mars exploration rover project, Acta Astronaut., 57, No. 2-8, 116-120, 2005.
Arvidson, R. E., et al., Overview of the Spirit Mars Exploration Rover Mission to Gusev Crater: Landing site to Backstay Rock in the Columbia Hills, J. Geophys. Res., 111, E02S01, doi:10.1029/2005JE002499, 2006.
"Spirit" Rover Images From Gusev Crater, Mars
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More "Spirit" Images of Gusev Crater "Opportunity" Images of Meridiani Planum
Press Release on the landing - 4 January 2004 Comparison of Spirit, Mars Pathfinder, and Viking Panoramas
Spirit's route on Mars, artist's concept of the rover on Mars and a map of the landing sites showing Gusev and Meridiani
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Mars Exploration Rover "Opportunity" Page
Labelled Diagram of the Mars Exploration Rover
NASA Mars Rovers Braving Severe Dust Storms - NASA Press Release 20 July 2007 Durable Mars Rovers Sent Into Third Overtime Period - NASA Press Release 5 April 2005 Spirit Rolls All Six Wheels Onto Martian Soil - NASA Press Release 15 January 2004 Spirit Lands on Mars and Sends Postcards - JPL Press Release 4 January 2004 Mars Rovers Head for Exciting Landings in January - NASA Press Release 2 December 2003 NASA Selects 28 Participating Scientists for Mars Rover Mission - NASA Press Release 29 May 2002 NASA Plans to Send Rover Twins to Mars in 2003 - NASA Press Release 10 August 2000 Announcement of Rover Option - NASA Press Release 27 July 2000 Mars Pathfinder Rover
Mars Exploration Rover Home Page - NASA JPL Athena Science Package Site - Cornell University
Mars Home Page Mars Fact Sheet
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DESCRIPCIÓN: Esta nueva misión de la NASA a Marte (conjuntamente con Dinamarca y Alemania) supone el retorno del 'rover', que tanto éxito tuvo en la misión Pathfinder en el año 1.997. En este caso serán dos los rovers que se utilizarán para la misión, ambos idénticos, con muchísima más capacidad que el conocido Sojourner de 1.997. Estos exploradores serán capaces de recorrer más de 100 metros diarios y llevarán consigo todos los instrumentos (Athena Science Payload) y sistemas de comunicaciones ya que no tendrán una base de operaciones como la 'Carl Sagan Memorial Station' de la misión Pathfinder. Su objetivo principal es la búsqueda de agua pasada o presente en el planeta y su interacción con las rocas del entorno.
Cada dos años, la Tierra y Marte se encuentran en una posición de su órbita alrededor del Sol que posibilita el envío de naves al planeta rojo con el mínimo gasto posible de combustible, resultando en un ahorro para la misión. Uno de estos períodos tendrá lugar a mediados del año 2.003 y será aprovechado para lanzar las dos sondas con apenas un mes de diferencia. El primero de ellos, el MER-A fue lanzado desde Cabo Cañaveral el 10 de junio de 2.003 en un cohete Delta II y el MER-B lo siguió el 8 de julio. Tras un viaje de siete meses llegarán a Marte en enero de 2.004 con pocos días de diferencia.
Diagramas del lanzamiento
Recorrido de las naves
Cada uno de los rovers aterrizará en una zona distinta del planeta cercana al ecuador para aprovechar mejor la energía solar. Para llegar a la superficie seguirán un procedimiento muy similar al de la misión Pathfinder.
Una vez pasadas las capas altas de la atmósfera se abrirá un paracaídas, cerca de la superficie se encenderán varios cohetes que disminuirán aún más la velocidad y poco después se abrirán unos gigantescos airbags que harán que el rover rebote una docena de veces durante 1 kilómetro. Una vez detenido el airbag, se desinflará y se abrirán los pétalos que protegían la nave dejando al rover al descubierto.
En esos momentos se abrirán los paneles solares, el mástil de la cámara y las ruedas y quedará listo para salir. Instantes después, tomará una panorámica completa de 360º de su entorno en color e infrarrojos y la mandará a Tierra para que los ingenieros conozcan el entorno y poder decidir que primer camino tomará la nave. Lo fascinante de esta misión es que cada día se podrá analizar todo el entorno del rover desde una posición nueva. Los científicos analizaran las tomas panorámicas del rover para decidir el día siguiente que camino tomará para fotografiar desde allí nuevos lugares y nuevos análisis de las rocas del lugar. Y todo ello por duplicado. En un sólo día recorrerán la misma distancia que Sojourner en toda la misión. Como comparación, el rover Sojourner pesaba 11 kg. por 185 kg. de estos rovers y su altura es 5 veces mayor. Cada rover analizará el suelo y las rocas, usando espectrómetros, abriendo la roca para analizar su interior y fotografiando su estructura microscópica y se espera que duren al menos 90 días sobre la superficie del planeta hasta mayo del 2.004, pero si se mantiene su buena salud podrá ampliarse la misión.
Mapa Global de Marte. Zonas elegidas para el aterrizaje Gusev Crater / Meridiani Hematite
Fase de reentrada en la atmósfera. (Pulsa para ampliar la imagen) FECHAS PRINCIPALES:
Lanzamiento MER-A / MER-2 / Spirit: 10 de junio 2.003 Lanzamiento MER-B / MER-1 / Opportunity: 8 de julio 2.003 Llegada a Marte MER-A: 4 de enero 2.004 Llegada a Marte MER-B: 25 de enero 2.004 Fin de las operaciones de ambos rovers: mayo 2.004 (ampliable).
COMPONENTES E INSTRUMENTOS:
- PANCAM. Es la cámara principal de la nave y la encargada de realizar las fotografías panorámicas de alta resolución, en estéreo y en color, siendo su resolución tres veces mayor que la del Sojourner. Las cámaras ayudarán a los técnicos a decidir el camino a emprender y tomar imágenes de las rocas y lugares que rodean en cada momento al rover. Imagen de prueba.
- MINI-TES o Mini-Thermal Emission Spectrometer. Es un espectrómetro que tomará imágenes en infrarrojo de las rocas y el suelo y nos permitirá saber su composición. Va situado en el mástil de la cámara panorámica. De todas las imágenes que tome, se podrá sacar el espectro completo por separado de cada uno de los pixeles que la componen.
- APXS o Alpha-Particle-X-Ray Spectrometer . Es el espectrómetro de rayos X que determinará la química y composición del suelo y las rocas marciana, así como la abundancia de los distintos elementos químicos.
- Mössbauer Spectrometer. Es otro espectrómetro que determinará con gran precisión la abundancia y distribución de minerales derivados del hierro, lo que nos dará información sobre el magnetismo y la interacción del agua con esos minerales.
- RAT o Rock Abrasion Tool. Es un aparato que funcionará a modo de perforador sobre las rocas NASA - NSSDC - Spacecraft - Details
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Personnel Spitzer Space Telescope
Publications NSSDC ID: 2003-038A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The Spitzer Space Telescope (formerly SIRTF, the Space Space InfraRed Infrared Telescope Facility) is a 0.85-meter telescope with Telescope Facility three cryogenically cooled instruments, operating in the 3 - 180 SST micron range. The observatory is the final element in NASA's Great Observatories Program. The science capabilities include 27871 imaging/photometry at 3 - 180 microns, spectroscopy at 5 - 40 microns, and spectrophotometry at 50 - 100 microns. Spitzer Facts in Brief will study a wide variety of astronomical phenomena, extending from our Solar System to the distant reaches of the early Launch Date: 2003-08- Universe. 25 Launch Vehicle: Delta The spacecraft consists of an octagonal bus structure, and a 7920H ELV solar array to power the science instruments. The pointing Launch Site: Cape control subsystem employs a celestial-inertial, three-axis Canaveral, United States stabilized control system. Spitzer has an Earth-trailing Mass: 865.0 kg Heliocentric orbit.
The Spitzer telescope is a lightweight reflector of Ritchey- Funding Agency Chrétien design. The telescope has an 85 cm diameter NASA-Office of Space aperture. The instruments selected include: 1) a four-channel Science (United States) infrared array camera imaging at 3.6, 4.5, 5.8, and 8 microns. 2) an imaging photometer, with three detector arrays imaging at 24, 70, and 160 microns (one array will also take low- Discipline resolution spectra at 50 - 100 microns); 3) a spectrograph providing high- and low-resolution spectroscopy at mid-infrared Astronomy wavelengths (5 - 40 microns). Additional Information
Launch/Orbital information for Spitzer Space Telescope PDMP information for Spitzer Space Telescope Telecommunications information for Spitzer Space Telescope
Experiments on Spitzer Space Telescope
Data collections from Spitzer Space Telescope
Questions or comments about this spacecraft can
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Personnel
Name Role Original Affiliation E-mail Dr. Michael W. Project NASA Jet Propulsion [email protected] Werner Scientist Laboratory Mr. David B Project NASA Jet Propulsion [email protected] Gallagher Manager Laboratory
Other Sources of Spitzer Information/Data
Spitzer Project page
Spitzer Infrared Array Camera (IRAC) Spitzer Multiband Imaging Photometer (MIPS) Spitzer Infrared Spectrograph (IRS) Home Page
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Personnel STS 107
Publications NSSDC ID: 2003-003A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Space Shuttle Columbia, STS 107 was an American shuttle Columbia spacecraft launched from Cape Canaveral at 15:39 UT on 16 27647 January 2003. It was the first flight in recent years that was not related to International Space Station (ISS) activities. It carried seven astronauts who helped oversee 80 microgravity Facts in Brief expriments on board. These ranged from K-12 interest to significant commercial and scientific potential. Launch Date: 2003-01- 16 After a 16 day mission, the shuttle began its reentry on 1 Launch February 2003, but communications failed at 14:00 UT when Vehicle: Shuttle the shuttle was at an altitude of 60 km with a speed of 20,100 Launch Site: Cape km/hr. It soon disintegrated over east central Texas on its path Canaveral, United States towards Cape Canaveral. The debris was scattered over hundreds of square miles. There were no survivors. This was Funding Agency the 28th mission for Columbia. National Aeronautics and Space Administration (United States)
Disciplines
Engineering Human Crew Life Science Microgravity
Additional Information
Launch/Orbital information for STS 107
Experiments on STS 107
Data collections from STS 107
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Thuraya 2
Publications NSSDC ID: 2003-026A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Thuraya 2 is a UAE (United Arab Emitrate) geostationary 27825 communications spacecraft that was launched by a Zenit 3SL rocket fired from Odyssey (the floating launch platform in the equatorial Pacif ocean) at 13:56 UT on 10 June 2003. The 5.2 Facts in Brief tonne (with fuel), 11 kW satellite carries many transponders to Launch Date: 2003-06- relay mobile telephone calls from/to countries in and around 10 the Middle East and the Indian subcontinent, after parking over Launch Vehicle: Zenit 44 deg-E longitude. Its 200 spot beams can be steered to 3SL meet the varying call densities, and will enable it to handle Launch Site: Odyssey 13,750 calls simultaneously. (Sea Launch Platform), null
Funding Agency
Unknown (United Arab Emirates)
Discipline
Communications
Additional Information
Launch/Orbital information for Thuraya 2
Experiments on Thuraya 2
Data collections from Thuraya 2
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel UFO 11
Publications NSSDC ID: 2003-057A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events UFO 11, also known as USA 174, is an American USA 174 geostationary military communications satellite that was 28117 launched by an Atlas 3 rocket from Cape Canaveral at 02:30 UT on 18 December 2003. ("UFO" has been identified as the acronym for Uhf Follow-On.) The 1.4 tonne satellite is the Facts in Brief eleventh and final of the UFO constellation which provide secure communications in UHF band and frequencies among Launch Date: 2003-12- ships, aircraft, mobile ground terminals even during severe 18 weather conditions. It will be parked at 172 deg E longitude. Launch Vehicle: Atlas 3 Launch Site: Cape Canaveral, United States
Funding Agency
Unknown (United States)
Disciplines
Communications Surveillance and Other Military
Additional Information
Launch/Orbital information for UFO 11
Experiments on UFO 11
Data collections from UFO 11
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel USA 167
Publications NSSDC ID: 2003-008A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events USA 167, also known as DSCS 3A3, is an American DSCS 3A3 geostationary military communicatons spacecraft of the DSCS 27691 3 constellation that will provide super secure glabal links to the military. It was launched by a Delta 4 rocket from Cape Canaveral AFS at 00:59 UT. These DSCS 3 spacecraft are Facts in Brief triaxially stabilized spacecraft with solar power of 1.24 kW. They operate at 6 SHF frequencies between 40 and 85 MHz. Launch Date: 2003-03- Parking longitude will be unavailable. 11 Launch Vehicle: Delta IV Launch Site: Cape Canaveral, United States
Funding Agency
Unknown (United States)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for USA 167
Experiments on USA 167
Data collections from USA 167
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel USA 170
Publications NSSDC ID: 2003-040A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events USA 170, also known as DSCS 3B6, is an American, Defense DSCS 3B6 Satellite Communications System's geostationary, super- 27875 secure communication satellite that was launched by a Delta 4 rocket from Cape Canaveral AFS at 23:13 UT on 29 August 2003. It is the 10th and final member of the DSCS phase 3 Facts in Brief fleet enabling worldwide links among the American military personnel. The parking longitude is unavailable. Launch Date: 2003-08- 29 Launch Vehicle: Delta IV Launch Site: Cape Canaveral, United States
Funding Agency
Unknown (United States)
Discipline
Communications
Additional Information
Launch/Orbital information for USA 170
Experiments on USA 170
Data collections from USA 170
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel USA 171
Publications NSSDC ID: 2003-041A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events USA 171 is an American geostationary military spacecraft that 27937 was launched from Cape Canaveral at 04:29 UT on 9 September 2003. It is reported to be an ORION-class craft belonging to the National Reconnaissance Office. No further Facts in Brief information is available. Launch Date: 2003-09- 09 Launch Vehicle: null Launch Site: Cape Canaveral, United States
Funding Agency
Unknown (United States)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for USA 171
Experiments on USA 171
Data collections from USA 171
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel USA 173
Publications NSSDC ID: 2003-054A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events USA 173 is an American military satellite (operated by the 28095 National Reconnaissance Office) that was launched by an Atlas 2AS rocket from Vandenberg AFB at 10:04 UT on 2 December 2003. It is reported to be part of the NOSS (Naval Facts in Brief Ocean Surveillance System) fleet. Launch Date: 2003-12- 02 Launch Vehicle: Atlas 2AS Launch Site: Vandenberg AFB, United States
Funding Agency
Unknown (United States)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for USA 173
Experiments on USA 173
Data collections from USA 173
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel XSS 10
Publications NSSDC ID: 2003-005B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events XSS 10 is an American (AFRL/DoD) technology demonstration 27664 microsatellite (28 kg) that was launched by a Delta 2 rocket from Cape Canaveral at 18:06 UT on 29 January 2003. It will also keep its sight on the second stage of Deta 2. Its battery- Facts in Brief powered operational life was 24 hours. Launch Date: 2003-01- 29 Launch Vehicle: Delta II Launch Site: Cape Canaveral, United States
Funding Agency
Department of Defense- Department of the Air Force (United States)
Discipline
Technology Applications
Additional Information
Launch/Orbital information for XSS 10
Experiments on XSS 10
Data collections from XSS 10
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Yamal 201
Publications NSSDC ID: 2003-053B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Yamal 201 is one of a pair of Russian geostationary 28094 communications satellites that were launched by a Proton-K rocket from Baikonur at 06:22 UT on 24 November 2003. The pair, Yamal 201 and Yamal 202, are identical satellites, with a Facts in Brief mass of 1.3 kg, and power 3.6 kW. Yamal 201 carries nine C- Launch Date: 2003-11- band and six Ku-band transponders, while Yamal 202 carries 24 18 C-band transponders. They will provide voice and video Launch communications throughout the Eurasian continent, after Vehicle: Proton-K parking: Yamal 201 at 90 deg-E and Yamal 202 at 49 deg-E. Launch Site: Tyuratam (Baikonur Cosmodrome), Kazakhstan
Funding Agency
Unknown (Russia)
Discipline
Communications
Additional Information
Launch/Orbital information for Yamal 201
Experiments on Yamal 201
Data collections from Yamal 201
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Yamal 202
Publications NSSDC ID: 2003-053A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Yamal 202 is one of a pair of Russian geostationary 28089 communications satellites that were launched by a Proton-K rocket from Baikonur at 06:22 UT on 24 November 2003. The pair, Yamal 202 and Yamal 201, are identical satellites, with a Facts in Brief mass of 1.3 kg, and power 3.6 kW. Yamal 201 carries nine C- Launch Date: 2003-11- band and six Ku-band transponders, while Yamal 202 carries 24 18 C-band transponders. They will provide voice and video Launch communications throughout the Eurasian continent, after Vehicle: Proton-K parking: Yamal 201 at 90 deg-E and Yamal 202 at 49 deg-E. Launch Site: Tyuratam (Baikonur Cosmodrome), Kazakhstan
Funding Agency
Unknown (Russia)
Discipline
Communications
Additional Information
Launch/Orbital information for Yamal 202
Experiments on Yamal 202
Data collections from Yamal 202
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Zhongxing 20
Publications NSSDC ID: 2003-052A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Zhongxing 20 is a Chinese (PRC) military communications 28082 spececraft that was launched by a Long March 3A rocket from Xichang Satellite Launch Center (XSLC) on 14 November 2003. Facts in Brief Launch Date: 2003-11- 14 Launch Vehicle: Long March 3A Launch Site: Xichang, Peoples Republic of China
Funding Agency
Unknown (Peoples Republic of China)
Disciplines
Communications Surveillance and Other Military
Additional Information
Launch/Orbital information for Zhongxing 20
Experiments on Zhongxing 20
Data collections from Zhongxing 20
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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