NASA - NSSDC - Master Catalog

Transcripción

Cronología de
Lanzamientos
Espaciales
Año 1996
Recopilación de datos Ing. Eladio Miranda Batlle.
Los textos, imágenes y tablas fueron obtenidos de la National Space Science.
Data Center. NASA
NASA - NSSDC - Spacecraft - Query Results
Saturday, 28 May 2011
NSSDC Master
Catalog Search
Spacecraft
Experiments
Data Collections
Personnel
Spacecraft Query Results
Publications
There were 108 spacecraft returned.
Maps
Spacecraft Name
NSSDC ID
Launch Date
New/Updated Data
ADEOS
1996-046A
1996-08-16
Lunar/Planetary Events
AMOS 1
1996-030B
1996-05-15
Apstar 1A
1996-039A
1996-07-02
Arabsat 2A
1996-040A
1996-07-08
Arabsat 2B
1996-063A
1996-11-12
Astra 1F
1996-021A
1996-04-07
Bion 11
1996-073A
1996-12-23
Chinasat 7
1996-048A
1996-08-17
Cluster96
CLUSTR1
1996-06-03
Cosmos 2327
1996-004A
1996-01-15
Cosmos 2328
1996-009D
1996-02-18
Cosmos 2329
1996-009E
1996-02-18
Cosmos 2330
1996-009F
1996-02-18
Cosmos 2331
1996-016A
1996-03-13
Cosmos 2332
1996-025A
1996-04-23
Cosmos 2333
1996-051A
1996-09-03
Cosmos 2334
1996-052A
1996-09-04
Cosmos 2335
1996-069A
1996-12-10
Cosmos 2336
1996-071A
1996-12-19
Echostar 2
1996-055A
1996-09-10
Express 12
1996-058A
1996-09-25
FAST
1996-049A
1996-08-20
FSW-2 3
1996-059A
1996-10-19
Galaxy 9
1996-033A
1996-05-23
GE 1
1996-054A
1996-09-07
Gonets D1-1
1996-009A
1996-02-18
Gonets D1-2
1996-009B
1996-02-18
Gonets D1-3
1996-009C
1996-02-18
Gorizont 31
1996-005A
1996-01-24
Gorizont 32
1996-034A
1996-05-24
HETE 1
1996-061A
1996-11-03
Hot Bird 2
1996-067A
1996-11-20
IAE
1996-032C
1996-05-19
Inmarsat 3-F1
1996-020A
1996-04-02
Inmarsat 3-F2
1996-053A
1996-09-05
Inmarsat 3-F3
1996-070A
1996-12-17
http://nssdc.gsfc.nasa.gov/nmc/spacecraftSearch.do;jsessionid=ABABABE2C8FD0DDCC524D293AE803D49[28/05/2011 23:19:27]
INTELSAT 7 F-7
1996-015A
1996-03-13
INTELSAT 709
1996-035A
1996-06-14
Interball Auroral Probe
1996-050C
1996-08-28
IRS-P3
1996-017A
1996-03-20
Italsat 2
1996-044A
1996-08-07
JAS 2
1996-046B
1996-08-16
KH 12-3
1996-072A
1996-12-19
Koreasat 2
1996-003A
1996-01-13
Magion 5
1996-050B
1996-08-28
Mars 96 Orbiter
1996-064A
1996-11-15
Mars 96 Penetrator
MARS96D
1996-11-15
Mars 96 Penetrator
MARS96E
1996-11-15
Mars 96 Surface Station
MARS96B
1996-11-15
MARS96C
1996-11-15
Mars Global Surveyor
1996-062A
1996-11-06
Mars Pathfinder
1996-068A
1996-12-03
Mars Pathfinder Rover
MESURPR
1996-12-03
MEASAT 1
1996-002B
1996-01-11
MEASAT 2
1996-063B
1996-11-12
Microsat
1996-050A
1996-08-28
Molniya 1-89
1996-045A
1996-08-13
Molniya 3-48
1996-060A
1996-10-23
MSAT 1
1996-022A
1996-04-19
MSTI 3
1996-031A
1996-05-16
MSX
1996-024A
1996-04-23
N-Star-B
1996-007A
1996-02-04
Navstar 2A-16
1996-019A
1996-03-27
Navstar 2A-17
1996-041A
1996-07-15
Navstar 2A-18
1996-056A
1996-09-11
NEAR Shoemaker
1996-008A
1996-02-16
OAST Flyer
1996-001B
1996-01-10
ORFEUS-SPAS II
1996-065B
1996-11-19
OSL
OSL
1995-12-31
Palapa C-1
1996-006A
1996-01-31
Palapa C-2
1996-030A
1996-05-15
PAMS-STU
1996-032D
1996-05-21
PANAMSAT 3R
1996-002A
1996-01-11
Polar
1996-013A
1996-02-23
Priroda
1996-023A
1996-04-22
Progress M-31
1996-028A
1996-05-04
Progress M-32
1996-043A
1996-07-30
Progress M-33
1996-066A
1996-11-18
Raduga 33
1996-010A
1996-02-18
REX 2
1996-014A
1996-03-08
SAC-B
1996-061B
1996-11-03
SAX
1996-027A
1996-04-29
Soyuz-TM 23
1996-011A
1996-02-20
Soyuz-TM 24
1996-047A
1996-08-17
Spartan 207
1996-032B
1996-05-19
STS 72
1996-001A
1996-01-10
STS 75
1996-012A
1996-02-21
STS 76
1996-018A
1996-03-21
STS 77
1996-032A
1996-05-18
STS 78
1996-036A
1996-06-19
STS 79
1996-057A
1996-09-15
STS 80
1996-065A
1996-11-18
STS/SRL 3
SRL3
1996-01-31
TELECOM 2D
1996-044B
1996-08-07
TOMS-EP
1996-037A
1996-07-01
TSS-1R
1996-012B
1996-02-24
Turksat 1C
1996-040B
1996-07-08
UFO 7
1996-042A
1996-07-24
UNAMSAT-B
1996-052B
1996-09-04
USA 118
1996-026A
1996-04-23
USA 119
1996-029A
1996-05-11
USA 120
1996-029B
1996-05-11
USA 121
1996-029C
1996-05-11
USA 122
1996-029D
1996-05-11
USA 123
1996-029E
1996-05-11
USA 124
1996-029F
1996-05-11
USA 125
1996-038A
1996-07-02
WSF 3
1996-065C
1996-11-22
+ Privacy Policy and Important Notices
NASA Official: Dr. Ed Grayzeck
Curator: E. Bell, II
Version 4.0.16, 26 April 2011
NASA - NSSDC - Spacecraft - Details
Monday, 30 May 2011
NSSDC Master
Catalog Search
Spacecraft
Experiments
Data Collections
Personnel
ADEOS
Publications
NSSDC ID: 1996-046A
Maps
New/Updated Data
Description
The Japanese Advanced Earth Observing Satellite (ADEOS)
was developed to establish platform technology for Earth
Observing System (EOS) spacecraft and inter-orbit
communication technology for the transmission of Earth
observation data. In addition, ADEOS contributed global
observation of environmental change to the international
community during the pre-EOS era. NASA's Mission to Planet
Earth (MTPE) program contributed two instruments for the
ADEOS mission.
ADEOS was a sun-synchronous, morning equator-crossing (in
descending node at about 10:30 a.m.), polar orbiting
spacecraft. It had a modular type shape with a deployable one
wing solar paddle. The body measured 4 x 4 x 5 m and the
solar paddle was 3 x 13 m in size.
ADEOS was three-axis stabilized by a zero momentum strapdown attitude-control system. Attitude was maintained by four
reaction wheels, two magnetometers, an inertial reference unit,
and two hydrazine thrusters. Power was provided by a single
gallium arsenide flexible solar paddle and five 35 A-hr NiCd
batteries. Data was transmitted via direct transmission and
inter-orbit communication through ETS-6. A Mission Data
Recorder system on-board ADEOS stored high data rate and
low data rate data on separate tape recorders.
Eight experiments on ADEOS included: (1) Ocean Color and
Temperature Scanner (OCTS), a NASDA core instrument; (2)
Advanced Visible and Near-Infrared Radiometer (AVNIR), a
NASDA core instrument; (3) NASA Scatterometer (NSCAT), a
NASA/MTPE-provided instrument; (4) Total Ozone Mapping
Spectrometer (TOMS), a NASA/MTPE provided instrument; (5)
Polarization and Directionality of the Earth's Reflectances
(POLDER), provided by CNES of France; (6) Interferometric
Monitor for Greenhouse Gases (IMG), provided by MITI of
Japan; (7) Improved Limb Atmospheric Spectrometer (ILAS),
provided by Environmental Agency of Japan; and, (8)
Retroreflector in Space (RIS), provided by the Environmental
Agency of Japan.
Alternate Names
Midori
Advanced Earth
Observing Satellite
24277
Facts in Brief
Launch Date: 1996-0816
Launch Vehicle: H-2
Launch
Site: Tanegashima, Japan
Mass: 3500.0 kg
Nominal
Power: 5000.0 W
Funding Agency
National Space
Development Agency
(NASDA) (Japan)
Discipline
Earth Science
Additional
Information
Launch/Orbital
information for ADEOS
PDMP information for
ADEOS
Telecommunications
information for ADEOS
Experiments on ADEOS
The design lifetime for this mission was three years, but the
spacecraft ceased operating on 30 June 1997 for as yet
unknown reasons. Subsequent flights of ADEOS are planned
during the EOS era.
Data collections from
ADEOS
Questions or comments
about this spacecraft can
be directed to: Coordinated
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-046A[30/05/2011 22:47:16]
Request and User Support
Office.
Personnel
Name
Role
Original Affiliation
Dr. Robert
Douglas
Hudson
Project
Scientist
NASA Goddard Space Flight
Center
Dr. William
C. Patzert
Program
Scientist
NASA Headquarters
Dr. Robert T.
Watson
Program
Scientist
NASA Headquarters
Mr. K.
Yoneyama
Project
Director
National Space Development
Agency of Japan
Dr. George
F. Esenwein,
Jr.
Program
Manager
NASA Headquarters
Dr. Firouz M.
Naderi
Project
Manager
NASA Jet Propulsion
Laboratory
[email protected]
Mr. Donald
L. Margolies
Project
Manager
NASA Goddard Space Flight
Center
[email protected]
General
Contact
Laboratoire d'Etudes et de
Recherches en Teledetection
Spatiale
Program
Manager
National Space Development
Agency of Japan
Mr. T.
Tanaka
E-mail
[email protected]
Monday, 30 May 2011
NSSDC Master
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AMOS 1
Publications
NSSDC ID: 1996-030B
Maps
New/Updated Data
Alternate Names
Description
AMOS 1 was an Israeli 3-axis stabilized, geosynchronous
communications satellite that was launched by an Ariane 44 L
rocket along with Palapa C-2 from Kourou. It carried seven
transponders in the Ku-band to enable voice and vision
communications to a large area centered in Israel.
23865
Facts in Brief
Launch Vehicle: Ariane
44L
Launch Site: Kourou,
Israel
Mass: 471.0 kg
Nominal
Power: 1150.0 W
Funding Agency
Unknown (Israel)
Discipline
Communications
Additional
Information
Launch/Orbital
information for AMOS 1
Experiments on AMOS 1
AMOS 1
Office.
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-030B[30/05/2011 22:47:38]
Monday, 30 May 2011
NSSDC Master
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Spacecraft
Experiments
Data Collections
Personnel
Apstar 1A
Publications
NSSDC ID: 1996-039A
Maps
New/Updated Data
Alternate Names
Description
APSTAR 1A was a Chinese geosynchronous communications
satellite launched by a Long March 3 rocket from the Xichang
center in southeastern China. It provided TV coverage to the
Asian-Pacific countries through its 24 C-band transponders. It
is expected to provide 10 years of service. It had two
telescoping cylindrical solar panels and an antenna array that
folded down for launch. It measured 2.2 meters in diameter
and a compact 3.1 meters tall when stowed for launch. With
the solar panels deployed and the antennas unfolded in orbit, it
measured 7.5 meters. The solar panels were covered with K-4
3/4 solar cells, which produced 1130 watts at beginning of life.
During eclipse, two super nickel cadmium batteries provided
power for uninterrupted service.
23943
Facts in Brief
Launch Vehicle: Long
March 3
Launch Site: Xichang,
Peoples Republic of China
Mass: 726.0 kg
Nominal
Power: 1130.0 W
Funding Agency
APT Satellite Company
Ltd (Peoples Republic of
China)
Discipline
Communications
Additional
Information
Launch/Orbital
information for Apstar 1A
Experiments on Apstar 1A
Apstar 1A
Office.
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Personnel
Arabsat 2A
Publications
NSSDC ID: 1996-040A
Maps
New/Updated Data
Alternate Names
Description
Arabsat 2A was a geosynchronous communications satellite of
the 21-nation ARABSAT consortium and was launched by an
Ariane 44L rocket from the Kourou center in French Guiana.
The spacecraft provided radio and TV communications to the
Middle East and neighboring countries.
23948
Facts in Brief
44L
French Guiana
Mass: 2100.0 kg
Funding Agency
Arabsat Satellite
Communications
(International)
Discipline
Communications
Additional
Information
Launch/Orbital
information for Arabsat
2A
Experiments on Arabsat 2A
Arabsat 2A
Office.
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Spacecraft
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Data Collections
Personnel
Arabsat 2B
Publications
NSSDC ID: 1996-063A
Maps
New/Updated Data
Alternate Names
Description
Arabsat 2B was a geosynchronous communications satellite of
the 21-nation ARABSAT consortium and was launched by an
Ariane 44L rocket from the Kourou center in French Guiana.
The spacecraft provided radio and TV communications to the
Middle East and neighboring countries. It was parked in a
geostationary orbit at 21.9 deg E.
24652
Facts in Brief
44L
French Guiana
Mass: 2600.0 kg
Funding Agency
Arabsat Satellite
Communications
(International)
Discipline
Communications
Additional
Information
Launch/Orbital
information for Arabsat
2B
Experiments on Arabsat 2B
Arabsat 2B
Office.
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Spacecraft
Experiments
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Personnel
Astra 1F
Publications
NSSDC ID: 1996-021A
Maps
New/Updated Data
Alternate Names
Description
Astra 1F was a European (SES, Luxembourg)
geosynchronous communications satellite launched by a
Proton-K rocket from the Baykonur cosmodrome. It is parked
over 19.2 deg E longitude and provides direct broadcast TV to
Europe through its 16 Ku-band transponders.
23842
Facts in Brief
Launch
Vehicle: Proton-K
Launch Site: Tyuratam
(Baikonur Cosmodrome),
Kazakhstan
Mass: 3010.0 kg
Funding Agency
Societe Europeenne des
Satellites (Luxembourg)
(Luxembourg)
Discipline
Communications
Additional
Information
Launch/Orbital
information for Astra 1F
Experiments on Astra 1F
Data collections from Astra
1F
Office.
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Spacecraft
Experiments
Data Collections
Personnel
Bion 11
Publications
NSSDC ID: 1996-073A
Maps
New/Updated Data
Alternate Names
Description
Bion 11 was a Russia biological research satellite launched
from the Plesetsk cosmodrome aboard a Soyuz rocket. It
carried two monkeys named Lalik and Multik.
The spacecraft was based on the Zenit reconnaissance
satellite and launches began in 1973 with primary emphasis on
the problems of radiation effects on human beings. Launches
in the program included Cosmos 110, 605, 670, 782, plus
Nauka modules flown on Zenit-2M reconnaissance satellites.
90 kg of equipment could be contained in the external Nauka
module.
24701
Facts in Brief
Launch
Vehicle: Soyuz-U
Launch Site: Plesetsk,
Russia
Funding Agency
Institute of Biomedical
Problems, Moscow
(Russia)
Disciplines
Life Science
Microgravity
Additional
Information
Launch/Orbital
information for Bion 11
Experiments on Bion 11
Data collections from Bion
11
Office.
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Spacecraft
Experiments
Data Collections
Personnel
Chinasat 7
Publications
NSSDC ID: 1996-048A
Maps
New/Updated Data
Alternate Names
Description
Chinasat 7 was a geosynchronous communications spacecraft
launched by the PRC from the Xichang space center aboard a
Long March 3 rocket. A third stage rocket failure led to an
almost useless orbit.
24282
Facts in Brief
Launch Vehicle: Long
March 3
Launch Site: Xichang,
Peoples Republic of China
Mass: 734.0 kg
Nominal
Power: 1200.0 W
Funding Agency
Unknown (Peoples
Republic of China)
Discipline
Communications
Additional
Information
Launch/Orbital
information for Chinasat 7
Experiments on Chinasat 7
Chinasat 7
Office.
Monday, 30 May 2011
NSSDC Master
Catalog Search
Spacecraft
Experiments
Data Collections
Personnel
Cluster96
Publications
NSSDC ID: CLUSTR1
Maps
New/Updated Data
Description
Facts in Brief
The original Cluster program of four spacecraft (all launched
together on the same rocket) experienced a launch failure in
1996. Following that, a single replacement Cluster spacecraft
was authorized in July of 1996, and in April 1997 a further
three near-replicas of the original spacecraft were also
approved, thus completing the replication of the original fourspacecraft Cluster mission. The following text describes one of
the original identical four Cluster spacecraft destroyed at
launch. The spacecraft of the new replacement mission,
Cluster II, are described elsewhere, under the NSSDC IDs
2000-041A, 2000-041B, 2000-045A, and 2000-045B, and the
names Cluster 2/FM5 (Rumba), Cluster 2/FM6 (Salsa), Cluster
2/FM7 (Samba), and Cluster 2/FM8 (Tango).
5
French Guiana
Mass: 550.0 kg
Nominal
Power: 224.0 W
Cluster-A, one of the four similar spacecraft of the Cluster
mission, is part of ESA's and NASA's Solar-Terrestrial Science
Program (STSP). The purpose of the mission is to study smallscale structures in three dimensions in the Earth's plasma
environment, such as those involved in the interaction between
the solar wind and the magnetospheric plasma, in global
magnetotail dynamics, in cross-tail currents, and in the
formation and dynamics of the neutral line and of plasmoids.
The four spacecraft will orbit in a tetrahedral formation in 4 x 22
Re, near-polar orbits with relative separations of several
hundred kilometers at periapsis. The tetrahedral formation is
essential for making three-dimensional measurements and for
determining the curl of vectorial quantities such as the
magnetic field.
Each spacecraft will be spin-stabilized and cylindrical in shape,
with a 2.9 m diameter and 0.9 m length. It will have two rigid 5
m magnetometer booms and two pairs of wire booms, with
100 m tip-to-tip lengths, for electric field measurements. Each
spacecraft will have AC and DC magnetometers, an electric
fields and waves sensor, an electron emitter/detector, an
electron density sounder, electron and ion plasma analysers,
an energetic particle detector, an ion emitter, and a data
processing unit.
Cluster operations will be performed by ESA with support from
NASA's Deep Space Network. Cluster is also an IACG
mission. A more detailed description of the spacecraft and
experiments may be found in ``Cluster: Mission, payload and
supporting activities,'' ESA SP-1159, March 1993.
Personnel
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=CLUSTR1[30/05/2011 22:50:21]
Funding Agencies
European Space Agency
(International)
National Aeronautics and
Space Administration
(United States)
Discipline
Space Physics
Additional
Information
Launch/Orbital
information for Cluster96
Telecommunications
information for Cluster96
Experiments on Cluster96
Cluster96
be directed to: Dr. Ramona
L. Kessel.
Name
Role
E-mail
Dr. Melvyn L.
Goldstein
Project
Scientist
NASA Goddard Space
Flight Center
[email protected]
Dr. Elden C.
Whipple
Program
Scientist
NASA Headquarters
[email protected]
Mr. Raymond
S. Tatum
Project
Manager
NASA Goddard Space
Flight Center
Selected References
Cluster: Mission, payload and supporting activities, ESA SP-1159, Paris, France, Mar. 1993.
Other Cluster Information at NSSDC
Cluster96 (failed launch of four spacecraft)
Samba
Salsa
Rumba
Tango
Other Sources of Cluster Data/Information
Cluster home page (ESA)
Cluster Active Archive (ESA/ESTEC)
Cluster Summary Parameters (CDAWeb)
Cluster Prime Parameters (CDAWeb)
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=CLUSTR1[30/05/2011 22:50:21]
Monday, 30 May 2011
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Spacecraft
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Personnel
Cosmos 2327
Publications
NSSDC ID: 1996-004A
Maps
New/Updated Data
Alternate Names
Description
Cosmos 2327 was part of a 6-satellite Russian military
navigation system distributed in orbital planes spaced 30
degrees apart, and launched from the Plesetsk cosmodrome
aboard a Cosmos rocket. Navigation information was derived
from Doppler-shifted VHF transmissions (approximately 150
and 400 MHz) of the satellite position and orbital data. By
acquiring fixes from several satellite, a user's location could be
calculated with an accuracy of 100 m. The time needed to
ascertain a position was dependent upon the user's latitude
and the number of operational spacecraft in orbit. Normally,
accurate location determination could be made within 1-2
hours.
23773
Facts in Brief
Launch
Vehicle: Cosmos
Russia
Mass: 825.0 kg
Funding Agency
Unknown (Russia)
Discipline
Surveillance and Other
Military
Additional
Information
Launch/Orbital
information for Cosmos
2327
Experiments on Cosmos
2327
Cosmos 2327
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Cosmos 2328
Publications
NSSDC ID: 1996-009D
Maps
New/Updated Data
Alternate Names
Description
Cosmos 2328 was a Russian military spacecraft launched by a
Cyclon-3 rocket from the Plesetsk Cosmodrome along with
Cosmos 2329, 2330 and three Gonets spacecraft. It provided
military data messaging and photo reconnaissance for the
Russian Federation Ministry of Defense.
23790
Facts in Brief
Launch
Vehicle: Tsiklon-3
Russia
Mass: 225.0 kg
Funding Agency
Unknown (Russia)
Discipline
Military
Additional
Information
Launch/Orbital
2328
2328
Cosmos 2328
Office.
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-009D[30/05/2011 22:51:05]
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Personnel
Cosmos 2329
Publications
NSSDC ID: 1996-009E
Maps
New/Updated Data
Alternate Names
Description
military data messaging and photo reconnaissance for the
23791
Facts in Brief
Launch
Vehicle: Tsiklon-3
Russia
Mass: 225.0 kg
Funding Agency
Unknown (Russia)
Discipline
Military
Additional
Information
Launch/Orbital
2329
2329
Cosmos 2329
Office.
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-009E[30/05/2011 22:51:38]
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Personnel
Cosmos 2330
Publications
NSSDC ID: 1996-009F
Maps
New/Updated Data
Alternate Names
Description
military data messaging and photo reconnoissance for the
23792
Facts in Brief
Launch
Vehicle: Tsiklon-3
Russia
Mass: 225.0 kg
Funding Agency
Unknown (Russia)
Discipline
Military
Additional
Information
Launch/Orbital
2330
2330
Cosmos 2330
Office.
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-009F[30/05/2011 22:52:26]
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Personnel
Cosmos 2331
Publications
NSSDC ID: 1996-016A
Maps
New/Updated Data
Alternate Names
Description
Cosmos 2331, a Russian high resolution photo
reconnaissance spacecraft, was launched from the Plesetsk
cosmodrome. It returned film in two small SpK capsules during
the mission and with the main capsule at completion of the
mission.
23818
Facts in Brief
Launch
Vehicle: Soyuz-U
Russia
Mass: 6600.0 kg
Funding Agency
Unknown (Russia)
Discipline
Military
Additional
Information
Launch/Orbital
2331
2331
Cosmos 2331
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Cosmos 2332
Publications
NSSDC ID: 1996-025A
Maps
New/Updated Data
Alternate Names
Description
In 1969 KB Yuzhnoye introduced targets for exercise and test
of PVO air defence and space tracking systems. The second
generation consisted of Taifun-1 and Taifun-2 satellites, which
differed in the type of equipment installed. In 1972 KB-3 under
B E Khimrov, with the co-operation of assisting organisations
and the Ministry of Defence, completed the draft project. The
first Taifun-2 was completed in 1976. Flight trials were
conducted in the second half of the 1970's using Kosmos-3M
launch vehicles from Plesetsk and Kapustin Yar. The heads of
the State Trials Commission were B N Karpov, N N Zhukov,
and B G Zudin. Taifun-2 satellites were spherical in shape, 2
m in diameter, with no external solar cells or antennae.
23853
Facts in Brief
Launch
Vehicle: Cosmos
Russia
Funding Agency
Unknown (Russia)
Discipline
Military
Additional
Information
Launch/Orbital
2332
2332
Cosmos 2332
Office.
Monday, 30 May 2011
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Cosmos 2333
Publications
NSSDC ID: 1996-051A
Maps
New/Updated Data
Alternate Names
Description
Cosmos 2333 was a signals intelligence satellite of the Tselina
2 series, built by KB Yuzhnoe of the Ukraine. It was launched
on a Zenit 2 launch vehicle from the Baikonur cosmodrome
and was operated by the Russian Ministry of Defense.
24297
Facts in Brief
Launch Vehicle: Zenit
Kazakhstan
Funding Agency
Unknown (Russia)
Discipline
Military
Additional
Information
Launch/Orbital
2333
2333
Cosmos 2333
Office.
Monday, 30 May 2011
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Cosmos 2334
Publications
NSSDC ID: 1996-052A
Maps
New/Updated Data
Alternate Names
Description
hours.
24304
Facts in Brief
Launch
Vehicle: Cosmos
Russia
Funding Agency
Unknown (Russia)
Discipline
Navigation & Global
Positioning
Additional
Information
Launch/Orbital
2334
2334
Cosmos 2334
Office.
Monday, 30 May 2011
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Cosmos 2335
Publications
NSSDC ID: 1996-069A
Maps
New/Updated Data
Alternate Names
Description
Cosmos 2335 was a Russian naval reconnaisance satellite
launched from the Baikonur cosmodrome aboard a Tsyklon 2
rocket. This naval forces monitoring spacecraft was used to
determine the position of enemy naval forces through detection
and triangulation of their electromagnetic emissions (radio,
radar, etc).
24670
Facts in Brief
Launch
Vehicle: Tsiklon-2
Kazakhstan
Mass: 3150.0 kg
Funding Agency
Unknown (Russia)
Discipline
Military
Additional
Information
Launch/Orbital
2335
Telecommunications
2335
2335
Cosmos 2335
Office.
Monday, 30 May 2011
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Cosmos 2336
Publications
NSSDC ID: 1996-071A
Maps
New/Updated Data
Alternate Names
Description
hours.
24677
Facts in Brief
Launch
Vehicle: Cosmos
Russia
Funding Agency
Unknown (Russia)
Discipline
Military
Additional
Information
Launch/Orbital
2336
2336
Cosmos 2336
Office.
Monday, 30 May 2011
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Echostar 2
Publications
NSSDC ID: 1996-055A
Maps
New/Updated Data
Alternate Names
Description
Echostar 2, a Lockheed Martin satellite, was launched from the
Kourou space center in French Guiana aboard an Ariane 42P
rocket. This second in a series of DBS communications
satellites, was positioned at 119 deg W and provided video,
audio and data services to the continental US, Southern
Canada, and Northern Mexico.
24313
Facts in Brief
42P
French Guiana
Mass: 2885.0 kg
Nominal
Power: 7000.0 W
Funding Agency
Echostar
Communications
Corporation (United
States)
Discipline
Communications
Additional
Information
Launch/Orbital
information for Echostar 2
Experiments on Echostar 2
Echostar 2
Office.
Monday, 30 May 2011
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Express 12
Publications
NSSDC ID: 1996-058A
Maps
New/Updated Data
Alternate Names
Description
Express 12 was a Russian geostationary communications
satellite launched from the Baikonur cosmodrome aboard a
Proton rocket. Express will replace the widely used Gorizont
spacecraft, and current plans call for deployments at 13
locations (40 degrees, 53 degrees, 80 degrees, 90 degrees,
96.5 degrees, 99 degrees, 103 degrees, 140 degrees, 145
degrees, 205 degrees, 322.5 degrees, 346 degrees, and 349
degrees, all East longitude) just for domestic needs and to
support the Intersputnik Telecommunications Association. A
typical Express payload will include 10 C-band and two Kuband transponders.
24435
Facts in Brief
Launch Vehicle: Proton
Kazakhstan
Mass: 2500.0 kg
Funding Agency
Unknown (Russia)
Discipline
Communications
Additional
Information
Launch/Orbital
information for Express
12
Experiments on Express
12
Express 12
Office.
Monday, 30 May 2011
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FAST
Publications
NSSDC ID: 1996-049A
Maps
New/Updated Data
Description
The Fast Auroral SnapshoT Explorer (FAST) was successfully
launched on 1996-08-21 into its intended orbit. FAST
investigates the plasma physics of auroral phenomena at
extremely high time and spatial resolution using the full
complement of particle and fields instruments. FAST is the
second spacecraft (SAMPEX was first) in the Small Explorer
(SMEX) program at NASA-GSFC. SMEX was established to
provide rapid (3 year development) low cost ($35M
development) mission opportunities (1 per year) to the space
science community using a single designated Principal
Investigator (PI).
In order to capture the auroral phenomena over small time
(microseconds) and spatial scales, FAST utilizes high speed
data sampling, a large, fast-loading ("burst") memory, and a
smart, on-board software to trigger on the appearance of
various key phenomena. Using a 1 Gb solid-state memory and
a data acquisition rate of 8 Mbs (almost two orders of
magnitude faster than previous satellites), FAST produces
high-resolution "snapshots" of auroral arcs and other
interesting auroral events. FAST flies in a highly eccentric,
near-polar orbit precessing nominally one degree per day.
Scientific investigations are operate in a campaign mode
(about 60 days long) as apogee transitions through the
northern auroral zone and in less intense survey mode during
the rest of the orbit.
The FAST mission uses a unique (not a SAMPEX derivative),
lightweight, orbit-normal spinner spacecraft developed by the
SMEX project. The spacecraft has body-mounted solar arrays,
and is spin-stabilized, rotating at 12 rpm with the spin axis
normal to the orbit plane ("cartwheel"). The four FAST
experiments are: (1) the Electrostatic Analyzers (ESA) for
measuring the electron and ion distribution function, (2) the
Time-of-flight Energy Angle Mass Spectrograph (TEAMS) for
measuring the full 3-dimensional distribution function of the
major ion species, (3) the Tri-Axial Fluxgate and Search-coil
Magnetometers for measuring magnetic field data, and (4) the
Electric Field/Langmuir Probe Instrument for obtaining electric
field data and plasma density and temperature. The FAST
electric field instrument stopped providing meaningful data
around 2002, all other instruments and systems continue to
function nominally.
Alternate Names
Small Explorer/FAST
Explorer 70
SMEX/FAST
Fast Auroral SnapshoT
Explorer
24285
Facts in Brief
Launch
Vehicle: Pegasus XL
Launch
Site: Vandenberg AFB,
United States
Mass: 187.0 kg
Nominal Power: 60.0 W
Funding Agency
NASA-Office of Space
Science Applications
(United States)
Discipline
Space Physics
Additional
Information
Launch/Orbital
information for FAST
FAST
Telecommunications
information for FAST
Experiments on FAST
Data collections from FAST
be directed to: Dr. Dieter K.
Bilitza.
Personnel
Name
Role
E-mail
Dr. Robert F.
Pfaff
Project Scientist
NASA Goddard Space
Flight Center
[email protected]
Mr. Ronald E.
Adkins
Project Manager
NASA Goddard Space
Flight Center
Dr. Charles
W. Carlson
Mission Principal
Investigator
University of California,
Berkeley
[email protected]
Other Sources of FAST Data/Information
Five-second Survey Data (CDAWeb)
Orbit and conjunctions (SSCWeb)
FAST Project page (U. California, Berkeley)
Small Explorer Project page
Monday, 30 May 2011
FSW-2 3
NSSDC ID: 1996-059A
Description
FSW-2 3 was a People's Republic of China remote sensing satellite launched by a Long March 3 rocket from Xichuan.
Alternate Names
24634
Facts in Brief
Launch Date: 1996-10-20
Launch Vehicle: Long March 3
Launch Site: Jiuquan, Peoples Republic of China
Funding Agency
Unknown (Peoples Republic of China)
Discipline
Earth Science
Additional Information
Launch/Orbital information for FSW-2 3
Experiments on FSW-2 3
Data collections from FSW-2 3
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Maps
New/Updated Data
Wednesday, 08 June 2011
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Galaxy 9
Publications
NSSDC ID: 1996-033A
Maps
New/Updated Data
Alternate Names
Description
Galaxy 9 was a geosynchronous spacecraft launched by
Hughes Communications Inc from Cape Canaveral aboard a
Delta 2 rocket. It provided voice and vision communications to
North America.
23877
Facts in Brief
Launch Vehicle: Delta
II
Launch Site: Cape
Canaveral, United States
Funding Agency
Pan American Satellite
(United States)
Discipline
Communications
Additional
Information
Launch/Orbital
information for Galaxy 9
Experiments on Galaxy 9
Galaxy 9
Office.
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GE 1
Publications
NSSDC ID: 1996-054A
Maps
New/Updated Data
Alternate Names
Description
GE 1 was an AMERICOM Corp communications satellite
launched from Cape Canaveral aboard an Atlas 2A rocket. It
was placed into a geostationary orbit at 103 deg W.
24315
Facts in Brief
Launch Vehicle: Atlas
2A
Launch Site: Cape
Funding Agency
GE American
Communications, Inc.
(United States)
Discipline
Communications
Additional
Information
Launch/Orbital
information for GE 1
Experiments on GE 1
Data collections from GE 1
Office.
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Gonets D1-1
Publications
NSSDC ID: 1996-009A
Maps
New/Updated Data
Alternate Names
Description
Gonets D1-1 was a Russian communications/photoreconnoissance spacecraft launched by a Cyclon-3 rocket,
along with Gonets D1-2 and D1-3, and 3 Cosmos spacecraft.
It will monitor disasters like oil spills, illicit transport of
radioactive cargo, and provide prompt alerts.
23787
Facts in Brief
Launch
Vehicle: Tsiklon-3
Russia
Mass: 250.0 kg
Funding Agency
Unknown (Russia)
Discipline
Communications
Additional
Information
Launch/Orbital
information for Gonets
D1-1
Experiments on Gonets
D1-1
Gonets D1-1
Office.
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Gonets D1-2
Publications
NSSDC ID: 1996-009B
Maps
New/Updated Data
Alternate Names
Description
Gonets D1-2 was a Russian communications/photoreconnoissance spacecraft launched by a Cyclon-3 rocket
along with Gonets D1-1, D1-3, and three Cosmos spacecraft.
23788
Facts in Brief
Launch
Vehicle: Tsiklon-3
Russia
Mass: 250.0 kg
Funding Agency
Unknown (Russia)
Discipline
Communications
Additional
Information
Launch/Orbital
D1-2
D1-2
Gonets D1-2
Office.
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Gonets D1-3
Publications
NSSDC ID: 1996-009C
Maps
New/Updated Data
Alternate Names
Description
Gonets D1-3 was a Russian communications/photoreconnoissance spacecraft launched by a Cyclon-3 rocket
along with Gonets D1-1, D1-2, and three Cosmos spacecraft.
23789
Facts in Brief
Launch
Vehicle: Tsiklon-3
Russia
Mass: 250.0 kg
Funding Agency
Unknown (Russia)
Discipline
Communications
Additional
Information
Launch/Orbital
D1-3
D1-3
Gonets D1-3
Office.
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-009C[08/06/2011 0:15:24]
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Gorizont 31
Publications
NSSDC ID: 1996-005A
Maps
New/Updated Data
Alternate Names
Description
Gorizont 31 was a Russian geosynchronous communications
satellite. It was launched to provide telephone, telegraph and
fax communications services, in addition to relaying TV and
radio broadcasts, as well as support maritime and international
communications. It was stationed at 39 deg E.
The Gorizont spacecraft possessed an initial mass in excess of
2.1 metric tons and have demonstrated a lifetime of nearly 10
years, although a 5-year service life was more common. The
3-axis stabilized satellite was approximately 2 m in diameter
and 5 m long with two large solar arrays capable of generating
1.3 kW of electrical power for the first 3 years. Seven separate
transmission antennas allowed a variety of reception patterns
for both broad and localized terrestrial regions.
A typical Gorizont communications payload included six
general purpose (TV, audio, facsimile) 6/4 GHz transponders
(five 12.5 W and one 60 W), one Luch 14/11 GHz transponder
(15 W), and one Volna 1.6/1.5 GHz transponder (20 W). The
Volna transponders were INMARSAT-compatible and were
extensively used by the Russian merchant marine fleet via the
primary GEO television rebroadcasting system, supporting all
five Federation time zones: Zone 1 from 140 deg E, Zone 2
from 90 deg E, Zone 3 from 80 deg E, Zone 4 from 53 deg E,
and Zone 5 from 14 deg W. These transmissions were handled
by Orbita (12-m receiving antenna) and Moskva (2.5-m
receiving antenna) ground stations in the 6/4 GHz band. The
Moskva Globalnaya system was inaugurated in 1989 using 4m receiving antennas and serviced by Gorizonts at 96.5 deg E
and 11 deg W.
23775
Facts in Brief
Kazakhstan
Mass: 2125.0 kg
Funding Agency
Unknown (Russia)
Discipline
Communications
Additional
Information
Launch/Orbital
information for Gorizont
31
Experiments on Gorizont
31
Gorizont 31
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Gorizont 32
Publications
NSSDC ID: 1996-034A
Maps
New/Updated Data
Alternate Names
Description
Gorizont 32 was a Russian geosynchronous communications
satellite. It was launched to provide telephone, telegraph and
fax communications services, in addition to relaying TV and
radio broadcasts, as well as support maritime and international
communications. It was stationed at 53.2 deg E.
The Gorizont spacecraft possessed an initial mass in excess of
2.1 metric tons and have demonstrated a lifetime of nearly 10
years, although a 5-year service life was more common. The
3-axis stabilized satellite was approximately 2 m in diameter
and 5 m long with two large solar arrays capable of generating
1.3 kW of electrical power for the first 3 years. Seven separate
transmission antennas allowed a variety of reception patterns
for both broad and localized terrestrial regions.
23880
Facts in Brief
Launch
Vehicle: Proton-K
Kazakhstan
Mass: 2125.0 kg
Funding Agency
A typical Gorizont communications payload included six
general purpose (TV, audio, facsimile) 6/4 GHz transponders
(five 12.5 W and one 60 W), one Luch 14/11 GHz transponder
(15 W), and one Volna 1.6/1.5 GHz transponder (20 W). The
Volna transponders were INMARSAT-compatible and were
extensively used by the Russian merchant marine fleet via the
primary GEO television rebroadcasting system, supporting all
five Federation time zones: Zone 1 from 140 deg E, Zone 2
from 90 deg E, Zone 3 from 80 deg E, Zone 4 from 53 deg E,
and Zone 5 from 14 deg W. These transmissions were handled
by Orbita (12-m receiving antenna) and Moskva (2.5-m
receiving antenna) ground stations in the 6/4 GHz band. The
Moskva Globalnaya system was inaugurated in 1989 using 4m receiving antennas and serviced by Gorizonts at 96.5 deg E
and 11 deg W.
Unknown (Russia)
Discipline
Communications
Additional
Information
Launch/Orbital
information for Gorizont
32
Experiments on Gorizont
32
Gorizont 32
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HETE 1
Publications
NSSDC ID: 1996-061A
Maps
New/Updated Data
Description
The High Energy Transient Experiment (HETE) was to be an
international mission led by the Massachusetts Institute of
Technology (MIT). Its prime objective was to carry out the first
multiwavelength study of gamma-ray bursts (GRB) with UV, Xray and gamma ray instruments. A unique feature of the
mission was its capability to localize bursts with several arcsecond accuracy, in near real-time aboard the spacecraft. The
spacecraft hardware and software was developed by
AeroAstro, Inc. (USA). The HETE spacecraft was sun-pointing
with four solar panels connected to the bottom of the
spacecraft bus. Spacecraft attitude was to be controlled by
magnetic torque coils and a momentum wheel.
The HETE satellite was launched with the Argentine satellite
SAC-B. HETE was trapped within the Dual Payload
Attachment Fitting due to a battery failure in the Pegasus XL
rocket third stage. Due to its inability to deploy the solar
panels, HETE lost power several days after launch
Alternate Names
High Energy Transient
Experiment
High-Energy Transient
Explorer 1
24645
Facts in Brief
Launch
Vehicle: Pegasus XL
Launch Site: Wallops
Island, United States
Mass: 128.0 kg
Funding Agency
Science (United States)
Discipline
Astronomy
Additional
Information
Launch/Orbital
information for HETE 1
Experiments on HETE 1
HETE 1
Office.
Personnel
Name
Role
E-mail
Related Information/Data at NSSDC
HETE 2
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Hot Bird 2
Publications
NSSDC ID: 1996-067A
Maps
New/Updated Data
Alternate Names
Description
Hot Bird 2 was a geostationary communications spacecraft of
the European EUTELSAT consortium. With a constellation of 5
satellites, the Hot Bird family at 13 degrees E formed one of
the largest broadcasting systems in the world. By fourth
quarter 1998, the system was delivering over 320 analogue
and digital television channels, as well as radio and multimedia
services, to more than 70 million homes connected to a cable
network or equipped for satellite (direct-to-home or
community) reception. The Hot Bird satellites provided full
coverage of Europe and also took in parts of Africa and Asia,
including the entire Middle East.
Eurobird 9
24665
Facts in Brief
2A
Launch Site: Cape
Mass: 2800.0 kg
Funding Agency
European
Telecommunications
Satellite Consortium
(International)
Discipline
Communications
Additional
Information
Launch/Orbital
information for Hot Bird 2
Experiments on Hot Bird 2
Data collections from Hot
Bird 2
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IAE
Publications
NSSDC ID: 1996-032C
Maps
New/Updated Data
Alternate Names
Description
IAE (Inflatable Antenna Experiment) was a NASA inflatable
mylar antenna that was released from STS 77. It expanded to
a diameter of 16 meters and retained its shape with the help of
3 inflated 30-meter struts. It re-entered the atmosphere after
several orbits.
Inflatable Antenna
Experiment
23872
Facts in Brief
Launch
Vehicle: Shuttle
Launch Site: Cape
Funding Agency
(United States)
Discipline
Technology Applications
Additional
Information
Launch/Orbital
information for IAE
Experiments on IAE
Data collections from IAE
Office.
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Inmarsat 3-F1
Publications
NSSDC ID: 1996-020A
Maps
New/Updated Data
Alternate Names
Description
Inmarsat 3-F1 was the first in a series of five third generation
satellites. Launched from Cape Canaveral aboard an Atlas 2A
rocket, it is currently in service over the Indian Ocean. It used
the latest spot-beam technology and higher power to supply
voice and data communications services worldwide to mobile
terminals as small as pocket-size messaging units on ships,
aricraft and vehicles.
INMARSAT-3 development was carried out by prime contractor
Lockheed Martin and payload provider Matra Marconi Space.
With an end-of-life power rating of 2,800 W, each INMARSAT3 could deliver an IERP of up to 48dBW - eight times the
INMARSAT-2 level - in L-band. It could dynamically reallocate
both RF power and bandwidth among a global beam and five
spot beams, allowing greater reuse of the available spectrums.
Simultaneous voice channel capacity was up to eight times the
INMARSAT-2 figure.
Each INMARSAT-3 also carried a navigation transponder
designed to enhance the accuracy, availability and integrity of
the GPS and Glonass satellite navigation systems.
23839
Facts in Brief
2A
Launch Site: Cape
Mass: 2068.0 kg
Funding Agency
Inmarsat (International)
Discipline
Communications
Additional
Information
Launch/Orbital
information for Inmarsat
3-F1
Experiments on Inmarsat
3-F1
Inmarsat 3-F1
Office.
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Inmarsat 3-F2
Publications
NSSDC ID: 1996-053A
Maps
New/Updated Data
Alternate Names
Description
Inmarsat 3-F2 was the second in a series of five third
generation satellites. Launched from the Baikonur cosmodrome
aboard a Proton rocket, it is currently in service over the
Atlantic Ocean. It used the latest spot-beam technology and
higher power to supply voice and data communications
services worldwide to mobile terminals as small as pocket-size
messaging units on ships, aricraft and vehicles.
INMARSAT-2 figure.
24307
Facts in Brief
Kazakhstan
Funding Agency
International
Telecommunications
Satellite Corporation
(International)
Discipline
Communications
Additional
Information
Launch/Orbital
3-F2
3-F2
Inmarsat 3-F2
Office.
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Inmarsat 3-F3
Publications
NSSDC ID: 1996-070A
Maps
New/Updated Data
Alternate Names
Description
Inmarsat 3-F3 was the third in a series of five third generation
satellites. Launched from Cape Canaveral aboard an Atlas 2
rocket, it is currently in service over the Pacific Ocean. It used
the latest spot-beam technology and higher power to supply
voice and data communications services worldwide to mobile
terminals as small as pocket-size messaging units on ships,
aircraft and vehicles.
INMARSAT-2 figure.
24674
Facts in Brief
Launch Site: Cape
Funding Agency
International
Telecommunications
(International)
Discipline
Communications
Additional
Information
Launch/Orbital
3-F3
3-F3
Inmarsat 3-F3
Office.
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INTELSAT 7 F-7
Publications
NSSDC ID: 1996-015A
Maps
New/Updated Data
Alternate Names
Description
Intelsat 7-F7 was a geostationary communications spacecraft
for the Intelsat consortium that was launched by an Ariane
44LP rocket from the Kourou Space Center in French Guiana.
The 4,175 kg spacecraft carried 26 C-band and 14 K-band
transponders to provide Europe and the Americas with 3
television channels and 22,500 telephone circuits after parking
over the eastern coast of Brazil.
23816
Facts in Brief
44LP
French Guiana
Mass: 4175.0 kg
Funding Agency
International
Telecommunications
(International)
Discipline
Communications
Additional
Information
Launch/Orbital
information for INTELSAT
7 F-7
Experiments on INTELSAT
7 F-7
INTELSAT 7 F-7
Office.
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INTELSAT 709
Publications
NSSDC ID: 1996-035A
Maps
New/Updated Data
Alternate Names
Description
Intelsat 709 was a geosynchronous communications satellite of
the INTELSAT consortium. It was launched by an Ariane 44P
rocket from the Kourou site in French Guiana and carried 36
Ku- and C-band transponders to serve the Atlantic ocean
region.
23915
Facts in Brief
44P
French Guiana
Funding Agency
International
Telecommunications
(International)
Discipline
Communications
Additional
Information
Launch/Orbital
information for INTELSAT
709
Experiments on INTELSAT
709
INTELSAT 709
Office.
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Publications
NSSDC ID: 1996-050C
Maps
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Description
The Interball Project is a multi-national effort that consists of
four spacecraft: two main spacecraft of the Prognoz series,
made in Russia, each with a small subsatellite made in
Czechoslovakia. The main objective is to study the physical
mechanisms responsible for the transmission of solar wind
energy to the magnetosphere, its storage there, and
subsequent dissipation in the tail and auroral regions of the
magnetosphere, ionosphere, and atmosphere during
magnetospheric substorms. A ground-based support group will
provide coordinated and simultaneous ground-based data of
many types, including observations from auroral and polar cap
regions. Interball is an IACG-related mission. Key physical
parameters will be generated, and will be available for
exchange with other projects. Campaigns for intercomparison
with the Wind and Geotail spacecraft are expected. One pair
of spacecraft, Tail Probe and its subsatellite S2-X (X for the
first letter of the Russian word for ``Tail''), will be launched into
the magnetospheric tail. The second pair, Auroral Probe and
S2-A (A for ``Auroral''), will have an orbit that crosses the
auroral oval to observe the acceleration of auroral particles
and the flow of electric currents that connect the
magnetospheric tail with the conducting ionosphere. To study
the equilibrium tail structure, during about half of each year the
Tail Probe pair will cross the main parts of the magnetotail
every four days. The Auroral Probe pair will support the Tail
Probe pair with auroral region measurements. Each main
spacecraft has more than twenty scientific instruments. The
spacecraft is cylindrical, with spin axis toward the sun (within
10 degrees), and with spin period of ~120 s. The electric and
magnetic field sensors are on booms connected to the ends of
the solar panels. The subsatellites are small, each with about
ten scientific instruments. The spin axis will be directed within
10 degrees of the sun, with a spin period of ~120 s, as with the
main spacecraft. The subsatellites also carry gas-jet thrusters
for limited control of the orbit. Separation distance will range
from hundreds of kilometers to several tens of thousands of
kilometers for the Tail Probe pair. Separation distance will
range from hundreds of meters to hundreds of kilometers for
the Auroral Probe pair. The Tail Probe has two telemetry
systems, at up to 32 Kbps in real-time, with a memory mode
capacity of 30 Mb in the RTK telemetry system and 120 Mb in
the SSNI system. The Auroral Probe has similar capability plus
the additional real-time-only STO system, capable of 40 Kbps.
Each subsatellite has only the STO real-time telemetry system.
For S2-X the rate can be varied from 2--40 kbps. The Tail
Probe has an adapting alert mode while in the memory mode,
allowing time resolutions that are the same as in the real-time
mode. The aim is to have the highest time resolution available
at the thin borders of magnetospheric regions or the sharp
Alternate Names
Auroral Probe
Prognoz 2M
Interball 2
Prognoz 12
24293
Facts in Brief
Launch
Vehicle: Molniya-M
Russia
Mass: 1250.0 kg
Funding Agency
Russian Space Agency
(Russia)
Discipline
Space Physics
Additional
Information
Launch/Orbital
information for Interball
Auroral Probe
Experiments on Interball
Auroral Probe
be directed to: Dr. H. Kent
Hills.
Interball
borders of some features. In the alert mode (triggered by an
on-board computer monitoring plasma and field parameters),
the bit rate is increased for plasma, field, and wave
measurements. The duration of these alert periods is about 10
minutes, and there can be 5--6 of them during one orbit.
Data/Information at
NSSDC
Interball Tail Probe
Interball S2-X
Interball S2-A
Other Sources of Interball Data/Information
Interball project (IKI)
Interball data archive (IKI)
NSSDC Master
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Spacecraft
Experiments
Data Collections
Personnel
IRS-P3
Publications
NSSDC ID: 1996-017A
Maps
New/Updated Data
Alternate Names
Description
IRS-P3 is an Indian Remote Sensing spacecraft launched by a
4-stage PSLV-D3 developmental rocket from the Sriharikota
launch station on the southeast coast of India. The 930 kg
spacecraft carried two remote sensing experiments and an
astronomical x-ray detector. WIFS (WIde Field Sensor) was a
scanner with visible light and infrared photometers to study
crop conditions, geology, and snow cover. The German Space
Agency's (DLR's) modular opto-electronic scanner will monitor
oceanic chlorophyll, sediment transport and ocean dynamics.
Data will be downlinked at 3 Indian stations, and stations in
Russia, Germany, and Mauritius.
Indian Remote Sensing
Satellite P3
23827
Facts in Brief
Launch Vehicle: PSLV
Launch Site: Sriharikota,
India
Mass: 930.0 kg
Funding Agency
Indian Space Research
Organization (India)
Disciplines
Astronomy
Earth Science
Additional
Information
Launch/Orbital
information for IRS-P3
Experiments on IRS-P3
Data collections from IRSP3
Office.
NSSDC Master
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Spacecraft
Experiments
Data Collections
Personnel
Italsat 2
Publications
NSSDC ID: 1996-044A
Maps
New/Updated Data
Alternate Names
Description
Italy's second national communications satellite, ITALSAT 2
was dual launched aboard an Ariane 44L booster from Kourou,
French Guiana. Placed in geosynchronous orbit above 13.2
deg. e, the satellite served as a spaceborne telephone
switchboard, redirecting up to 12,000 calls at once. ITALSAT
was experimental in nature, a pre-operational component of a
proposed digital satellite network for Italy. Built by Selenia
Spazio for Agenzia Spaziale Italiana (the Italian Space
Agency), ITALSAT 2 was box-shaped, measuring 2.72 by 2.22
by 3.48 m. It was 6.1 m tall with its two 2-m reflector antennas
deployed. Solar arrays spanned 21 m and provided 1,600 W
of power. Its communications package housed six 20/30 GHz
multibeam transponders, three 20/30 GHz global beam
transponders and a propagation experiment operating at 40/50
GHz. The multibeam system, using advanced time division
multiple access (TDMA) techniques, was expected to undergo
two years of testing; the global beam system was considered
operational from the start and was used to test new services.
ITALSAT 2 had a 5-year design life.
24208
Facts in Brief
44L
French Guiana
Mass: 2000.0 kg
Funding Agency
Unknown (Italy)
Discipline
Communications
Additional
Information
Launch/Orbital
information for Italsat 2
Experiments on Italsat 2
Italsat 2
Office.
NSSDC Master
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JAS 2
Publications
NSSDC ID: 1996-046B
Maps
New/Updated Data
Alternate Names
Description
JAS-2 was a Japanese communications satellite launched from
the Tanegashima Space Center for NASDA. It succeeded
JAS-1b which was launched in February of 1990.
OSCAR 29
24278
Facts in Brief
Launch Vehicle: H-2
Launch
Site: Tanegashima, Japan
Mass: 50.0 kg
Funding Agency
Unknown (Japan)
Discipline
Communications
Additional
Information
Launch/Orbital
information for JAS 2
Experiments on JAS 2
Data collections from JAS
2
Office.
NSSDC Master
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Spacecraft
Experiments
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KH 12-3
Publications
NSSDC ID: 1996-072A
Maps
New/Updated Data
Alternate Names
Description
KH 12-3 was launched from Vandenberg AFB aboard a Titan 4
rocket for the US Department of Defense. It was an electrooptical reconnaisance satellite that succeeded the KH-11
series. It was heavier and believed to include a signals
intelligence payload, it had wider spectral band sensitivity,
perhaps "real time" television capability, and other
improvements compared to the KH-11 satellites. Data were
transmitted via the SDS military relay satellites.
USA 129
24680
Facts in Brief
Launch Vehicle: Titan
IV
Launch
United States
Mass: 19600.0 kg
Funding Agency
Department of DefenseDepartment of the Air
Force (United States)
Discipline
Military
Additional
Information
Launch/Orbital
information for KH 12-3
Experiments on KH 12-3
Data collections from KH
12-3
Office.
NSSDC Master
Catalog Search
Spacecraft
Experiments
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Personnel
Koreasat 2
Publications
NSSDC ID: 1996-003A
Maps
New/Updated Data
Alternate Names
Description
Koreasat 2, also known as Mugunghwa 2, was a South Korean
geostationary communications spacecraft launched from Cape
Canaveral by a Delta 2 rocket. It will be parked at 116 E
longitude over Borneo island to provide broadcasting and
telecommunications to South Korea beginning in July 1996.
Mugunghwa 2
23768
Facts in Brief
II
Launch Site: Cape
Funding Agency
Unknown (South Korea)
Discipline
Communications
Additional
Information
Launch/Orbital
information for Koreasat 2
Experiments on Koreasat 2
Koreasat 2
Office.
NSSDC Master
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Magion 5
Publications
NSSDC ID: 1996-050B
Maps
New/Updated Data
Description
The Interball Project is a multi-national effort that consists of
four spacecraft: two main spacecraft of the Prognoz series,
made in Russia, each with a small subsatellite made in
Czechoslovakia. The main objective is to study the physical
mechanisms responsible for the transmission of solar wind
energy to the magnetosphere, its storage there, and
subsequent dissipation in the tail and auroral regions of the
magnetosphere, ionosphere, and atmosphere during
magnetospheric substorms. A ground-based support group will
provide coordinated and simultaneous ground-based data of
many types, including observations from auroral and polar cap
regions. Interball is an IACG-related mission. Key physical
parameters will be generated, and will be available for
exchange with other projects. Campaigns for intercomparison
with the Wind and Geotail spacecraft are expected. One pair
of spacecraft, Tail Probe and its subsatellite S2-X (X for the
first letter of the Russian word for ``Tail''), will be launched into
the magnetospheric tail. The second pair, Auroral Probe and
S2-A (A for ``Auroral''), will have an orbit that crosses the
auroral oval to observe the acceleration of auroral particles
and the flow of electric currents that connect the
magnetospheric tail with the conducting ionosphere. To study
the equilibrium tail structure, during about half of each year the
Tail Probe pair will cross the main parts of the magnetotail
every four days. The Tail Probe, with approximately 30 earth
radii apogee, will cross the noon-midnight plane on December
1, so the measurements in the magnetotail will cover the
period from October 1995 to February 1996. The Auroral
Probe pair will support the Tail Probe pair with auroral region
measurements.
Each main spacecraft has more than twenty scientific
instruments. The spacecraft is cylindrical, with spin axis toward
the sun (within 10 degrees), and with spin period of ~120 s.
The electric and magnetic field sensors are on booms
connected to the ends of the solar panels.
The subsatellites are small, each with about ten scientific
instruments. The spin axis will be directed within 10 degrees of
the sun, with a spin period of ~120 s, as with the main
spacecraft. The subsatellites also carry gas-jet thrusters for
limited control of the orbit. Separation distance will range from
hundreds of kilometers to several tens of thousands of
kilometers for the Tail Probe pair. Separation distance will
range from hundreds of meters to hundreds of kilometers for
the Auroral Probe pair. The Tail Probe has two telemetry
systems, at up to 32 Kbps in real-time, with a memory mode
capacity of 30 Mb in the RTK telemetry system and 120 Mb in
the SSNI system. The Auroral Probe has similar capability plus
Alternate Names
Auroral Subsatellite S2-A
Interball S2-A
S2-A
24292
Facts in Brief
Launch
Vehicle: Molniya-M
Russia
Mass: 58.0 kg
Funding Agency
Unknown (Czech
Republic)
Discipline
Space Physics
Additional
Information
Launch/Orbital
information for Magion 5
Experiments on Magion 5
Magion 5
Hills.
Interball
Data/Information at
NSSDC
the additional real-time-only STO system, capable of 40 Kbps.
Each subsatellite has only the STO real-time telemetry system.
For S2-X the rate can be varied from 2--40 kbps.
The Tail Probe has an adapting alert mode while in the
memory mode, allowing time resolutions that are the same as
in the real-time mode. The aim is to have the highest time
resolution available at the thin borders of magnetospheric
regions or the sharp borders of some features. In the alert
mode (triggered by an on-board computer monitoring plasma
and field parameters), the bit rate is increased for plasma,
field, and wave measurements. The duration of these alert
periods is about 10 minutes, and there can be 5--6 of them
during one orbit.
Interball Tail Probe
Interball S2-X
Interball S2-A
Other Sources of
Interball
Data/Information
Interball project (IKI)
Interball data archive (IKI)
NSSDC Master
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Mars 96 Orbiter
Publications
NSSDC ID: 1996-064A
Maps
New/Updated Data
Mars 96 Orbiter
Description
Facts in Brief
The Mars 96 spacecraft was launched into Earth orbit, but
failed to achieve insertion into Mars cruise trajectory and reentered the Earth's atmosphere at about 00:45 to 01:30 UT on
17 November 1996 and crashed within a presumed 320 km by
80 km area which includes parts of the Pacific Ocean, Chile,
and Bolivia. The cause of the crash is not known.
Launch
Vehicle: Proton-K
Kazakhstan
Mass: 3159.0 kg
The Russian Mars 96 mission was designed to send an orbiter,
two small autonomous stations, and two surface penetrators to
Mars to investigate the evolution and contemporary physics of
the planet by studying the physical and chemical processes
which took place in the past and which currently take place.
The Mars 96 Orbiter was a 3-axis sun/star stabilized craft
based on the Phobos design with two platforms for pointing
and stabilizing instruments. The propulsion units were mounted
on the bottom and two large solar panels extended out from
opposite sides of the craft. The two penetrators were mounted
on the bottom by the propulsion system, the two small stations
were connected on top of the spacecraft, and a dish antenna
extended off one of the sides perpendicular to the solar
panels. The Mars 96 spacecraft had a launch mass (including
propellant) of 6180 kg.
Funding Agency
(Russia)
Discipline
Planetary Science
Additional
Information
Launch/Orbital
information for Mars 96
Orbiter
Mars 96 was scheduled to arrive at Mars on 12 September
1997, about 10 months after launch, on a direct trajectory.
About 4 to 5 days before arrival the small surface stations
would have been released. The orbiter was to go into an
elliptical 3-day transfer orbit about Mars, and the two
penetrators to descend to the surface during the first month of
orbit. The final orbit would have been a 14.77 hour elliptical
orbit with a periapsis of 300 km.
The Mars 96 Orbiter carried 12 instruments to study the
surface and atmosphere of Mars, 7 instruments to study
plasma, fields, and particles, and 3 instruments for
astrophysical studies. There were also radio science, a
navigation TV camera, and a radiation and dosimetry control
complex. The instruments were located directly on the sides of
the craft, on one of the two platforms attached to the sides of
the craft, or on the edges of the solar panels.
Mars 96 Orbiter
Telecommunications
Orbiter
Experiments on Mars 96
Orbiter
Data collections from Mars
96 Orbiter
be directed to: Dr. David R.
Williams.
Personnel
Name
Role
E-mail
Dr. Albert A. Galeev
Program
Scientist
Russian Academy of
Sciences
[email protected]
Dr. Alexander V.
Zakharov
Project
Scientist
Russian Academy of
Sciences
[email protected]
Selected References
Galeev, A. A., Russian program of planetary missions, Acta Astronautica, 39, No. 1-4, 9-14,
1996.
Other Mars 96 Information from NSSDC
Mars 96 Failure - Timeline from launch to re-entry
Mars 96 Penetrator
Other Sources of Mars 96 Information
Mars 96 Project (IKI)
Information about Mars
Mars Page
NSSDC Master
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Mars 96 Penetrator
Publications
NSSDC ID: MARS96D
Maps
New/Updated Data
Description
Facts in Brief
Russia
Mass: 45.0 kg
Funding Agency
(Russia)
Discipline
Mars 96 Penetrator
The two Mars 96 Penetrators were mounted on the bottom of
the orbiter near the propulsion system. The penetrators were
long thin cylinders, pointed at the bottom, or forebody, and with
a widened, funnel-shaped top. Instruments were contained
inside throughout the length of the cylinder. The scientific
objectives of the penetrator experiments were to obtain images
of the surface, study martian meteorology, examine the
physical, chemical, magnetic, and mechanical properties of the
martian regolith, including its water content, collect data on the
magnetic field, and record seismic activity.
After orbit insertion, adjustment to 300 km periapsis, and 7 to
28 days of orbital maneuvers, the orbiter would be properly
oriented and the first penetrator would be spun about its long
axis and released. When the penetrator had moved away from
the orbiter, its solid rocket motor was to ignite and put it into an
atmospheric entry trajectory. Entry would occur 21 to 22 hours
later. The penetrator was to enter the atmosphere at about 4.9
km/sec at an angle 10-14 degrees. The probe would first be
slowed aerodynamically, followed by inflation of a braking
device. The penetrator was to strike the surface at
approximately 80 m/s. The forebody would separate on impact
and can penetrate 5 to 6 meters into the ground, attached by
wires to the aftbody, the top of the aftbody remaining above the
surface. The plan called for the first penetrator to land near the
site of one of the surface stations, and the second to land at
least 90 degrees away. Both pentrators could have been
released on the same orbit.
The penetrator was equipped with instruments in both the
forebody and aftbody. The forebody held a seismometer,
accelerometer, thermoprobe, neutron detector, and an alphaproton-X-ray spectrometer. The aftbody contained a gammaray spectrometer and thermoprobe within the part of the
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=MARS96D[08/06/2011 23:04:42]
Planetary Science
Additional
Information
Launch/Orbital
Penetrator
Mars 96 Penetrator
Telecommunications
Penetrator
Penetrator
96 Penetrator
Williams.
cylinder underground, and meteorology sensors, a
magnetometer, a television camera, and transmitter exposed
at the top. The experiments were to begin after landing. Data
was to be transmitted to the orbiter and then relayed to Earth.
The penetrators have an expected lifetime of 1 year.
Personnel
Name
Role
E-mail
Program
Scientist
Russian Academy of
Sciences
[email protected]
Dr. Alexander V.
Zakharov
Project
Scientist
Russian Academy of
Sciences
[email protected]
Mars 96 Orbiter
Mars Page
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Mars 96 Penetrator
Publications
NSSDC ID: MARS96E
Maps
New/Updated Data
Description
Facts in Brief
Russia
Mass: 45.0 kg
Funding Agency
(Russia)
Discipline
Mars 96 Penetrator
The two Mars 96 Penetrators were mounted on the bottom of
the orbiter near the propulsion system. The penetrators were
long thin cylinders, pointed at the bottom, or forebody, and with
a widened, funnel-shaped top. Instruments were contained
inside throughout the length of the cylinder. The scientific
objectives of the penetrator experiments were to obtain images
of the surface, study martian meteorology, examine the
physical, chemical, magnetic, and mechanical properties of the
martian regolith, including its water content, collect data on the
magnetic field, and record seismic activity.
After orbit insertion, adjustment to 300 km periapsis, and 7 to
28 days of orbital maneuvers, the orbiter would be properly
oriented and the first penetrator would be spun about its long
axis and released. When the penetrator had moved away from
the orbiter, its solid rocket motor was to ignite and put it into an
atmospheric entry trajectory. Entry would occur 21 to 22 hours
later. The penetrator was to enter the atmosphere at about 4.9
km/sec at an angle 10-14 degrees. The probe would first be
slowed aerodynamically, followed by inflation of a braking
device. The penetrator was to strike the surface at
approximately 80 m/s. The forebody would separate on impact
and can penetrate 5 to 6 meters into the ground, attached by
wires to the aftbody, the top of the aftbody remaining above the
surface. The plan called for the first penetrator to land near the
site of one of the surface stations, and the second to land at
least 90 degrees away. Both penetrators could have been
released on the same orbit.
The penetrator was equipped with instruments in both the
forebody and aftbody. The forebody held a seismometer,
accelerometer, thermoprobe, neutron detector, and an alphaproton-X-ray spectrometer. The aftbody contained a gammaray spectrometer and thermoprobe within the part of the
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=MARS96E[08/06/2011 23:05:06]
Planetary Science
Additional
Information
Launch/Orbital
Penetrator
Mars 96 Penetrator
Telecommunications
Penetrator
Penetrator
96 Penetrator
Williams.
cylinder underground, and meteorology sensors, a
magnetometer, a television camera, and transmitter exposed
at the top. The experiments were to begin after landing. Data
was to be transmitted to the orbiter and then relayed to Earth.
The penetrators have an expected lifetime of 1 year.
Personnel
Name
Role
E-mail
Program
Scientist
Russian Academy of
Sciences
[email protected]
Dr. Alexander V.
Zakharov
Project
Scientist
Russian Academy of
Sciences
[email protected]
Mars 96 Orbiter
Mars Page
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=MARS96E[08/06/2011 23:05:06]
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Publications
NSSDC ID: MARS96B
Maps
New/Updated Data
Description
Facts in Brief
Russia
Mass: 8.0 kg
were to be released.
Funding Agency
(Russia)
Discipline
Planetary Science
The small station was contained inside a cylindrical aeroshell
approximately 1 meter in diameter and 1 meter high with a
mass of 25.5 kg for a total mass (station plus aeroshell) of 33.5
kg. Each station was to enter the atmosphere at a velocity of
less than 5.75 km/s at an entry angle between 10.5 and 20.5
degrees and an entry azimuth between 115 and 145 degrees.
The aeroshells were to be shed before landing and parachutes
will be used to slow the descent. On landing the station
covering would open into four triangular petals which extending
approximately 30 cm from the central base.
The primary landing sites were 41.31 N, 153.77 W and 32.48
N, 169.32 W, with a backup site at 3.65 N, 193 W. Landing
dispersion was to be 10 degrees along track and 2 degrees
across track. All sites are in the Arcadia Planitia region in the
northern hemisphere of Mars.
The station was to study the vertical structure of the
atmosphere and take images during its descent. On the
surface it would have a meteorology station mounted
approximately 1 meter above the base of the station to study
diurnal, seasonal, and annual variations in the atmosphere. A
magnetometer would have extended from one of the petals to
measure the planet's surface magnetic field and its variation
with time. A seismometer would collect data on the seismic
environment. An Alpha-Proton-X-Ray spectrometer would
extend from one petal and measure the elemental composition
of the surface. An oxidant sensor, extending from a third petal,
was to measure oxidant abundances. A panoramic camera is
mounted on a mast on the base of the station. The stations
were planned to have an active lifetime of about 700 days
(approximately 1 martian year) on the surface.
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=MARS96B[08/06/2011 23:05:34]
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Launch/Orbital
Surface Station
Surface Station
96 Surface Station
Williams.
The station was to be powered by two radio-isotope
thermogenerators (RTG's), a battery, and a secondary power
source. The surface station was equipped with a transmitter to
radio data back to the orbiter for return to Earth, and a receiver
to download commands from Earth via the orbiter.
Personnel
Name
Role
E-mail
Program
Scientist
Russian Academy of
Sciences
[email protected]
Dr. Alexander V.
Zakharov
Project
Scientist
Russian Academy of
Sciences
[email protected]
Mars 96 Orbiter
Mars 96 Penetrator
Mars Page
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Publications
NSSDC ID: MARS96C
Maps
New/Updated Data
Description
Facts in Brief
Russia
Mass: 8.0 kg
were to be released.
Funding Agency
(Russia)
Discipline
Planetary Science
The small station was contained inside a cylindrical aeroshell
approximately 1 meter in diameter and 1 meter high with a
mass of 25.5 kg for a total mass (station plus aeroshell) of 33.5
kg. Each station was to enter the atmosphere at a velocity of
less than 5.75 km/s at an entry angle between 10.5 and 20.5
degrees and an entry azimuth between 115 and 145 degrees.
The aeroshells were to be shed before landing and parachutes
will be used to slow the descent. On landing the station
covering would open into four triangular petals which extending
approximately 30 cm from the central base.
The primary landing sites were 41.31 N, 153.77 W and 32.48
N, 169.32 W, with a backup site at 3.65 N, 193 W. Landing
dispersion was to be 10 degrees along track and 2 degrees
across track. All sites are in the Arcadia Planitia region in the
northern hemisphere of Mars.
The station was to study the vertical structure of the
atmosphere and take images during its descent. On the
surface it would have a meteorology station mounted
approximately 1 meter above the base of the station to study
diurnal, seasonal, and annual variations in the atmosphere. A
magnetometer would have extended from one of the petals to
measure the planet's surface magnetic field and its variation
with time. A seismometer would collect data on the seismic
environment. An Alpha-Proton-X-Ray spectrometer would
extend from one petal and measure the elemental composition
of the surface. An oxidant sensor, extending from a third petal,
was to measure oxidant abundances. A panoramic camera is
mounted on a mast on the base of the station. The stations
were planned to have an active lifetime of about 700 days
(approximately 1 martian year) on the surface.
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=MARS96C[08/06/2011 23:06:22]
Additional
Information
Launch/Orbital
Surface Station
Telecommunications
Surface Station
Surface Station
96 Surface Station
Williams.
The station was to be powered by two radio-isotope
thermogenerators (RTG's), a battery, and a secondary power
source. The surface station was equipped with a transmitter to
radio data back to the orbiter for return to Earth, and a receiver
to download commands from Earth via the orbiter.
Personnel
Name
Role
E-mail
Program
Scientist
Russian Academy of
Sciences
[email protected]
Dr. Alexander V.
Zakharov
Project
Scientist
Russian Academy of
Sciences
[email protected]
Mars 96 Orbiter
Mars 96 Penetrator
Mars Page
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Publications
NSSDC ID: 1996-062A
Maps
New/Updated Data
Description
The Mars Global Surveyor (MGS) orbited Mars over a seven
year period and collected data on the surface morphology,
topography, composition, gravity, atmospheric dynamics, and
magnetic field. This data will be used to investigate the surface
processes, geology, distribution of material, internal properties,
evolution of the magnetic field, and the weather and climate of
Mars.
Spacecraft and Subsystems
The spacecraft itself is a rectangular box approximately 1.17 x
1.17 x 1.7 meters in size, made up of two parts, the equipment
module and the propulsion module. All instruments except the
magnetometer are stored on the nadir equipment deck, on one
of the 1.17 x 1.17 meter surfaces. This is the top of the
equipment module, which is 0.735 m high. The main thruster
and propulsion tanks are on the opposite side from the
instruments, on the propulsion module, which is approximately
1 meter high. Two solar panels, each 3.5 x 1.9 m in size,
extend out from opposite sides of the craft. A 1.5 meter
diameter parabolic high gain dish antenna is mounted on an
adjacent side, and attached to a 2 meter boom, which is
extended for mapping operations so the antenna is held away
from the body of the spacecraft.
The spacecraft is three-axis stabilized with no scan platform.
The main 596 N thruster wil use hydrazine and N2O4
propellant. Control is through 12 4.45 N hydrazine thrusters,
mounted in four groups of three (two aft facing and one roll
control thruster). The initial propellant load was 216.5 kg of
hydrazine and 144 kg of N2O4. Four solar array panels (2
GaAs, 2 SI) provide 980 W of power to the spacecraft. Energy
is stored in two 20 Amp-hr nickel hydrogen batteries, and
supplied at 28 V DC. Temperature control is primarily passive
with multilayer insulation, thermal radiators, and louvers,
augmented by electrical heaters. Communications is achieved
via the deep space network using the high gain antenna and
two low gain antennas, one mounted on the high gain antenna
and one on the equipment module. Uplink is in the X-band,
downlink in the X and Ka bands. Minimum downlink rate is
21.33 kbps, 2 kbps engineering data downlink, and 10 bps
emergency downlink.
The instruments on the nadir equipment deck consist of a
camera, thermal emission spectrometer, laser altimeter, and a
radio transmission relay. A magnetometer/electron
reflectometer sensor is attached to the end of each solar
array, and an ultra-stable oscillator is used for tracking and
gravity determination. An 8086 processor is used for the
payload data subsystem, and 1750A processors for the
Alternate Names
MGS
24648
Facts in Brief
II 7925
Launch Site: Cape
Mass: 1030.5 kg
Nominal
Power: 980.0 W
Funding Agency
Discipline
Planetary Science
Additional
Information
Launch/Orbital
information for Mars
Global Surveyor
Telecommunications
Global Surveyor
Experiments on Mars
Global Surveyor
Global Surveyor
standard controls processor and the engineering data
formatter. Data is stored on four 0.75 Gb solid state recorders.
Williams.
Mission Profile
After launch on a Delta 7925 (a Delta II Lite launch vehicle with
nine strap-on solid-rocket boosters and a Star 48 (PAM-D)
third stage) and a 10 month cruise phase, the Mars Global
Surveyor was inserted into an elliptical capture orbit at 01:17
UT 12 September 1997. Over the next four months, it was
intended that aerobraking maneuvers and thrusters would be
used to lower the orbit to the final circular mapping orbit.
However, one of the solar panels failed to latch properly when
it was deployed and subsequently showed unexpected motion
and moved past its fully deployed position when aerobraking
began (thought to be due to the fracture of a damper arm and
subsequent structural damage). A new aerobraking schedule
was employed, which involved slower aerobraking putting less
pressure on the solar panels through April 1998, at which time
an 11.6 hour science phasing orbit with a 171 km periapsis
was achieved and aerobraking was halted. After a 5 month
hiatus, aerobraking was resumed on 23 September 1998.
Science observations were made periodically during these
maneuvers.
After aerobraking ended in February 1999, MGS was in a 118
minute circular polar science mapping orbit with an index
altitude of 378 km. The orbit is sun-synchronous (2 a.m./2
p.m.) and maps over the 2 p.m. crossing from south to north
(instead of north to south as originally planned). The orbit has
a 7 day near-repeat cycle so Mars will be mapped in 26 day
cycles. Science mapping began in mid-March 1999, which was
summer in the northern hemisphere on Mars. The primary
mission lasted one martian year (687 Earth days) through
January, 2001. An extended mission took place until April
2002, further extensions were added until contact with the
spacecraft was lost on 2 November 2006.
The Mars Global Surveyor mission cost about $154 million to
develop and build and $65 million to launch. Mission
operations and data analysis cost approximately $20
million/year.
Personnel
Name
Role
E-mail
Dr. Mary K.
Olsen
Program
Manager
NASA Headquarters
[email protected]
Dr. Arden L.
Albee
Project
Scientist
California Institute of
Technology
[email protected]
Mr. Glenn F.
Cunningham
Project
Manager
NASA Jet Propulsion
Laboratory
[email protected]
Ms. Patricia G.
Rogers
Program
Scientist
NASA Headquarters
Selected References
Albee, A. L., et al., Mars Global Surveyor mission: Overview and status, Science, 279, No.
5357, 1671-1672, Mar. 1998.
Albee, A. L., et al., Overview of the Mars Global Surveyor mission, J. Geophys. Res., 106, No.
E10, 23291-23316, Oct. 2001.
Mars Global Surveyor NSSDC Home Page
Mars Home Page
Mars Fact Sheet
Mars Global Surveyor Sampler CD-ROM
Preliminary Report on Loss of MGS Released
Science Press Releases
Mars Global Surveyor Project Home Page
Mars Pathfinder Mission Information
Viking Mission Information
DESCRIPCIÓN:
Esta misión ha sido la primera en 20 años en llegar con éxito al planeta rojo. Durante su primer
año y medio se dedicó a la fase de aerofrenado consistente en ir adquiriendo la órbita definitiva
a base de pasar por las capas superiores de la atmósfera marciana y así ir frenando su
velocidad hasta conseguir una órbita adecuada. Este periodo fue más largo de lo previsto para
no dañar los paneles solares en exceso. Ahora sigue una órbita polar cercana a la superficie y
desde allí nos manda las fotos con mayor resolución de la exploración de Marte y nos ha
mandado más datos que todas las misiones anteriores juntas.
FECHAS PRINCIPALES:
Lanzamiento: 7 noviembre 1.996
Llegada Marte: 12 septiembre 1.997
Comienzo misión primaria: marzo 1.999
Comienzo misión extendida: enero 2.001
Camino recorrido y fases de la misión
LA NAVE: Tiene forma de caja de 1.7x1.17x1.17 metros con 2 partes bien diferenciadas, una
para los instrumentos y otra para la propulsión. Los paneles solares tienen una envergadura de
3.5x1.9 metros y proporcionan 980W de potencia para los instrumentos. La parabólica tiene un
diámetro de 1.5 metros y un brazo extensible de 2 metros.
INSTRUMENTOS:
Vista frontal de los instrumentos
Vista posterior del resto de equipos.
- Mars Orbital Camera (MOC): Es la encargada de tomar las imágenes de alta resolución del
planeta así como otras de menor calidad para tener una visión general de la atmósfera y el
clima en todo el planeta.
- Thermal Emission Spectrometer (TES):Es un interferómetro que mide la cantidad de luz
infrarroja emitida por la superficie de Marte.
- Mars Orbital Laser Altimeter (MOLA):Su misión es construir un mapa topográfico de Marte con
un rayo laser lanzado a la superficie.
- Radio Science Investigations (RS):Mide las variaciones de la señal enviada desde la Tierra
para medir las desviaciones gravitatorias.
- Magnetic Fields Investigation (MAG/ER):Magnetómetro dedicado al estudio del campo
magnético de Marte y su intensidad.
- Mars Relay:Antena de apoyo a otras misiones de la NASA, Japón y la ESA.
ORGANISMOS:
La misión está financiada por la NASA y será controlada desde el JPL y por Lockheed Martin
Astronautics.
La cámara MOC está controlada por Malin Space Science Systems (MSSS
NSSDC Master
Catalog Search
Spacecraft
Experiments
Data Collections
Personnel
Mars Pathfinder
Publications
NSSDC ID: 1996-068A
Maps
New/Updated Data
Mars Pathfinder
Description
The Mars Pathfinder was the second of NASA's low-cost
planetary Discovery missions to be launched. The mission
consists of a stationary lander and a surface rover. The
mission had the primary objective of demonstrating the
feasibility of low-cost landings on and exploration of the
Martian surface. This objective was met by tests of
communications between the rover and lander, and the lander
and Earth, tests of the imaging devices and sensors, and tests
of the maneuverability and systems of the rover on the
surface. The scientific objectives include atmospheric entry
science, long-range and close-up surface imaging, rock and
soil composition and material properties experiments, and
meteorology, with the general objective being to characterize
the Martian environment for further exploration. (Mars
Pathfinder was formerly known as the Mars Environmental
Survey (MESUR) Pathfinder.)
Mars Pathfinder was launched on a Delta 7925 (a Delta II Lite
launch vehicle with nine strap-on solid-rocket boosters and a
Star 48 (PAM-D) third stage) at 6:58:00 UT (1:58 a.m. EST) on
4 December 1996. The spacecraft entered the Martian
atmosphere on 4 July 1997 directly from its approach
hyperbola at about 7300 m/s without going into orbit around
the planet. The cruise stage was jettisoned 30 minutes before
atmospheric entry. The lander took atmospheric
measurements as it descended. The entry vehicle's heat shield
slowed the craft to 400 m/s in about 160 seconds. A 12.5
meter parachute was deployed at this time, slowing the craft to
about 70 m/s. The heat shield was released 20 seconds after
parachute deployment, and the bridle, a 20 meter long braided
Kevlar tether, deployed below the spacecraft. The lander
separated from the backshell and slid down to the bottom of
the bridle over about 25 seconds. At an altitude of about 1.6
km, the radar altimeter acquired the ground, and about 10
seconds before landing four air bags inflated in about 0.3
seconds forming a 5.2 meter diameter protective 'ball' around
the lander. Four seconds later at an altitude of 98 m the three
solid rockets, mounted in the backshell, fired to slow the
descent, and about 2 seconds later the bridle was cut 21.5 m
above the ground, releasing the airbag-encased lander. The
lander dropped to the ground in 3.8 seconds and impacted at
16:56:55 UT (12:56:55 p.m. EDT) on 4 July 1997 at a velocity
of 18 m/s - approximately 14 m/s vertical and 12 m/s horizontal
- and bounced about 12 meters (40 feet) into the air, bouncing
at least another 15 times and rolling before coming to rest
approximately 2.5 minutes after impact and about 1 km from
the initial impact site.
After landing, the airbags deflated and were retracted.
Alternate Names
MESUR Pathfinder
Carl Sagan Memorial
Station
Pathfinder
24667
Facts in Brief
II 7925
Launch Site: Cape
Mass: 463.0 kg
Funding Agency
Discipline
Planetary Science
Additional
Information
Launch/Orbital
Pathfinder
Mars Pathfinder
Telecommunications
Pathfinder
Experiments on Mars
Pathfinder
Pathfinder
Pathfinder opened its three metallic triangular solar panels
(petals) 87 minutes after landing. The lander first transmitted
the engineering and atmospheric science data collected during
entry and landing, the first signal being received at Earth at
18:34 UT (2:34 p.m. EDT). The imaging system obtained
views of the rover and immediate surroundings and a
panoramic view of the landing area and transmitted it to Earth
at 23:30 UT. After some maneuvers to clear an airbag out of
the way, ramps were deployed and the rover, stowed against
one of the petals, rolled onto the surface on 6 July at about
05:40 UT (1:40 a.m. EDT).
Williams.
The bulk of the lander's task was to support the rover by
imaging rover operations and relaying data from the rover to
Earth. The lander was also equipped with a meteorology
station. Over 2.5 meters of solar cells on the lander petals, in
combination with rechargeable batteries, powered the lander.
The lander on-board computer is based on 32-bit architecture
with 4 million bytes of static random access memory and 64
million bytes of mass memory for storing images. The main
lander components are held in a tetrahedral shaped unit in the
center of the three petals, with three low-gain antennas
extending from three corners of the box and a camera
extending up from the center on a 0.8 meter high pop-up mast.
Images were taken and experiments performed by the lander
and rover until 27 September 1997 when communications
were lost for unknown reasons.
The landing site in the Ares Vallis region of Mars is at 19.33 N,
33.55 W. The lander has been named the Sagan Memorial
Station. The Ares Vallis region of Mars is a large outwash plain
near Chryse Planitia. This region is one of the largest outflow
channels on Mars, the result of a huge flood (possibly an
amount of water equivalent to the volume of all five Great
Lakes) over a short period of time flowing into the martian
northern lowlands.
The Mars Pathfinder mission cost approximately $265 million
including launch and operations. Development and
construction of the lander cost $150 million and the rover
about $25 million.
Personnel
Name
Role
E-mail
Dr. Mark A.
Saunders
Project
Manager
NASA Headquarters
Dr. Matthew
Golombek
Project
Scientist
NASA Jet Propulsion
Laboratory
[email protected]
Dr. Joseph M.
Boyce
Program
Scientist
NASA Headquarters
[email protected]
Mr. Anthony J.
Spear
Project
Manager
NASA Jet Propulsion
Laboratory
[email protected]
Mr. Donald T.
Ketterer
Program
Manager
NASA Headquarters
[email protected]
Selected References
Golombek, M. P., The Mars Pathfinder mission, J. Geophys. Res., 102, No. E2, 3953-3965,
Feb. 1997.
Golombek, M. P., et al., Overview of the Mars Pathfinder Mission: Launch through landing,
surface operations, data sets, and science results, J. Geophys. Res., 104, No. E4, 8523-8553,
Apr. 1999.
Mars Pathfinder Page
Mars Pathfinder Rover - NSSDC Master Catalog.
Mars Pathfinder Flight Status Report
Information on the entry and landing strategy
Information on the landing site
Information on post-landing itinerary - operations and image availability
Mars Pathfinder Project Home Page
Mars Fact Sheet
Mars Home Page
Mars Pathfinder
La sonda Mars Pathfinder fue la segunda misión del programa Discovery de la NASA, una
iniciativa para la exploración del Sistema Solar con desarrollos cortos del proyectos y bajo
coste. Esta misión fue dirigida por el JPL de la NASA y su objetivo principal era la realización
de una demostración de tecnologías y conceptos clave que serían usados en futuras misiones
a Marte empleando aterrizadores.
INTRODUCCIÓN
Además la misión llevaba instrumentos científicos hasta la superficie del planeta rojo para
investigar la estructura de la atmósfera marciana, la meteorología, la geología y la composición
elemental de las rocas y el suelo. Por último un rover llamado Sojourner sería desplegado para
realizar experimentos tecnológicos y para estudiar las rocas del entorno, convirtiéndose en el
primer rover marciano de la historia.
Lanzamiento de la misión Pathfinder
LANZAMIENTO Y VIAJE
La nave de crucero fue lanzada en un cohete Delta II - 7925 que llevaba acoplado una etapa
superior PAM-D (Payload Assist Module), desde Cabo Cañaveral (Torre 17B) en una ventana
de lanzamiento de 29 días que comenzaba el 2 de diciembre de 1.996. La nave salió disparada
al espacio el 4 de diciembre de 1.996 a las 06:58 GMT. Tras el lanzamiento la nave requiere
unos 7 meses de viaje de crucero para llegar a Marte. En esta fase se programaron 4
maniobras de corrección de trayectoria (TCM) para ajustar el recorrido de la etapa de crucero
de la sonda los días 10 de enero, 3 de febrero, 6 de mayo y 25 de junio. El seguimiento, la
telemetría y los comandos son enviados usando las antenas de la Deep Space Network de la
NASA.
Etapa de crucero con el aterrizador en su interior
El objetivo para la nave era entrar en la atmósfera marciana, desplegar un paracaidas de
frenado que la llevara hasta cerca de la superficie de Marte. Allí unos retro-cohetes y varios
airbags protegerían al aterrizador del impacto contra el suelo. Tras esto comenzaría la fase
primaria de toma de datos con una duración estimada de 30 días marcianos o soles. Además el
microrover debía moverse por la superficie al menos durante 7 soles. Si pasado este periodo
ambos funcionaran correctamente, la NASA ampliaría la misión del aterrizador hasta 1 año y la
del microrover durante un mes.
LUGAR DE ATERRIZAJE
El lugar de aterrizaje de Pathfinder pasó una serie de rigurosos estudios de ingeniería para
determinar la seguridad del lugar: suficiente luz solar, pendientes aceptables, poca rugosidad
del suelo, baja elevación del polvo para tener la suficiente densidad atmosférica, poco potencial
para tormentas, etc. Además debía proporcionar un buen retorno de datos científicos.
Finalmente se seleccionó un lugar cerca de la boca de un canal donde se produjo un
desbordamiento catastrófico en el pasado en Ares Vallis y que además permitía tener rocas de
diferentes tipos en el mismo lugar. Aunque era imposible saber durante la misión el lugar de
procedencia de cada roca, el uso de los datos de los orbitadores posteriores pudo ser usado
para determinar el camino que siguieron la rocas estudiadas por Pathfinder. La zona de
aterrizaje para la nave tenía forma de elipse con una dimensiones de 200 x 70 kilómetros.
Elipse de aterrizaje en Ares Vallis. 19,33º N y 33,55º O
ENTRADA, DESCENSO Y ATERRIZAJE
La etapa de entrada, descenso y aterrizaje (EDL) para Mars Pathfinder comenzó varios días
antes de la llegada a Marte cuando los controladores del JPL enviaron comandos a la nave
para decirle cuando y como debía ejecutar las complejas maniobras de la secuencia para llegar
a la superficie marciana de una pieza. Este proceso se repite hasta unas horas antes de la
llegada para aumentar la precisión del recorrido y los datos enviados, ya que la gravedad
marciana sólo es perceptible para la nave las 48 horas previas a la llegada.
Desde una hora y media antes del aterrizaje hasta 3 horas y media después, la nave está bajo
el control del programa autónomo de abordo que dirige los eventos que ocurrirán. La primera
tarea de la nave es hacer circular el líquido de enfriamiento por toda la nave unos 90 minutos
antes de la llegada. Este fluido circuló por el perímetro de la etapa de crucero y dentro del
aterrizador para mantener los fríos durante los 7 meses de la etapa de crucero. Con su misión
cumplida, la etapa de crucero es expulsada media hora antes de la llegada a 8.500 kilómetros
de la superficie de Marte. Esta etapa de crucero usaba como combustible para la propulsión
hidrazina monopropelante, que hacía funcionar 8 toberas de 4,4 N y proporcionando un delta-V
(diferencia de velocidad) de 130 m/s.
Algunos minutos antes de la llegada, la nave comienza a sentir las capas exteriores de la
atmósfera a unos 125 kilómetros de altura y quedando ya tan sólo 4 minutos para llegar al
suelo. Con el giro estabilizado a 2 revoluciones por minuto y a 7,5 km/s de velocidad, la nave
entra en la atmósfera con un ángulo de 14,8º. El escudo térmico derivado de los Viking protege
la nave del intenso calor de la reentrada. En el momento de máximo calor, el escudo absorbe
más de 100 megavatios de energía termal, de tal manera que la nave baja su velocidad hasta
los 400 m/s. La deceleración es superior a los 20 G's y es detectada por los acelerómetros de
abordo, lo que provoca que una secuencia de eventos programados comience a funcionar en
una rápida sucesión.
Fase completa de entrada y descenso (EDL)
El despliegue del paracaidas de 7,5 metros ocurre a los 2 minutos y medio tras la entrada
atmosférica a una altura de entre 5 y 11 kilómetros de la superficie bajando la velocidad hasta
los 65 m/s. El escudo térmico es separado pirotécnicamente unos 20 segundos más tarde y
cae desde una altura entre los 2 y los 9 kilómetros. El aterrizador comienza a separarse del
escudo trasero descendiendo en una cuerda de Kevlar de 20 metros de longitud, lo que deja
espacio para el inflado de los airbags, una distancia prudente para el encendido de los motores
y una estabilidad adicional. Una vez que el aterrizador está en posición se activa el radar
altímetro y ayuda en la secuencia de eventos que llegan a continuación (inflado de airbags,
encendido de motores del escudo trasero y corte del cable de Kevlar).
El radar del aterrizador comenzará a detectar la superficie unos 32 segundos antes del
aterrizaje a una altura de 1,5 kilómetros. Los airbags se inflan 8 segundos antes del aterrizaje a
300 metros de altura. Los airbags tienen dos dispositivos explosivos, el primero de los cuales
corta los cables y libera las bolsas para que puedan ser infladas. El segundo explosivo se
enciende 0,25 segundos después y 4 segundos antes de que se enciendan los cohetes, para
activar tres generadores de gas que inflan en 0,3 segundos las tres bolsas de 5,2 metros de
diámetro a una presión de poco menos de 1 psi.
Primeras etapas de la entrada
El escudo cónico trasero sobre el aterrizador contiene los tres motores de combustible sólido
que provocan una fuerza de una tonelada durante dos segundos. El ordenador enciende los
motores por unos instantes a una altura de entre 80 y 100 metros del suelo, para que la
velocidad sea nula a una altura de 12 metros de la superficie. En ese instante se corta el cable
de tal forma que el escudo junto con el paracaidas es lanzado lejos de la zona y el aterrizador
envuelto en los airbags cae al suelo. El último impulso de los cohetes debería provocar una
gran velocidad lateral al aterrizador, de hasta 25 m/s y un ángulo de 30º para evitar que el
paracaidas y el escudo le caigan encima. Tras esto el aterrizador comenzará a botar hasta a 12
metros de altura y recorriendo más de 100 metros entre los botes.
Los retrocohetes frenan la caída y se suelta el airbag que comienza a botar
Tras pararse en la superficie, se activan dispositivos pirotécnicos en los pétalos para que
puedan ser abiertos y permitan al aterrizador que comienze su actividad. El aterrizaje ocurrió
sobre las 03:00 de la hora local marciana, las 17:07:25 GMT del viernes 4 de julio de 1.997.
RETRO-COHETES
Los motores de Pathfinder eran esenciales para un aterrizaje seguro. Al ser la atmósfera
marciana tan delgada, el paracaidas no podría frenar lo suficiente la nave para evitar que se
estrellara. Sin estos cohetes la velocidad de impacto contra el suelo habría sido de 62 m/s y los
airbags hubieran reventados junto con la nave. Construidos por la empresa Thiokol, los cohetes
apenas tienen una longitud de 90 centímetros pero poseen una gran potencia. De esta forma,
en tan sólo 2,4 segundos eran capaces de frenar el descenso y dejar a Pathfinder sin velocidad
de caída Durante el instante que son encendidos, podrían generar la suficiente electricidad
como para abastecer a una localidad de 15.000 personas. Los gases expulsados llegan a una
temperatura de 3.000º C (la mitad de la temperatura de la superficie solar) y una velocidad de
2,6 km/s (10 veces más rápido que un avión de pasajeros). Los tres cohetes son anclados en
un estructura que va insertada en el escudo trasero.
Un test de los retrocohetes
RETRACCIÓN DE LOS AIRBAGS Y ORIENTACIÓN DEL ROVER
Una vez que Mars Pathfinder ha aterrizado en la superficie, se activan los sistemas
pirotécnicos en los petalos del aterrizador, de tal manera que permitan su apertura. Las juntas
que unen los pétalos laterales son necesarias debido a las fuerzas ejercidas en los pétalos del
aterrizador por el sistema de airbags desplegado.
En paralelo con la apertura de los pétalos, un sistema de retracción comenzará a recoger los
airbags hacia el aterrizador, practicando una apertura en el lateral de cada bolsa para facilitar el
proceso de desinflado a través de un filtro. Los airbags son traídos hacia los pétalos por cables
internos que se extienden por las uniones entre los airbags y las pequeñas aberturas en cada
una de las caras del aterrizador. El proceso dura unos 64 minutos en desinflar y retraer
completamente los airbags.
Hay un motor de giro en cada una de las bisagras de los 3 pétalos. Si el lander aterriza sobre
uno de los laterales, será colocado en la posición correcta por la apertura de un pétalo lateral
con un motor que colocará el aterrizador en posición vertical. Una vez colocado correctamente
se abren los otros dos pétalos.
El proceso de retraer los airbags y desplegar los pétalos del aterrizador dura unas 3 horas en
total. Mientras tanto el sistema de radio en banda X del aterrizador es desconectado por
primera vez desde el lanzamiento el 4 de diciembre de 1.996. Esto ahorra baterías y permite al
sistema electrónico enfriarse tras haberse calentado durante la entrada al no disponer de
sistema de enfriamiento. Tras este periodo la Tierra ya es visible bien alta sobre el horizonte y
estará en buena posición para comunicarse con el aterrizador a través de la antena de baja
ganancia a última hora de la mañana.
LA NAVE. EL ATERRIZADOR Y EL ROVER.
El rover Sojourner
La masa total del microrover era de 11,5 kilogramos incluyendo el mecanismo de despliegue
del APXS y el propio instrumento. Otros 6 kilogramos están situados en el aterrizador como
parte del sistema de comunicaciones UHF con el rover, los sistemas de despliegue y de
soporte estructural durante el viaje. La altura es de 28 centímetros con una elevación inferior de
13 centímetros sobre el suelo. El espacio dentro del aterrizador para el rover era de tan sólo 20
centímetros por lo que debía viajar con las ruedas plegadas con una altura de tan sólo 18
centímetros. Su longitud total es de 63 centímetros y su anchura de 48 cm.
Esquema del rover. Imagen: Wikipedia
Todo el rover es un experimento de tecnología en si mismo, para determinar el rendimiento de
los microrovers en el por entonces poco conocido terreno marciano, de forma que permita a las
siguientes generaciones de rovers una navegación y movimiento más efectivo en Marte.
El rover Sojourner
Tiene tres objetivos principales:
1.
Experimentos tecnológicos
2.
Experimentos de ciencia con el rover
3.
Experimentos de la misión del lander
El rover tenía libertad de movimientos respecto al aterrizador y tenía un sistema básico de
navegación autónoma usando dos lásers para la detección de obstáculos. Para desplazarse
contaba con 6 ruedas autónomas y un sistema de suspensión que permitía sortear pequeñas
rocas, viajando a una velocidad máxima de 1 centímetro por segundo. Los datos los enviaba y
recibía a través de una antena UHF que conectaba con el aterrizador.
Su carga científica constaba de:
- Cámara fotográfica trasera a color y doble cámara delantera para imágenes en 3D
- Mecanismo de despliegue del APXS
- Espectrómetro APXS
Para funcionar portaba sobre él un panel solar de 0,25 m2 que proporcionaba un pico de
energía de 16 W-hora y una batería con capacidad para 50 W-hora. La temperatura era
mantenida en unos límites aceptables gracias a 3 calentadores de radio-isótopos o RHU. El
ordenador era un 80C85, con 0,1 MIPS y 0,5 MB de RAM para almacenar datos, todo ello con
un peso de 500 gramos y un consumo de 1,5 W. Debido a las limitaciones energéticas, el rover
podía funcionar entre las 10 de la mañana y las 2 de la tarde (4 horas en total), de cada sol.
El aterrizador. Carl Sagan Memorial Station.
La masa total del conjunto de la misión en el lanzamiento era de 890 kilogramos incluyendo el
combustible para el viaje. La masa de entrada en la atmósfera del planeta (sin el módulo de
crucero) era de 570 kilogramos y la masa del aterrizador era de 360 kilogramos, incluyendo
airbags, paneles y rover.
Los objetivos de la Estación Aterrizadora eran varios:
- Permitir al rover llegar hasta la superficie mediante dos rampas de descenso.
- Recibir los datos del rover para reenviarlos a la Tierra y enviarle al rover las órdenes de los
controladores.
- Obtener datos científicos con la estación meteorológica y las cámaras del mástil.
El ordenador del aterrizador era un R6000 con un bus VME, con 22 millones de instrucciones
por segundo (MIPS) y 128 MB de memoria de almacenamiento. El aterrizador estaba
alimentado por paneles solares y las comunicaciones de telemetría se enviaban por la antena
de Alta Ganancia (HGA) de banda-X a un ritmo de 6 kb/s a las antenas de 70 metros de la
DSN. Para los comandos de operaciones en superficie se usaba la HGA a un ritmo de 250 b/s.
Esquema del aterrizador rebautizado 'Carl Sagan Memorial Station'. Imagen: Wikipedia
Realización de pruebas de movimiento y comunicaciones en el aterrizador y el rover
El mástil, las antenas y las cámaras
SISTEMA DE TELECOMUNICACIONES DEL ROVER
El sistema de telecomunicaciones del rover es un sistema en dos direcciones en UHF entre el
lander y el rover, usado para enviar comandos desde la Tierra al rover y recibir los datos e
imágenes obtenidas. Debido a que el alcance es similar al de un walkie-talkie no es posible la
comunicación directa con el rover. Todas las comunicaciones del rover se realizan con la ayuda
del sistema de comunicaciones del aterrizador.
Está formado por dos radios UHF y dos antenas UHF. La radio está localizada dentro del WEB
(Warm Electronic Box) del rover, donde está protegida del frío extremo del ambiente marciano.
La radio está conectada a la antena usando un cable coaxial.
Enlaces de comunicación
SISTEMA ELÉCTRICO DEL ROVER
Panel Solar
Toda la energía del rover es proporcionada por un ligero panel solar colocado como un panel
plano en la parte superior del rover. El panel es una red de varios cientos de celdas solares
muy ligeras y frágiles. La producción al medio día es de unos 16 W, el equivalente a una luz de
un horno, pero que permite al rover realizar todas sus actividades científicas.
El panel solar antes de ser instalado
Baterías
Durante los momentos en los cuales hay muy poca luz solar o ninguna, el rover usaba la
electricidad almacenada en las baterías de forma moderada ya que si se descargan por
completo ya no hubieran podido ser cargadas de nuevo. Se utilizaron sobretodo para
experimentos nocturnos y operaciones a primera hora de la mañana, así como para los
chequeos de salud a los que fue sometido durante los 7 meses de crucero hasta la Tierra.
INSTRUMENTOS
La misión llevaba 3 instrumentos científicos entre el rover y la base:
· Cámara de Mars Pathfinder - Imager For Mars Pathfinder (IMP)
· Espectrómetro de Rayos-X Protones Alfa - Alpha Proton X-Ray Spectrometer (APXS) con un
Mecanismo de despliegue del APXS.
· Instrumentos de Estructura Atmosférica y Meteorología - Atmospheric Structure
Instrument/Meteorology Package (ASI/MET)
Imager For Mars Pathfinder (IMP)
La cámara IMP (Imager for Mars Pathfinder) es un sistema de obtención de imágenes en
estereo con la posibilidad añadida de captar imágenes en color usando filtros seleccionables en
cada una de dos cámaras de las que consta el instrumento. Fue desarrollado por la
Universidad de Arizona. El sistema está formado por la cabeza de la cámara (óptica estereo,
rueda de filtros, CCDs, preamplificadores y motores de movimiento), el mástil extensible con el
cableado y dos tarjetas electrónicas (tarjeta de los datos de CCD y tarjeta de los motores).
Tenía un peso de 5,2 kilogramos y gastaba 2,6 Watios.
La cámara IMP
Los movimientos en azimut y elevación para la cámara están proporcionados por motores de
paso que permiten un movimiento de ±180 grados en azimut y +83/-72 grados en elevación. La
cámara está situada en lo más alto del mástil desplegable con una elevación de un metro sobre
la superficie del lander. Las imágenes adquiridas son de 256x256 píxeles y es idéntica a la
cámara DISR de Huygens. Las dos ruedas llevaban cada una 12 filtros que eran combinados
de hasta 30 formas diferentes para obtener las imágenes para observar la atmósfera,
elementos geológicos o en estereo. Uno de los filtros era una lente que permitía algunos
aumentos para fotografiar imágenes de los imanes que acumulaban el polvo del viento durante
la misión y situados en la plataforma de la IMP.
Durante la misión se adquirieron varios panoramas completos de la zona de aterrizaje en color
y en estereo. Antes del despliegue del mástil se obtuvo un panorama de 360 grados para luego
comparar las distintas perspectivas a las dos alturas.
La cámara en el mástil desplegado
Usando las imágenes obtenidas por la cámara se llevaron a cabo investigaciones atmosféricas.
La opacidad de los aerosoles se mide realizando fotos del Sol en dos bandas estrechas con
dos filtros distintos. Las partículas de polvo en la atmósfera se caracterizaron observando
Phobos durante la noche. Además se estudió la abundancia de vapor de agua en la atmósfera
con imágenes del Sol en varios filtros en la banda de absorción del agua. Durante algunos
soles se fotografiaron los sensores de viento a varias alturas para conocer su dirección y
velocidad.
Otra parte de las investigaciones estuvo centrada en las propiedades magnéticas del polvo
marciano. Se colocaron imanes de diferente fuerza en una placa acoplada al aterrizador y
durante la misión se obtuvieron imágenes para determinar la acumulación de los componentes
magnéticos llevados por el polvo marciano. Además las imágenes se obtuvieron con varios
filtros para diferenciar los diversos minerales encontrados. Las observaciones también se
centraron en un objetivo de referencia para la calibración de las imágenes que portaba un
pequeño sensor de viento.
Alpha Proton X-Ray Spectrometer
Este instrumento es un derivado directo de los espectrómetros de rayos X que volaron en las
misiones rusas Vega y Phobos y es idéntico al que fue usado en la misión Mars 96. Con la
movilidad proporcionada por el rover y el sistema de despliegue, el espectrómetro APX no sólo
adquirió el espectro del polvo marciano, sino que por primera vez permitió el análisis de
distintas rocas de la superficie marciana. El espectrómetro alfa y de protones ha sido
proporcionado por el Instituto Max Planck de Alemania y el de rayos X por la Universidad de
Chicago. Pesaba 0,74 kilogramos y gastaba 0,8 W.
El APXS en el frontal del rover
El instrumento permite conocer la composición elemental de los materiales de las rocas y el
suelo utilizando para ello una fuente radiactiva de partículas alfa y detectores de estas
partículas, de protones y rayos X que analizaron la energía del espectro devuelto por las
muestras. De esta manera se dedujo la composición química elemental de las rocas en todos
sus elementos menos el hidrógeno.
Sensores del instrumento
El sensor del APXS va montado externo al chasis del rover en un sistema desplegable. Este
sistema coloca al APXS en contacto con la roca y el suelo. El resto de la electrónica va en el
rover en un sistema de temperatura controlada.
APXS Deployment Mechanism
El sistema de despliegue soporta al APXS bajo las condiciones del lanzamiento y aterrizaje y
proporciona los medios necesarios para colocar al APXS en su objetivo con un solo
movimiento. El mecanismo es lo bastante flexible como para permitir la colocación del APXS a
diversas alturas y orientaciones. Varios mecanismos de contacto en el anillo frontal permiten al
rover saber que el aparato se encuentra ya bien posicionado, terminando los movimientos del
mecanismo.
El mini-brazo con el APXS en el extremo
Atmospheric Structure Instrument/Meterology Package
El ASI/MET es un subsistema de ingeniería que adquiere información atmosférica durante el
descenso del aterrizador a través de la atmósfera y durante la misión. Está diseñado por el JPL
de sistemas heredados de las misiones Viking. Los datos adquiridos durante la entrada y
descenso permitieron la reconstrucción de perfiles de densidad atmosférica, temperatura y
presión desde los 100 kilómetros de altura hasta la superficie. Pesaba 2 kilogramos y gastaba
3,2 W.
El ASI consiste en un acelerómetro con sensores en los 3 ejes que permiten conocer los
movimientos y fuerzas de aceleración durante la entrada y los eventos del aterrizaje, hasta los
50 G's. Entre los instrumentos se encuentran sensores de temperatura, presión y viento, así
como la electrónica necesaria para los sensores y el tratamiento digital de los datos obtenidos.
La temperatura es medida por termopares montados en un mástil que se despliega tras el
aterrizaje. Uno de ellos permite conocer la temperatura durante el descenso y otros tres están
colocados a 25, 50 y 100 cm del suelo en la misión.
ASI/MET con los sensores de temperatura y viento
Tres sensores de viento están colocados a varias alturas del mástil para determinar las
velocidades y direcciones del viento en la zona de aterrizaje. Este sensor fue muy fotografiado
por la cámara IMP durante la misión. De esta manera es posible conocer la orientación de los
alerones para determinar la dirección y velocidad del viento a las 3 alturas, permitiendo la
obtención de perfiles verticales del viento.
NSSDC Master
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Publications
NSSDC ID: MESURPR
Maps
New/Updated Data
Description
The Mars Pathfinder was the second of NASA's low-cost
planetary Discovery missions to be launched. The mission
consists of a stationary lander and a surface rover. The
mission had the primary objective of demonstrating the
feasibility of low-cost landings on and exploration of the
Martian surface. This objective was met by tests of
communications between the rover and lander, and the lander
and Earth, tests of the imaging devices and sensors, and tests
of the maneuverability and systems of the rover on the
surface. The scientific objectives include atmospheric entry
science, long-range and close-up surface imaging, rock and
soil composition and material properties experiments, and
meteorology, with the general objective being to characterize
the Martian environment for further exploration. (Mars
Pathfinder was formerly known as the Mars Environmental
Survey (MESUR) Pathfinder.)
The rover, which has been named "Sojourner" is a six-wheeled
vehicle, 280 mm high, 630 mm long, and 480 mm wide with a
ground clearance of 130 mm, mounted on a "rocker-bogie"
suspension. The rover was stowed on the lander at a height of
180 mm. At deployment, the rover extended to its full height
and rolled down a deployment ramp at about 05:40 UT on 6
July 1997 (1:40 a.m. EDT). The rover was controlled by an
Earth-based operator who used images obtained by both the
rover and lander systems. Note that the time delay was
between 10 and 15 minutes depending on the relative position
of Earth and Mars over the course of the mission, requiring
some autonomous control, provided by a hazard avoidance
system on the rover. The on-board control system is an Intel
80C85 8-bit processor which runs about 100,000 instructions
per second. The computer is capable of compressing and
storing a single image on-board. The rover is powered by 0.2
square meters of solar cells, which will provide energy for
several hours of operations per sol (1 Martian day = 24.6 Earth
hours). Non-rechargeable lithium thionyl chloride (LiSOCl2) Dcell batteries provide backup. All rover communications were
done through the lander.
The rover is equipped with black and white and color imaging
systems which were used to image the lander in order to
assess its condition after touchdown. The goal was to acquire
three black and white images spaced 120 degrees apart of the
lander. Images of the surrounding terrain were also acquired
to study size and distribution of soils and rocks, as well as
locations of larger features. Imaging of the rover wheel tracks
will be used to estimate soil properties. Imaging of the rover by
the lander was also done to assess rover performance and soil
and site properties. The rover's performance was monitored to
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=MESURPR[08/06/2011 23:10:00]
Alternate Names
Rocky IV
MFEX
Microrover Flight
Experiment
MESUR Pathfinder Rover
Sojourner
Facts in Brief
II
Launch Site: Cape
Mass: 10.5 kg
Funding Agency
Discipline
Planetary Science
Additional
Information
Launch/Orbital
Pathfinder Rover
Telecommunications
Pathfinder Rover
Experiments on Mars
Pathfinder Rover
Pathfinder Rover
determine tracking capabilities, drive performance, thermal
behavior, and sensor performance. UHF Communications
between the rover and lander were studied to determine the
effectiveness of the link between the rover and lander.
Assessments of rock and soil mechanics will be made based
on abrasion of the wheels and adherence of dust. An alphaproton-X-ray spectrometer (APXS) is on-board the rover to
assess the composition of rocks and soil. Images of all
samples tested are transmitted to Earth. The primary
objectives were scheduled for the first seven sols, all within
about 10 meters of the lander. The extended mission included
slightly longer trips away from the lander, and even longer
journeys were planned. Images were taken and experiments
performed by the lander and rover until 27 September 1997
when communications were lost for unknown reasons.
Williams.
The landing site in the Ares Vallis region of Mars is at 19.33 N,
33.55 W. The lander has been named the Sagan Memorial
Station. The Ares Vallis region of Mars is a large outwash plain
near Chryse Planitia. This region is one of the largest outflow
channels on Mars, the result of a huge flood (possibly an
amount of water equivalent to the volume of all five Great
Lakes) over a short period of time flowing into the martian
northern lowlands.
The Mars Pathfinder mission cost approximately $265 million
including launch and operations. Development and
construction of the lander cost $150 million and the rover
about $25 million.
Personnel
Name
Role
E-mail
Dr. Mark A.
Saunders
Project
Manager
NASA Headquarters
Dr. Matthew
Golombek
Project
Scientist
NASA Jet Propulsion
Laboratory
[email protected]
Dr. Joseph M.
Boyce
Program
Scientist
NASA Headquarters
[email protected]
Mr. Anthony J.
Spear
Project
Manager
NASA Jet Propulsion
Laboratory
[email protected]
Mr. Donald T.
Ketterer
Project
Manager
NASA Headquarters
[email protected]
Selected References
The Rover Team, The Pathfinder microrover, J. Geophys. Res., 102, No. E2, 3989-4001, Feb.
1997.
Matijevic, J., Sojourner: The Mars Pathfinder microrover flight experiment, Space Technol., 17,
No. 3/4, 143-149, 1997.
Golombek, M. P., et al., Overview of the Mars Pathfinder Mission: Launch through landing,
surface operations, data sets, and science results, J. Geophys. Res., 104, No. E4, 8523-8553,
Apr. 1999.
Mars Pathfinder Page
Mars Pathfinder Lander - NSSDC Master Catalog.
Mars Pathfinder Flight Status Report
Information on the entry and landing strategy
Information on the landing site
Information on post-landing itinerary - operations and image availability
Mars Pathfinder Project Home Page
Mars Fact Sheet
Mars Home Page
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MEASAT 1
Publications
NSSDC ID: 1996-002B
Maps
New/Updated Data
Alternate Names
Description
MEASAT 1 was a Malaysian geostationary communications
spacecraft launched by an Ariane 44L rocket from the Kourou
Space Center in French Guiana. After parking at 91.5 E
longitude, the 1,450 kg spacecraft will provide communications
and direct-to-home television services to Malaysia and
neighboring countires through its 4 Ku-band and 12 C-band
transponders.
Malaysia East Asia Sat 1
23765
Facts in Brief
44L
French Guiana
Mass: 886.0 kg
Funding Agency
Binariang Sdn Bhd,
Malaysia (Malaysia)
Discipline
Communications
Additional
Information
Launch/Orbital
information for MEASAT
1
Experiments on MEASAT 1
MEASAT 1
Office.
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MEASAT 2
Publications
NSSDC ID: 1996-063B
Maps
New/Updated Data
Alternate Names
Description
MEASAT 2 (Malaysia East Asia Satellite 2) was a
geostationary communications satellite designed to provide 12
years of both direct-to-user television service in Malaysia and
general communications services in the region from Malaysia
to the Philippines and from Beijing to Indonesia. It had 11
active transponders in Ku-band (uplink 13.75 - 14.45 GHz,
downlink 10.960-11.700 GHz). Eight of these used 95-watt
traveling-wave amplifiers, and three had 62 watts. There were
also six active transponders in C-band (uplink 5.925-6.425
GHz, downlink 3.700-4.200 GHz), powered by 12-watt solidstate amplifiers. It was located at 148 degrees E.
Malaysia East Asia Sat 2
24653
Facts in Brief
44L
French Guiana
Mass: 886.0 kg
Funding Agency
Binariang Sdn Bhd,
Malaysia (Malaysia)
Discipline
Communications
Additional
Information
Launch/Orbital
information for MEASAT
2
Experiments on MEASAT 2
MEASAT 2
Office.
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Microsat
Publications
NSSDC ID: 1996-050A
Maps
New/Updated Data
Alternate Names
Description
MICROSAT, also known as MuSat, is an Argentine 33 kg
microsatellite that was launched by a Molniya-M booster from
Plesetsk cosmodrome at 05:22 UT. It carries instruments to
photograph natural resources.
MuSat
24291
Facts in Brief
Launch
Vehicle: Molniya-M
Russia
Mass: 33.0 kg
Funding Agency
Unknown (Argentina)
Discipline
Earth Science
Additional
Information
Launch/Orbital
information for Microsat
Experiments on Microsat
Microsat
Office.
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Molniya 1-89
Publications
NSSDC ID: 1996-045A
Maps
New/Updated Data
Alternate Names
Description
Molniya 1/89 was a first-generation Russian communications
satellite orbited to test and perfect a system of radio
communications and television broadcasting using earth
satellites as active transponders and to experiment with the
system in practical use. The basic function of the satellite was
to relay television programs and long-distance two-way
multichannel telephone, phototelephone, and telegraph links
from Moscow to the various standard ground receiving stations
in the 'Orbita' system. The satellite was in the form of a
hermetically sealed cylinder with conical ends -- one end
contained the orbital correcting engine and a system of
microjets, and the other end contained externally mounted
solar and earth sensors. Inside the cylinder were (1) a highsensitivity receiver and three 800-MHz 40-w transmitters (one
operational and two in reserve), (2) telemetering devices that
monitored equipment operation, (3) chemical batteries that
were constantly recharged by solar cells, and (4) an electronic
computer that controlled all equipment on board. Mounted
around the central cylinder were six large solar battery panels
and two directional, high-gain parabolic aerials, 180 deg apart.
One of the aerials was directed continually toward the earth by
the highly sensitive earth sensors. The second aerial was held
in reserve. Signals were transmitted in a fairly narrow beam
ensuring a strong reception at the earth's surface. The satellite
received telemetry at 1000 MHz. Television service was
provided in a frequency range of 3.4 to 4.1 GHz at 40 w.
Molniya 1/89, whose cylindrical body was 3.4 m long and 1.6 m
in diameter, was much heavier than corresponding U.S.
COMSATs, and it had about 10 times the power output of the
Early Bird COMSAT. In addition, it did not employ a
geosynchronous equatorial orbit as have most U.S. COMSATs
because such an orbit would not provide coverage for areas
north of 70 deg n latitude. Instead, the satellite was boosted
from a low-altitude parking orbit into a highly elliptical orbit with
two high apogees daily over the northern hemisphere -- one
over Russia and one over North America -- and relatively low
perigees over the southern hemisphere. During its apogee,
Molniya 1/89 remained relatively stationary with respect to the
earth below for nearly 8 of every 12 hr. By placing three or
more Molniya 1 satellites in this type of orbit, spacing them
suitably, and shifting their orbital planes relative to each other
by 120 deg, a 24-hr/day communication system could be
obtained.
Molniya 1T
24273
Facts in Brief
Launch
Vehicle: Molniya-M
Russia
Funding Agency
Unknown (Russia)
Discipline
Communications
Additional
Information
Launch/Orbital
information for Molniya 189
Experiments on Molniya 189
Molniya 1-89
Office.
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Molniya 3-48
Publications
NSSDC ID: 1996-060A
Maps
New/Updated Data
Alternate Names
Description
The Molniya-3 Russian communications satellites were used to
create the 'Orbita' communications system for northern
regions, with groups of four satellites. The first Molniya 3
spacecraft appeared in 1974, primarily to support civil
communications (domestic and international), with a slightly
enhanced electrical power system and a communications
payload of three 6/4 GHz transponders with power outputs of
40 W or 80 W. The land segment used a 12 m diameter
parabolic antenna, which was pointed automatically at the
satellite using autonomous electromechanical equipment. Later
versions were to be part of the YeSSS Unified Satellite
Communications System. Trials of this version began in the
1980's, with the system being accepted by the Russian military
in 1983-1985.
24640
Facts in Brief
Launch
Vehicle: Molniya-M
Russia
Funding Agency
Unknown (Russia)
Discipline
Communications
Additional
Information
Launch/Orbital
information for Molniya 348
Experiments on Molniya 348
Molniya 3-48
Office.
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MSAT 1
Publications
NSSDC ID: 1996-022A
Maps
New/Updated Data
Alternate Names
Description
M-SAT 1 was a Canadian geostationary mobile telephone
communications satellite launched by an Ariane 42P rocket
from the Kourou Space Center to serve the North American
continent. The spacecraft and its transponders are very similar
to those of the American AMSC 1. It had the capability to
support 2000 radio channels in L-band. The footprint covered
the entire continental US and Canada, as well as Alaska,
Hawaii, Puerto Rico, the Virgin Islands, and 200 mile of US
and Canadian coastal waters. It was one of the first satellites
to use Hughes' springback antennas, flexible 17-foot-by-22foot ovals made of graphite.
23846
Facts in Brief
42P
French Guiana
Funding Agency
TMI Communications and
Co. Ltd (Canada)
Discipline
Communications
Additional
Information
Launch/Orbital
information for MSAT 1
Experiments on MSAT 1
MSAT 1
Office.
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MSTI 3
Publications
NSSDC ID: 1996-031A
Maps
New/Updated Data
Description
MSTI 3 is the third satellite developed by the MSTI (Miniature
Sensor Technology Integration) Program within the US Air
Force. The satellite carries three sensors: a medium
wavelength infrared (MWIR) camera, a short wavelength
infrared (SWIR) camera, and a visible imaging spectrometer.
It's primary mission, to last for one year, is intended to gather
extensive background clutter statistics at medium wavelengths
in the infrared at sufficient resolution to resolve whether
tracking theater ballistic missiles (TBMs) in the coast phase
against a warm earth background is achievable. The visible
imaging spectrometer will gather environmental data of similar
quality to the Land-Remote Sensing Satellite to support
environmental and ecological studies.
Alternate Names
Miniature Sensor
Technology Integration 3
23868
Facts in Brief
Launch
Vehicle: Pegasus
Launch
United States
Mass: 175.0 kg
Funding Agency
Disciplines
Earth Science
Military
Additional
Information
Launch/Orbital
information for MSTI 3
Experiments on MSTI 3
Data collections from MSTI
3
Office.
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MSX
Publications
NSSDC ID: 1996-024A
Maps
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MSX
Description
The Midcourse Space Experiment (MSX) was a test project of
the Ballistic Missile Defense Organization (BMDO). Its primary
purpose was to gather data over a wide-wavelength interval to
demonstrate the feasibility of identifying and tracking ballistic
missiles during their midcourse flight phase. Its multispectral
instruments were capable of obtaining wide band and spectral
images in the range of ultraviolet to infrared wavelengths (110
nm to 28,000 nm). The instruments were also utilized for
civilian aeronomic and auroral studies.
The 5.1 m spacecraft consisted of three sections each of 1.5 m
x 1.5 m cross-section to house three payload components: an
electronics section, an 8.5 K frozen hydrogen section, and an
instruments section. The three instruments were: SPIRIT III
(Space Infrared Imaging Telescope), a five-color, high-spatial
resolution scanning radiometer and a six-channel, highspectral resolution, Fourier-transform spectrometer; UVISI
(Ultraviolet and Visible Imagers and Spectrographic Imagers),
five spectrographic imagers and four UV/visible imagers with
capabilities from the far ultraviolet through visible wavelengths;
and, Space-Based Visible (SBV), a visible band telescope with
a six-inch aperturn, a charge-coupled device, and image
processing electronics. Also on-board were the On-board
Signal and Data Processor (OSDP), which provided real-time
signal processing for target detection and tracking for data
generated by SPIRIT III, sensors for monitoring and measuring
instrument contamination and degradation of performance
largely due to outgassing, and a number of small (2.0 cm)
reference spheres, deployed as reference objects from MSX
for instrument calibration.
Alternate Names
Midcourse Space
eXperiment
23851
Facts in Brief
II
Launch
United States
Mass: 2700.0 kg
Nominal
Power: 1200.0 W
Funding Agencies
Department of DefenseDepartment of the Navy
(United States)
Air Force Ballistic Missile
Defense Organization
(United States)
Disciplines
Astronomy
Engineering
Earth Science
Planetary Science
Space Physics
Additional
Information
Launch/Orbital
information for MSX
MSX
Telecommunications
information for MSX
Experiments on MSX
Data collections from MSX
Bilitza.
Personnel
Name
Role
E-mail
Dr. John D. Mill
Project
Scientist
Environmental Research
Institute of Michigan(ERIM)
[email protected]
Dr. Max R.
Peterson
Program
Manager
Applied Physics Laboratory
[email protected]
Lcol Bruce D.
Guilmain,
USAF
Program
Manager
USAF Ballistic Missile
Defense Organization
[email protected]
Other Sources of MSX Information/Data
MSX information (Applied Physics Laboratory)
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N-Star-B
Publications
NSSDC ID: 1996-007A
Maps
New/Updated Data
Alternate Names
Description
N-Star-B as a Japanese geosynchronous spacecraft launched
by an Ariane rocket from the Kourou Space Center in French
Guiana. The 3,400 kg spacecraft is expected to provide voice
and TV broadcasts to Japan and neighboring regions.
23781
Facts in Brief
French Guiana
Mass: 3400.0 kg
Funding Agency
Unknown (Japan)
Discipline
Communications
Additional
Information
Launch/Orbital
information for N-Star-B
Experiments on N-Star-B
Data collections from NStar-B
Office.
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Navstar 2A-16
Publications
NSSDC ID: 1996-019A
Maps
New/Updated Data
Description
Global Positioning System (GPS) was developed by the US
Department of Defense to provide all-weather round-the-clock
navigation capabilities for military ground, sea, and air forces.
Since its implementation, GPS has also become an integral
asset in numerous civilian applications and industries around
the globe, including recreational used (e.g., boating, aircraft,
hiking), corporate vehicle fleet tracking, and surveying. GPS
employs 24 spacecraft in 20,200 km circular orbits inclined at
55 degrees. These vehicles are placed in 6 orbit planes with
four operational satellites in each plane.
GPS Block 2 was the operational system, following the
demonstration system comprised of Block 1 (Navstar 1 - 11)
spacecraft. These spacecraft were 3-axis stabilized, nadir
pointing using reaction wheels. Dual solar arrays supplied 710
watts of power. They used S-band (SGLS) communications for
control and telemetry and UHF cross-link between spacecraft.
The payload consisted of two L-band navigation signals at
1575.42 MHz (L1) and 1227.60 MHz (L2). Each spacecraft
carried 2 rubidium and 2 cesium clocks and nuclear detonation
detection sensors. Built by Rockwell Space Systems for the
US Air Force, the spacecraft measured 5.3 m across with solar
panels deployed and had a design life of 7.5 years.
Alternate Names
USA 117
GPS 2-25
23833
Facts in Brief
II 7925
Launch Site: Cape
Mass: 840.0 kg
Nominal
Power: 710.0 W
Funding Agency
Disciplines
Military
Navigation & Global
Positioning
Additional
Information
Launch/Orbital
information for Navstar
2A-16
Experiments on Navstar
2A-16
Navstar 2A-16
Office.
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Navstar 2A-17
Publications
NSSDC ID: 1996-041A
Maps
New/Updated Data
Description
Alternate Names
GPS 2-26
USA 126
23953
Facts in Brief
II
Launch Site: Cape
Mass: 840.0 kg
Nominal
Power: 710.0 W
Funding Agency
Discipline
Navigation & Global
Positioning
Additional
Information
Launch/Orbital
2A-17
2A-17
Navstar 2A-17
Office.
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Navstar 2A-18
Publications
NSSDC ID: 1996-056A
Maps
New/Updated Data
Description
Alternate Names
USA 128
GPS 2-27
24320
Facts in Brief
II
Launch Site: Cape
Mass: 840.0 kg
Nominal
Power: 710.0 W
Funding Agency
Disciplines
Military
Navigation & Global
Positioning
Additional
Information
Launch/Orbital
2A-18
2A-18
Navstar 2A-18
Office.
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NEAR Shoemaker
Publications
NSSDC ID: 1996-008A
Maps
New/Updated Data
NEAR Shoemaker
Description
The Near Earth Asteroid Rendezvous - Shoemaker (NEAR
Shoemaker), renamed in honor of Gene Shoemaker, was
designed to study the near Earth asteroid Eros from close orbit
over a period of a year. The mission was the first-ever to orbit
an asteroid and to touch down on the surface of an asteroid.
The primary scientific objectives of NEAR were to return data
on the bulk properties, composition, mineralogy, morphology,
internal mass distribution and magnetic field of Eros.
Secondary objectives include studies of regolith properties,
interactions with the solar wind, possible current activity as
indicated by dust or gas, and the asteroid spin state. This data
will be used to help understand the characteristics of asteroids
in general, their relationship to meteorites and comets, and the
conditions in the early solar system. To accomplish these
goals, the spacecraft is equipped with an X-ray/gamma ray
spectrometer, a near infrared imaging spectrograph, a multispectral camera fitted with a CCD imaging detector, a laser
rangefinder, and a magnetometer. A radio science experiment
was also performed using the NEAR tracking system to
estimate the gravity field of the asteroid. The total mass of the
instruments is 56 kg, and they require 81 W power.
Mission Profile
The ultimate goal of the mission was to study the near Earth
asteroid 433 Eros from orbit for approximately one year. Eros
is an S-class asteroid approximately 13 x 13 x 33 km in size,
the second largest near-Earth asteroid. Initially the orbit was
circular with a radius of 200 km. The radius of the orbit was
brought down in stages to a 50 x 50 km orbit on 30 April 2000
and decreased to 35 x 35 km on 14 July 2000. The orbit was
raised over succeeding months to a 200 x 200 km orbit and
then slowly decreased and altered to a 35 x 35 km retrograde
orbit on 13 December 2000. The mission ended with a
touchdown in the "saddle" region of Eros on 12 February 2001.
After launch on a Delta 7925-8 (a Delta II Lite launch vehicle
with nine strap-on solid-rocket boosters and a Star 48 (PAM-D)
third stage) and exit from Earth orbit, NEAR entered the first
part of its cruise phase. It spent most of this phase in a
minimal activity "hibernation" state, which ended a few days
before the flyby of the 61 km diameter asteroid 253 Mathilde
on June 27, 1997. The spacecraft flew within 1200 km of
Mathilde at 12:56 UT at 9.93 km/sec, returning imaging and
other instrument data. On July 3, 1997 NEAR executed the
first major deep space maneuver, a two-part burn of the main
450 Newton thruster. This decreased the velocity by 279
m/sec and lowered perihelion from 0.99 AU to 0.95 AU. The
Earth gravity assist swingby occurred on January 23, 1998 at
7:23 UT. The closest approach was 540 km, altering the orbital
Alternate Names
Near Earth Asteroid
Rendezvous
NEAR
23784
Facts in Brief
II 7925
Launch Site: Cape
Mass: 487.0 kg
Nominal
Power: 1800.0 W
Funding Agency
(United States)
Disciplines
Planetary Science
Space Physics
Additional
Information
Launch/Orbital
information for NEAR
Shoemaker
NEAR Shoemaker
Telecommunications
information for NEAR
Shoemaker
Experiments on NEAR
Shoemaker
NEAR Shoemaker
inclination from 0.5 to 10.2 degrees, and the aphelion distance
from 2.17 to 1.77 AU, nearly matching those of Eros.
Instrumentation was active at this time.
The first of four scheduled rendezvous burns on 20 December
1998 at 22:00 UT aborted due to a software problem. Contact
was lost immediately after this and was not re-established for
over 24 hours. The original mission plan called for these four
burns to be followed by an orbit insertion burn on 10 January
1999, but the abort of the first burn and loss of communication
made this impossible. A new plan was put into effect in which
NEAR flew by Eros on 23 December 1998 at 18:41:23 UT at a
speed of 0.965 km/s and a distance of 3827 km from the
center of mass of Eros. Images of Eros were taken by the
camera, data was collected by the near IR spectrograph, and
radio tracking was performed during the flyby. A rendezvous
maneuver was performed on 3 January 1999 involving a
thruster burn to match NEAR's orbital speed to that of Eros. A
hydrazine thruster burn took place on 20 January to fine-tune
the trajectory. On 12 August a 2 minute thruster burn slowed
the spacecraft velocity relative to Eros to 300 km/hr.
Orbit insertion around Eros occurred on 14 February 2000 at
15:33 UT (10:33 AM EST) after NEAR completed a 13 month
heliocentric orbit which closely matched the orbit of Eros. A
rendezvous maneuver was completed on 3 February at 17:00
UT, slowing the spacecraft from 19.3 to 8.1 m/s relative to
Eros. Another maneuver took place on 8 February increasing
the relative velocity slightly to 9.9 m/s. Searches for satellites
of Eros took place on 28 January, and 4 and 9 February, none
were found. The scans were for for scientific purposes and to
mitigate any chances of collision with a satellite. NEAR went
into a 321 x 366 km orbit around Eros on 14 February. The
orbit was slowly decreased to a 35 km circular polar orbit by 14
July. NEAR remained in this orbit for 10 days and then was
backed out in stages to a 100 km circular orbit by 5 September
2000. Maneuvers in mid-October led to a flyby of Eros within
5.3 km of the surface at 07:00 UT on 26 October.
Following the flyby NEAR moved to a 200 km circular orbit and
shifted the orbit from prograde near-polar to a retrograde nearequatorial orbit. By 13 December 2000 the orbit was be shifted
back to a circular 35 km low orbit. where NEAR will remain
until the nominal end of mission on 12 February 2001. Starting
on 24 January 2001 the spacecraft began a series of close
passes (5 to 6 km) to the surface and on 28 January passed 2
to 3 km from the asteroid. The spacecraft made a slow
controlled descent to the surface of Eros ending with a
touchdown in the "saddle" region of Eros on 12 February 2001
at 20:01:52 UT (3:01:52 p.m. EST). This was the first
spacecraft touchdown on an asteroid. After landing, the
spacecraft continued to operate until the final contact was
made on 28 February. The gamma-ray spectrometer collected
data from the asteroid's surface over this time. A later attempt
to contact the spacecraft on 10 December 2002 was
unsuccessful.
Spacecraft and Subsystems
The spacecraft has the shape of an octagonal prism,
approximately 1.7 m on a side, with four fixed gallium arsenide
solar panels in a windmill arrangement, a fixed 1.5 m X-band
high-gain radio antenna with a magnetometer mounted on the
antenna feed, and an X-ray solar monitor on one end (the
forward deck), with the other instruments fixed on the opposite
end (the aft deck). Most electronics are mounted on the inside
of the decks. The propulsion module is contained in the
interior.
The craft is three-axis stabilized and uses a single bipropellant
Williams.
(hydrazine / nitrogen tetroxide) 450 Newton (N) main thruster,
and four 21 N and seven 3.5 N hydrazine thrusters for
propulsion, for a total delta-V potential of 1450 m/s. Attitude
control is achieved using the hydrazine thrusters and 4
reaction wheels. The propulsion system carries 209 kilograms
of hydrazine and 109 kilograms of NTO oxidizer in two oxidizer
and three fuel tanks.
Power is provided by four 1.8 by 1.2 meter gallium arsenide
solar panels which can produce 400 W at 2.2 AU (NEAR's
maximum distance from the Sun) and 1800 W at 1 AU. Power
is stored in a 9 amp-hour, 22-cell rechargeable super nickelcadmium battery.
Spacecraft guidance is achieved through the use of a sensor
suite of five digital solar attitude detectors, an inertial
measurement unit, (IMU) and a star tracker camera pointed
opposite the instrument pointing direction. The IMU contains
hemispherical resonator gyros and accelerometers. Four
reaction wheels (arranged so that any three can provide
complete three-axis control) are used for normal attitude
control. The thrusters are used to dump angular momentum
from the reaction wheels, as well as for rapid slew and
propulsive maneuvers. Attitude control is to 0.1 degree, line-ofsight pointing stability is within 50 microradians over 1 second,
and post-processing attitude knowledge is to 50 microradians.
The command and data handling subsytem is composed of
two redundant command and telemetry processors and solid
state recorders, a power switching unit, and an interface to two
redundant 1553 standard data buses for communications with
other subsystems. The solid state recorders are constructed
from 16 Mbit IBM Luna-C DRAMs. One recorder has 1.1 Gbits
of storage, the other has 0.67 Gbits.
The NEAR mission was the first launch of NASA's Discovery
program, a series of small-scale spacecraft designed to
proceed from development to flight in under three years for a
cost of less than $150 million. The total cost of the mission
was $220.5 million, which included $43.5 million for the launch
vehicle and $60.8 million for mission operations after launch.
Personnel
Name
Role
E-mail
Dr. John Kerridge
Program
Scientist
NASA Headquarters
Mr. Thomas B.
Coughlin
Project
Manager
Applied Physics
Laboratory
[email protected]
Dr. Robert W.
Farquhar
Mission
Manager
Applied Physics
Laboratory
[email protected]
Dr. Elizabeth E.
Beyer
Program
Manager
NASA Headquarters
[email protected]
Dr. Andrew F.
Cheng
Project
Scientist
Applied Physics
Laboratory
[email protected]
Selected References
Cheng, A. F., Near Earth Asteroid Rendezvous: Mission overview, Space Sci. Rev., 82, No. 1-2,
3-29, 1997.
Cheng, A. F., et al., Near-Earth Asteroid Rendezvous: Mission overview, J. Geophys. Res., 102,
No. E10, 23695-23708, Oct. 1997.
Dunham, D. W., et al., Implementation of the first asteroid landing, Icarus, 159, No. 2, 433-438,
Oct. 2002.
Prockter, L., et al., The NEAR Shoemaker mission to asteroid 433 Eros, Acta Astronaut., 51,
No. 1-9, 491-500, 2002.
NEAR data is currently being validated and prepared for archive. The preliminary data sets can be
found at the PDS Small Bodies Node Archive.
Diagram showing location of NEAR science instruments
NSSDC NEAR Home Page - Links to further information on NEAR
Images of Eros
Images from the Earth Flyby
Images from the Eros and Mathilde Flybys
Asteroid Fact Sheet
NSSDC Asteroid Home Page
Information on NASA's Discovery program
NEAR project home page
Low-cost innovation in spaceflight - The NEAR Shoemaker mission (3.3 Mb PDF)
Information on the NEAR Mission Profile and Trajectory
NEAR (Discovery 2,
Shoemaker)
NEAR (Near Earth
Asteroid
Rendezvous) was a
mission to rendezvous
and orbit around an
near earth asteroid
(433 Eros). On the
cruise to Eros, it flew
by asteroid 253
Mathilde on 27 Jun
1997 and flew by earth
on 23 January 1998.
After failing to insert
itself into Eros' orbit in
January 1999, NEAR
finally inserted itself
into orbit around the
asteroid on the second
try on 14 February
NEAR [NASA]
2000. Initially in a 323
km x 370 km orbit, it
lowered its altitude
during observation. After reaching orbit, NEAR was renamed NEAR-Shoemaker.
After completing its one year mission, NEAR Shoemaker gently landed on the tips of two solar
panels and its bottom edge on February 12, 2001. The spacecraft snapped 69 detailed pictures
during the final 5 km of its descent, the highest resolution images ever obtained of an asteroid,
showing features as small as one centimeter across. The slow touchdown speed left the
spacecraft intact and still sending a signal back to Earth. NASA decided to extend the mission
to February 28th, to get "bonus science" from the spacecraft, which had already collected 10
times more data than originally planned. This allowed the gamma-ray spectrometer to collect
data from an ideal vantage point about four inches (10 cm) from the surface
The primary scientific goals were to measure the asteroid's:
bulk properties (size, shape, volume, mass, gravity field, and spin state);
surface properties (elemental and mineral composition, geology, morphology, and
texture);
internal properties (mass distribution and magnetic field).
Science instruments:
MultiSpectral Imager (MSI) - a refractive telescope with passively cooled Si CCD array
(244 x 537) that will determine the overall size, shape, and spin characteristics of the
asteroid, map the morphology and composition of the surface, and search for
satellites of Eros.2.25 x 2.9 deg FOV, 10-16 meter resolution from 100 km altitude,
sensitive between 400 and 1100 nm.
X-Ray/Gamma-Ray Spectrometer (XGRS) - containing two sensors (an X-ray
fluorescence spectrometer and a gamma-ray spectrometer), XGRS will be used to
determining the surface/near-surface elemental composition of the asteroid.
Near-Infrared Spectrograph (NIS) - a spectrometer covering 800-2700 nm, NIS is
designed to map the mineralogical composition of Eros. Magnetometer - a three-axis
fluxgate sensor that will be used to measure Eros' magnetic field. These
measurements will help determine the internal composition of the asteroid.
NEAR Laser Rangefinder (NLR) - an altimeter that uses a solid-state pulsed laser to
measure the distance between the spacecraft and the surface of the asteroid. It will
be used to make will make accurate measurements of the asteroid's shape and
detailed surface structure. Nd-YAG laser operating at 1.064 mm wavelength, 6 meter
resolution, 50 km range.
Radio Science - uses the satellite's telemetry system to map Eros' gravity field.
Nation:
Type / Application:
Operator:
Contractors:
Equipment:
Configuration:
Propulsion:
Lifetime:
Mass:
Orbit:
USA
Asteroid Orbiter / Lander
NASA
Johns Hopkins University Applied Physics Laboratory (APL)
MSI, XGRS, NIS, NLR
Octagonal Prism, 1.5 m dish antenna, 4 deployed fixed solar arrays
LEROS-1
818 kg
Heliocentric, later orbit around Asteroid 433 Eros, finally landed on Eros
Satellite
Date
LS
NEAR (Discovery 2, Shoemaker) 17.02.1996 CC LC-17B
Launcher
Delta-7925-8
Remarks:
NSSDC Master
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OAST Flyer
Publications
NSSDC ID: 1996-001B
Maps
New/Updated Data
Description
OAST Flyer (NASA's Office of Aeronautical and Space
Technology Flyer) is an American minispacecraft that was
released from the shuttle STS 72. It carried 4 experimental
packages: to measure spacecraft contamination levels at lowearth orbits, to test GPS equipment, to test amateur radio
gear, and finally to determine the effects of solar radiation on
the explosives aboard satellite systems.
Alternate Names
23763
Facts in Brief
Launch
Vehicle: Shuttle
Launch Site: Cape
Funding Agency
NASA-Office of
Aeronautics and Space
Technology (United
States)
Disciplines
Communications
Navigation & Global
Positioning
Solar Physics
Additional
Information
Launch/Orbital
information for OAST
Flyer
Experiments on OAST
Flyer
OAST Flyer
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ORFEUS-SPAS II
Publications
NSSDC ID: 1996-065B
Maps
New/Updated Data
Description
The ORFEUS-SPAS II mission followed the ORFEUS-SPAS I
mission flown in 1993, motivated by improvements in
instrument performance and the critical need for additional
observation time. The purpose of the ORFEUS-SPAS II
mission was to conduct investigations of celestial sources in
the far and extreme ultraviolet spectral range, and to increase
understanding of the evolution of stars, the structure of
galaxies, and the nature of the interstellar medium. ORFEUSSPAS II was one of a series of planned joint DARA (German
Space Agency) /NASA missions. The name arises from the
reusable Astro-Shuttle Pallet Satellite (Astro-SPAS), and the
Orbiting Retrievable Far and Extreme Ultraviolet
Spectrometers (ORFEUS) Telescope carried on Astro-SPAS.
ORFEUS-SPAS was a free-flying platform designed to be
deployed and retrieved from the space shuttle. The AstroSPAS carrier was powered by batteries, and data from the
instruments were stored on tape. Absolute pointing was
accurate to within a few arc seconds. ORFEUS-SPAS is 4.5m
in length and has a 2.5m width base. Operation of ORFEUSSPAS was approximately 40km from the shuttle.
ORFEUS-SPAS II carried the same three spectrometers,
operating over the wavelength range 400 - 1250 Angstroms, as
was carried on ORFEUS-SPAS I. The Tubingen Ultraviolet
Echelle Spectrometer (TUES) and the Berkeley Extreme and
Far-UV Spectrometer (BEFS) were housed on the primary
instrument - the ORFEUS 1-m telescope. The Interstellar
Medium Absorption Profile Spectrograph (IMAPS) was
operated independently from ORFEUS.
The ORFEUS-SPAS II mission was flown in NovemberDecember 1996. The mission acquired spectra of numerous
celestial objects during 14 days of observations. Efficiency of
62.5% for all instruments was achieved.
Alternate Names
STS 80/ ORFEUS
ORFEUS II
24661
Facts in Brief
Launch
Vehicle: Shuttle
Launch Site: Cape
Mass: 3500.0 kg
Funding Agencies
(United States)
German Space Agency
(Federal Republic of
Germany)
Discipline
Astronomy
Additional
Information
Launch/Orbital
information for ORFEUSSPAS II
Experiments on ORFEUSSPAS II
ORFEUS-SPAS II
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OSL
Publications
NSSDC ID: OSL
Maps
New/Updated Data
Alternate Names
Description
The main objective of the Orbiting Solar Laboratory (OSL) is to
acquire images of the solar surface with the high spatial
resolution required for the determination of density,
temperature, magnetic field, and non-thermal velocity field in
solar features on the scale at which many basic physical
processes occur -- less than 0.2 arcsec. In addition, highresolution spectroscopy is performed. OSL consists of five
instruments. The main telescope uses an f/24 on-axis
Gregorian configuration with primary mirror 1.1 m in diameter,
useful throughout the 220 - 1000 nm range and providing a 3.9
arcmin field of view with 0.15 arcsec resolution. Three
instruments make up the Coordinated Instrument Package
(CIP) and share the focal plane at the Gregorian focus. These
instruments obtain narrow-band and broad-band filtergrams as
well as high-resolution spectrograms. Charge-coupled Device
(CCD) cameras are employed in each instrument in the CIP
while the remaining instrument packages use self-contained
telescopes and acquire high-resolution UV spectra and XUV
and X-ray images. A finder telescope provides a continuous
full-Sun image for reference by users of the other, limited fieldof-view instruments. The OSL spacecraft is three-axis
stabilized, with pointing accuracy of 9 arcsec in pitch/yaw and
30 arcmin in roll; image motion compensation is carried out
within the individual instruments to achieve better than 0.2
arcsec stability. A polar, Sun-synchronous orbit is used to
achieve more than 250 full-Sun days per year. Solar arrays
provide power. The Tracking and Data Relay Satellite System
(TDRSS) contact provides 2E7 bit/s telemetry for eight
hours/day on average. The mission is planned for three years
or longer and mission operations are to include near-realtime
targeting during TDRSS contacts. Further information may be
obtained through D. F. Spicer (NASA-GSFC), Project Scientist.
Orbiting Solar Lab
Facts in Brief
II
Launch Site: Cape
Mass: 3364.0 kg
Funding Agencies
(United States)
Discipline
Solar Physics
Additional
Information
Launch/Orbital
information for OSL
Experiments on OSL
Data collections from OSL
Hills.
Personnel
Name
Role
E-mail
Ms. Maureen C.
Project
NASA Headquarters
mlocke@hst-
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=OSL[08/06/2011 23:27:07]
Locke
Manager
Dr. J. David
Bohlin
Program
Scientist
NASA Headquarters
Dr. Daniel S.
Spicer
Project
Scientist
NASA Goddard Space
Flight Center
Mr. Roger A.
Mattson
Project
Manager
NASA Goddard Space
Flight Center
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=OSL[08/06/2011 23:27:07]
popb8.gsfc.nasa.gov
[email protected]
NSSDC Master
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Palapa C-1
Publications
NSSDC ID: 1996-006A
Maps
New/Updated Data
Alternate Names
Description
Palapa C-1 was an Indonesian geosynchronous spacecraft
launched from Cape Canaveral by an Atlas 2AS rocket. It will
provide voice and TV communications to the 17,000 islands of
Indonesia, and the nearby Asian-Pacific region. It carried 24 Cband, 6 extended C-band, and 4 Ku-band transponders, most
of which were leased to several countries.
23779
Facts in Brief
Launch Vehicle: Atlas2 AS
Launch Site: Cape
Funding Agency
Unknown (Indonesia)
Discipline
Communications
Additional
Information
Launch/Orbital
information for Palapa C1
Experiments on Palapa C1
Palapa C-1
Office.
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Palapa C-2
Publications
NSSDC ID: 1996-030A
Maps
New/Updated Data
Alternate Names
Description
Palapa C-2 was an Indonesian geosynchronous
communications satellite that was launched from Kourou,
French Guiana, by an Ariane 44L rocket. With its 34
transponders and parked at 113 E longitude, it is expected to
provide voice and vision communications to a large area
bounded by Iran, Vlodivostok, Australia and New Zealand.
23864
Facts in Brief
44LP
French Guiana
Funding Agency
Unknown (Indonesia)
Discipline
Communications
Additional
Information
Launch/Orbital
information for Palapa C2
Experiments on Palapa C2
Palapa C-2
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PAMS-STU
Publications
NSSDC ID: 1996-032D
Maps
New/Updated Data
Alternate Names
Description
PAMS-STU was a NASA experimental spacecraft launched
from STS 77 to test an attitude stabilization design. It had an
unbalanced mass distribution and two magnetic rods. The
interaction of the rods with Earth's magnetic field was expected
to damp any wobble or spin. There were some problems in
ascertaining the success fully because of the malfunction of
the laser ranger. It reentered the atmosphere on October 26.
23876
Facts in Brief
Launch
Vehicle: Shuttle
Launch Site: Cape
Mass: 35.0 kg
Funding Agency
(United States)
Discipline
Technology Applications
Additional
Information
Launch/Orbital
information for PAMSSTU
Experiments on PAMSSTU
PAMS-STU
Office.
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PANAMSAT 3R
Publications
NSSDC ID: 1996-002A
Maps
New/Updated Data
Description
PAS 3R, also known as PANAMSAT 3R, as an American
geostationary communications spacecraft launched by an
Ariane 44L rocket from the Kourou Space Center in French
Guiana. After parking at 43.0 W longitude, the 2,900 kg
spacecraft will provide TV and communications services to
North and South American countries through its 16 C-band
transponders.
Alternate Names
PAS 3R
Intelsat 3R
IS-3R
23764
Facts in Brief
44L
French Guiana
Mass: 2900.0 kg
Funding Agencies
Pan American Satellite
(United States)
International
Telecommunications
(International)
Discipline
Communications
Additional
Information
Launch/Orbital
information for
PANAMSAT 3R
Experiments on
PANAMSAT 3R
PANAMSAT 3R
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Polar
Publications
NSSDC ID: 1996-013A
Maps
New/Updated Data
Polar
Description
POLAR is one of four spacecraft in the Global Geospace
Science (GGS) program. These are among the six spacecraft
in the International Solar Terrestrial Physics (ISTP) program.
POLAR provides multi-wavelength imaging of the aurora,
measuring plasma entry into the polar magnetosphere and
geomagnetic tail, the flow of plasmas to and from the
ionosphere, and the deposition of particle energy in the
ionosphere and upper atmosphere. POLAR has on-board
propulsion systems and a design lifetime of three to five years,
with redundant subsystems. POLAR is cylindrical,
approximately 2.8 m in diameter by 1.25 m high (plus 1.25 m
for its two despun platforms), with body-mounted solar cells,
weighs 1250 kg and uses 333 W of power. The spin rate is 10
rpm around an axis approximately normal to the orbital plane. It
has long wire spin-plane antennas, inertial booms, and spinplane appendages to support sensors. POLAR has two
despun gimbaled instrument platforms, and booms are
deployed along both Z axes. Data are stored using on-board
tape recorders and are relayed to the Deep Space Network at
600 kbps maximum (250 kbps nominal) although the average
real-time data rate for POLAR is 41.6 kbps. POLAR has a
22.6-h polar orbit (90 deg inclination), with perigee and apogee
of 11,500 and 57,000 km. Polar was launched to observe the
polar magnetosphere and, as its orbit has precessed with time,
has observed the equatorial inner magnetosphere and is now
carrying out an extended period of southern hemisphere
coverage. Details on the POLAR mission and instrumentation
are provided in Space Science Reviews (Vol. 71, Nos. 1-4,
1995) and reprinted in The Global Geospace Mission, edited
by C. T. Russell (Kluwer, 1995).
Alternate Names
Polar Plasma Laboratory
GGS/Polar
ISTP/Polar
23802
Facts in Brief
II
Launch
United States
Mass: 1300.0 kg
Funding Agency
(United States)
Discipline
Space Physics
Additional
Information
Launch/Orbital
information for Polar
Polar
Experiments on Polar
Data collections from Polar
be directed to: Dr. Timothy
E. Eastman.
Personnel
Name
Role
E-mail
Dr. Keith W.
Ogilvie
Mission Principal
Investigator
NASA Goddard Space
Flight Center
[email protected]
Dr. John B.
Sigwarth
Project Scientist
NASA Goddard Space
Flight Center
Dr. Charles
P. Holmes
Program Scientist
NASA Headquarters
[email protected]
Other Sources of Polar Data/Information
ISTP Home Page
Charge and Mass Magnetospheric Ion Composition Experiment (CAMMICE) and
Comprehensive Energetic Particle and Pitch Angle Distribution (CEPPAD) teams
Electric Fields Investigation (EFI) team
Hot Plasma Analyzer (Hydra) team
Magnetic Fields Experiment (MFE) team
Polar Ionospheric X-ray Imaging Experiment (PIXIE) team
Plasma and Radio Waves Instrument (PWI) team
Thermal Ion Dynamics Experiment (TIDE) team
Toroidal Imaging Mass-Angle Spectrograph (TIMAS) team
Ultraviolet Imager (UVI) team
Visible Imaging System (VIS) team
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Priroda
Publications
NSSDC ID: 1996-023A
Maps
New/Updated Data
Alternate Names
Description
Priroda was the last of the scheduled 5 Russian modules of Mir
and was launched from the Baykonur cosmodrome by a
Proton-K rocket to dock after 3 days rather than the usual 9
days. The launch itself was 3 days earlier than the planned
date in order to facilitate an American microbiology program.
Priroda carried 900 kg of American equipment to be delivered
to the American astronaut on Mir. Other cargo on board
included several remote sensing Russian instruments. It is
likely that Priroda may later be attached to the planned
international space station, Alpha.
23848
Facts in Brief
Launch
Vehicle: Proton-K
Kazakhstan
Mass: 19000.0 kg
Funding Agency
Unknown (Russia)
Disciplines
Earth Science
Resupply/Refurbishment/Repair
Additional
Information
Launch/Orbital
information for Priroda
Experiments on Priroda
Priroda
Office.
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Progress M-31
Publications
NSSDC ID: 1996-028A
Maps
New/Updated Data
Alternate Names
Description
An improved version of cargo freighters used to supply the Mir
space station, the Progress M series had greater cargo
capacity, a modernized approach/docking system and carried 2
solar panels to generate electrical power. Progress M can fly
for 30 days independently and 108 days docked with Mir.
Spare propellent in Progress M's tanks can be transferred to
Mir before it is consigned to burn up in reentry. In the past,
extra fuel was abandoned with the craft. Future Progress
vehicles will carry a recoverable reentry capsule for the speedy
return of up to 150 kg of material from Mir to earth.
Progress M-31 was launched by a Soyuz U rocket from the
Baykonur cosmodrome. It docked with Mir and delivered 3000
kg of food, fuel and water. It undocked on August 1 at 16:45
UT and was deorbited over the south Pacific later that day.
23860
Facts in Brief
Launch
Vehicle: Soyuz-U
Kazakhstan
Mass: 7250.0 kg
Funding Agency
Unknown (Russia)
Discipline
Additional
Information
Launch/Orbital
information for Progress
M-31
Experiments on Progress
M-31
Progress M-31
Office.
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Progress M-32
Publications
NSSDC ID: 1996-043A
Maps
New/Updated Data
Alternate Names
Description
Progress M-32 was launched from the Baikonur cosmodrome
aboard a Soyuz-U rocket. It delivered 2,500 kg of supplies and
equipment to the Mir space station.
24071
Facts in Brief
Launch
Vehicle: Soyuz-U
Kazakhstan
Mass: 2500.0 kg
Funding Agency
Unknown (Russia)
Discipline
Additional
Information
Launch/Orbital
M-32
M-32
Progress M-32
Office.
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Progress M-33
Publications
NSSDC ID: 1996-066A
Maps
New/Updated Data
Alternate Names
Description
Progress M-33 was launched by a Soyuz-Y rocket from the
Baykonur cosmodrome. It delivered 2,400 kg of food, fuel and
equipment.
24633
Facts in Brief
Launch
Vehicle: Soyuz-Y
Kazakhstan
Funding Agency
Unknown (Russia)
Discipline
Additional
Information
Launch/Orbital
M-33
M-33
Progress M-33
Office.
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Raduga 33
Publications
NSSDC ID: 1996-010A
Maps
New/Updated Data
Alternate Names
Description
Raduga 33 was a Russian communications spacecraft
launched by a Proton-K rocket from the Baykonur
Cosmodrome. It was intended to be geostationary but it turned
out to be a failed launch due to the explosion of the fourth
stage just prior to the final maneuver.
23794
Facts in Brief
Launch
Vehicle: Proton-K
Kazakhstan
Mass: 1965.0 kg
Funding Agency
(Russia)
Discipline
Communications
Additional
Information
Launch/Orbital
information for Raduga
33
Experiments on Raduga 33
Raduga 33
Office.
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Experiments
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Personnel
REX 2
Publications
NSSDC ID: 1996-014A
Maps
New/Updated Data
Alternate Names
Description
REX 2 (Radiation EXperiment 2) was an American military
minispacecraft launched from Vandenberg AFB by a Pegasus
XL rocket. The rocket was carried aloft in the belly of a L-1011
aircraft to 12 km altitude before release and ignition. It is an Air
Force Rome Laboratory ionospheric research satellite which
will test the effects of the atmosphere on radio transmissions,
and will employ GPS for on-board navigation and attitude
control.
23814
Facts in Brief
Launch
Vehicle: Pegasus XL
Launch
United States
Mass: 110.0 kg
Funding Agency
Unknown (United States)
Discipline
Military
Additional
Information
Launch/Orbital
information for REX 2
Experiments on REX 2
Data collections from REX
2
Office.
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SAC-B
Publications
NSSDC ID: 1996-061B
Maps
New/Updated Data
Description
Satellite de Aplicaciones Cientifico-B (SAC-B) was a small
satellite built by the Argentinean National Commission of
Space Activities (CoNAE). SAC-B was designed to advance
the study of solar physics and astrophysics through the
examination of solar flares, gamma ray bursts, diffuse X-ray
cosmic background, and energetic neutral atoms. The satellite
was also designed to test and characterize the performance of
new equipment and technologies which may be used in future
operational or scientific missions. The satellite payload
included three astronomical instruments - the Hard X-ray
Spectrometer (HXRS), the Goddard X-ray Experiment (GXRE),
and the Cosmic Unresolved X-ray Background Instrument
(CUBIC). Also flying was an Italian instrument called ISENA
which plans to measure energetic netral atoms. The spacecraft
body was a 62 x 62 cm wide by 80 cm high rectangular
parallelepiped wotj 4 extended solar panels 62 cm wide by 76
cm long.
SAC-B satellite was launched with the NASA satellite HETE 1.
The SAC-B solar arrays did not automatically deploy due to a
battery failure in the Pegasus XL rocket third stage. The solar
arrays were deployed via ground commands, however
because of spacecraft tumbling and shadowing of the Pegasus
XL third stage, they were unable to generate enough power to
keep the satellite's batteries charged.
Alternate Names
Satelite de Aplicaciones
Cientificas - B
24645
Facts in Brief
Launch
Vehicle: Pegasus XL
Launch Site: Wallops
Island, United States
Mass: 181.0 kg
Funding Agencies
National Commission of
Space Activities
(Argentina)
Disciplines
Astronomy
Solar Physics
Space Physics
Additional
Information
Launch/Orbital
information for SAC-B
Experiments on SAC-B
Data collections from SACB
Office.
Personnel
Name
Role
E-mail
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SAX
Publications
NSSDC ID: 1996-027A
Maps
New/Updated Data
Description
SAX is the X-Ray Astronomy Satellite selected by the Italian
National Space Plan for inclusion in the Science Plan. The
objective of the mission is to perform spectroscopic and time
variability studies of celestial X-ray sources in the energy band
from 1 to 200 keV, including an all-sky monitoring investigation
of transients in the 2-30 keV energy range. The payload
includes the following narrow-field detectors coaligned to a
common pointing axis: (1) four X-ray imaging concentrators
sensitive from 1 to 10 keV (one of them extending down to 0.1
keV), (2) one gas scintillation proportional counter sensitive
from 3 to 12 keV, and (3) a sodium iodide scintillator crystal in
phoswich configuration operating from 15 to 200 keV. At 90
deg to the axis of the narrow field instruments is an array of
three identical wide field camera units sensitive from 2 to 30
keV. The SAX mission payload and science program is under
the responsibility of a consortium of Italian institutes together
with institutes from Holland. The participation of the Space
Science Department of ESA is also foreseen. A listing of the
SAX Consortium of Institutes is given in Appendix B8.
Alternate Names
Satellite for X-Ray
Astronomy
Beppo-SAX
23857
Facts in Brief
Launch Vehicle: AtlasCentaur
Launch Site: Cape
Mass: 900.0 kg
Funding Agency
Agenzia Spaziale Italiana
(Italy)
Discipline
Astronomy
Additional
Information
Launch/Orbital
information for SAX
Experiments on SAX
Data collections from SAX
Office.
US Active Arvhive for Beppo-SAX Information/Data
The Beppo-SAX Data Archive at HEASARC
Other Sources of SAX Information/Data
Beppo-SAX home page (Italian Space Agency)
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Soyuz-TM 23
Publications
NSSDC ID: 1996-011A
Maps
New/Updated Data
Alternate Names
Description
Soyuz TM-33 was a Russian transportation spacecraft that
was launched from the Baykonur Cosmodrome carrying 2
cosmonauts. It docked with the Mir space station on February
23rd.
Designed and manufactured by RKK Energiya, the Soyuz TM
was capable of carrying three cosmonauts and had a gross
weight of just over seven metric tons, a length of seven
meters, and a maximum diameter of 2.7 m. The spacecraft
consisted of three main sections: the orbital module, the
command and reentry module, and the service module. Two
solar arrays (10.6 m span) provided electrical power for the
typical 50-hour journey to Mir and could be interconnected with
the space station's electrical system to furnish additional 1.3
kW. The nominal flight time for Soyuz TM spaceship was 5-6
months.
23798
Facts in Brief
Launch Vehicle: Soyuz
Kazakhstan
Mass: 7150.0 kg
Funding Agency
Unknown (Russia)
Discipline
Human Crew
Additional
Information
Launch/Orbital
information for Soyuz-TM
23
Experiments on Soyuz-TM
23
Soyuz-TM 23
Office.
Soyuz TM-23
Launch, orbit and landing data
Launch date:
Launch time:
Launch site:
Launch pad:
Altitude:
Inclination:
Landing date:
Landing time:
Landing site:
21.02.1996
12:34 UT
Baikonur
1
201 - 246 km
51,6°
02.09.1996
07:41 UT
50° 17' N, 70° 50' E
Crew
No
.
1
2
Surname
Given name
Onufriyenk
Yuri Ivanovich
o
Yuri
Usachyov
Vladimirovich
Duration
Orbit
s
Job
Flight No.
Commander
1
193d 19h 07m 3066
Flight
Engineer
2
193d 19h 07m 3066
Crew seating arrangement
Launch
1 Onufriyenko
2 Usachyov
3
Landing
1 Onufriyenko
2 Usachyov
3 André-Deshays
Double Crew
No
.
1
2
Surname
Given name
Tsibliye Vasili
v
Vasiliyevich
Aleksandr
Lazutkin
Ivanovich
Job
Commande
r
Flight
Engineer
Flight
Launch from Baikonur; landing 107 km southwest of Akmola.
Docking on MIR spacestation; both cosmonauts became the 21st resident crew after crew
exchanging; both cosmonauts performed six EVA`s on 15.03.1996 (5h 51m), 20.05.1996 (5h
20m), 24.05.1996 (5h 43m), 30.05.1996 (4h 20m), 06.06.1996 (3h 34m) and 13.06.1996 (5h
42m) carrying out following work: installation of the telescopic boom, the MSCA solar array,
the multi-spectral scanner, exchanging materials samples and deploying of a radar antenna;
protein crystal growth experiments; more experiments in materials science using high
temperture melting oven "Optizon"; module "Priroda" arrived on 26.04.1996; supplies arrived
with cargo spacecraft Progress M-31.
Crew was visited by crew of STS-76; since that time (24.03.1996) U.S. astronaut Shannon
Lucid completed resident crew.
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Soyuz-TM 24
Publications
NSSDC ID: 1996-047A
Maps
New/Updated Data
Alternate Names
Description
Soyuz TM-24 carried a crew of three to the Mir space station.
The crew consisted of Cosmonauts Valery Korzun and
Alexander Kalery, and the first French woman in space,
Claudie Andre-Deshays. They joined American astronaut
Shannon Lucid and Mir 21 crewmates Yuri Onufriyenko and
Yuri Usachev. Andre-Deshays carried out biological and
medical experiments on Mir for 16 days before returning to
Earth with Onufriyenko and Usachev.
24280
Facts in Brief
Launch
Vehicle: Soyuz-U
Kazakhstan
Funding Agency
Unknown (Russia)
Discipline
Human Crew
Additional
Information
Launch/Orbital
information for Soyuz-TM
24
Experiments on Soyuz-TM
24
Soyuz-TM 24
Office.
Soyuz TM-24
Launch date:
Launch time:
Launch site:
Launch pad:
Altitude:
Inclination:
Landing date:
Landing time:
Landing site:
17.08.1996
13:18 UT
Baikonur
1
195,8 - 242,8 km
51,63°
02.03.1997
06:44 UT
47° 49' N, 69° 24' E
Crew
No
.
Surname
1
Korzun
2
Kaleri
3
AndréDeshays
Given name
Valeri
Grigoriyevich
Aleksandr
Yuriyevich
Claudie
Job
Flight No.
Commander
1
Flight Engineer
2
Research
Cosmonaut
1
Orbi
ts
196d 17h 3113
26m
196d 17h 3113
26m
Duration
15d 18h 23m 249
Launch
1 Korzun
2 Kaleri
3 André-Deshays
Landing
1 Korzun
2 Kaleri
3 Ewald
Double Crew
No.
3
Surname
Given
name
Eyharts Léopold
Job
Research
Cosmonaut
Flight
Launch from Baikonur; landing 128 km east of Dzheskasgan.
Former prime crew (Manakov and Vinogradov) was exchanged five days before launch due
of medical problems of Manakov.
Docking on MIR spacestation; 22nd resident crew (first together with Shannon Lucid, later
John Blaha/Jerry Linenger); French mission CASSIOPÈE; physiological and neurological
experiments; crew was visited by STS-79, MIR97 and STS-81-crews; EVA`s by Korzun and
Kaleri on 02.12.1996 (5h 57m) and 09.12.1996 (6h 36m), (external cable installation of the
MSCA solar array).
Note
André-Deshays returned to Earth on 02.09.1996 at 07:41 UT with Soyuz TM-23-spacecraft.
Photos / Drawings
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Spartan 207
Publications
NSSDC ID: 1996-032B
Maps
New/Updated Data
Alternate Names
Description
Spartan 207 was an 850 kg module released from STS 77 as
a platform from which to launch an inflatable antenna (IAE). It
was captured back into the shuttle soon after the antenna
release.
23871
Facts in Brief
Launch
Vehicle: Shuttle
Launch Site: Cape
Mass: 850.0 kg
Funding Agency
(United States)
Discipline
Astronomy
Additional
Information
Launch/Orbital
information for Spartan
207
Experiments on Spartan
207
Spartan 207
Office.
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STS 72
Publications
NSSDC ID: 1996-001A
Maps
New/Updated Data
Description
STS 72 was a US shuttle spacecraft launched from Cape
Canaveral. It carried, released, and retrieved the OAST Flyer.
It also retrieved a long orbiting Japanese reusable spacecraft,
SFU, that had amassed astronomical data and material
science products since March 1995.
The primary objective of the STS-72 mission was to capture
and return to Earth a Japanese microgravity research
spacecraft known as Space Flyer Unit (SFU). The 7,885lbs
SFU spacecraft was launched by Japan's National Space
Development Agency (NASDA) from Tanegashima Space
Center in Japan at 8:01 UT on March 18, 1995 aboard a
Japanese H-II rocket (HII-3).
Alternate Names
23762
Facts in Brief
Launch
Vehicle: Shuttle
Launch Site: Cape
Mass: 6510.0 kg
Funding Agency
The STS-72 mission also deployed (for about 50 hours) and
then retrieved the Office of Aeronautics and Space Technology
Flyer (OAST-Flyer) spacecraft. OAST-Flyer was the seventh in
a series of missions aboard reuseable free-flying Spartan
carriers. It consisted of four experiments: Return Flux
Experiment (REFLEX), Global Positioning System Attitude
Determination and Control Experiment (GADACS), Solar
Exposure to Laser Ordnance Device (SELODE) and the
University of Maryland Spartan Packet Radio Experiment
(SPRE).
Other experiments onboard STS-72 included the Shuttle Solar
Backscatter Ultraviolet Experiment (SSBUV-8) (previously
flown on STS-34, STS-41, STS-43, STS-45, STS-56, STS-62
and STS-66), EDFT-03, Shuttle Laser Altimeter Payload (SLA01/GAS(5)), VDA-2, National Institutes of Health NIH-R3
Experiment, Space Tissue Loss Experiment (STL/NIH-C), Pool
Boiling Experiment (PBE) (hardware previously flown on STS47, STS-57 and STS-60) and the Thermal Energy Storage
(TES-2) experiment (previously flown on STS-69).
Get Away Special payloads included the United States Air
Force Academy G-342 Flexible Beam Experiment
(FLEXBEAM-2), Society of Japanese Aerospace Companies'
G-459 - Protein Crystal Growth Experiment and the Jet
Propulsion Laboratory GAS Ballast Can with Sample Return
Experiment.
Endeavour's 10th flight also included two 6.5 hour spacewalks
by three astronauts to test hardware and tools that will be
used in the assembly of the International Space Station
starting in late 1997. EVA-1 on flight day five consists of
Crewmembers Leroy Chiao (EV1) and Dan Barry (EV2) while
EVA-2 on Flight Day 7 consists of Leroy Chiao (EV1) and
Winston Scott (EV2).
Flight (United States)
Discipline
Human Crew
Additional
Information
Launch/Orbital
information for STS 72
Experiments on STS 72
Data collections from STS
72
Office.
STS-72
Endeavour (10)
USA
Launch date:
Launch time:
Launch site:
Launch pad:
Altitude:
Inclination:
Landing date:
Landing time:
Landing site:
11.01.1996
09:41 UT
Cape Canaveral (KSC)
39-B
463 km
28,45°
20.01.1996
07:41 UT
Crew
No.
Surname
Given name
Job
Flight No.
Duration
Orbits
CDR
3
8d 22h 01m
142
1
Duffy
Brian
2
Jett
Brent Ward, Jr. PLT
1
8d 22h 01m
142
3
Chiao
Leroy
2
8d 22h 01m
142
MSP
4
Scott
Winston Elliott MSP
1
8d 22h 01m
142
5
Wakata Koichi
MSP
1
8d 22h 01m
142
6
Barry
Daniel Thomas MSP
1
8d 22h 01m
142
1
2
3
4
5
6
Launch
Duffy
Jett
Chiao
Scott
Wakata
Barry
Landing
1 Duffy
2 Jett
3 Wakata
4 Scott
5 Chiao
6 Barry
Flight
Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC).
Space Flyer Unit from Japan was captured and brought to Earth; EVA by Chiao and Barry on
15.01.1996 (6h 9m) and by Chiao and Scott on 17.01.1996 (6h 41m) to test tools and
hardware that will be used in the assembly of the ISS; crew also deployed and retrieved the
OAST-Flyer.
Photos / Drawings
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STS 75
Publications
NSSDC ID: 1996-012A
Maps
New/Updated Data
Description
The STS 75 mission was the 75th shuttle mission and the 19th
flight of the Columbia orbiter. The primary tasks of this shuttle
flight were to conduct experiments as part of the third flight of
the United States Microgravity Payload (USMP-3) and to
deploy the joint Italian-US Tethered Satellite System (TSS1R).
The TSS-1R mission was a reflight of TSS-1 which was flown
onboard Space Shuttle Atlantis on STS-46 in July/August of
1992. During that flight, the tether was deployed a distance of
860 feet. STS-75 mission scientist hope to deploy the tether to
a distance of over 12 miles (20.7km).
STS 75
The Tether Satellite System circled the Earth at an altitude of
296 kilometers which placed the tether system within the
rarefied electrically charged layer of the atmosphere known as
the ionosphere. The conducting tether generated high voltage
and electrical currents as it moved through the ionosphere
across the magnetic field lines of the earth. Scientists were
able to learn more about the electrodynamics of a conducting
tether system to deepen our understanding of physical
processes in the near-Earth space environment. These studies
will help provide explanations for events such as the formation
and behavior of comet tails and bursts of radio "noise"
detected from other planets.
The specific TSS1-R mission objectives were: characterize the
current-voltage response of the TSS-orbiter system,
characterize the satellites high-voltage sheath structure and
current collection process, demonstrate electric power
generation, verify tether control laws and basic tether
dynamics, demonstrate the effect of neutral gas on the plasma
sheath and current collection, characterize the TSS radio
frequency and plasma wave emissions and characterize the
TSS dynamic-electrodynamic coupling.
TSS-1R Science Investigations include: TSS Deployer Core
Equipment and Satellite Core Equipment (DCORE/SCORE),
Research on Orbital Plasma Electrodynamics (ROPE),
Research on Electrodynamic Tether Effects (RETE), Magnetic
Field Experiment for TSS Missions (TEMAG), Shuttle
Electrodynamic Tether System (SETS), Shuttle Potential and
Return Electron Experiment (SPREE), Tether Optical
Phenomena Experiment (TOP), Investigation of
Electromagnetic Emissions by the Electrodynamic Tether
(EMET), Observations at the Earth's Surface of
Electromagnetic Emissions by TSS (OESSE), Investigation
and Measurement of Dynamic Noise in the TSS (IMDN),
Theoretical and Experimental Investigation of TSS Dynamics
Alternate Names
23801
Facts in Brief
Launch
Vehicle: Shuttle
Launch Site: Cape
Mass: 10592.0 kg
Funding Agency
Disciplines
Human Crew
Space Physics
Additional
Information
Launch/Orbital
75
Office.
(TEID) and the Theory and Modeling in Support of Tethered
Satellite Applications (TMST).
The USMP-3 payload consisted of four major experiments
mounted on two Mission Peculiar Experiment Support
Structures (MPESS) and three Shuttle Mid-deck experiments.
The experiments are: Advanced Automated Directional
Solidification Furnace (AADSF), Material pour l'Etude des
Phenomenes Interessant la Solidification sur Terre et en Orbite
(MEPHISTO), Space Acceleration Measurement System
(SAMS), Orbital Acceleration Research Experiment (OARE),
Critical Fluid Light Scattering Experiment (ZENO) and
Isothermal Dendritic Growth Experiment (IDGE).
During this flight, the tether on TSS-1R broke after the satellite
had been deployed to a distance of 19.7 km. The shuttle
ended its mission after 251 orbits and a total mission duration
of 15 days, 17 hours, 41 minutes, and 25 seconds.
TSS-1R
Other Sources of STS 75 Information/Data
STS 75 information (NASA KSC)
STS 75 Electronic Photo File (NASA KSC)
STS 75 Press Release images (NASA JSC)
STS-75
Columbia (19)
USA
Sour
Launch date:
Launch time:
Launch site:
Launch pad:
Altitude:
Inclination:
Landing date:
Landing time:
Landing site:
22.02.1996
20:18 UT
39-B
296 km
28,45°
09.03.1996
13:58 UT
Crew
No.
Surname
Given name
Job
Flight No.
Duration
Orbits
1
Allen
Andrew Michael "Andy" CDR
3
15d 17h 41m
251
2
Horowitz
Scott Jay "Doc"
PLT
1
15d 17h 41m
251
3
Hoffman
Jeffrey Alan
MSP
5
15d 17h 41m
251
4
Cheli
Maurizio
MSP
1
15d 17h 41m
251
5
Nicollier
Claude
MSP
3
15d 17h 41m
251
6
Chang-Diaz Franklin Ramon
MSP
5
15d 17h 41m
251
7
Guidoni
MSP
1
15d 17h 41m
251
Umberto
1
2
3
4
5
6
7
Launch
Allen
Horowitz
Hoffman
Cheli
Nicollier
Chang-Diaz
Guidoni
1
2
3
4
5
6
7
Landing
Allen
Horowitz
Nicollier
Cheli
Hoffman
Chang-Diaz
Guidoni
Flight
Mission "US Microgravity Payload-3" with several experiment in different sientific fields;
deploying of Italian Tethered Satellite System-1 failed, because the tether has broken after a
distance of 19 km; satellite was lost; mission was extended one day due of bad weather on
Cape Canaveral (KSC).
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STS 76
Publications
NSSDC ID: 1996-018A
Maps
New/Updated Data
Description
STS 76 was a US shuttle mission launched from Cape
Canaveral. The primary mission objective was the third
docking between the Space Shuttle Atlantis and the Russian
Space Station Mir. It included a crew transfer, an
extravehicular activity (EVA), logistics operations and scientific
research.
Rendezvous and docking with Mir was scheduled to occur on
flight day three using the same approach as previously used
during STS-74. Docking occured between the Orbiter Docking
System in the forward area of Atlantis' payload bay and the
Docking Module installed during STS-74 on Mir's Kristall
module docking port.
Alternate Names
23831
Facts in Brief
Launch
Vehicle: Shuttle
Launch Site: Cape
Mass: 6753.0 kg
Funding Agency
The mission also featured a SPACEHAB module, middeck
experiments, a Get Away Special (GAS) canister and a 6-hour
EVA. Over 1,900 pounds (862 kilograms) of equipment are
being transfered from Atlantis to Mir including a gyrodyne,
transformer, batteries, food, water, film and clothing.
Planned Experiments included the Mir Electric Field
Characterization (MEFC) experiment, numerious European
Space Agency's (ESA) Biorack life sciences experiments, the
Queen's University Experiment in Liquid Diffusion (QUELD)
experiment, the Optizone Liquid Phase Sintering Experiment
(OLIPSE) and a Naval Research Laboratory (NRL) Get Away
Special (GAS) payload Trapped Ions in Space (TRIS)
experiment. TRIS measured low-energy particle radiation in
the inner magnetosphere. Another experiment conducted on
Mir during STS-76 was the Mir Wireless Network Experiment
(WNE) which was launched on STS-74 in November 1995. It
tested the first wireless client-server network in the space
environment.
The mission also included KidSat, a prototype of Earth viewing
cameras and instruments that allows students in grades
Kindergarden to Grade 12 (K-12) to see and direct the capture
of pictures from space.
Mission Specialists Godwin and Clifford perform a six-hour
spacewalk on flight day six. They attached four experiments,
known collectively as the Mir Environmental Effects Payload
MEEP, onto handrails located on the Mir Docking Module.
These experiments include the Polished Plate Micrometeoroid
Debris (PPMD) experiment, the Orbital Debris Collector (ODC)
experiment, and the Passive Optical Samples (POSA) I and II
experiments.
Discipline
Human Crew
Additional
Information
Launch/Orbital
76
Office.
STS-76
Atlantis (16)
Launch date:
Launch time:
Launch site:
Launch pad:
Altitude:
Inclination:
Landing date:
Landing time:
Landing site:
22.03.1996
08:13 UT
39-B
296 km
51,6°
31.03.1996
13:28 UT
Edwards AFB
Crew
No
.
Surname
1
Chilton
2
Searfos
Richard Alan
s
Flight No.
Duration
Orbit
s
Given name
Job
Kevin Patrick "Chily"
CD
R
3
9d 05h 16m
144
PLT
2
9d 05h 16m
144
3
Sega
Ronald Michael
4
Clifford
Michael Richard Uram
"Rich"
5
Godwin
Linda Maxine
6
Lucid
Matilda Shannon Wells
MS
P
MS
P
MS
P
MS
P
2
9d 05h 16m
144
3
9d 05h 16m
144
3
9d 05h 16m
144
5
188d 04h 00m 2977
1
2
3
4
5
6
Launch
Chilton
Searfoss
Sega
Clifford
Godwin
Lucid
Landing
1 Chilton
2 Searfoss
3 Godwin
4 Clifford
5 Sega
6
Backup Crew
No.
6
Surname Given name Job
Blaha
John Elmer MSP
Flight
Launch from Cape Canaveral (KSC); landing on Edwards AFB; small leak of hydraulic fluid
from the hydraulic system, but no Minimum Duration Flight was necessary.
Docking on MIR spacestation; Shannon Lucid became member of the 21st resident crew
onboard the MIR (as research cosmonaut); during the common-flight of STS-76 and MIR
Godwin and Clifford performed an EVA on 27.03.1996 (6h 2m) to attach the Mir
Environmental Effects Payload (MEEP), including 4 different experiments, onto handrails
located on the Mir Docking Module; after 5 days of common flight separation.
Note
Lucid landed on 26.09.1996 at 12:13 UT with STS-79.
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STS 77
Publications
NSSDC ID: 1996-032A
Maps
New/Updated Data
Alternate Names
Description
STS 77 was a Shuttle Endeavour mission launched from Cape
Canaveral. The main mission was to release an inflatable
antenna, IAE. The release occurred from a platform called
Spartan 207 which in turn was released from the shuttle a few
hours later. The third object released was an experimental 35
kg minispacecraft, PAMS-STU. STS 77 carried the usual
complement of crystal, metal, and biomedical experimental
gear along with 32,000 sea urchin eggs and a supply of sperm
to squirt on them, all in the Spacelab module. A new fizzy
Coca-Cola delivering experimental device failed to perform
satisfactorily.
23870
Facts in Brief
Launch
Vehicle: Shuttle
Launch Site: Cape
Mass: 12233.0 kg
Funding Agency
Disciplines
Human Crew
Life Science
Additional
Information
Launch/Orbital
Telecommunications
77
Office.
STS-77
Endeavour (11)
USA
Launch date:
Launch time:
Launch site:
Launch pad:
Altitude:
Inclination:
Landing date:
Landing time:
Landing site:
19.05.1996
10:30 UT
39-B
283 km
39°
29.05.1996
11:09 UT
Crew
No.
Surname
1
Casper
Given name
John Howard
Job
Flight No.
CDR
4
Duration
10d 00h 40m
Orbits
161
2
Brown
3
Curtis Lee, Jr. "Curt"
PLT
3
10d 00h 40m
161
Thomas Andrew Sydney Withiel
MSP
1
10d 00h 40m
161
4
Bursch
Daniel Wheeler
MSP
3
10d 00h 40m
161
5
Runco
Mario, Jr. "Trooper"
MSP
3
10d 00h 40m
161
6
Garneau Joseph Jean-Marie Marc MSP
2
10d 00h 40m
161
1
2
3
4
5
6
Launch
Casper
Brown
Thomas
Bursch
Runco
Garneau
Landing
1 Casper
2 Brown
3 Runco
4 Bursch
5 Thomas
6 Garneau
Flight
Mission "Spacehab-4"; deploying and retrieval of a SPARTAN-satellite and deploying of a
PAMS/STU-satellite; several rendezvous-maneuvers with both satellites; various additional
experiments in different fields.
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STS 78
Publications
NSSDC ID: 1996-036A
Maps
New/Updated Data
Description
STS 78 was a NASA shuttle spacecraft launched from Cape
Canaveral for a 17 day mission. It carried a Spacelab (LMS-1)
with many supplies and instruments for 41 microgravity
experiments involving fish embryos, rats, Bonzai plants, fluid
dynamics, metallurgy, protein crystal growth, etc.
Five space agencies (NASA/USA; European Space
Agency/Europe; French Space Agency/France; Canadian
Space Agency/Canada; and Italian Space Agency/Italy) and
research scientists from 10 countries worked together on the
primary payload of STS-78, the Life and Microgravity Spacelab
(LMS). More than 40 experiments flown were grouped into two
areas: life sciences, which included human physiology and
space biology, and microgravity science, which included basic
fluid physics investigations, advanced semiconductor and
metal alloy materials processing, and medical research in
protein crystal growth.
LMS investigations were conducted via the most extensive
telescience to date. Investigators were located at four remote
European and four remote U.S. locations, similar to what will
happen with the International Space Station. The mission also
made extensive use of video imaging to help crew members
perform inflight maintenance procedures on the experiment
hardware.
Previous life science investigations have delved into what
physiological changes take place in microgravity environment;
the integrated LMS experiments explored why these changes
occur. The most extensive studies ever were conducted on
bone and muscle loss in space. STS-78 marked the first time
researchers collected muscle tissue biopsy samples both
before and after flight. Crew members also were scheduled to
undergo Magnetic Resonance Imaging (MRI) scans almost
immediately after landing. Findings from comparison of the
biopsy samples, along with various musculoskeletal tests
conducted during mission, could lead to effective
countermeasures to reduce inflight muscle atrophy.
Other life science investigations included: First ever
comprehensive study of sleep cycles, 24-hour circadian
rhythms and task performance in microgravity. Spacecraft
orbiting Earth pass through 16 sunrises and sunsets in single
24-hour period, which could disrupt normal body rhythms.
During two 72-hour time blocks, crew members completed
questionnaires and measured such functions as eye
movement and muscle activity during sleep. In the
Performance Assessment Work Station, crew members
performed a series of drills involving math problems and other
Alternate Names
23931
Facts in Brief
Launch
Vehicle: Shuttle
Launch Site: Cape
Funding Agency
Discipline
Human Crew
Additional
Information
Launch/Orbital
78
Office.
mental tests to measure the microgravity effects on cognitive,
or thinking, skills.
The microgravity science investigations included Advanced
Gradient Heating Facility, in which samples of pure aluminum
containing zirconia particles were solidified. This could lead to
more inexpensive ways to make mixtures of metals and
ceramics, particularly useful to the metal casting industry. The
Advanced Protein Crystallization Facility is the first ever
designed to use three methods for growing protein crystals. In
Electrohydrodynamics of Liquid Bridges, which focused on
changes that occur in a fluid bridge suspended between two
electrodes. This research could finds applications in industrial
processes where control of a liquid column or spray is used,
including in ink-jet printing.
The crew performed in-flight fixes to problem hardware on the
Bubble, Drop and Particle Unit (BDPU), designed to study fluid
physics.
The orbiter itself played a key part in a test that could help
raise the Hubble Space Telescope to a higher orbit in 1997
during the second servicing mission. Columbia's vernier
Reaction Control System jets were gently pulsed to boost the
orbiter's altitude without jarring payloads. The same exercise
could be conducted with orbiter Discovery during Mission STS82 to raise HST's orbit without impacting its solar arrays.
No significant in-flight problems were experienced with orbiter.
STS-78
Columbia (20)
USA
Launch date:
Launch time:
Launch site:
Launch pad:
Altitude:
Inclination:
Landing date:
Landing time:
Landing site:
20.06.1996
14:49 UT
39-B
278 km
39°
07.07.1996
12:37 UT
Crew
No.
Surname
Given name
Job
Flight No.
Duration
Orbits
1
Henricks Terence Thomas "Tom" CDR
4
16d 21h 48m
271
2
Kregel
2
16d 21h 48m
271
Kevin Richard
PLT
3
Linnehan Richard Michael
MSP
1
16d 21h 48m
271
4
Helms
Susan Jane
MSP
3
16d 21h 48m
271
5
Brady
Charles Eldon, Jr.
MSP
1
16d 21h 48m
271
6
Favier
Jean-Jacques
PSP
1
16d 21h 48m
271
7
Thirsk
Robert Brent
PSP
1
16d 21h 48m
271
1
2
3
4
5
6
7
Launch
Henricks
Kregel
Linnehan
Helms
Brady
Favier
Thirsk
Landing
1 Henricks
2 Kregel
3 Brady
4 Helms
5 Linnehan
6 Favier
7 Thirsk
Backup Crew
No.
Surname
Given name
Job
6
Duque
Pedro Francisco PSP
7
Urbani
Luca
PSP
Flight
Mission "Life and Microgravity Spacelab"; experiments in the areas of life science and
materials science; experiments for planned long-duration mission onboard the ISS; longest
Shuttle-flight to date.
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STS 79
Publications
NSSDC ID: 1996-057A
Maps
New/Updated Data
Description
STS 79 was the 79th Shuttle mission, the 4th Shuttle-Mir
docking, the 1st US crew exchange, and the 32nd KSC
landing. The mission was highlighted by the return to Earth of
US astronaut Shannon Lucid after 188 days in space which
set a new US record for long-duration as well as a world
record for a woman. Succeeding her on Mir for an
approximately four-month stay was Mission Specialist John E.
Blaha who returned with the STS 81 crew.
STS 79 marked the second flight of the SPACEHAB module in
support of the Shuttle-Mir activities and first flight of the
SPACEHAB Double Module configuration. During 5 days of
mated operations, two crews transferred more than 4,000
pounds (1,814 kg) of supplies to Mir, including logistics, food
and water generated by orbiter fuel cells. Three experiments
also were transferred: Biotechnology System (BTS) for study
of cartilage development; Material in Devices as
Superconductors (MIDAS) to measure electrical properties of
high- temperature superconductor materials; and Commercial
Generic Bioprocessing Apparatus (CGBA), containing several
smaller experiments, including self- contained aquatic systems.
About 2,000 pounds (907 kg) of experiment samples and
equipment were transferred from Mir to Atlantis. During her
approximately six-month stay on Mir, Lucid conducted research
in the following fields: advanced technology, Earth sciences,
fundamental biology, human life sciences, microgravity
research and space sciences. Specific experiments included:
Environmental Radiation Measurements to ascertain ionizing
radiation levels aboard Mir; Greenhouse- Integrated Plant
Experiments, to study the effects of microgravity on plants,
specifically dwarf wheat; and Assessment of Humoral Immune
Function During Long-Duration Space flight, to gather data on
the effect of long-term spaceflight on the human immune
system and involving the collection of blood serum and saliva
samples. Some research was conducted in the newest and
final Mir module, Priroda, which arrived at the space station
during Lucid's stay.
Three experiments remained on Atlantis: Extreme Temperature
Translation Furnace (ETTF), a new furnace design allowing
space-based processing up to 871 degrees F (1,600 degrees
C) and above; Commercial Protein Crystal Growth (CPCG)
complement of 128 individual samples involving 12 different
proteins; and Mechanics of Granular Materials, designed to
further understanding of behavior of cohesionless granular
materials, which could in turn lead to better understanding of
how the Earth's surface responds during earthquakes and
landslides.
Alternate Names
24324
Facts in Brief
Launch
Vehicle: Shuttle
Launch Site: Cape
Funding Agency
Discipline
Human Crew
Additional
Information
Launch/Orbital
79
Office.
STS 79's crew consisted of the following:
Commander : Willaim F. Readdy (3rd Shuttle flight) Pilot :
Terrence W. Wilcutt (2) Mission Specialist : Tom Akers (4)
Mission Specialist : Jay Apt (4) Mission Specialist : Carl E.
Walz (3) Mission Specialist : John E. Blaha (5)
STS-79
Atlantis (17)
USA
Launch date:
Launch time:
Launch site:
Launch pad:
Altitude:
Inclination:
Landing date:
Landing time:
Landing site:
16.09.1996
08:54 UT
39-A
315 - 394 km
51,6°
26.09.1996
12:13 UT
Crew
No.
Surname
Given name
Job
Flight No.
Duration
Orbits
1
Readdy William Francis "Bill" CDR
3
10d 03h 19m
160
2
Wilcutt
Terrence Wade
PLT
2
10d 03h 19m
160
3
Apt
Jerome "Jay"
MSP
4
10d 03h 19m
160
4
Akers
Thomas Dale
MSP
4
10d 03h 19m
160
5
Walz
Carl Erwin
MSP
3
10d 03h 19m
160
6
Blaha
John Elmer
MSP
5
128d 05h 28m 2027
1
2
3
4
5
6
Launch
Readdy
Wilcutt
Apt
Akers
Walz
Blaha
Landing
1 Readdy
2 Wilcutt
3 Walz
4 Akers
5 Apt
6 Lucid
Backup Crew
No.
6
Surname Given name
Job
Linenger Jerry Michael MSP
hi res version (880 KB)
Flight
Fourth docking with MIR space station; common mission with the 22. MIR resident crew (19.
- 24.09.1996); partly crew exchange with MIR resident crew (Shannon Lucid returned to
Earth, Blaha remained on MIR); supplies and equipment were also transferred between the
MIR and the Shuttle including an IMAX-camera.
Note
Blaha returned to Earth on 22.01.1997 at 14:23 UT with STS-81.
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STS 80
Publications
NSSDC ID: 1996-065A
Maps
New/Updated Data
Description
The final shuttle flight of 1996 was highlighted by the
successful deployment, operation and retrieval of two freeflying research spacecraft. Two planned extravehicular
activities (EVAs) were cancelled.
Orbiting and Retrievable Far and Extreme Ultraviolet
Spectrometer-Shuttle Pallet Satellite II (ORFEUS-SPAS-II)
was deployed on flight day one and began approximately two
weeks of data gathering. It featured three primary scientific
instruments: the ORFEUS-Telescope with the Far Ultraviolet
(FUV) Spectrometer and Extreme Ultraviolet (EUV)
Spectrograph. A secondary but highly complementary payload
was the Interstellar Medium Absorption Profile Spectrograph
(IMAPS). Non-astronomy payloads included the Surface
Effects Sample Monitor (SESAM), the ATV Rendezvous PreDevelopment Project (ARP) and the Student Experiment on
ASTRO-SPACE (SEAS).
The Wake Shield Facility-3 (WSF-3) was deployed on flight
day 4. It was a 12-foot diameter, free-flying stainless steel disk
designed to generate an ultravacuum environment in which to
grow semiconductor then films for use in advanced electronics.
This third flight was successful, with a maximum of seven film
growths of semiconductor materials achieved and the satellite
hardware performing nearly flawlessly. It was retrieved after
three days of free-flight.
Two planned six-hour EVAs by astronauts Jernigan and Jones
were designed to evaluate equipment and procedures that
would be used during construction and maintenance of the
International Space Station. However, the crew could not open
the outer airlock hatch and when troubleshooting did not reveal
the cause, mission managers concluded that it would not be
prudent to attempt the two EVAs and risk unnecessary
damage to the hatch or seals.
Other experiments included the Space Experiment Module
(SEM) which provided increased educational access to space;
NIH-R4, the fourth in a series of collaborative experiments
developed by NASA and the National Institutes of Health, to
investigate the role of calcium in blood pressure regulation;
NASA/CCM-A, one of a series of shuttle bone cell
experiments; Biological Research in Canister (BRIC)-09
experiment to study the influence of microgravity on
genetically-altered tomato and tobacco seedlings; Commercial
MDA ITA experiment (CMIX-5), the last in a series of shuttle
experiments; and Visualization in an Experimental Water
Capillary Pumped Loop (VIEW-CPL), a middeck experiment to
investigate the method for spacecraft thermal management.
Alternate Names
24660
Facts in Brief
Launch
Vehicle: Shuttle
Launch Site: Cape
Funding Agency
Discipline
Human Crew
Additional
Information
Launch/Orbital
80
Office.
The crew consisted of the following:
Kenneth D. Cockrell - Commander Kent V. Rominger - Pilot
Tamara E. Jernigan - Mission Specialist Thomas D. Jones Mission Specialist Story Musgrave - Mission Specialist
STS-80
Columbia (21)
USA
Launch date:
Launch time:
Launch site:
Launch pad:
Altitude:
Inclination:
Landing date:
Landing time:
Landing site:
19.11.1996
19:55 UT
39-B
351 km
28,45°
07.12.1996
11:49 UT
Crew
No
.
Surname
1
Cockrell
2
3
Given name
Kenneth Dale "Taco"
Rominge
Kent Vernon
r
Tamara Elizabeth
Jernigan
"Tammy"
Job
Flight No.
Duration
Orbit
s
CD
R
3
17d 15h 53m
279
PLT
2
17d 15h 53m
279
MS
P
4
17d 15h 53m
279
4
Jones
Thomas David
5
Musgrav
e
Franklin Story
MS
P
MS
P
3
17d 15h 53m
279
6
17d 15h 53m
279
1
2
3
4
5
Launch
Cockrell
Rominger
Jernigan
Jones
Musgrave
1
2
3
4
5
Landing
Cockrell
Rominger
Musgrave
Jones
Jernigan
Flight
Mission ORFEUS-SPAS-02; two planned EVA's were cancelled, because a hatch couldn't be
opened; deploying and retrieval of German built astronomy-satellite ORFEUS-SPAS-02 and
of the Wake Shield Facility (WSF 03); several secondary experiments; longest Shuttlemission to date, landing was postponed due of bad weather at landing site; Musgrave
became the oldest astronaut to date flying into space.
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STS/SRL 3
Publications
NSSDC ID: SRL3
Maps
New/Updated Data
Description
The Space Radar Laboratory 3 (SRL 3) was the third in a
series of flights of this payload which was designed to (1)
acquire radar imagery of the Earth's surface for studies in
geology, geography, hydrology, oceanography, agronomy, and
botony; (2) gather data for future space-borne radar systems
including Earth Observing System (EOS); and (3) provide
measurements of the global distribution of carbon dioxide
(CO2) in the troposphere. Instruments on board included the
Shuttle Imaging Radar-C (SIR-C) with multi-frequency (C- and
L-Bands), multi-polarization (HH, VV, HV, VH), and multiincidence angle (15 to 55 degrees) capabilities thus lending
itself to a wide range of earth surface applications; the X-band
Synthetic Aperture Radar (X-SAR), an X-band, VV-polarized
imaging radar system, built by Dornier (Germany) and Alenia
(Italy) for the German Space Agency (DARA)/German
Aerospace Research Establishment (DLR) and the Italian
Space Agency (ASI); and, the Mapping Air Pollution from
Space (MAPS) for the study of global air pollution. Also, onboard the SRL, was an ocean wave spectra processor,
designed and built by Johns Hopkins Applied Physics
Laboratory, which collected data on ocean surface wave
length, direction, and height. Four 45-Mbps data channels
were recorded on special high data rate tape recorders and
real-time data was transmitted to ground stations. About 50
hours each of SIR-C and X-SAR data were recorded during
the mission. The combined SIR-C/X-SAR Science Team was
made up of 49 members and 3 associates representing 13
countries. SIR-C/X-SAR data collection was focused on
several worldwide supersites and correlated with ground and
aircraft measurements. Radar data was also calibrated to allow
comparisons with other operating spaceborne radars (ERS-1
SAR, JERS-1 SAR).
Alternate Names
SRL 3/STS
Shuttle Radar Lab 3
Space Radar Lab 3
SIR-C/X-SAR
Facts in Brief
Launch
Vehicle: Shuttle
Launch Site: Cape
Mass: 12094.0 kg
Funding Agencies
Agenzia Spaziale Italiana
(Italy)
(United States)
Bundesministerium fuer
Forschung und
Tecnnologie (Federal
Republic of Germany)
Discipline
Earth Science
Additional
Information
Launch/Orbital
information for STS/SRL
3
STS/SRL 3
Telecommunications
information for STS/SRL
3
Experiments on STS/SRL
3
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=SRL3[08/06/2011 23:42:33]
STS/SRL 3
Office.
Personnel
Name
Role
E-mail
Mr. Richard M.
Monson
Program
Manager
NASA Headquarters
Dr. Paulo
Pampaloni
Project
Scientist
Consiglio Nazionale delle
Ricerche
[email protected]
Dr. Diane L.
Evans
Project
Scientist
NASA Jet Propulsion
Laboratory
[email protected]
Dr. Manfred
Wahl
Project
Manager
Deutsche Agentur fur
Ramfahrt-Angelegenheiten
[email protected]
Dr. Herwig Ottl
Project
Scientist
Deutsche Forschungsenstalt
fuer Luft-und Raumfahrt
[email protected]
Dr. Paulo
Ammendola
Deputy
Project
Manager
Italian Space Agency
[email protected]
Dr. George F.
Esenwein, Jr.
Program
Manager
NASA Headquarters
Mr. R. Wayne
Richie
Program
Manager
NASA Headquarters
Dr. Robert J.
McNeal
Program
Scientist
NASA Headquarters
Mr. Michael J.
Sander
Project
Manager
NASA Jet Propulsion
Laboratory
Selected References
Jordan, R. L., et al., SIR-C/X-SAR synthetic aperture radar system, IEEE Proc., 79, No. 6, 827838, June 1991.
Evans, D. L., et al., The Shuttle Imaging Radar-C and X-SAR mission, EOS, 74, No. 13, Mar.
1993.
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=SRL3[08/06/2011 23:42:33]
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TELECOM 2D
Publications
NSSDC ID: 1996-044B
Maps
New/Updated Data
Alternate Names
Description
TELECOM 2D was a French geosynchronous satellite
launched from the Kourou space center in French Guiana
aboard an Ariane 44L rocket. It provided voice and video
communications to western Europe.
24209
Facts in Brief
44L
French Guiana
Funding Agency
France Telecom (France)
Discipline
Communications
Additional
Information
Launch/Orbital
information for TELECOM
2D
Experiments on TELECOM
2D
TELECOM 2D
Office.
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TOMS-EP
Publications
NSSDC ID: 1996-037A
Maps
New/Updated Data
Description
The goal of the Total Ozone Mapping Spectrometer (TOMS)
Earth Probe mission (part of NASA's Mission To Planet Earth
(MTPE) Phase I program) was to continue the high-resolution
global mapping of total ozone on a daily basis (begun with the
Nimbus 7 SBUV/TOMS) as well as to detect global ozone
trends to verify depletion predicted by atmospheric chemistry
models.
The TOMS-Earth Probe (TOMS-EP), the first of a series of
NASA Earth Probe missions, was one of three TOMS missions
which included METEOR 3/TOMS2 (launched 1991) and
ADEOS/TOMS (launched 1995). The TOMS-EP carried only
one instrument: the Total Ozone Mapping Spectrometer
(TOMS).
The TOMS-EP spacecraft was based on the TRW/DSI Eagle
bus developed under the USAF STEP program. The
spacecraft was three-axis stabilized so that the TOMS
instrument was nadir-pointed with about 0.5 degree control
and about 0.1 degree knowledge from measured altitude data.
The TOMS-EP spacecraft bus was designed to accomodate all
of the TOMS instrument requirements to support a two-year
lifetime with a three-year lifetime goal.
Alternate Names
SMEX/TOMS-Earth
Probe
Small Explorer/TOMSEarth Probe
TOMS-EP96
TOMS-Earth Probe
23940
Facts in Brief
Launch
Vehicle: Pegasus XL
Launch
United States
Mass: 248.0 kg
Funding Agency
(United States)
Discipline
Earth Science
Additional
Information
Launch/Orbital
information for TOMS-EP
TOMS-EP
Telecommunications
information for TOMS-EP
Experiments on TOMS-EP
TOMS-EP
Office.
Personnel
Name
Role
Dr. Robert
Douglas
Hudson
Project
Scientist
NASA Goddard Space
Flight Center
Dr. George F.
Esenwein, Jr.
Program
Manager
NASA Headquarters
Mr. Donald L.
Margolies
Project
Manager
NASA Goddard Space
Flight Center
E-mail
[email protected]
NSSDC Master
Catalog Search
Spacecraft
Experiments
Data Collections
Personnel
TSS-1R
Publications
NSSDC ID: 1996-012B
Maps
New/Updated Data
Description
The TSS-1R mission is a reflight of the Tethered Satellite TSS1 that had been flown on the Space Shuttle mission STS-46 in
July of 1992. A protruding bolt had prevented full release of
the tether during the TSS-1 mission. The TSS mission
equipment consists of the deployer system, the Italian-build
satellite, the electrically conductive tether (22km total length)
and 6 science instruments. The TSS-1 is to be deployed from a
reel in the orbiter payload bay upward (away from Earth) to up
to 20 Km (12.5 miles) above the Orbiter. The objectives of this
mission are: (1) to verify engineering performance of the
Tethered Satellite System (TSS); (2) to determine and to
understand the electro-magnetic interaction between the
tether/satellite/orbiter system and the ambient space plasma;
(3) to investigate and to understand the dynamical forces
acting upon a tethered satellite; (4) to demonstrate electrical
power generation; and, (5) to develop the capability for future
tether applications on the Shuttle and Space Station. The
deploying system consists of a motor- driven tether storage
reel and level wind system. A separate multipurpose
equipment support structure (MPESS) carries all science
instruments not integrated on the satellite, with the exception
of the Tethered Optical Phenomena (TOP) equipment, which is
carried in the crew compartment. The spherical satellite is 1.6
meters in diameter and 6.5 meters in length. The S-band
antenna, magnetometers, and Research on Orbital Plasma
Electrodynamics (ROPE) equipment are mounted on stationary
booms, and the Research on Electrodynamic Tether Effects
(RETE) Langmuir probe and dipole field antenna are mounted
on 2.5 meter deployable/retractable booms. At the base of the
satellite, a swivel joint and a bayonet pin attache the tether to
the satellite. A connector routes the tether conductor to an
ammeter and then to the satellite's skin. The satellite contained
cold gas (nitrogen) thrusters used for deployment, retrieval,
and attitude control. The 2.54 mm diameter conducting tether
was constructed using Kevlar and Nomex with 10 strands of
34 AWG copper wire and a Teflon sheath. NASA is reponsible
for the TSS deployer and systems integration, and Italy for
building the satellite. Five hours after deployment began on
February 25, 1996, with 19.7 km (of 20.7 planned) of tether
released, the tether cable suddenly snapped near the top of
the deployment boom. The TSS satellite shot away into a
higher orbit. TSS instruments could be re-actived and
produced science data for three days until battery power ran
out. An independent review panel was formed to review the
TSS-1R failure.
Alternate Names
Tethered Satellite System
1R
23805
Facts in Brief
Launch
Vehicle: Shuttle
Launch Site: Cape
Mass: 518.0 kg
Funding Agencies
Piano Spaziale Nazionale
of CNR (Italy)
(United States)
Disciplines
Engineering
Space Physics
Additional
Information
Launch/Orbital
information for TSS-1R
TSS-1R
Telecommunications
information for TSS-1R
Experiments on TSS-1R
Data collections from TSS1R
Bilitza.
Personnel
Name
Role
E-mail
Mr. Robert O.
McBrayer
Project
Manager
NASA Marshall Space
Flight Center
Prof. Franco
Mariani
Program
Scientist
Ricerche
[email protected]
Dr. Michael A.
Calabrese
Program
Manager
NASA Headquarters
[email protected]
Mr. Nobie H.
Stone
Project
Scientist
NASA Marshall Space
Flight Center
Mr. James M.
Sisson
Mission
Manager
NASA Marshall Space
Flight Center
Dr. Robert A.
Hoffman
Program
Scientist
NASA Goddard Space
Flight Center
[email protected]
Prof. Marino
Dobrowolny
Program
Scientist
Ricerche
[email protected]
Dr. G. Manarini
Program
Manager
Ricerche
Dr. Stanley D.
Shawhan
Program
Scientist
NASA Headquarters
Other TSS-1R Data/Information at NSSDC
Independant panel formed to review TSS-1R loss (02/26/96)
Early results from TSS-1R may cause revision to theory (05/23/96)
Report on TSS-1R tether failure released (06/04/96)
STS 75
TSS-1
Other Sources of TSS-1R Information/Data
TSS home page
NSSDC Master
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Spacecraft
Experiments
Data Collections
Personnel
Turksat 1C
Publications
NSSDC ID: 1996-040B
Maps
New/Updated Data
Alternate Names
Description
Turksat 1C was a Turkish geosynchronous communications
satellite that was launched by an Ariane 44L rocket from the
Kourou site in French Guiana. After parking at 42 deg E, the
spacecraft provided radio and TV communications to Turkey
and neighboring countries.
23949
Facts in Brief
44L
French Guiana
Mass: 2100.0 kg
Funding Agency
Unknown (Turkey)
Discipline
Communications
Additional
Information
Launch/Orbital
information for Turksat
1C
Experiments on Turksat 1C
Turksat 1C
Office.
NSSDC Master
Catalog Search
Spacecraft
Experiments
Data Collections
Personnel
UFO 7
Publications
NSSDC ID: 1996-042A
Maps
New/Updated Data
Alternate Names
Description
UFO 7 (UHF Follow On 7) was a US Navy satellite launched to
replace the FLTSATCOM and Leasat spacecraft currently
supporting the Navy's global communications network, serving
ships at sea and a variety of other US military fixed and mobile
terminals. It was compatible with ground- and sea-based
terminals already in service.
The UHF F/O satellites offered increased communications
channel capacity over the same frequency spectrum used by
previous systems. Each spacecraft had 11 solid-state UHF
amplifiers and 39 UHF channels with a total of 555 kHz
bandwidth. The UHF payload compresed 21 narrow band
channels at 5 kHz each and 17 relay channels at 25 kHz. In
comparison, FLTSATCOM offered 22 channels. The F-1
through F-7 spacecraft included an SHF (super high frequency)
subsystem, which provided command and ranging capabilities
when the satellite was on station as well as the secure uplink
for Fleet Broadcast service, which was downlinked at UHF.
Each satellite measured more than 60 feet long from the tip of
one three-panel solar array wing to the tip of the other. These
arrays generated a combined 2500 watts of electrical power on
the first three satellites, 2800 watts for F-4 through F-7, and
3800 watts for F-8 through F-10 with GBS. The arrays were
folded against the spacecraft bus for launch, forming a cube
roughly 11 feet per side.
USA 127
UHF Follow On 7
23967
Facts in Brief
Launch Vehicle: Atlas 2
Launch Site: Cape
Mass: 3015.0 kg
Funding Agency
(United States)
Disciplines
Communications
Military
Additional
Information
Launch/Orbital
information for UFO 7
Experiments on UFO 7
Data collections from UFO
7
Office.
NSSDC Master
Catalog Search
Spacecraft
Experiments
Data Collections
Personnel
UNAMSAT-B
Publications
NSSDC ID: 1996-052B
Maps
New/Updated Data
Alternate Names
Description
A secondary payload launched with Cosmos 2334 was the
UNAMSAT-B small satellite, for the Automonous University of
Mexico (UNAM). It repaced a satellite lost in a launch failure in
1995. It used the 25 cm AMSAT Microsat bus and carried an
experiment to determine the velocity of meteors using radio
doppler echo, and a communications data relay for
environmental sensors in remote locations.
OSCAR 30
24305
Facts in Brief
Launch
Vehicle: Cosmos
Russia
Mass: 10.0 kg
Funding Agency
Automonous University of
Mexico (Mexico)
Disciplines
Communications
Space Physics
Additional
Information
Launch/Orbital
information for
UNAMSAT-B
Experiments on
UNAMSAT-B
UNAMSAT-B
Office.
NSSDC Master
Catalog Search
Spacecraft
Experiments
Data Collections
Personnel
USA 118
Publications
NSSDC ID: 1996-026A
Maps
New/Updated Data
Alternate Names
Description
USA 118 was an American military (USAF) electronic
inteligence satellite launched from Cape Canaveral aboard a
Titan 4 rocket.
23855
Facts in Brief
IV
Launch Site: Cape
Funding Agency
Discipline
Military
Additional
Information
Launch/Orbital
information for USA 118
Experiments on USA 118
Data collections from USA
118
Office.
NSSDC Master
Catalog Search
Spacecraft
Experiments
Data Collections
Personnel
USA 119
Publications
NSSDC ID: 1996-029A
Maps
New/Updated Data
Alternate Names
Description
This US Navy Ocean Surveillance Satellite (NOSS) was
launched from Vandenberg AFB aboard an Atlas E/F rocket. It
placed a cluster of one primary satellite and three smaller subsatellites (that trailed along at distances of several hundred
kilometers) into low polar orbit. This satellite array determined
the location of radio and radars transmitters, using
triangulation, and the identity of naval units, by analysis of the
operating frequencies and transmission patterns.
SDS-2
23893
Facts in Brief
IV
Launch Site: Cape
Mass: 700.0 kg
Funding Agency
Discipline
Military
Additional
Information
Launch/Orbital
119
Office.
NSSDC Master
Catalog Search
Spacecraft
Experiments
Data Collections
Personnel
USA 120
Publications
NSSDC ID: 1996-029B
Maps
New/Updated Data
Alternate Names
Description
USA 120 was a naval reconnaisance, electronic intelligence
satellite launched from Vandenberg AFB aboard a Titan 4
rocket along with USA 119, 121 - 124.
23907
Facts in Brief
IV
Launch Site: Cape
Funding Agency
Discipline
Military
Additional
Information
Launch/Orbital
120
Office.
NSSDC Master
Catalog Search
Spacecraft
Experiments
Data Collections
Personnel
USA 121
Publications
NSSDC ID: 1996-029C
Maps
New/Updated Data
Alternate Names
Description
USA 121 was a US Naval reconnaisance satellite, part of the
NOSS 2 series, launched from Vandenberg AFB aboard a
Titan 4 rocket along with USA 119, 120, 122 - 124.
23908
Facts in Brief
IV
Launch Site: Cape
Funding Agency
(United States)
Discipline
Military
Additional
Information
Launch/Orbital
121
Office.
NSSDC Master
Catalog Search
Spacecraft
Experiments
Data Collections
Personnel
USA 122
Publications
NSSDC ID: 1996-029D
Maps
New/Updated Data
Alternate Names
Description
USA 122 was a US naval reconnaisance satellite, part of the
Titan 4 rocket along with USA 119 - 121, 123 and 124.
23862
Facts in Brief
IV
Launch Site: Cape
Funding Agency
(United States)
Discipline
Military
Additional
Information
Launch/Orbital
122
Office.
NSSDC Master
Catalog Search
Spacecraft
Experiments
Data Collections
Personnel
USA 123
Publications
NSSDC ID: 1996-029E
Maps
New/Updated Data
Alternate Names
Description
USA 123 was a naval tether spacecraft launched from
Vandenberg AFB aboard a Titan 4 rocket along with USA 119 122 and 124.
23936
Facts in Brief
IV
Launch Site: Cape
Funding Agency
(United States)
Discipline
Military
Additional
Information
Launch/Orbital
123
Office.
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-029E[08/06/2011 23:50:12]
NSSDC Master
Catalog Search
Spacecraft
Experiments
Data Collections
Personnel
USA 124
Publications
NSSDC ID: 1996-029F
Maps
New/Updated Data
Alternate Names
Description
USA 124 was a naval reconnaisance satellite, part of the
Titan 4 rocket along with USA 119 - 123.
23937
Facts in Brief
IV
Launch Site: Cape
Funding Agency
(United States)
Discipline
Military
Additional
Information
Launch/Orbital
124
Office.
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-029F[08/06/2011 23:50:33]
NSSDC Master
Catalog Search
Spacecraft
Experiments
Data Collections
Personnel
USA 125
Publications
NSSDC ID: 1996-038A
Maps
New/Updated Data
Alternate Names
Description
USA 125 was an Air Force surveillance satellite launched by a
Titan 4 rocket from Cape Canaveral. It was part of the NOSS
program.
23945
Facts in Brief
IV
Launch Site: Cape
Mass: 700.0 kg
Funding Agency
Discipline
Military
Additional
Information
Launch/Orbital
125
Office.
NSSDC Master
Catalog Search
Spacecraft
Experiments
Data Collections
Personnel
WSF 3
Publications
NSSDC ID: 1996-065C
Maps
New/Updated Data
Alternate Names
Description
WSF 3 (Wake Field Facility 3) is an American microgravity
module that was released from STS 80. The four-meter
diameter, 2,000 kg steel saucer was to grow ultra-purity
semiconductors on its rear side where the module's wake is an
ultra-vacuum. Its orbital parameters were very close to those
of STS 80. It was recaptured by the shuttle on the 26
November 1996.
Wake Shield Facility 3
24662
Facts in Brief
Launch
Vehicle: Shuttle
Launch Site: Cape
Mass: 2000.0 kg
Funding Agency
Discipline
Microgravity
Additional
Information
Launch/Orbital
information for WSF 3
Experiments on WSF 3
Data collections from WSF
3
Office.

NASA - NSSDC - Master Catalog

Transcripción

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