nasa - nssdc - master catalog - spacecraft query · 2011. 8. 4. · nasa . nasa - nssdc -...

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

http://nssdc.gsfc.nasa.gov/nmc/spacecraftSearch.do;jsessionid=ABABABE2C8FD0DDCC524D293AE803D49[28/05/2011 23:19:27]

Saturday, 28 May 2011

Spacecraft Query Results

There were 108 spacecraft returned.

Spacecraft Name NSSDC ID Launch Date

ADEOS 1996-046A 1996-08-16

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

NSSDC MasterCatalog Search

Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data

Lunar/Planetary Events

http://www.nasa.gov/

http://nssdc.gsfc.nasa.gov/nmc/SpacecraftQuery.jsp

http://nssdc.gsfc.nasa.gov/nmc/ExperimentQuery.jsp

http://nssdc.gsfc.nasa.gov/nmc/DatasetQuery.jsp

http://nssdc.gsfc.nasa.gov/nmc/PersonQuery.jsp

http://nssdc.gsfc.nasa.gov/nmc/PublicationQuery.jsp

http://nssdc.gsfc.nasa.gov/nmc/MapQuery.jsp

http://nssdc.gsfc.nasa.gov/nmc/NewDataQuery.jsp

http://nssdc.gsfc.nasa.gov/nmc/EventQuery.jsp



INTELSAT 7 F-7 1996-015A 1996-03-13

INTELSAT 709 1996-035A 1996-06-14

Interball Auroral Probe 1996-050C 1996-08-28

IRS-P3 1996-017A 1996-03-20

Italsat 2 1996-044A 1996-08-07

JAS 2 1996-046B 1996-08-16

KH 12-3 1996-072A 1996-12-19

Koreasat 2 1996-003A 1996-01-13

Magion 5 1996-050B 1996-08-28

Mars 96 Orbiter 1996-064A 1996-11-15

Mars 96 Penetrator MARS96D 1996-11-15

Mars 96 Penetrator MARS96E 1996-11-15

Mars 96 Surface Station MARS96B 1996-11-15

Mars 96 Surface Station MARS96C 1996-11-15

Mars Global Surveyor 1996-062A 1996-11-06

Mars Pathfinder 1996-068A 1996-12-03

Mars Pathfinder Rover MESURPR 1996-12-03

MEASAT 1 1996-002B 1996-01-11

MEASAT 2 1996-063B 1996-11-12

Microsat 1996-050A 1996-08-28

Molniya 1-89 1996-045A 1996-08-13

Molniya 3-48 1996-060A 1996-10-23

MSAT 1 1996-022A 1996-04-19

MSTI 3 1996-031A 1996-05-16

MSX 1996-024A 1996-04-23

N-Star-B 1996-007A 1996-02-04

Navstar 2A-16 1996-019A 1996-03-27

Navstar 2A-17 1996-041A 1996-07-15

Navstar 2A-18 1996-056A 1996-09-11

NEAR Shoemaker 1996-008A 1996-02-16

OAST Flyer 1996-001B 1996-01-10

ORFEUS-SPAS II 1996-065B 1996-11-19

OSL OSL 1995-12-31

Palapa C-1 1996-006A 1996-01-31

Palapa C-2 1996-030A 1996-05-15

PAMS-STU 1996-032D 1996-05-21

PANAMSAT 3R 1996-002A 1996-01-11

Polar 1996-013A 1996-02-23

Priroda 1996-023A 1996-04-22

Progress M-31 1996-028A 1996-05-04

Progress M-32 1996-043A 1996-07-30

Progress M-33 1996-066A 1996-11-18

Raduga 33 1996-010A 1996-02-18

REX 2 1996-014A 1996-03-08

SAC-B 1996-061B 1996-11-03

SAX 1996-027A 1996-04-29

Soyuz-TM 23 1996-011A 1996-02-20

Soyuz-TM 24 1996-047A 1996-08-17

Spartan 207 1996-032B 1996-05-19



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 GrayzeckCurator: E. Bell, IIVersion 4.0.16, 26 April 2011

http://www.usa.gov/

http://www.nasa.gov/about/highlights/HP_Privacy.html


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NASA - NSSDC - Spacecraft - Details

http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-046A[30/05/2011 22:47:16]

Monday, 30 May 2011

Description

The Japanese Advanced Earth Observing Satellite (ADEOS)was developed to establish platform technology for EarthObserving System (EOS) spacecraft and inter-orbitcommunication technology for the transmission of Earthobservation data. In addition, ADEOS contributed globalobservation of environmental change to the internationalcommunity during the pre-EOS era. NASA's Mission to PlanetEarth (MTPE) program contributed two instruments for theADEOS mission.

ADEOS was a sun-synchronous, morning equator-crossing (indescending node at about 10:30 a.m.), polar orbitingspacecraft. It had a modular type shape with a deployable onewing solar paddle. The body measured 4 x 4 x 5 m and thesolar paddle was 3 x 13 m in size.

ADEOS was three-axis stabilized by a zero momentum strap-down attitude-control system. Attitude was maintained by fourreaction wheels, two magnetometers, an inertial reference unit,and two hydrazine thrusters. Power was provided by a singlegallium arsenide flexible solar paddle and five 35 A-hr NiCdbatteries. Data was transmitted via direct transmission andinter-orbit communication through ETS-6. A Mission DataRecorder system on-board ADEOS stored high data rate andlow data rate data on separate tape recorders.

Eight experiments on ADEOS included: (1) Ocean Color andTemperature Scanner (OCTS), a NASDA core instrument; (2)Advanced Visible and Near-Infrared Radiometer (AVNIR), aNASDA core instrument; (3) NASA Scatterometer (NSCAT), aNASA/MTPE-provided instrument; (4) Total Ozone MappingSpectrometer (TOMS), a NASA/MTPE provided instrument; (5)Polarization and Directionality of the Earth's Reflectances(POLDER), provided by CNES of France; (6) InterferometricMonitor for Greenhouse Gases (IMG), provided by MITI ofJapan; (7) Improved Limb Atmospheric Spectrometer (ILAS),provided by Environmental Agency of Japan; and, (8)Retroreflector in Space (RIS), provided by the EnvironmentalAgency of Japan.

The design lifetime for this mission was three years, but thespacecraft ceased operating on 30 June 1997 for as yetunknown reasons. Subsequent flights of ADEOS are plannedduring the EOS era.

ADEOS

NSSDC ID: 1996-046A

Alternate Names

Midori

Advanced EarthObserving Satellite

24277

Facts in Brief

Launch Date: 1996-08-16Launch Vehicle: H-2LaunchSite: Tanegashima, JapanMass: 3500.0 kgNominalPower: 5000.0 W

Funding Agency

National SpaceDevelopment Agency(NASDA) (Japan)

Discipline

Earth Science

AdditionalInformation

Launch/Orbitalinformation for ADEOS

PDMP information forADEOS

Telecommunicationsinformation for ADEOS

Experiments on ADEOS

Data collections fromADEOS

Questions or commentsabout this spacecraft canbe directed to: Coordinated


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data



http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1996-046A


http://nssdc.gsfc.nasa.gov/nmc/spacecraftPdmp.do?id=1996-046A


http://nssdc.gsfc.nasa.gov/nmc/spacecraftTelemetry.do?id=1996-046A


http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=ADEOS

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=ADEOS

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=ADEOS

mailto:[email protected]?Subject=NMC Comment/Question: ADEOS (1996-046A)











Request and User SupportOffice.

Personnel

Name Role Original Affiliation E-mail

Dr. RobertDouglasHudson

ProjectScientist

NASA Goddard Space FlightCenter

Dr. WilliamC. Patzert

ProgramScientist

NASA Headquarters [email protected]

Dr. Robert T.Watson

ProgramScientist

NASA Headquarters

Mr. K.Yoneyama

ProjectDirector

National Space DevelopmentAgency of Japan

Dr. GeorgeF. Esenwein,Jr.

ProgramManager

NASA Headquarters

Dr. Firouz M.Naderi

ProjectManager

NASA Jet PropulsionLaboratory

[email protected]

Mr. DonaldL. Margolies

ProjectManager

NASA Goddard Space FlightCenter

[email protected]

GeneralContact

Laboratoire d'Etudes et deRecherches en TeledetectionSpatiale

Mr. T.Tanaka

ProgramManager

National Space DevelopmentAgency of Japan




http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-030B[30/05/2011 22:47:38]

Monday, 30 May 2011

Description

AMOS 1 was an Israeli 3-axis stabilized, geosynchronouscommunications satellite that was launched by an Ariane 44 Lrocket along with Palapa C-2 from Kourou. It carried seventransponders in the Ku-band to enable voice and visioncommunications to a large area centered in Israel.

AMOS 1

NSSDC ID: 1996-030B

Alternate Names

23865

Facts in Brief

Launch Date: 1996-05-15Launch Vehicle: Ariane44LLaunch Site: Kourou,IsraelMass: 471.0 kgNominalPower: 1150.0 W

Funding Agency

Unknown (Israel)

Discipline

Communications


Launch/Orbitalinformation for AMOS 1

Experiments on AMOS 1

Data collections fromAMOS 1

Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1996-030B


http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=AMOS 1

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=AMOS 1

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=AMOS 1

mailto:[email protected]?Subject=NMC Comment/Question: AMOS 1 (1996-030B)











http://www.usa.gov/







Monday, 30 May 2011

Description

APSTAR 1A was a Chinese geosynchronous communicationssatellite launched by a Long March 3 rocket from the Xichangcenter in southeastern China. It provided TV coverage to theAsian-Pacific countries through its 24 C-band transponders. Itis expected to provide 10 years of service. It had twotelescoping cylindrical solar panels and an antenna array thatfolded down for launch. It measured 2.2 meters in diameterand a compact 3.1 meters tall when stowed for launch. Withthe solar panels deployed and the antennas unfolded in orbit, itmeasured 7.5 meters. The solar panels were covered with K-43/4 solar cells, which produced 1130 watts at beginning of life.During eclipse, two super nickel cadmium batteries providedpower for uninterrupted service.

Apstar 1A

NSSDC ID: 1996-039A

Alternate Names

23943

Facts in Brief

Launch Date: 1996-07-03Launch Vehicle: LongMarch 3Launch Site: Xichang,Peoples Republic of ChinaMass: 726.0 kgNominalPower: 1130.0 W

Funding Agency

APT Satellite CompanyLtd (Peoples Republic ofChina)

Discipline

Communications


Launch/Orbitalinformation for Apstar 1A

Experiments on Apstar 1A

Data collections fromApstar 1A



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Apstar 1A

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Apstar 1A

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Apstar 1A

mailto:[email protected]?Subject=NMC Comment/Question: Apstar 1A (1996-039A)











http://www.usa.gov/







Monday, 30 May 2011

Description

Arabsat 2A was a geosynchronous communications satellite ofthe 21-nation ARABSAT consortium and was launched by anAriane 44L rocket from the Kourou center in French Guiana.The spacecraft provided radio and TV communications to theMiddle East and neighboring countries.

Arabsat 2A

NSSDC ID: 1996-040A

Alternate Names

23948

Facts in Brief

Launch Date: 1996-07-09Launch Vehicle: Ariane44LLaunch Site: Kourou,French GuianaMass: 2100.0 kg

Funding Agency

Arabsat SatelliteCommunications(International)

Discipline

Communications


Launch/Orbitalinformation for Arabsat2A

Experiments on Arabsat 2A

Data collections fromArabsat 2A



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Arabsat 2A

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Arabsat 2A

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Arabsat 2A

mailto:[email protected]?Subject=NMC Comment/Question: Arabsat 2A (1996-040A)











http://www.usa.gov/







Monday, 30 May 2011

Description

Arabsat 2B was a geosynchronous communications satellite ofthe 21-nation ARABSAT consortium and was launched by anAriane 44L rocket from the Kourou center in French Guiana.The spacecraft provided radio and TV communications to theMiddle East and neighboring countries. It was parked in ageostationary orbit at 21.9 deg E.

Arabsat 2B

NSSDC ID: 1996-063A

Alternate Names

24652

Facts in Brief


Funding Agency

Arabsat SatelliteCommunications(International)

Discipline

Communications


Launch/Orbitalinformation for Arabsat2B

Experiments on Arabsat 2B

Data collections fromArabsat 2B



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Arabsat 2B

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Arabsat 2B

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Arabsat 2B

mailto:[email protected]?Subject=NMC Comment/Question: Arabsat 2B (1996-063A)











http://www.usa.gov/







Monday, 30 May 2011

Description

Astra 1F was a European (SES, Luxembourg)geosynchronous communications satellite launched by aProton-K rocket from the Baykonur cosmodrome. It is parkedover 19.2 deg E longitude and provides direct broadcast TV toEurope through its 16 Ku-band transponders.

Astra 1F

NSSDC ID: 1996-021A

Alternate Names

23842

Facts in Brief

Launch Date: 1996-04-08LaunchVehicle: Proton-KLaunch Site: Tyuratam(Baikonur Cosmodrome),KazakhstanMass: 3010.0 kg

Funding Agency

Societe Europeenne desSatellites (Luxembourg)(Luxembourg)

Discipline

Communications


Launch/Orbitalinformation for Astra 1F

Experiments on Astra 1F

Data collections from Astra1F



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Astra 1F

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Astra 1F

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Astra 1F

mailto:[email protected]?Subject=NMC Comment/Question: Astra 1F (1996-021A)











http://www.usa.gov/







Monday, 30 May 2011

Description

Bion 11 was a Russia biological research satellite launchedfrom the Plesetsk cosmodrome aboard a Soyuz rocket. Itcarried two monkeys named Lalik and Multik.

The spacecraft was based on the Zenit reconnaissancesatellite and launches began in 1973 with primary emphasis onthe problems of radiation effects on human beings. Launchesin the program included Cosmos 110, 605, 670, 782, plusNauka modules flown on Zenit-2M reconnaissance satellites.90 kg of equipment could be contained in the external Naukamodule.

Bion 11

NSSDC ID: 1996-073A

Alternate Names

24701

Facts in Brief

Launch Date: 1996-12-24LaunchVehicle: Soyuz-ULaunch Site: Plesetsk,Russia

Funding Agency

Institute of BiomedicalProblems, Moscow(Russia)

Disciplines

Life Science

Microgravity


Launch/Orbitalinformation for Bion 11

Experiments on Bion 11

Data collections from Bion11



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Bion 11

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Bion 11

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Bion 11

mailto:[email protected]?Subject=NMC Comment/Question: Bion 11 (1996-073A)











http://www.usa.gov/







Monday, 30 May 2011

Description

Chinasat 7 was a geosynchronous communications spacecraftlaunched by the PRC from the Xichang space center aboard aLong March 3 rocket. A third stage rocket failure led to analmost useless orbit.

Chinasat 7

NSSDC ID: 1996-048A

Alternate Names

24282

Facts in Brief

Launch Date: 1996-08-18Launch Vehicle: LongMarch 3Launch Site: Xichang,Peoples Republic of ChinaMass: 734.0 kgNominalPower: 1200.0 W

Funding Agency

Unknown (PeoplesRepublic of China)

Discipline

Communications


Launch/Orbitalinformation for Chinasat 7

Experiments on Chinasat 7

Data collections fromChinasat 7



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Chinasat 7

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Chinasat 7

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Chinasat 7

mailto:[email protected]?Subject=NMC Comment/Question: Chinasat 7 (1996-048A)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=CLUSTR1[30/05/2011 22:50:21]

Monday, 30 May 2011

Description

The original Cluster program of four spacecraft (all launchedtogether on the same rocket) experienced a launch failure in1996. Following that, a single replacement Cluster spacecraftwas authorized in July of 1996, and in April 1997 a furtherthree near-replicas of the original spacecraft were alsoapproved, thus completing the replication of the original four-spacecraft Cluster mission. The following text describes one ofthe original identical four Cluster spacecraft destroyed atlaunch. The spacecraft of the new replacement mission,Cluster II, are described elsewhere, under the NSSDC IDs2000-041A, 2000-041B, 2000-045A, and 2000-045B, and thenames Cluster 2/FM5 (Rumba), Cluster 2/FM6 (Salsa), Cluster2/FM7 (Samba), and Cluster 2/FM8 (Tango).

Cluster-A, one of the four similar spacecraft of the Clustermission, is part of ESA's and NASA's Solar-Terrestrial ScienceProgram (STSP). The purpose of the mission is to study small-scale structures in three dimensions in the Earth's plasmaenvironment, such as those involved in the interaction betweenthe solar wind and the magnetospheric plasma, in globalmagnetotail dynamics, in cross-tail currents, and in theformation and dynamics of the neutral line and of plasmoids.The four spacecraft will orbit in a tetrahedral formation in 4 x 22Re, near-polar orbits with relative separations of severalhundred kilometers at periapsis. The tetrahedral formation isessential for making three-dimensional measurements and fordetermining the curl of vectorial quantities such as themagnetic 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 5m magnetometer booms and two pairs of wire booms, with100 m tip-to-tip lengths, for electric field measurements. Eachspacecraft will have AC and DC magnetometers, an electricfields and waves sensor, an electron emitter/detector, anelectron density sounder, electron and ion plasma analysers,an energetic particle detector, an ion emitter, and a dataprocessing unit.

Cluster operations will be performed by ESA with support fromNASA's Deep Space Network. Cluster is also an IACGmission. A more detailed description of the spacecraft andexperiments may be found in ``Cluster: Mission, payload andsupporting activities,'' ESA SP-1159, March 1993.

Cluster96

NSSDC ID: CLUSTR1

Facts in Brief

Launch Date: 1996-06-04Launch Vehicle: Ariane5Launch Site: Kourou,French GuianaMass: 550.0 kgNominalPower: 224.0 W

Funding Agencies

European Space Agency(International)

National Aeronautics andSpace Administration(United States)

Discipline

Space Physics


Launch/Orbitalinformation for Cluster96

Telecommunicationsinformation for Cluster96

Experiments on Cluster96

Data collections fromCluster96

Questions or commentsabout this spacecraft canbe directed to: Dr. RamonaL. Kessel.

Personnel


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data



http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=CLUSTR1

http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=CLUSTR1

http://nssdc.gsfc.nasa.gov/nmc/spacecraftTelemetry.do?id=CLUSTR1

http://nssdc.gsfc.nasa.gov/nmc/spacecraftTelemetry.do?id=CLUSTR1

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Cluster96

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Cluster96

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Cluster96

mailto:[email protected]?Subject=NMC Comment/Question: Cluster96 (CLUSTR1)

mailto:[email protected]?Subject=NMC Comment/Question: Cluster96 (CLUSTR1)










http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=CLUSTR1[30/05/2011 22:50:21]


Dr. Melvyn L.Goldstein

ProjectScientist

NASA Goddard SpaceFlight Center

[email protected]

Dr. Elden C.Whipple

ProgramScientist


Mr. RaymondS. Tatum

ProjectManager


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)SambaSalsaRumbaTango

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=2000-041A

http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2000-041B


http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2000-045B

http://clusterlaunch.esa.int/science-e/www/area/index.cfm?fareaid=8

http://caa.estec.esa.int/caa/home.xml

http://cdaweb.gsfc.nasa.gov/cdaweb/istp_public

http://cdaweb.gsfc.nasa.gov/cdaweb/

http://www.usa.gov/







Monday, 30 May 2011

Description

Cosmos 2327 was part of a 6-satellite Russian militarynavigation system distributed in orbital planes spaced 30degrees apart, and launched from the Plesetsk cosmodromeaboard a Cosmos rocket. Navigation information was derivedfrom Doppler-shifted VHF transmissions (approximately 150and 400 MHz) of the satellite position and orbital data. Byacquiring fixes from several satellite, a user's location could becalculated with an accuracy of 100 m. The time needed toascertain a position was dependent upon the user's latitudeand the number of operational spacecraft in orbit. Normally,accurate location determination could be made within 1-2hours.

Cosmos 2327

NSSDC ID: 1996-004A

Alternate Names

23773

Facts in Brief

Launch Date: 1996-01-16LaunchVehicle: CosmosLaunch Site: Plesetsk,RussiaMass: 825.0 kg

Funding Agency

Unknown (Russia)

Discipline

Surveillance and OtherMilitary


Launch/Orbitalinformation for Cosmos2327

Experiments on Cosmos2327

Data collections fromCosmos 2327



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Cosmos 2327


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Cosmos 2327


mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 2327 (1996-004A)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-009D[30/05/2011 22:51:05]

Monday, 30 May 2011

Description

Cosmos 2328 was a Russian military spacecraft launched by aCyclon-3 rocket from the Plesetsk Cosmodrome along withCosmos 2329, 2330 and three Gonets spacecraft. It providedmilitary data messaging and photo reconnaissance for theRussian Federation Ministry of Defense.

Cosmos 2328

NSSDC ID: 1996-009D

Alternate Names

23790

Facts in Brief

Launch Date: 1996-02-18LaunchVehicle: Tsiklon-3Launch Site: Plesetsk,RussiaMass: 225.0 kg

Funding Agency

Unknown (Russia)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1996-009D







mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 2328 (1996-009D)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-009E[30/05/2011 22:51:38]

Monday, 30 May 2011

Description

Cosmos 2329 was a Russian military spacecraft launched by aCyclon-3 rocket from the Plesetsk Cosmodrome along withCosmos 2328, 2330 and three Gonets spacecraft. It providedmilitary data messaging and photo reconnaissance for theRussian Federation Ministry of Defense.

Cosmos 2329

NSSDC ID: 1996-009E

Alternate Names

23791

Facts in Brief


Funding Agency

Unknown (Russia)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1996-009E







mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 2329 (1996-009E)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-009F[30/05/2011 22:52:26]

Monday, 30 May 2011

Description

Cosmos 2330 was a Russian military spacecraft launched by aCyclon-3 rocket from the Plesetsk Cosmodrome along withCosmos 2328, 2329 and three Gonets spacecraft. It providedmilitary data messaging and photo reconnoissance for theRussian Federation Ministry of Defense.

Cosmos 2330

NSSDC ID: 1996-009F

Alternate Names

23792

Facts in Brief


Funding Agency

Unknown (Russia)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1996-009F







mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 2330 (1996-009F)











http://www.usa.gov/







Monday, 30 May 2011

Description

Cosmos 2331, a Russian high resolution photoreconnaissance spacecraft, was launched from the Plesetskcosmodrome. It returned film in two small SpK capsules duringthe mission and with the main capsule at completion of themission.

Cosmos 2331

NSSDC ID: 1996-016A

Alternate Names

23818

Facts in Brief

Launch Date: 1996-03-14LaunchVehicle: Soyuz-ULaunch Site: Plesetsk,RussiaMass: 6600.0 kg

Funding Agency

Unknown (Russia)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/







Monday, 30 May 2011

Description

In 1969 KB Yuzhnoye introduced targets for exercise and testof PVO air defence and space tracking systems. The secondgeneration consisted of Taifun-1 and Taifun-2 satellites, whichdiffered in the type of equipment installed. In 1972 KB-3 underB E Khimrov, with the co-operation of assisting organisationsand the Ministry of Defence, completed the draft project. Thefirst Taifun-2 was completed in 1976. Flight trials wereconducted in the second half of the 1970's using Kosmos-3Mlaunch vehicles from Plesetsk and Kapustin Yar. The heads ofthe State Trials Commission were B N Karpov, N N Zhukov,and B G Zudin. Taifun-2 satellites were spherical in shape, 2m in diameter, with no external solar cells or antennae.

Cosmos 2332

NSSDC ID: 1996-025A

Alternate Names

23853

Facts in Brief

Launch Date: 1996-04-24LaunchVehicle: CosmosLaunch Site: Plesetsk,Russia

Funding Agency

Unknown (Russia)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/







Monday, 30 May 2011

Description

Cosmos 2333 was a signals intelligence satellite of the Tselina2 series, built by KB Yuzhnoe of the Ukraine. It was launchedon a Zenit 2 launch vehicle from the Baikonur cosmodromeand was operated by the Russian Ministry of Defense.

Cosmos 2333

NSSDC ID: 1996-051A

Alternate Names

24297

Facts in Brief

Launch Date: 1996-09-04Launch Vehicle: ZenitLaunch Site: Tyuratam(Baikonur Cosmodrome),Kazakhstan

Funding Agency

Unknown (Russia)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/







Monday, 30 May 2011

Description


Cosmos 2334

NSSDC ID: 1996-052A

Alternate Names

24304

Facts in Brief


Funding Agency

Unknown (Russia)

Discipline

Navigation & GlobalPositioning







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/







Monday, 30 May 2011

Description

Cosmos 2335 was a Russian naval reconnaisance satellitelaunched from the Baikonur cosmodrome aboard a Tsyklon 2rocket. This naval forces monitoring spacecraft was used todetermine the position of enemy naval forces through detectionand triangulation of their electromagnetic emissions (radio,radar, etc).

Cosmos 2335

NSSDC ID: 1996-069A

Alternate Names

24670

Facts in Brief

Launch Date: 1996-12-11LaunchVehicle: Tsiklon-2Launch Site: Tyuratam(Baikonur Cosmodrome),KazakhstanMass: 3150.0 kg

Funding Agency

Unknown (Russia)

Discipline




Telecommunicationsinformation for Cosmos2335





Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck



























Monday, 30 May 2011

Description


Cosmos 2336

NSSDC ID: 1996-071A

Alternate Names

24677

Facts in Brief


Funding Agency

Unknown (Russia)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/







Monday, 30 May 2011

Description

Echostar 2, a Lockheed Martin satellite, was launched from theKourou space center in French Guiana aboard an Ariane 42Procket. This second in a series of DBS communicationssatellites, was positioned at 119 deg W and provided video,audio and data services to the continental US, SouthernCanada, and Northern Mexico.

Echostar 2

NSSDC ID: 1996-055A

Alternate Names

24313

Facts in Brief

Launch Date: 1996-09-10Launch Vehicle: Ariane42PLaunch Site: Kourou,French GuianaMass: 2885.0 kgNominalPower: 7000.0 W

Funding Agency

EchostarCommunicationsCorporation (UnitedStates)

Discipline

Communications


Launch/Orbitalinformation for Echostar 2

Experiments on Echostar 2

Data collections fromEchostar 2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Echostar 2

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Echostar 2

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Echostar 2

mailto:[email protected]?Subject=NMC Comment/Question: Echostar 2 (1996-055A)











http://www.usa.gov/







Monday, 30 May 2011

Description

Express 12 was a Russian geostationary communicationssatellite launched from the Baikonur cosmodrome aboard aProton rocket. Express will replace the widely used Gorizontspacecraft, and current plans call for deployments at 13locations (40 degrees, 53 degrees, 80 degrees, 90 degrees,96.5 degrees, 99 degrees, 103 degrees, 140 degrees, 145degrees, 205 degrees, 322.5 degrees, 346 degrees, and 349degrees, all East longitude) just for domestic needs and tosupport the Intersputnik Telecommunications Association. Atypical Express payload will include 10 C-band and two Ku-band transponders.

Express 12

NSSDC ID: 1996-058A

Alternate Names

24435

Facts in Brief

Launch Date: 1996-09-26Launch Vehicle: ProtonLaunch Site: Tyuratam(Baikonur Cosmodrome),KazakhstanMass: 2500.0 kg

Funding Agency

Unknown (Russia)

Discipline

Communications


Launch/Orbitalinformation for Express12

Experiments on Express12

Data collections fromExpress 12



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Express 12

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Express 12

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Express 12

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Express 12

mailto:[email protected]?Subject=NMC Comment/Question: Express 12 (1996-058A)











http://www.usa.gov/







Monday, 30 May 2011

Description

The Fast Auroral SnapshoT Explorer (FAST) was successfullylaunched on 1996-08-21 into its intended orbit. FASTinvestigates the plasma physics of auroral phenomena atextremely high time and spatial resolution using the fullcomplement of particle and fields instruments. FAST is thesecond spacecraft (SAMPEX was first) in the Small Explorer(SMEX) program at NASA-GSFC. SMEX was established toprovide rapid (3 year development) low cost ($35Mdevelopment) mission opportunities (1 per year) to the spacescience community using a single designated PrincipalInvestigator (PI).

In order to capture the auroral phenomena over small time(microseconds) and spatial scales, FAST utilizes high speeddata sampling, a large, fast-loading ("burst") memory, and asmart, on-board software to trigger on the appearance ofvarious key phenomena. Using a 1 Gb solid-state memory anda data acquisition rate of 8 Mbs (almost two orders ofmagnitude faster than previous satellites), FAST produceshigh-resolution "snapshots" of auroral arcs and otherinteresting 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 thenorthern auroral zone and in less intense survey mode duringthe rest of the orbit.

The FAST mission uses a unique (not a SAMPEX derivative),lightweight, orbit-normal spinner spacecraft developed by theSMEX project. The spacecraft has body-mounted solar arrays,and is spin-stabilized, rotating at 12 rpm with the spin axisnormal to the orbit plane ("cartwheel"). The four FASTexperiments are: (1) the Electrostatic Analyzers (ESA) formeasuring the electron and ion distribution function, (2) theTime-of-flight Energy Angle Mass Spectrograph (TEAMS) formeasuring the full 3-dimensional distribution function of themajor ion species, (3) the Tri-Axial Fluxgate and Search-coilMagnetometers for measuring magnetic field data, and (4) theElectric Field/Langmuir Probe Instrument for obtaining electricfield data and plasma density and temperature. The FASTelectric field instrument stopped providing meaningful dataaround 2002, all other instruments and systems continue tofunction nominally.

FAST

NSSDC ID: 1996-049A

Alternate Names

Small Explorer/FAST

Explorer 70

SMEX/FAST

Fast Auroral SnapshoTExplorer

24285

Facts in Brief

Launch Date: 1996-08-21LaunchVehicle: Pegasus XLLaunchSite: Vandenberg AFB,United StatesMass: 187.0 kgNominal Power: 60.0 W

Funding Agency

NASA-Office of SpaceScience Applications(United States)

Discipline

Space Physics


Launch/Orbitalinformation for FAST

PDMP information forFAST

Telecommunicationsinformation for FAST

Experiments on FAST

Data collections from FAST

Questions or comments


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data









http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=FAST

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=FAST











about this spacecraft canbe directed to: Dr. Dieter K.Bilitza.

Personnel


Dr. Robert F.Pfaff

Project Scientist NASA Goddard SpaceFlight Center

[email protected]

Mr. Ronald E.Adkins

Project Manager NASA Goddard SpaceFlight Center

Dr. CharlesW. Carlson

Mission PrincipalInvestigator

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


mailto:[email protected]?Subject=NMC Comment/Question: FAST (1996-049A)

mailto:[email protected]?Subject=NMC Comment/Question: FAST (1996-049A)

http://cdaweb.gsfc.nasa.gov/

http://sscweb.gsfc.nasa.gov/

http://plasma2.ssl.berkeley.edu/fast/

http://sunland.gsfc.nasa.gov/smex/smexhomepage.html

http://www.usa.gov/







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 Names24634

Facts in Brief

Launch Date: 1996-10-20Launch Vehicle: Long March 3Launch Site: Jiuquan, Peoples Republic of China

Funding AgencyUnknown (Peoples Republic of China)

DisciplineEarth Science

Additional InformationLaunch/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.


SpacecraftExperimentsData CollectionsPersonnelPublicationsMapsNew/Updated DataLunar/Planetary Events

+ Privacy Policy and Important Notices

NASA Official: Dr. Ed GrayzeckCurator: E. Bell, II

Monday, 30 May 2011



http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=FSW-2 3

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=FSW-2 3

mailto:[email protected]?Subject=NMC Comment/Question: FSW-2 3 (1996-059A)









http://www.usa.gov/







Wednesday, 08 June 2011

Description

Galaxy 9 was a geosynchronous spacecraft launched byHughes Communications Inc from Cape Canaveral aboard aDelta 2 rocket. It provided voice and vision communications toNorth America.

Galaxy 9

NSSDC ID: 1996-033A

Alternate Names

23877

Facts in Brief

Launch Date: 1996-05-23Launch Vehicle: DeltaIILaunch Site: CapeCanaveral, United States

Funding Agency

Pan American Satellite(United States)

Discipline

Communications


Launch/Orbitalinformation for Galaxy 9

Experiments on Galaxy 9

Data collections fromGalaxy 9



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Galaxy 9

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Galaxy 9

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Galaxy 9

mailto:[email protected]?Subject=NMC Comment/Question: Galaxy 9 (1996-033A)











http://www.usa.gov/








Description

GE 1 was an AMERICOM Corp communications satellitelaunched from Cape Canaveral aboard an Atlas 2A rocket. Itwas placed into a geostationary orbit at 103 deg W.

GE 1

NSSDC ID: 1996-054A

Alternate Names

24315

Facts in Brief

Launch Date: 1996-09-08Launch Vehicle: Atlas2ALaunch Site: CapeCanaveral, United States

Funding Agency

GE AmericanCommunications, Inc.(United States)

Discipline

Communications


Launch/Orbitalinformation for GE 1

Experiments on GE 1

Data collections from GE 1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=GE 1

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=GE 1

mailto:[email protected]?Subject=NMC Comment/Question: GE 1 (1996-054A)











http://www.usa.gov/








Description

Gonets D1-1 was a Russian communications/photo-reconnoissance spacecraft launched by a Cyclon-3 rocket,along with Gonets D1-2 and D1-3, and 3 Cosmos spacecraft.It will monitor disasters like oil spills, illicit transport ofradioactive cargo, and provide prompt alerts.

Gonets D1-1

NSSDC ID: 1996-009A

Alternate Names

23787

Facts in Brief


Funding Agency

Unknown (Russia)

Discipline

Communications


Launch/Orbitalinformation for GonetsD1-1

Experiments on GonetsD1-1

Data collections fromGonets D1-1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Gonets D1-1


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Gonets D1-1


mailto:[email protected]?Subject=NMC Comment/Question: Gonets D1-1 (1996-009A)











http://www.usa.gov/








Description

Gonets D1-2 was a Russian communications/photo-reconnoissance spacecraft launched by a Cyclon-3 rocketalong with Gonets D1-1, D1-3, and three Cosmos spacecraft.It will monitor disasters like oil spills, illicit transport ofradioactive cargo, and provide prompt alerts.

Gonets D1-2

NSSDC ID: 1996-009B

Alternate Names

23788

Facts in Brief


Funding Agency

Unknown (Russia)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data











mailto:[email protected]?Subject=NMC Comment/Question: Gonets D1-2 (1996-009B)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-009C[08/06/2011 0:15:24]


Description

Gonets D1-3 was a Russian communications/photo-reconnoissance spacecraft launched by a Cyclon-3 rocketalong with Gonets D1-1, D1-2, and three Cosmos spacecraft.It will monitor disasters like oil spills, illicit transport ofradioactive cargo, and provide prompt alerts.

Gonets D1-3

NSSDC ID: 1996-009C

Alternate Names

23789

Facts in Brief


Funding Agency

Unknown (Russia)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1996-009C







mailto:[email protected]?Subject=NMC Comment/Question: Gonets D1-3 (1996-009C)











http://www.usa.gov/








Description

Gorizont 31 was a Russian geosynchronous communicationssatellite. It was launched to provide telephone, telegraph andfax communications services, in addition to relaying TV andradio broadcasts, as well as support maritime and internationalcommunications. It was stationed at 39 deg E.

The Gorizont spacecraft possessed an initial mass in excess of2.1 metric tons and have demonstrated a lifetime of nearly 10years, although a 5-year service life was more common. The3-axis stabilized satellite was approximately 2 m in diameterand 5 m long with two large solar arrays capable of generating1.3 kW of electrical power for the first 3 years. Seven separatetransmission antennas allowed a variety of reception patternsfor both broad and localized terrestrial regions.

A typical Gorizont communications payload included sixgeneral 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). TheVolna transponders were INMARSAT-compatible and wereextensively used by the Russian merchant marine fleet via theprimary GEO television rebroadcasting system, supporting allfive Federation time zones: Zone 1 from 140 deg E, Zone 2from 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 handledby Orbita (12-m receiving antenna) and Moskva (2.5-mreceiving antenna) ground stations in the 6/4 GHz band. TheMoskva Globalnaya system was inaugurated in 1989 using 4-m receiving antennas and serviced by Gorizonts at 96.5 deg Eand 11 deg W.

Gorizont 31

NSSDC ID: 1996-005A

Alternate Names

23775

Facts in Brief

Launch Date: 1996-01-25Launch Vehicle: ProtonLaunch Site: Tyuratam(Baikonur Cosmodrome),KazakhstanMass: 2125.0 kg

Funding Agency

Unknown (Russia)

Discipline

Communications


Launch/Orbitalinformation for Gorizont31

Experiments on Gorizont31

Data collections fromGorizont 31



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Gorizont 31


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Gorizont 31


mailto:[email protected]?Subject=NMC Comment/Question: Gorizont 31 (1996-005A)











http://www.usa.gov/








Description

Gorizont 32 was a Russian geosynchronous communicationssatellite. It was launched to provide telephone, telegraph andfax communications services, in addition to relaying TV andradio broadcasts, as well as support maritime and internationalcommunications. It was stationed at 53.2 deg E.

The Gorizont spacecraft possessed an initial mass in excess of2.1 metric tons and have demonstrated a lifetime of nearly 10years, although a 5-year service life was more common. The3-axis stabilized satellite was approximately 2 m in diameterand 5 m long with two large solar arrays capable of generating1.3 kW of electrical power for the first 3 years. Seven separatetransmission antennas allowed a variety of reception patternsfor both broad and localized terrestrial regions.

A typical Gorizont communications payload included sixgeneral 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). TheVolna transponders were INMARSAT-compatible and wereextensively used by the Russian merchant marine fleet via theprimary GEO television rebroadcasting system, supporting allfive Federation time zones: Zone 1 from 140 deg E, Zone 2from 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 handledby Orbita (12-m receiving antenna) and Moskva (2.5-mreceiving antenna) ground stations in the 6/4 GHz band. TheMoskva Globalnaya system was inaugurated in 1989 using 4-m receiving antennas and serviced by Gorizonts at 96.5 deg Eand 11 deg W.

Gorizont 32

NSSDC ID: 1996-034A

Alternate Names

23880

Facts in Brief


Funding Agency

Unknown (Russia)

Discipline

Communications


Launch/Orbitalinformation for Gorizont32

Experiments on Gorizont32

Data collections fromGorizont 32



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

The High Energy Transient Experiment (HETE) was to be aninternational mission led by the Massachusetts Institute ofTechnology (MIT). Its prime objective was to carry out the firstmultiwavelength study of gamma-ray bursts (GRB) with UV, X-ray and gamma ray instruments. A unique feature of themission was its capability to localize bursts with several arc-second accuracy, in near real-time aboard the spacecraft. Thespacecraft hardware and software was developed byAeroAstro, Inc. (USA). The HETE spacecraft was sun-pointingwith four solar panels connected to the bottom of thespacecraft bus. Spacecraft attitude was to be controlled bymagnetic torque coils and a momentum wheel.

The HETE satellite was launched with the Argentine satelliteSAC-B. HETE was trapped within the Dual PayloadAttachment Fitting due to a battery failure in the Pegasus XLrocket third stage. Due to its inability to deploy the solarpanels, HETE lost power several days after launch

HETE 1

NSSDC ID: 1996-061A

Alternate Names

High Energy TransientExperiment

High-Energy TransientExplorer 1

24645

Facts in Brief

Launch Date: 1996-11-04LaunchVehicle: Pegasus XLLaunch Site: WallopsIsland, United StatesMass: 128.0 kg

Funding Agency

NASA-Office of SpaceScience (United States)

Discipline

Astronomy


Launch/Orbitalinformation for HETE 1

Experiments on HETE 1

Data collections fromHETE 1


Personnel


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=HETE 1

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=HETE 1

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=HETE 1

mailto:[email protected]?Subject=NMC Comment/Question: HETE 1 (1996-061A)














Related Information/Data at NSSDC

HETE 2



http://www.usa.gov/








Description

Hot Bird 2 was a geostationary communications spacecraft ofthe European EUTELSAT consortium. With a constellation of 5satellites, the Hot Bird family at 13 degrees E formed one ofthe largest broadcasting systems in the world. By fourthquarter 1998, the system was delivering over 320 analogueand digital television channels, as well as radio and multimediaservices, to more than 70 million homes connected to a cablenetwork or equipped for satellite (direct-to-home orcommunity) reception. The Hot Bird satellites provided fullcoverage of Europe and also took in parts of Africa and Asia,including the entire Middle East.

Hot Bird 2

NSSDC ID: 1996-067A

Alternate Names

Eurobird 9

24665

Facts in Brief

Launch Date: 1996-11-21Launch Vehicle: Atlas2ALaunch Site: CapeCanaveral, United StatesMass: 2800.0 kg

Funding Agency

EuropeanTelecommunicationsSatellite Consortium(International)

Discipline

Communications


Launch/Orbitalinformation for Hot Bird 2

Experiments on Hot Bird 2

Data collections from HotBird 2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Hot Bird 2

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Hot Bird 2

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Hot Bird 2

mailto:[email protected]?Subject=NMC Comment/Question: Hot Bird 2 (1996-067A)











http://www.usa.gov/








Description

IAE (Inflatable Antenna Experiment) was a NASA inflatablemylar antenna that was released from STS 77. It expanded toa diameter of 16 meters and retained its shape with the help of3 inflated 30-meter struts. It re-entered the atmosphere afterseveral orbits.

IAE

NSSDC ID: 1996-032C

Alternate Names

Inflatable AntennaExperiment

23872

Facts in Brief

Launch Date: 1996-05-20LaunchVehicle: ShuttleLaunch Site: CapeCanaveral, United States

Funding Agency


Discipline

Technology Applications


Launch/Orbitalinformation for IAE

Experiments on IAE

Data collections from IAE



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=IAE

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=IAE

mailto:[email protected]?Subject=NMC Comment/Question: IAE (1996-032C)











http://www.usa.gov/








Description

Inmarsat 3-F1 was the first in a series of five third generationsatellites. Launched from Cape Canaveral aboard an Atlas 2Arocket, it is currently in service over the Indian Ocean. It usedthe latest spot-beam technology and higher power to supplyvoice and data communications services worldwide to mobileterminals as small as pocket-size messaging units on ships,aricraft and vehicles.

INMARSAT-3 development was carried out by prime contractorLockheed Martin and payload provider Matra Marconi Space.With an end-of-life power rating of 2,800 W, each INMARSAT-3 could deliver an IERP of up to 48dBW - eight times theINMARSAT-2 level - in L-band. It could dynamically reallocateboth RF power and bandwidth among a global beam and fivespot beams, allowing greater reuse of the available spectrums.Simultaneous voice channel capacity was up to eight times theINMARSAT-2 figure.

Each INMARSAT-3 also carried a navigation transponderdesigned to enhance the accuracy, availability and integrity ofthe GPS and Glonass satellite navigation systems.

Inmarsat 3-F1

NSSDC ID: 1996-020A

Alternate Names

23839

Facts in Brief

Launch Date: 1996-04-03Launch Vehicle: Atlas2ALaunch Site: CapeCanaveral, United StatesMass: 2068.0 kg

Funding Agency

Inmarsat (International)

Discipline

Communications


Launch/Orbitalinformation for Inmarsat3-F1

Experiments on Inmarsat3-F1

Data collections fromInmarsat 3-F1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Inmarsat 3-F1


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Inmarsat 3-F1


mailto:[email protected]?Subject=NMC Comment/Question: Inmarsat 3-F1 (1996-020A)











http://www.usa.gov/








Description

Inmarsat 3-F2 was the second in a series of five thirdgeneration satellites. Launched from the Baikonur cosmodromeaboard a Proton rocket, it is currently in service over theAtlantic Ocean. It used the latest spot-beam technology andhigher power to supply voice and data communicationsservices worldwide to mobile terminals as small as pocket-sizemessaging units on ships, aricraft and vehicles.



Inmarsat 3-F2

NSSDC ID: 1996-053A

Alternate Names

24307

Facts in Brief

Launch Date: 1996-09-06Launch Vehicle: ProtonLaunch Site: Tyuratam(Baikonur Cosmodrome),Kazakhstan

Funding Agency

InternationalTelecommunicationsSatellite Corporation(International)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Inmarsat 3-F3 was the third in a series of five third generationsatellites. Launched from Cape Canaveral aboard an Atlas 2rocket, it is currently in service over the Pacific Ocean. It usedthe latest spot-beam technology and higher power to supplyvoice and data communications services worldwide to mobileterminals as small as pocket-size messaging units on ships,aircraft and vehicles.



Inmarsat 3-F3

NSSDC ID: 1996-070A

Alternate Names

24674

Facts in Brief

Launch Date: 1996-12-17Launch Vehicle: AtlasLaunch Site: CapeCanaveral, United States

Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Intelsat 7-F7 was a geostationary communications spacecraftfor the Intelsat consortium that was launched by an Ariane44LP rocket from the Kourou Space Center in French Guiana.The 4,175 kg spacecraft carried 26 C-band and 14 K-bandtransponders to provide Europe and the Americas with 3television channels and 22,500 telephone circuits after parkingover the eastern coast of Brazil.

INTELSAT 7 F-7

NSSDC ID: 1996-015A

Alternate Names

23816

Facts in Brief

Launch Date: 1996-03-14Launch Vehicle: Ariane44LPLaunch Site: Kourou,French GuianaMass: 4175.0 kg

Funding Agency


Discipline

Communications


Launch/Orbitalinformation for INTELSAT7 F-7

Experiments on INTELSAT7 F-7

Data collections fromINTELSAT 7 F-7



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=INTELSAT 7 F-7

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=INTELSAT 7 F-7

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=INTELSAT 7 F-7

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=INTELSAT 7 F-7

mailto:[email protected]?Subject=NMC Comment/Question: INTELSAT 7 F-7 (1996-015A)











http://www.usa.gov/








Description

Intelsat 709 was a geosynchronous communications satellite ofthe INTELSAT consortium. It was launched by an Ariane 44Procket from the Kourou site in French Guiana and carried 36Ku- and C-band transponders to serve the Atlantic oceanregion.

INTELSAT 709

NSSDC ID: 1996-035A

Alternate Names

23915

Facts in Brief

Launch Date: 1996-06-15Launch Vehicle: Ariane44PLaunch Site: Kourou,French Guiana

Funding Agency


Discipline

Communications


Launch/Orbitalinformation for INTELSAT709

Experiments on INTELSAT709

Data collections fromINTELSAT 709



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=INTELSAT 709

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=INTELSAT 709

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=INTELSAT 709

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=INTELSAT 709

mailto:[email protected]?Subject=NMC Comment/Question: INTELSAT 709 (1996-035A)











http://www.usa.gov/








Description

The Interball Project is a multi-national effort that consists offour spacecraft: two main spacecraft of the Prognoz series,made in Russia, each with a small subsatellite made inCzechoslovakia. The main objective is to study the physicalmechanisms responsible for the transmission of solar windenergy to the magnetosphere, its storage there, andsubsequent dissipation in the tail and auroral regions of themagnetosphere, ionosphere, and atmosphere duringmagnetospheric substorms. A ground-based support group willprovide coordinated and simultaneous ground-based data ofmany types, including observations from auroral and polar capregions. Interball is an IACG-related mission. Key physicalparameters will be generated, and will be available forexchange with other projects. Campaigns for intercomparisonwith the Wind and Geotail spacecraft are expected. One pairof spacecraft, Tail Probe and its subsatellite S2-X (X for thefirst letter of the Russian word for ``Tail''), will be launched intothe magnetospheric tail. The second pair, Auroral Probe andS2-A (A for ``Auroral''), will have an orbit that crosses theauroral oval to observe the acceleration of auroral particlesand the flow of electric currents that connect themagnetospheric tail with the conducting ionosphere. To studythe equilibrium tail structure, during about half of each year theTail Probe pair will cross the main parts of the magnetotailevery four days. The Auroral Probe pair will support the TailProbe pair with auroral region measurements. Each mainspacecraft has more than twenty scientific instruments. Thespacecraft is cylindrical, with spin axis toward the sun (within10 degrees), and with spin period of ~120 s. The electric andmagnetic field sensors are on booms connected to the ends ofthe solar panels. The subsatellites are small, each with aboutten scientific instruments. The spin axis will be directed within10 degrees of the sun, with a spin period of ~120 s, as with themain spacecraft. The subsatellites also carry gas-jet thrustersfor limited control of the orbit. Separation distance will rangefrom hundreds of kilometers to several tens of thousands ofkilometers for the Tail Probe pair. Separation distance willrange from hundreds of meters to hundreds of kilometers forthe Auroral Probe pair. The Tail Probe has two telemetrysystems, at up to 32 Kbps in real-time, with a memory modecapacity of 30 Mb in the RTK telemetry system and 120 Mb inthe SSNI system. The Auroral Probe has similar capability plusthe 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 TailProbe has an adapting alert mode while in the memory mode,allowing time resolutions that are the same as in the real-timemode. The aim is to have the highest time resolution availableat the thin borders of magnetospheric regions or the sharp

Interball Auroral Probe

NSSDC ID: 1996-050C

Alternate Names

Auroral Probe

Prognoz 2M

Interball 2

Prognoz 12

24293

Facts in Brief

Launch Date: 1996-08-29LaunchVehicle: Molniya-MLaunch Site: Plesetsk,RussiaMass: 1250.0 kg

Funding Agency

Russian Space Agency(Russia)

Discipline

Space Physics


Launch/Orbitalinformation for InterballAuroral Probe

Experiments on InterballAuroral Probe

Data collections fromInterball Auroral Probe

Questions or commentsabout this spacecraft canbe directed to: Dr. H. KentHills.

Interball


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Interball Auroral Probe

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Interball Auroral Probe

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Interball Auroral Probe

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Interball Auroral Probe

mailto:[email protected]?Subject=NMC Comment/Question: Interball Auroral Probe (1996-050C)

mailto:[email protected]?Subject=NMC Comment/Question: Interball Auroral Probe (1996-050C)











borders of some features. In the alert mode (triggered by anon-board computer monitoring plasma and field parameters),the bit rate is increased for plasma, field, and wavemeasurements. The duration of these alert periods is about 10minutes, and there can be 5--6 of them during one orbit.

Data/Information atNSSDC

Interball Tail ProbeInterball S2-XInterball Auroral ProbeInterball S2-A

Other Sources of Interball Data/Information

Interball project (IKI)Interball data archive (IKI)



http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1995-039F

http://www.iki.rssi.ru/interball.html

http://www.iki.rssi.ru/ida.html

http://www.usa.gov/








Description

IRS-P3 is an Indian Remote Sensing spacecraft launched by a4-stage PSLV-D3 developmental rocket from the Sriharikotalaunch station on the southeast coast of India. The 930 kgspacecraft carried two remote sensing experiments and anastronomical x-ray detector. WIFS (WIde Field Sensor) was ascanner with visible light and infrared photometers to studycrop conditions, geology, and snow cover. The German SpaceAgency's (DLR's) modular opto-electronic scanner will monitoroceanic chlorophyll, sediment transport and ocean dynamics.Data will be downlinked at 3 Indian stations, and stations inRussia, Germany, and Mauritius.

IRS-P3

NSSDC ID: 1996-017A

Alternate Names

Indian Remote SensingSatellite P3

23827

Facts in Brief

Launch Date: 1996-03-20Launch Vehicle: PSLVLaunch Site: Sriharikota,IndiaMass: 930.0 kg

Funding Agency

Indian Space ResearchOrganization (India)

Disciplines

Astronomy

Earth Science


Launch/Orbitalinformation for IRS-P3

Experiments on IRS-P3

Data collections from IRS-P3



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=IRS-P3

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=IRS-P3

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=IRS-P3

mailto:[email protected]?Subject=NMC Comment/Question: IRS-P3 (1996-017A)











http://www.usa.gov/








Description

Italy's second national communications satellite, ITALSAT 2was dual launched aboard an Ariane 44L booster from Kourou,French Guiana. Placed in geosynchronous orbit above 13.2deg. e, the satellite served as a spaceborne telephoneswitchboard, redirecting up to 12,000 calls at once. ITALSATwas experimental in nature, a pre-operational component of aproposed digital satellite network for Italy. Built by SeleniaSpazio for Agenzia Spaziale Italiana (the Italian SpaceAgency), ITALSAT 2 was box-shaped, measuring 2.72 by 2.22by 3.48 m. It was 6.1 m tall with its two 2-m reflector antennasdeployed. Solar arrays spanned 21 m and provided 1,600 Wof power. Its communications package housed six 20/30 GHzmultibeam transponders, three 20/30 GHz global beamtransponders and a propagation experiment operating at 40/50GHz. The multibeam system, using advanced time divisionmultiple access (TDMA) techniques, was expected to undergotwo years of testing; the global beam system was consideredoperational from the start and was used to test new services.ITALSAT 2 had a 5-year design life.

Italsat 2

NSSDC ID: 1996-044A

Alternate Names

24208

Facts in Brief


Funding Agency

Unknown (Italy)

Discipline

Communications


Launch/Orbitalinformation for Italsat 2

Experiments on Italsat 2

Data collections fromItalsat 2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Italsat 2

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Italsat 2

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Italsat 2

mailto:[email protected]?Subject=NMC Comment/Question: Italsat 2 (1996-044A)











http://www.usa.gov/








Description

JAS-2 was a Japanese communications satellite launched fromthe Tanegashima Space Center for NASDA. It succeededJAS-1b which was launched in February of 1990.

JAS 2

NSSDC ID: 1996-046B

Alternate Names

OSCAR 29

24278

Facts in Brief

Launch Date: 1996-08-16Launch Vehicle: H-2LaunchSite: Tanegashima, JapanMass: 50.0 kg

Funding Agency

Unknown (Japan)

Discipline

Communications


Launch/Orbitalinformation for JAS 2

Experiments on JAS 2

Data collections from JAS2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=JAS 2

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=JAS 2

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=JAS 2

mailto:[email protected]?Subject=NMC Comment/Question: JAS 2 (1996-046B)











http://www.usa.gov/








Description

KH 12-3 was launched from Vandenberg AFB aboard a Titan 4rocket for the US Department of Defense. It was an electro-optical reconnaisance satellite that succeeded the KH-11series. It was heavier and believed to include a signalsintelligence payload, it had wider spectral band sensitivity,perhaps "real time" television capability, and otherimprovements compared to the KH-11 satellites. Data weretransmitted via the SDS military relay satellites.

KH 12-3

NSSDC ID: 1996-072A

Alternate Names

USA 129

24680

Facts in Brief

Launch Date: 1996-12-20Launch Vehicle: TitanIVLaunchSite: Vandenberg AFB,United StatesMass: 19600.0 kg

Funding Agency

Department of Defense-Department of the AirForce (United States)

Discipline



Launch/Orbitalinformation for KH 12-3

Experiments on KH 12-3

Data collections from KH12-3



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=KH 12-3

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=KH 12-3

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=KH 12-3

mailto:[email protected]?Subject=NMC Comment/Question: KH 12-3 (1996-072A)











http://www.usa.gov/








Description

Koreasat 2, also known as Mugunghwa 2, was a South Koreangeostationary communications spacecraft launched from CapeCanaveral by a Delta 2 rocket. It will be parked at 116 Elongitude over Borneo island to provide broadcasting andtelecommunications to South Korea beginning in July 1996.

Koreasat 2

NSSDC ID: 1996-003A

Alternate Names

Mugunghwa 2

23768

Facts in Brief

Launch Date: 1996-01-14Launch Vehicle: DeltaIILaunch Site: CapeCanaveral, United States

Funding Agency

Unknown (South Korea)

Discipline

Communications


Launch/Orbitalinformation for Koreasat 2

Experiments on Koreasat 2

Data collections fromKoreasat 2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Koreasat 2

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Koreasat 2

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Koreasat 2

mailto:[email protected]?Subject=NMC Comment/Question: Koreasat 2 (1996-003A)











http://www.usa.gov/








Description

The Interball Project is a multi-national effort that consists offour spacecraft: two main spacecraft of the Prognoz series,made in Russia, each with a small subsatellite made inCzechoslovakia. The main objective is to study the physicalmechanisms responsible for the transmission of solar windenergy to the magnetosphere, its storage there, andsubsequent dissipation in the tail and auroral regions of themagnetosphere, ionosphere, and atmosphere duringmagnetospheric substorms. A ground-based support group willprovide coordinated and simultaneous ground-based data ofmany types, including observations from auroral and polar capregions. Interball is an IACG-related mission. Key physicalparameters will be generated, and will be available forexchange with other projects. Campaigns for intercomparisonwith the Wind and Geotail spacecraft are expected. One pairof spacecraft, Tail Probe and its subsatellite S2-X (X for thefirst letter of the Russian word for ``Tail''), will be launched intothe magnetospheric tail. The second pair, Auroral Probe andS2-A (A for ``Auroral''), will have an orbit that crosses theauroral oval to observe the acceleration of auroral particlesand the flow of electric currents that connect themagnetospheric tail with the conducting ionosphere. To studythe equilibrium tail structure, during about half of each year theTail Probe pair will cross the main parts of the magnetotailevery four days. The Tail Probe, with approximately 30 earthradii apogee, will cross the noon-midnight plane on December1, so the measurements in the magnetotail will cover theperiod from October 1995 to February 1996. The AuroralProbe pair will support the Tail Probe pair with auroral regionmeasurements.

Each main spacecraft has more than twenty scientificinstruments. The spacecraft is cylindrical, with spin axis towardthe sun (within 10 degrees), and with spin period of ~120 s.The electric and magnetic field sensors are on boomsconnected to the ends of the solar panels.

The subsatellites are small, each with about ten scientificinstruments. The spin axis will be directed within 10 degrees ofthe sun, with a spin period of ~120 s, as with the mainspacecraft. The subsatellites also carry gas-jet thrusters forlimited control of the orbit. Separation distance will range fromhundreds of kilometers to several tens of thousands ofkilometers for the Tail Probe pair. Separation distance willrange from hundreds of meters to hundreds of kilometers forthe Auroral Probe pair. The Tail Probe has two telemetrysystems, at up to 32 Kbps in real-time, with a memory modecapacity of 30 Mb in the RTK telemetry system and 120 Mb inthe SSNI system. The Auroral Probe has similar capability plus

Magion 5

NSSDC ID: 1996-050B

Alternate Names

Auroral Subsatellite S2-A

Interball S2-A

S2-A

24292

Facts in Brief


Funding Agency

Unknown (CzechRepublic)

Discipline

Space Physics


Launch/Orbitalinformation for Magion 5

Experiments on Magion 5

Data collections fromMagion 5


InterballData/Information atNSSDC


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Magion 5

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Magion 5

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Magion 5

mailto:[email protected]?Subject=NMC Comment/Question: Magion 5 (1996-050B)

mailto:[email protected]?Subject=NMC Comment/Question: Magion 5 (1996-050B)











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 thememory mode, allowing time resolutions that are the same asin the real-time mode. The aim is to have the highest timeresolution available at the thin borders of magnetosphericregions or the sharp borders of some features. In the alertmode (triggered by an on-board computer monitoring plasmaand field parameters), the bit rate is increased for plasma,field, and wave measurements. The duration of these alertperiods is about 10 minutes, and there can be 5--6 of themduring one orbit.

Interball Tail ProbeInterball S2-XInterball Auroral ProbeInterball S2-A

Other Sources ofInterballData/Information

Interball project (IKI)Interball data archive (IKI)



http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1995-039F

http://www.iki.rssi.ru/interball.html

http://www.iki.rssi.ru/ida.html

http://www.usa.gov/








Description

The Mars 96 spacecraft was launched into Earth orbit, butfailed to achieve insertion into Mars cruise trajectory and re-entered the Earth's atmosphere at about 00:45 to 01:30 UT on17 November 1996 and crashed within a presumed 320 km by80 km area which includes parts of the Pacific Ocean, Chile,and Bolivia. The cause of the crash is not known.

The Russian Mars 96 mission was designed to send an orbiter,two small autonomous stations, and two surface penetrators toMars to investigate the evolution and contemporary physics ofthe planet by studying the physical and chemical processeswhich took place in the past and which currently take place.The Mars 96 Orbiter was a 3-axis sun/star stabilized craftbased on the Phobos design with two platforms for pointingand stabilizing instruments. The propulsion units were mountedon the bottom and two large solar panels extended out fromopposite sides of the craft. The two penetrators were mountedon the bottom by the propulsion system, the two small stationswere connected on top of the spacecraft, and a dish antennaextended off one of the sides perpendicular to the solarpanels. The Mars 96 spacecraft had a launch mass (includingpropellant) of 6180 kg.

Mars 96 was scheduled to arrive at Mars on 12 September1997, about 10 months after launch, on a direct trajectory.About 4 to 5 days before arrival the small surface stationswould have been released. The orbiter was to go into anelliptical 3-day transfer orbit about Mars, and the twopenetrators to descend to the surface during the first month oforbit. The final orbit would have been a 14.77 hour ellipticalorbit with a periapsis of 300 km.

The Mars 96 Orbiter carried 12 instruments to study thesurface and atmosphere of Mars, 7 instruments to studyplasma, fields, and particles, and 3 instruments forastrophysical studies. There were also radio science, anavigation TV camera, and a radiation and dosimetry controlcomplex. The instruments were located directly on the sides ofthe craft, on one of the two platforms attached to the sides ofthe craft, or on the edges of the solar panels.

Mars 96 Orbiter

NSSDC ID: 1996-064A

Facts in Brief


Funding Agency


Discipline

Planetary Science


Launch/Orbitalinformation for Mars 96Orbiter

PDMP information forMars 96 Orbiter

Telecommunicationsinformation for Mars 96Orbiter

Experiments on Mars 96Orbiter

Data collections from Mars96 Orbiter

Questions or commentsabout this spacecraft canbe directed to: Dr. David R.Williams.

Personnel



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


Mars 96 Orbiter










http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Mars 96 Orbiter

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Mars 96 Orbiter

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Mars 96 Orbiter

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Mars 96 Orbiter

mailto:[email protected]?Subject=NMC Comment/Question: Mars 96 Orbiter (1996-064A)

mailto:[email protected]?Subject=NMC Comment/Question: Mars 96 Orbiter (1996-064A)









http://nssdc.gsfc.nasa.gov/image/spacecraft/mars96a.jpg



Dr. Albert A. Galeev ProgramScientist

Russian Academy ofSciences

[email protected]

Dr. Alexander V.Zakharov

ProjectScientist


[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-entryMars 96 Surface StationMars 96 Penetrator

Other Sources of Mars 96 Information

Mars 96 Project (IKI)

Information about Mars

Mars Page


http://nssdc.gsfc.nasa.gov/planetary/text/mars96_timeline.txt

http://www.iki.rssi.ru/mars96/mars96hp.html

http://nssdc.gsfc.nasa.gov/planetary/planets/marspage.html

http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=MARS96D[08/06/2011 23:04:42]


Description


The Russian Mars 96 mission was designed to send an orbiter,two small autonomous stations, and two surface penetrators toMars to investigate the evolution and contemporary physics ofthe planet by studying the physical and chemical processeswhich took place in the past and which currently take place.Mars 96 was scheduled to arrive at Mars on 12 September1997, about 10 months after launch, on a direct trajectory.

The two Mars 96 Penetrators were mounted on the bottom ofthe orbiter near the propulsion system. The penetrators werelong thin cylinders, pointed at the bottom, or forebody, and witha widened, funnel-shaped top. Instruments were containedinside throughout the length of the cylinder. The scientificobjectives of the penetrator experiments were to obtain imagesof the surface, study martian meteorology, examine thephysical, chemical, magnetic, and mechanical properties of themartian regolith, including its water content, collect data on themagnetic field, and record seismic activity.

After orbit insertion, adjustment to 300 km periapsis, and 7 to28 days of orbital maneuvers, the orbiter would be properlyoriented and the first penetrator would be spun about its longaxis and released. When the penetrator had moved away fromthe orbiter, its solid rocket motor was to ignite and put it into anatmospheric entry trajectory. Entry would occur 21 to 22 hourslater. The penetrator was to enter the atmosphere at about 4.9km/sec at an angle 10-14 degrees. The probe would first beslowed aerodynamically, followed by inflation of a brakingdevice. The penetrator was to strike the surface atapproximately 80 m/s. The forebody would separate on impactand can penetrate 5 to 6 meters into the ground, attached bywires to the aftbody, the top of the aftbody remaining above thesurface. The plan called for the first penetrator to land near thesite of one of the surface stations, and the second to land atleast 90 degrees away. Both pentrators could have beenreleased on the same orbit.

The penetrator was equipped with instruments in both theforebody and aftbody. The forebody held a seismometer,accelerometer, thermoprobe, neutron detector, and an alpha-proton-X-ray spectrometer. The aftbody contained a gamma-ray spectrometer and thermoprobe within the part of the

Mars 96 Penetrator

NSSDC ID: MARS96D

Facts in Brief

Launch Date: 1996-11-16Launch Vehicle: ProtonLaunch Site: Tyuratam(Baikonur Cosmodrome),RussiaMass: 45.0 kg

Funding Agency


Discipline

Planetary Science


Launch/Orbitalinformation for Mars 96Penetrator

PDMP information forMars 96 Penetrator

Telecommunicationsinformation for Mars 96Penetrator

Experiments on Mars 96Penetrator

Data collections from Mars96 Penetrator



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


Mars 96 Penetrator


http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=MARS96D



http://nssdc.gsfc.nasa.gov/nmc/spacecraftPdmp.do?id=MARS96D

http://nssdc.gsfc.nasa.gov/nmc/spacecraftPdmp.do?id=MARS96D

http://nssdc.gsfc.nasa.gov/nmc/spacecraftTelemetry.do?id=MARS96D



http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Mars 96 Penetrator


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Mars 96 Penetrator


mailto:[email protected]?Subject=NMC Comment/Question: Mars 96 Penetrator (MARS96D)

mailto:[email protected]?Subject=NMC Comment/Question: Mars 96 Penetrator (MARS96D)









http://nssdc.gsfc.nasa.gov/image/spacecraft/mars96_penetrator.gif


http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=MARS96D[08/06/2011 23:04:42]

cylinder underground, and meteorology sensors, amagnetometer, a television camera, and transmitter exposedat the top. The experiments were to begin after landing. Datawas to be transmitted to the orbiter and then relayed to Earth.The penetrators have an expected lifetime of 1 year.

Personnel




[email protected]


ProjectScientist


[email protected]


Mars 96 Failure - Timeline from launch to re-entryMars 96 OrbiterMars 96 Surface Station




Mars Page





http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=MARS96E[08/06/2011 23:05:06]


Description


The Russian Mars 96 mission was designed to send an orbiter,two small autonomous stations, and two surface penetrators toMars to investigate the evolution and contemporary physics ofthe planet by studying the physical and chemical processeswhich took place in the past and which currently take place.Mars 96 was scheduled to arrive at Mars on 12 September1997, about 10 months after launch, on a direct trajectory.

The two Mars 96 Penetrators were mounted on the bottom ofthe orbiter near the propulsion system. The penetrators werelong thin cylinders, pointed at the bottom, or forebody, and witha widened, funnel-shaped top. Instruments were containedinside throughout the length of the cylinder. The scientificobjectives of the penetrator experiments were to obtain imagesof the surface, study martian meteorology, examine thephysical, chemical, magnetic, and mechanical properties of themartian regolith, including its water content, collect data on themagnetic field, and record seismic activity.

After orbit insertion, adjustment to 300 km periapsis, and 7 to28 days of orbital maneuvers, the orbiter would be properlyoriented and the first penetrator would be spun about its longaxis and released. When the penetrator had moved away fromthe orbiter, its solid rocket motor was to ignite and put it into anatmospheric entry trajectory. Entry would occur 21 to 22 hourslater. The penetrator was to enter the atmosphere at about 4.9km/sec at an angle 10-14 degrees. The probe would first beslowed aerodynamically, followed by inflation of a brakingdevice. The penetrator was to strike the surface atapproximately 80 m/s. The forebody would separate on impactand can penetrate 5 to 6 meters into the ground, attached bywires to the aftbody, the top of the aftbody remaining above thesurface. The plan called for the first penetrator to land near thesite of one of the surface stations, and the second to land atleast 90 degrees away. Both penetrators could have beenreleased on the same orbit.

The penetrator was equipped with instruments in both theforebody and aftbody. The forebody held a seismometer,accelerometer, thermoprobe, neutron detector, and an alpha-proton-X-ray spectrometer. The aftbody contained a gamma-ray spectrometer and thermoprobe within the part of the

Mars 96 Penetrator

NSSDC ID: MARS96E

Facts in Brief


Funding Agency


Discipline

Planetary Science


Launch/Orbitalinformation for Mars 96Penetrator

PDMP information forMars 96 Penetrator

Telecommunicationsinformation for Mars 96Penetrator

Experiments on Mars 96Penetrator

Data collections from Mars96 Penetrator



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


Mars 96 Penetrator


http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=MARS96E



http://nssdc.gsfc.nasa.gov/nmc/spacecraftPdmp.do?id=MARS96E

http://nssdc.gsfc.nasa.gov/nmc/spacecraftPdmp.do?id=MARS96E

http://nssdc.gsfc.nasa.gov/nmc/spacecraftTelemetry.do?id=MARS96E







mailto:[email protected]?Subject=NMC Comment/Question: Mars 96 Penetrator (MARS96E)

mailto:[email protected]?Subject=NMC Comment/Question: Mars 96 Penetrator (MARS96E)









http://nssdc.gsfc.nasa.gov/image/spacecraft/mars96_penetrator.gif


http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=MARS96E[08/06/2011 23:05:06]

cylinder underground, and meteorology sensors, amagnetometer, a television camera, and transmitter exposedat the top. The experiments were to begin after landing. Datawas to be transmitted to the orbiter and then relayed to Earth.The penetrators have an expected lifetime of 1 year.

Personnel




[email protected]


ProjectScientist


[email protected]


Mars 96 Failure - Timeline from launch to re-entryMars 96 OrbiterMars 96 Surface Station




Mars Page





http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=MARS96B[08/06/2011 23:05:34]


Description


The Russian Mars 96 mission was designed to send an orbiter,two small autonomous stations, and two surface penetrators toMars to investigate the evolution and contemporary physics ofthe planet by studying the physical and chemical processeswhich took place in the past and which currently take place.Mars 96 was scheduled to arrive at Mars on 12 September1997, about 10 months after launch, on a direct trajectory.About 4 to 5 days before arrival the small surface stationswere to be released.

The small station was contained inside a cylindrical aeroshellapproximately 1 meter in diameter and 1 meter high with amass of 25.5 kg for a total mass (station plus aeroshell) of 33.5kg. Each station was to enter the atmosphere at a velocity ofless than 5.75 km/s at an entry angle between 10.5 and 20.5degrees and an entry azimuth between 115 and 145 degrees.The aeroshells were to be shed before landing and parachuteswill be used to slow the descent. On landing the stationcovering would open into four triangular petals which extendingapproximately 30 cm from the central base.

The primary landing sites were 41.31 N, 153.77 W and 32.48N, 169.32 W, with a backup site at 3.65 N, 193 W. Landingdispersion was to be 10 degrees along track and 2 degreesacross track. All sites are in the Arcadia Planitia region in thenorthern hemisphere of Mars.

The station was to study the vertical structure of theatmosphere and take images during its descent. On thesurface it would have a meteorology station mountedapproximately 1 meter above the base of the station to studydiurnal, seasonal, and annual variations in the atmosphere. Amagnetometer would have extended from one of the petals tomeasure the planet's surface magnetic field and its variationwith time. A seismometer would collect data on the seismicenvironment. An Alpha-Proton-X-Ray spectrometer wouldextend from one petal and measure the elemental compositionof the surface. An oxidant sensor, extending from a third petal,was to measure oxidant abundances. A panoramic camera ismounted on a mast on the base of the station. The stationswere planned to have an active lifetime of about 700 days(approximately 1 martian year) on the surface.

Mars 96 Surface Station

NSSDC ID: MARS96B

Facts in Brief


Funding Agency


Discipline

Planetary Science


Launch/Orbitalinformation for Mars 96Surface Station

PDMP information forMars 96 Surface Station

Experiments on Mars 96Surface Station

Data collections from Mars96 Surface Station



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=MARS96B



http://nssdc.gsfc.nasa.gov/nmc/spacecraftPdmp.do?id=MARS96B

http://nssdc.gsfc.nasa.gov/nmc/spacecraftPdmp.do?id=MARS96B

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Mars 96 Surface Station


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Mars 96 Surface Station


mailto:[email protected]?Subject=NMC Comment/Question: Mars 96 Surface Station (MARS96B)

mailto:[email protected]?Subject=NMC Comment/Question: Mars 96 Surface Station (MARS96B)









http://nssdc.gsfc.nasa.gov/image/spacecraft/mars96_station.jpg


http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=MARS96B[08/06/2011 23:05:34]

The station was to be powered by two radio-isotopethermogenerators (RTG's), a battery, and a secondary powersource. The surface station was equipped with a transmitter toradio data back to the orbiter for return to Earth, and a receiverto download commands from Earth via the orbiter.

Personnel




[email protected]


ProjectScientist


[email protected]


Mars 96 Failure - Timeline from launch to re-entryMars 96 OrbiterMars 96 Penetrator




Mars Page





http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=MARS96C[08/06/2011 23:06:22]


Description


The Russian Mars 96 mission was designed to send an orbiter,two small autonomous stations, and two surface penetrators toMars to investigate the evolution and contemporary physics ofthe planet by studying the physical and chemical processeswhich took place in the past and which currently take place.Mars 96 was scheduled to arrive at Mars on 12 September1997, about 10 months after launch, on a direct trajectory.About 4 to 5 days before arrival the small surface stationswere to be released.

The small station was contained inside a cylindrical aeroshellapproximately 1 meter in diameter and 1 meter high with amass of 25.5 kg for a total mass (station plus aeroshell) of 33.5kg. Each station was to enter the atmosphere at a velocity ofless than 5.75 km/s at an entry angle between 10.5 and 20.5degrees and an entry azimuth between 115 and 145 degrees.The aeroshells were to be shed before landing and parachuteswill be used to slow the descent. On landing the stationcovering would open into four triangular petals which extendingapproximately 30 cm from the central base.

The primary landing sites were 41.31 N, 153.77 W and 32.48N, 169.32 W, with a backup site at 3.65 N, 193 W. Landingdispersion was to be 10 degrees along track and 2 degreesacross track. All sites are in the Arcadia Planitia region in thenorthern hemisphere of Mars.

The station was to study the vertical structure of theatmosphere and take images during its descent. On thesurface it would have a meteorology station mountedapproximately 1 meter above the base of the station to studydiurnal, seasonal, and annual variations in the atmosphere. Amagnetometer would have extended from one of the petals tomeasure the planet's surface magnetic field and its variationwith time. A seismometer would collect data on the seismicenvironment. An Alpha-Proton-X-Ray spectrometer wouldextend from one petal and measure the elemental compositionof the surface. An oxidant sensor, extending from a third petal,was to measure oxidant abundances. A panoramic camera ismounted on a mast on the base of the station. The stationswere planned to have an active lifetime of about 700 days(approximately 1 martian year) on the surface.


NSSDC ID: MARS96C

Facts in Brief


Funding Agency


Discipline

Planetary Science


Launch/Orbitalinformation for Mars 96Surface Station

PDMP information forMars 96 Surface Station

Telecommunicationsinformation for Mars 96Surface Station

Experiments on Mars 96Surface Station

Data collections from Mars96 Surface Station



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=MARS96C



http://nssdc.gsfc.nasa.gov/nmc/spacecraftPdmp.do?id=MARS96C

http://nssdc.gsfc.nasa.gov/nmc/spacecraftPdmp.do?id=MARS96C

http://nssdc.gsfc.nasa.gov/nmc/spacecraftTelemetry.do?id=MARS96C







mailto:[email protected]?Subject=NMC Comment/Question: Mars 96 Surface Station (MARS96C)

mailto:[email protected]?Subject=NMC Comment/Question: Mars 96 Surface Station (MARS96C)









http://nssdc.gsfc.nasa.gov/image/spacecraft/mars96_station.jpg


http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=MARS96C[08/06/2011 23:06:22]

The station was to be powered by two radio-isotopethermogenerators (RTG's), a battery, and a secondary powersource. The surface station was equipped with a transmitter toradio data back to the orbiter for return to Earth, and a receiverto download commands from Earth via the orbiter.

Personnel




[email protected]


ProjectScientist


[email protected]


Mars 96 Failure - Timeline from launch to re-entryMars 96 OrbiterMars 96 Penetrator




Mars Page





http://www.usa.gov/








Description

The Mars Global Surveyor (MGS) orbited Mars over a sevenyear period and collected data on the surface morphology,topography, composition, gravity, atmospheric dynamics, andmagnetic field. This data will be used to investigate the surfaceprocesses, geology, distribution of material, internal properties,evolution of the magnetic field, and the weather and climate ofMars.

Spacecraft and SubsystemsThe spacecraft itself is a rectangular box approximately 1.17 x1.17 x 1.7 meters in size, made up of two parts, the equipmentmodule and the propulsion module. All instruments except themagnetometer are stored on the nadir equipment deck, on oneof the 1.17 x 1.17 meter surfaces. This is the top of theequipment module, which is 0.735 m high. The main thrusterand propulsion tanks are on the opposite side from theinstruments, on the propulsion module, which is approximately1 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 meterdiameter parabolic high gain dish antenna is mounted on anadjacent side, and attached to a 2 meter boom, which isextended for mapping operations so the antenna is held awayfrom the body of the spacecraft.

The spacecraft is three-axis stabilized with no scan platform.The main 596 N thruster wil use hydrazine and N2O4propellant. Control is through 12 4.45 N hydrazine thrusters,mounted in four groups of three (two aft facing and one rollcontrol thruster). The initial propellant load was 216.5 kg ofhydrazine and 144 kg of N2O4. Four solar array panels (2GaAs, 2 SI) provide 980 W of power to the spacecraft. Energyis stored in two 20 Amp-hr nickel hydrogen batteries, andsupplied at 28 V DC. Temperature control is primarily passivewith multilayer insulation, thermal radiators, and louvers,augmented by electrical heaters. Communications is achievedvia the deep space network using the high gain antenna andtwo low gain antennas, one mounted on the high gain antennaand one on the equipment module. Uplink is in the X-band,downlink in the X and Ka bands. Minimum downlink rate is21.33 kbps, 2 kbps engineering data downlink, and 10 bpsemergency downlink.

The instruments on the nadir equipment deck consist of acamera, thermal emission spectrometer, laser altimeter, and aradio transmission relay. A magnetometer/electronreflectometer sensor is attached to the end of each solararray, and an ultra-stable oscillator is used for tracking andgravity determination. An 8086 processor is used for thepayload data subsystem, and 1750A processors for the

Mars Global Surveyor

NSSDC ID: 1996-062A

Alternate Names

MGS

24648

Facts in Brief

Launch Date: 1996-11-07Launch Vehicle: DeltaII 7925Launch Site: CapeCanaveral, United StatesMass: 1030.5 kgNominalPower: 980.0 W

Funding Agency


Discipline

Planetary Science


Launch/Orbitalinformation for MarsGlobal Surveyor

PDMP information forMars Global Surveyor

Telecommunicationsinformation for MarsGlobal Surveyor

Experiments on MarsGlobal Surveyor

Data collections from MarsGlobal Surveyor

Questions or commentsabout this spacecraft canbe directed to: Dr. David R.


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data












http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Mars Global Surveyor

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Mars Global Surveyor

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Mars Global Surveyor

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Mars Global Surveyor

mailto:[email protected]?Subject=NMC Comment/Question: Mars Global Surveyor (1996-062A)









http://nssdc.gsfc.nasa.gov/planetary/image/mars_global_surveyor.jpg



standard controls processor and the engineering dataformatter. Data is stored on four 0.75 Gb solid state recorders.

Mission ProfileAfter launch on a Delta 7925 (a Delta II Lite launch vehicle withnine strap-on solid-rocket boosters and a Star 48 (PAM-D)third stage) and a 10 month cruise phase, the Mars GlobalSurveyor was inserted into an elliptical capture orbit at 01:17UT 12 September 1997. Over the next four months, it wasintended that aerobraking maneuvers and thrusters would beused to lower the orbit to the final circular mapping orbit.However, one of the solar panels failed to latch properly whenit was deployed and subsequently showed unexpected motionand moved past its fully deployed position when aerobrakingbegan (thought to be due to the fracture of a damper arm andsubsequent structural damage). A new aerobraking schedulewas employed, which involved slower aerobraking putting lesspressure on the solar panels through April 1998, at which timean 11.6 hour science phasing orbit with a 171 km periapsiswas achieved and aerobraking was halted. After a 5 monthhiatus, aerobraking was resumed on 23 September 1998.Science observations were made periodically during thesemaneuvers.

After aerobraking ended in February 1999, MGS was in a 118minute circular polar science mapping orbit with an indexaltitude of 378 km. The orbit is sun-synchronous (2 a.m./2p.m.) and maps over the 2 p.m. crossing from south to north(instead of north to south as originally planned). The orbit hasa 7 day near-repeat cycle so Mars will be mapped in 26 daycycles. Science mapping began in mid-March 1999, which wassummer in the northern hemisphere on Mars. The primarymission lasted one martian year (687 Earth days) throughJanuary, 2001. An extended mission took place until April2002, further extensions were added until contact with thespacecraft was lost on 2 November 2006.

The Mars Global Surveyor mission cost about $154 million todevelop and build and $65 million to launch. Missionoperations and data analysis cost approximately $20million/year.

Williams.

Personnel


Dr. Mary K.Olsen

ProgramManager


Dr. Arden L.Albee

ProjectScientist

California Institute ofTechnology

[email protected]

Mr. Glenn F.Cunningham

ProjectManager


[email protected]

Ms. Patricia G.Rogers

ProgramScientist

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.

mailto:[email protected]?Subject=NMC Comment/Question: Mars Global Surveyor (1996-062A)



Mars Global Surveyor NSSDC Home PageMars Home PageMars 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 InformationViking Mission Information


http://nssdc.gsfc.nasa.gov/planetary/marsurv.html


http://nssdc.gsfc.nasa.gov/planetary/factsheet/marsfact.html

http://nssdc.gsfc.nasa.gov/cd-rom/web_store.cgi?category=mgs

http://nssdc.gsfc.nasa.gov/planetary/text/mgs_pr_20070413.txt

http://nssdc.gsfc.nasa.gov/planetary/marsurv.html#press

http://mpfwww.jpl.nasa.gov/mgs/index.html

http://nssdc.gsfc.nasa.gov/planetary/mesur.html

http://nssdc.gsfc.nasa.gov/planetary/viking.html

http://www.usa.gov/






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




Description

The Mars Pathfinder was the second of NASA's low-costplanetary Discovery missions to be launched. The missionconsists of a stationary lander and a surface rover. Themission had the primary objective of demonstrating thefeasibility of low-cost landings on and exploration of theMartian surface. This objective was met by tests ofcommunications between the rover and lander, and the landerand Earth, tests of the imaging devices and sensors, and testsof the maneuverability and systems of the rover on thesurface. The scientific objectives include atmospheric entryscience, long-range and close-up surface imaging, rock andsoil composition and material properties experiments, andmeteorology, with the general objective being to characterizethe Martian environment for further exploration. (MarsPathfinder was formerly known as the Mars EnvironmentalSurvey (MESUR) Pathfinder.)

Mars Pathfinder was launched on a Delta 7925 (a Delta II Litelaunch vehicle with nine strap-on solid-rocket boosters and aStar 48 (PAM-D) third stage) at 6:58:00 UT (1:58 a.m. EST) on4 December 1996. The spacecraft entered the Martianatmosphere on 4 July 1997 directly from its approachhyperbola at about 7300 m/s without going into orbit aroundthe planet. The cruise stage was jettisoned 30 minutes beforeatmospheric entry. The lander took atmosphericmeasurements as it descended. The entry vehicle's heat shieldslowed the craft to 400 m/s in about 160 seconds. A 12.5meter parachute was deployed at this time, slowing the craft toabout 70 m/s. The heat shield was released 20 seconds afterparachute deployment, and the bridle, a 20 meter long braidedKevlar tether, deployed below the spacecraft. The landerseparated from the backshell and slid down to the bottom ofthe bridle over about 25 seconds. At an altitude of about 1.6km, the radar altimeter acquired the ground, and about 10seconds before landing four air bags inflated in about 0.3seconds forming a 5.2 meter diameter protective 'ball' aroundthe lander. Four seconds later at an altitude of 98 m the threesolid rockets, mounted in the backshell, fired to slow thedescent, and about 2 seconds later the bridle was cut 21.5 mabove the ground, releasing the airbag-encased lander. Thelander dropped to the ground in 3.8 seconds and impacted at16:56:55 UT (12:56:55 p.m. EDT) on 4 July 1997 at a velocityof 18 m/s - approximately 14 m/s vertical and 12 m/s horizontal- and bounced about 12 meters (40 feet) into the air, bouncingat least another 15 times and rolling before coming to restapproximately 2.5 minutes after impact and about 1 km fromthe initial impact site.

After landing, the airbags deflated and were retracted.

Mars Pathfinder

NSSDC ID: 1996-068A

Alternate Names

MESUR Pathfinder

Carl Sagan MemorialStation

Pathfinder

24667

Facts in Brief

Launch Date: 1996-12-04Launch Vehicle: DeltaII 7925Launch Site: CapeCanaveral, United StatesMass: 463.0 kgNominal Power: 35.0 W

Funding Agency


Discipline

Planetary Science


Launch/Orbitalinformation for MarsPathfinder

PDMP information forMars Pathfinder

Telecommunicationsinformation for MarsPathfinder

Experiments on MarsPathfinder

Data collections from MarsPathfinder


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


Mars Pathfinder










http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Mars Pathfinder

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Mars Pathfinder

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Mars Pathfinder

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Mars Pathfinder









http://nssdc.gsfc.nasa.gov/planetary/image/marspath_lander.jpg



Pathfinder opened its three metallic triangular solar panels(petals) 87 minutes after landing. The lander first transmittedthe engineering and atmospheric science data collected duringentry and landing, the first signal being received at Earth at18:34 UT (2:34 p.m. EDT). The imaging system obtainedviews of the rover and immediate surroundings and apanoramic view of the landing area and transmitted it to Earthat 23:30 UT. After some maneuvers to clear an airbag out ofthe way, ramps were deployed and the rover, stowed againstone of the petals, rolled onto the surface on 6 July at about05:40 UT (1:40 a.m. EDT).

The bulk of the lander's task was to support the rover byimaging rover operations and relaying data from the rover toEarth. The lander was also equipped with a meteorologystation. Over 2.5 meters of solar cells on the lander petals, incombination with rechargeable batteries, powered the lander.The lander on-board computer is based on 32-bit architecturewith 4 million bytes of static random access memory and 64million bytes of mass memory for storing images. The mainlander components are held in a tetrahedral shaped unit in thecenter of the three petals, with three low-gain antennasextending from three corners of the box and a cameraextending up from the center on a 0.8 meter high pop-up mast.Images were taken and experiments performed by the landerand rover until 27 September 1997 when communicationswere 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 MemorialStation. The Ares Vallis region of Mars is a large outwash plainnear Chryse Planitia. This region is one of the largest outflowchannels on Mars, the result of a huge flood (possibly anamount of water equivalent to the volume of all five GreatLakes) over a short period of time flowing into the martiannorthern lowlands.

The Mars Pathfinder mission cost approximately $265 millionincluding launch and operations. Development andconstruction of the lander cost $150 million and the roverabout $25 million.


Personnel


Dr. Mark A.Saunders

ProjectManager

NASA Headquarters

Dr. MatthewGolombek

ProjectScientist


[email protected]

Dr. Joseph M.Boyce

ProgramScientist


Mr. Anthony J.Spear

ProjectManager


[email protected]

Mr. Donald T.Ketterer

ProgramManager


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.

mailto:[email protected]?Subject=NMC Comment/Question: Mars Pathfinder (1996-068A)

mailto:[email protected]?Subject=NMC Comment/Question: Mars Pathfinder (1996-068A)



Mars Pathfinder PageMars Pathfinder Rover - NSSDC Master Catalog.

Mars Pathfinder Flight Status Report

Information on the entry and landing strategyInformation on the landing siteInformation on post-landing itinerary - operations and image availability

Mars Pathfinder Project Home Page

Mars Fact SheetMars Home Page



http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=MESURPR

http://nssdc.gsfc.nasa.gov/planetary/text/marspath_status.txt

http://nssdc.gsfc.nasa.gov/planetary/marsentry.html

http://nssdc.gsfc.nasa.gov/planetary/marsland.html

http://nssdc.gsfc.nasa.gov/planetary/marspath_postland.html

http://mars.jpl.nasa.gov/MPF/index1.html



http://www.usa.gov/





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.


http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=MESURPR[08/06/2011 23:10:00]


Description

The Mars Pathfinder was the second of NASA's low-costplanetary Discovery missions to be launched. The missionconsists of a stationary lander and a surface rover. Themission had the primary objective of demonstrating thefeasibility of low-cost landings on and exploration of theMartian surface. This objective was met by tests ofcommunications between the rover and lander, and the landerand Earth, tests of the imaging devices and sensors, and testsof the maneuverability and systems of the rover on thesurface. The scientific objectives include atmospheric entryscience, long-range and close-up surface imaging, rock andsoil composition and material properties experiments, andmeteorology, with the general objective being to characterizethe Martian environment for further exploration. (MarsPathfinder was formerly known as the Mars EnvironmentalSurvey (MESUR) Pathfinder.)

The rover, which has been named "Sojourner" is a six-wheeledvehicle, 280 mm high, 630 mm long, and 480 mm wide with aground clearance of 130 mm, mounted on a "rocker-bogie"suspension. The rover was stowed on the lander at a height of180 mm. At deployment, the rover extended to its full heightand rolled down a deployment ramp at about 05:40 UT on 6July 1997 (1:40 a.m. EDT). The rover was controlled by anEarth-based operator who used images obtained by both therover and lander systems. Note that the time delay wasbetween 10 and 15 minutes depending on the relative positionof Earth and Mars over the course of the mission, requiringsome autonomous control, provided by a hazard avoidancesystem on the rover. The on-board control system is an Intel80C85 8-bit processor which runs about 100,000 instructionsper second. The computer is capable of compressing andstoring a single image on-board. The rover is powered by 0.2square meters of solar cells, which will provide energy forseveral hours of operations per sol (1 Martian day = 24.6 Earthhours). Non-rechargeable lithium thionyl chloride (LiSOCl2) D-cell batteries provide backup. All rover communications weredone through the lander.

The rover is equipped with black and white and color imagingsystems which were used to image the lander in order toassess its condition after touchdown. The goal was to acquirethree black and white images spaced 120 degrees apart of thelander. Images of the surrounding terrain were also acquiredto study size and distribution of soils and rocks, as well aslocations of larger features. Imaging of the rover wheel trackswill be used to estimate soil properties. Imaging of the rover bythe lander was also done to assess rover performance and soiland site properties. The rover's performance was monitored to

Mars Pathfinder Rover

NSSDC ID: MESURPR

Alternate Names

Rocky IV

MFEX

Microrover FlightExperiment

MESUR Pathfinder Rover

Sojourner

Facts in Brief

Launch Date: 1996-12-04Launch Vehicle: DeltaIILaunch Site: CapeCanaveral, United StatesMass: 10.5 kgNominal Power: 13.0 W

Funding Agency


Discipline

Planetary Science


Launch/Orbitalinformation for MarsPathfinder Rover

PDMP information forMars Pathfinder Rover

Telecommunicationsinformation for MarsPathfinder Rover

Experiments on MarsPathfinder Rover

Data collections from MarsPathfinder Rover


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


Mars Pathfinder Rover


http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=MESURPR



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http://nssdc.gsfc.nasa.gov/nmc/spacecraftTelemetry.do?id=MESURPR



http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Mars Pathfinder Rover

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Mars Pathfinder Rover

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http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Mars Pathfinder Rover









http://nssdc.gsfc.nasa.gov/image/spacecraft/sojourner.jpg



determine tracking capabilities, drive performance, thermalbehavior, and sensor performance. UHF Communicationsbetween the rover and lander were studied to determine theeffectiveness of the link between the rover and lander.Assessments of rock and soil mechanics will be made basedon abrasion of the wheels and adherence of dust. An alpha-proton-X-ray spectrometer (APXS) is on-board the rover toassess the composition of rocks and soil. Images of allsamples tested are transmitted to Earth. The primaryobjectives were scheduled for the first seven sols, all withinabout 10 meters of the lander. The extended mission includedslightly longer trips away from the lander, and even longerjourneys were planned. Images were taken and experimentsperformed by the lander and rover until 27 September 1997when 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 MemorialStation. The Ares Vallis region of Mars is a large outwash plainnear Chryse Planitia. This region is one of the largest outflowchannels on Mars, the result of a huge flood (possibly anamount of water equivalent to the volume of all five GreatLakes) over a short period of time flowing into the martiannorthern lowlands.

The Mars Pathfinder mission cost approximately $265 millionincluding launch and operations. Development andconstruction of the lander cost $150 million and the roverabout $25 million.


Personnel


Dr. Mark A.Saunders

ProjectManager

NASA Headquarters

Dr. MatthewGolombek

ProjectScientist


[email protected]

Dr. Joseph M.Boyce

ProgramScientist


Mr. Anthony J.Spear

ProjectManager


[email protected]

Mr. Donald T.Ketterer

ProjectManager


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.

mailto:[email protected]?Subject=NMC Comment/Question: Mars Pathfinder Rover (MESURPR)

mailto:[email protected]?Subject=NMC Comment/Question: Mars Pathfinder Rover (MESURPR)



Mars Pathfinder PageMars Pathfinder Lander - NSSDC Master Catalog.

Mars Pathfinder Flight Status Report

Information on the entry and landing strategyInformation on the landing siteInformation on post-landing itinerary - operations and image availability

Mars Pathfinder Project Home Page

Mars Fact SheetMars Home Page


http://nssdc.gsfc.nasa.gov/planetary/image/marspathrov.jpg


http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1996-068A

http://nssdc.gsfc.nasa.gov/planetary/text/marspath_status.txt

http://nssdc.gsfc.nasa.gov/planetary/marsentry.html

http://nssdc.gsfc.nasa.gov/planetary/marsland.html

http://nssdc.gsfc.nasa.gov/planetary/marspath_postland.html

http://mars.jpl.nasa.gov/MPF/index1.html



http://www.usa.gov/








Description

MEASAT 1 was a Malaysian geostationary communicationsspacecraft launched by an Ariane 44L rocket from the KourouSpace Center in French Guiana. After parking at 91.5 Elongitude, the 1,450 kg spacecraft will provide communicationsand direct-to-home television services to Malaysia andneighboring countires through its 4 Ku-band and 12 C-bandtransponders.

MEASAT 1

NSSDC ID: 1996-002B

Alternate Names

Malaysia East Asia Sat 1

23765

Facts in Brief


Funding Agency

Binariang Sdn Bhd,Malaysia (Malaysia)

Discipline

Communications


Launch/Orbitalinformation for MEASAT1

Experiments on MEASAT 1

Data collections fromMEASAT 1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=MEASAT 1

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=MEASAT 1


mailto:[email protected]?Subject=NMC Comment/Question: MEASAT 1 (1996-002B)











http://www.usa.gov/








Description

MEASAT 2 (Malaysia East Asia Satellite 2) was ageostationary communications satellite designed to provide 12years of both direct-to-user television service in Malaysia andgeneral communications services in the region from Malaysiato the Philippines and from Beijing to Indonesia. It had 11active transponders in Ku-band (uplink 13.75 - 14.45 GHz,downlink 10.960-11.700 GHz). Eight of these used 95-watttraveling-wave amplifiers, and three had 62 watts. There werealso six active transponders in C-band (uplink 5.925-6.425GHz, downlink 3.700-4.200 GHz), powered by 12-watt solid-state amplifiers. It was located at 148 degrees E.

MEASAT 2

NSSDC ID: 1996-063B

Alternate Names

Malaysia East Asia Sat 2

24653

Facts in Brief


Funding Agency

Binariang Sdn Bhd,Malaysia (Malaysia)

Discipline

Communications


Launch/Orbitalinformation for MEASAT2

Experiments on MEASAT 2

Data collections fromMEASAT 2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=MEASAT 2














http://www.usa.gov/








Description

MICROSAT, also known as MuSat, is an Argentine 33 kgmicrosatellite that was launched by a Molniya-M booster fromPlesetsk cosmodrome at 05:22 UT. It carries instruments tophotograph natural resources.

Microsat

NSSDC ID: 1996-050A

Alternate Names

MuSat

24291

Facts in Brief


Funding Agency

Unknown (Argentina)

Discipline

Earth Science


Launch/Orbitalinformation for Microsat

Experiments on Microsat

Data collections fromMicrosat



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Microsat

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Microsat

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Microsat

mailto:[email protected]?Subject=NMC Comment/Question: Microsat (1996-050A)











http://www.usa.gov/








Description

Molniya 1/89 was a first-generation Russian communicationssatellite orbited to test and perfect a system of radiocommunications and television broadcasting using earthsatellites as active transponders and to experiment with thesystem in practical use. The basic function of the satellite wasto relay television programs and long-distance two-waymultichannel telephone, phototelephone, and telegraph linksfrom Moscow to the various standard ground receiving stationsin the 'Orbita' system. The satellite was in the form of ahermetically sealed cylinder with conical ends -- one endcontained the orbital correcting engine and a system ofmicrojets, and the other end contained externally mountedsolar and earth sensors. Inside the cylinder were (1) a high-sensitivity receiver and three 800-MHz 40-w transmitters (oneoperational and two in reserve), (2) telemetering devices thatmonitored equipment operation, (3) chemical batteries thatwere constantly recharged by solar cells, and (4) an electroniccomputer that controlled all equipment on board. Mountedaround the central cylinder were six large solar battery panelsand two directional, high-gain parabolic aerials, 180 deg apart.One of the aerials was directed continually toward the earth bythe highly sensitive earth sensors. The second aerial was heldin reserve. Signals were transmitted in a fairly narrow beamensuring a strong reception at the earth's surface. The satellitereceived telemetry at 1000 MHz. Television service wasprovided 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 min diameter, was much heavier than corresponding U.S.COMSATs, and it had about 10 times the power output of theEarly Bird COMSAT. In addition, it did not employ ageosynchronous equatorial orbit as have most U.S. COMSATsbecause such an orbit would not provide coverage for areasnorth of 70 deg n latitude. Instead, the satellite was boostedfrom a low-altitude parking orbit into a highly elliptical orbit withtwo high apogees daily over the northern hemisphere -- oneover Russia and one over North America -- and relatively lowperigees over the southern hemisphere. During its apogee,Molniya 1/89 remained relatively stationary with respect to theearth below for nearly 8 of every 12 hr. By placing three ormore Molniya 1 satellites in this type of orbit, spacing themsuitably, and shifting their orbital planes relative to each otherby 120 deg, a 24-hr/day communication system could beobtained.

Molniya 1-89

NSSDC ID: 1996-045A

Alternate Names

Molniya 1T

24273

Facts in Brief

Launch Date: 1996-08-14LaunchVehicle: Molniya-MLaunch Site: Plesetsk,Russia

Funding Agency

Unknown (Russia)

Discipline

Communications


Launch/Orbitalinformation for Molniya 1-89

Experiments on Molniya 1-89

Data collections fromMolniya 1-89



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Molniya 1-89


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Molniya 1-89


mailto:[email protected]?Subject=NMC Comment/Question: Molniya 1-89 (1996-045A)











http://www.usa.gov/








Description

The Molniya-3 Russian communications satellites were used tocreate the 'Orbita' communications system for northernregions, with groups of four satellites. The first Molniya 3spacecraft appeared in 1974, primarily to support civilcommunications (domestic and international), with a slightlyenhanced electrical power system and a communicationspayload of three 6/4 GHz transponders with power outputs of40 W or 80 W. The land segment used a 12 m diameterparabolic antenna, which was pointed automatically at thesatellite using autonomous electromechanical equipment. Laterversions were to be part of the YeSSS Unified SatelliteCommunications System. Trials of this version began in the1980's, with the system being accepted by the Russian militaryin 1983-1985.

Molniya 3-48

NSSDC ID: 1996-060A

Alternate Names

24640

Facts in Brief

Launch Date: 1996-10-24LaunchVehicle: Molniya-MLaunch Site: Plesetsk,Russia

Funding Agency

Unknown (Russia)

Discipline

Communications


Launch/Orbitalinformation for Molniya 3-48

Experiments on Molniya 3-48

Data collections fromMolniya 3-48



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

M-SAT 1 was a Canadian geostationary mobile telephonecommunications satellite launched by an Ariane 42P rocketfrom the Kourou Space Center to serve the North Americancontinent. The spacecraft and its transponders are very similarto those of the American AMSC 1. It had the capability tosupport 2000 radio channels in L-band. The footprint coveredthe entire continental US and Canada, as well as Alaska,Hawaii, Puerto Rico, the Virgin Islands, and 200 mile of USand Canadian coastal waters. It was one of the first satellitesto use Hughes' springback antennas, flexible 17-foot-by-22-foot ovals made of graphite.

MSAT 1

NSSDC ID: 1996-022A

Alternate Names

23846

Facts in Brief

Launch Date: 1996-04-20Launch Vehicle: Ariane42PLaunch Site: Kourou,French Guiana

Funding Agency

TMI Communications andCo. Ltd (Canada)

Discipline

Communications


Launch/Orbitalinformation for MSAT 1

Experiments on MSAT 1

Data collections fromMSAT 1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=MSAT 1

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=MSAT 1

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=MSAT 1

mailto:[email protected]?Subject=NMC Comment/Question: MSAT 1 (1996-022A)











http://www.usa.gov/








Description

MSTI 3 is the third satellite developed by the MSTI (MiniatureSensor Technology Integration) Program within the US AirForce. The satellite carries three sensors: a mediumwavelength infrared (MWIR) camera, a short wavelengthinfrared (SWIR) camera, and a visible imaging spectrometer.It's primary mission, to last for one year, is intended to gatherextensive background clutter statistics at medium wavelengthsin the infrared at sufficient resolution to resolve whethertracking theater ballistic missiles (TBMs) in the coast phaseagainst a warm earth background is achievable. The visibleimaging spectrometer will gather environmental data of similarquality to the Land-Remote Sensing Satellite to supportenvironmental and ecological studies.

MSTI 3

NSSDC ID: 1996-031A

Alternate Names

Miniature SensorTechnology Integration 3

23868

Facts in Brief

Launch Date: 1996-05-16LaunchVehicle: PegasusLaunchSite: Vandenberg AFB,United StatesMass: 175.0 kg

Funding Agency


Disciplines

Earth Science



Launch/Orbitalinformation for MSTI 3

Experiments on MSTI 3

Data collections from MSTI3



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=MSTI 3

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=MSTI 3

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=MSTI 3

mailto:[email protected]?Subject=NMC Comment/Question: MSTI 3 (1996-031A)














Description

The Midcourse Space Experiment (MSX) was a test project ofthe Ballistic Missile Defense Organization (BMDO). Its primarypurpose was to gather data over a wide-wavelength interval todemonstrate the feasibility of identifying and tracking ballisticmissiles during their midcourse flight phase. Its multispectralinstruments were capable of obtaining wide band and spectralimages in the range of ultraviolet to infrared wavelengths (110nm to 28,000 nm). The instruments were also utilized forcivilian aeronomic and auroral studies.

The 5.1 m spacecraft consisted of three sections each of 1.5 mx 1.5 m cross-section to house three payload components: anelectronics section, an 8.5 K frozen hydrogen section, and aninstruments section. The three instruments were: SPIRIT III(Space Infrared Imaging Telescope), a five-color, high-spatialresolution scanning radiometer and a six-channel, high-spectral resolution, Fourier-transform spectrometer; UVISI(Ultraviolet and Visible Imagers and Spectrographic Imagers),five spectrographic imagers and four UV/visible imagers withcapabilities from the far ultraviolet through visible wavelengths;and, Space-Based Visible (SBV), a visible band telescope witha six-inch aperturn, a charge-coupled device, and imageprocessing electronics. Also on-board were the On-boardSignal and Data Processor (OSDP), which provided real-timesignal processing for target detection and tracking for datagenerated by SPIRIT III, sensors for monitoring and measuringinstrument contamination and degradation of performancelargely due to outgassing, and a number of small (2.0 cm)reference spheres, deployed as reference objects from MSXfor instrument calibration.

MSX

NSSDC ID: 1996-024A

Alternate Names

Midcourse SpaceeXperiment

23851

Facts in Brief

Launch Date: 1996-04-24Launch Vehicle: DeltaIILaunchSite: Vandenberg AFB,United StatesMass: 2700.0 kgNominalPower: 1200.0 W

Funding Agencies

Department of Defense-Department of the Navy(United States)

Air Force Ballistic MissileDefense Organization(United States)

Disciplines

Astronomy

Engineering

Earth Science

Planetary Science

Space Physics


Launch/Orbitalinformation for MSX

PDMP information forMSX

Telecommunicationsinformation for MSX


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


MSX
















http://nssdc.gsfc.nasa.gov/image/spacecraft/msx.jpg



Experiments on MSX

Data collections from MSX

Questions or commentsabout this spacecraft canbe directed to: Dr. Dieter K.Bilitza.

Personnel


Dr. John D. Mill ProjectScientist

Environmental ResearchInstitute of Michigan(ERIM)

[email protected]

Dr. Max R.Peterson

ProgramManager

Applied Physics Laboratory [email protected]

Lcol Bruce D.Guilmain,USAF

ProgramManager

USAF Ballistic MissileDefense Organization

[email protected]

Other Sources of MSX Information/Data

MSX information (Applied Physics Laboratory)


http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=MSX

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=MSX

mailto:[email protected]?Subject=NMC Comment/Question: MSX (1996-024A)

mailto:[email protected]?Subject=NMC Comment/Question: MSX (1996-024A)

http://sd-www.jhuapl.edu/MSX/

http://www.usa.gov/








Description

N-Star-B as a Japanese geosynchronous spacecraft launchedby an Ariane rocket from the Kourou Space Center in FrenchGuiana. The 3,400 kg spacecraft is expected to provide voiceand TV broadcasts to Japan and neighboring regions.

N-Star-B

NSSDC ID: 1996-007A

Alternate Names

23781

Facts in Brief

Launch Date: 1996-02-05Launch Vehicle: ArianeLaunch Site: Kourou,French GuianaMass: 3400.0 kg

Funding Agency

Unknown (Japan)

Discipline

Communications


Launch/Orbitalinformation for N-Star-B

Experiments on N-Star-B

Data collections from N-Star-B



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=N-Star-B

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=N-Star-B

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=N-Star-B

mailto:[email protected]?Subject=NMC Comment/Question: N-Star-B (1996-007A)











http://www.usa.gov/








Description

Global Positioning System (GPS) was developed by the USDepartment of Defense to provide all-weather round-the-clocknavigation capabilities for military ground, sea, and air forces.Since its implementation, GPS has also become an integralasset in numerous civilian applications and industries aroundthe globe, including recreational used (e.g., boating, aircraft,hiking), corporate vehicle fleet tracking, and surveying. GPSemploys 24 spacecraft in 20,200 km circular orbits inclined at55 degrees. These vehicles are placed in 6 orbit planes withfour operational satellites in each plane.

GPS Block 2 was the operational system, following thedemonstration system comprised of Block 1 (Navstar 1 - 11)spacecraft. These spacecraft were 3-axis stabilized, nadirpointing using reaction wheels. Dual solar arrays supplied 710watts of power. They used S-band (SGLS) communications forcontrol and telemetry and UHF cross-link between spacecraft.The payload consisted of two L-band navigation signals at1575.42 MHz (L1) and 1227.60 MHz (L2). Each spacecraftcarried 2 rubidium and 2 cesium clocks and nuclear detonationdetection sensors. Built by Rockwell Space Systems for theUS Air Force, the spacecraft measured 5.3 m across with solarpanels deployed and had a design life of 7.5 years.

Navstar 2A-16

NSSDC ID: 1996-019A

Alternate Names

USA 117

GPS 2-25

23833

Facts in Brief


Funding Agency


Disciplines




Launch/Orbitalinformation for Navstar2A-16

Experiments on Navstar2A-16

Data collections fromNavstar 2A-16



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Navstar 2A-16


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Navstar 2A-16


mailto:[email protected]?Subject=NMC Comment/Question: Navstar 2A-16 (1996-019A)















http://www.usa.gov/








Description



Navstar 2A-17

NSSDC ID: 1996-041A

Alternate Names

GPS 2-26

USA 126

23953

Facts in Brief

Launch Date: 1996-07-15Launch Vehicle: DeltaIILaunch Site: CapeCanaveral, United StatesMass: 840.0 kgNominalPower: 710.0 W

Funding Agency


Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data
























Description



Navstar 2A-18

NSSDC ID: 1996-056A

Alternate Names

USA 128

GPS 2-27

24320

Facts in Brief

Launch Date: 1996-09-12Launch Vehicle: DeltaIILaunch Site: CapeCanaveral, United StatesMass: 840.0 kgNominalPower: 710.0 W

Funding Agency


Disciplines









Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data

























http://www.usa.gov/








Description

The Near Earth Asteroid Rendezvous - Shoemaker (NEARShoemaker), renamed in honor of Gene Shoemaker, wasdesigned to study the near Earth asteroid Eros from close orbitover a period of a year. The mission was the first-ever to orbitan asteroid and to touch down on the surface of an asteroid.The primary scientific objectives of NEAR were to return dataon 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 asindicated by dust or gas, and the asteroid spin state. This datawill be used to help understand the characteristics of asteroidsin general, their relationship to meteorites and comets, and theconditions in the early solar system. To accomplish thesegoals, the spacecraft is equipped with an X-ray/gamma rayspectrometer, a near infrared imaging spectrograph, a multi-spectral camera fitted with a CCD imaging detector, a laserrangefinder, and a magnetometer. A radio science experimentwas also performed using the NEAR tracking system toestimate the gravity field of the asteroid. The total mass of theinstruments is 56 kg, and they require 81 W power.

Mission ProfileThe ultimate goal of the mission was to study the near Earthasteroid 433 Eros from orbit for approximately one year. Erosis an S-class asteroid approximately 13 x 13 x 33 km in size,the second largest near-Earth asteroid. Initially the orbit wascircular with a radius of 200 km. The radius of the orbit wasbrought down in stages to a 50 x 50 km orbit on 30 April 2000and decreased to 35 x 35 km on 14 July 2000. The orbit wasraised over succeeding months to a 200 x 200 km orbit andthen slowly decreased and altered to a 35 x 35 km retrogradeorbit on 13 December 2000. The mission ended with atouchdown in the "saddle" region of Eros on 12 February 2001.

After launch on a Delta 7925-8 (a Delta II Lite launch vehiclewith nine strap-on solid-rocket boosters and a Star 48 (PAM-D)third stage) and exit from Earth orbit, NEAR entered the firstpart of its cruise phase. It spent most of this phase in aminimal activity "hibernation" state, which ended a few daysbefore the flyby of the 61 km diameter asteroid 253 Mathildeon June 27, 1997. The spacecraft flew within 1200 km ofMathilde at 12:56 UT at 9.93 km/sec, returning imaging andother instrument data. On July 3, 1997 NEAR executed thefirst major deep space maneuver, a two-part burn of the main450 Newton thruster. This decreased the velocity by 279m/sec and lowered perihelion from 0.99 AU to 0.95 AU. TheEarth gravity assist swingby occurred on January 23, 1998 at7:23 UT. The closest approach was 540 km, altering the orbital

NEAR Shoemaker

NSSDC ID: 1996-008A

Alternate Names

Near Earth AsteroidRendezvous

NEAR

23784

Facts in Brief


Funding Agency


Disciplines

Planetary Science

Space Physics


Launch/Orbitalinformation for NEARShoemaker

PDMP information forNEAR Shoemaker

Telecommunicationsinformation for NEARShoemaker

Experiments on NEARShoemaker

Data collections fromNEAR Shoemaker


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


NEAR Shoemaker










http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=NEAR Shoemaker

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=NEAR Shoemaker

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=NEAR Shoemaker

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=NEAR Shoemaker









http://nssdc.gsfc.nasa.gov/image/spacecraft/near_config.jpg



inclination from 0.5 to 10.2 degrees, and the aphelion distancefrom 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 December1998 at 22:00 UT aborted due to a software problem. Contactwas lost immediately after this and was not re-established forover 24 hours. The original mission plan called for these fourburns to be followed by an orbit insertion burn on 10 January1999, but the abort of the first burn and loss of communicationmade this impossible. A new plan was put into effect in whichNEAR flew by Eros on 23 December 1998 at 18:41:23 UT at aspeed of 0.965 km/s and a distance of 3827 km from thecenter of mass of Eros. Images of Eros were taken by thecamera, data was collected by the near IR spectrograph, andradio tracking was performed during the flyby. A rendezvousmaneuver was performed on 3 January 1999 involving athruster burn to match NEAR's orbital speed to that of Eros. Ahydrazine thruster burn took place on 20 January to fine-tunethe trajectory. On 12 August a 2 minute thruster burn slowedthe spacecraft velocity relative to Eros to 300 km/hr.

Orbit insertion around Eros occurred on 14 February 2000 at15:33 UT (10:33 AM EST) after NEAR completed a 13 monthheliocentric orbit which closely matched the orbit of Eros. Arendezvous maneuver was completed on 3 February at 17:00UT, slowing the spacecraft from 19.3 to 8.1 m/s relative toEros. Another maneuver took place on 8 February increasingthe relative velocity slightly to 9.9 m/s. Searches for satellitesof Eros took place on 28 January, and 4 and 9 February, nonewere found. The scans were for for scientific purposes and tomitigate any chances of collision with a satellite. NEAR wentinto a 321 x 366 km orbit around Eros on 14 February. Theorbit was slowly decreased to a 35 km circular polar orbit by 14July. NEAR remained in this orbit for 10 days and then wasbacked out in stages to a 100 km circular orbit by 5 September2000. Maneuvers in mid-October led to a flyby of Eros within5.3 km of the surface at 07:00 UT on 26 October.

Following the flyby NEAR moved to a 200 km circular orbit andshifted the orbit from prograde near-polar to a retrograde near-equatorial orbit. By 13 December 2000 the orbit was be shiftedback to a circular 35 km low orbit. where NEAR will remainuntil the nominal end of mission on 12 February 2001. Startingon 24 January 2001 the spacecraft began a series of closepasses (5 to 6 km) to the surface and on 28 January passed 2to 3 km from the asteroid. The spacecraft made a slowcontrolled descent to the surface of Eros ending with atouchdown in the "saddle" region of Eros on 12 February 2001at 20:01:52 UT (3:01:52 p.m. EST). This was the firstspacecraft touchdown on an asteroid. After landing, thespacecraft continued to operate until the final contact wasmade on 28 February. The gamma-ray spectrometer collecteddata from the asteroid's surface over this time. A later attemptto contact the spacecraft on 10 December 2002 wasunsuccessful.

Spacecraft and SubsystemsThe spacecraft has the shape of an octagonal prism,approximately 1.7 m on a side, with four fixed gallium arsenidesolar panels in a windmill arrangement, a fixed 1.5 m X-bandhigh-gain radio antenna with a magnetometer mounted on theantenna feed, and an X-ray solar monitor on one end (theforward deck), with the other instruments fixed on the oppositeend (the aft deck). Most electronics are mounted on the insideof the decks. The propulsion module is contained in theinterior.

The craft is three-axis stabilized and uses a single bipropellant


mailto:[email protected]?Subject=NMC Comment/Question: NEAR Shoemaker (1996-008A)

mailto:[email protected]?Subject=NMC Comment/Question: NEAR Shoemaker (1996-008A)



(hydrazine / nitrogen tetroxide) 450 Newton (N) main thruster,and four 21 N and seven 3.5 N hydrazine thrusters forpropulsion, for a total delta-V potential of 1450 m/s. Attitudecontrol is achieved using the hydrazine thrusters and 4reaction wheels. The propulsion system carries 209 kilogramsof hydrazine and 109 kilograms of NTO oxidizer in two oxidizerand three fuel tanks.

Power is provided by four 1.8 by 1.2 meter gallium arsenidesolar panels which can produce 400 W at 2.2 AU (NEAR'smaximum distance from the Sun) and 1800 W at 1 AU. Poweris stored in a 9 amp-hour, 22-cell rechargeable super nickel-cadmium battery.

Spacecraft guidance is achieved through the use of a sensorsuite of five digital solar attitude detectors, an inertialmeasurement unit, (IMU) and a star tracker camera pointedopposite the instrument pointing direction. The IMU containshemispherical resonator gyros and accelerometers. Fourreaction wheels (arranged so that any three can providecomplete three-axis control) are used for normal attitudecontrol. The thrusters are used to dump angular momentumfrom the reaction wheels, as well as for rapid slew andpropulsive maneuvers. Attitude control is to 0.1 degree, line-of-sight pointing stability is within 50 microradians over 1 second,and post-processing attitude knowledge is to 50 microradians.

The command and data handling subsytem is composed oftwo redundant command and telemetry processors and solidstate recorders, a power switching unit, and an interface to tworedundant 1553 standard data buses for communications withother subsystems. The solid state recorders are constructedfrom 16 Mbit IBM Luna-C DRAMs. One recorder has 1.1 Gbitsof storage, the other has 0.67 Gbits.

The NEAR mission was the first launch of NASA's Discoveryprogram, a series of small-scale spacecraft designed toproceed from development to flight in under three years for acost of less than $150 million. The total cost of the missionwas $220.5 million, which included $43.5 million for the launchvehicle and $60.8 million for mission operations after launch.

Personnel


Dr. John Kerridge ProgramScientist

NASA Headquarters

Mr. Thomas B.Coughlin

ProjectManager

Applied PhysicsLaboratory

[email protected]

Dr. Robert W.Farquhar

MissionManager


[email protected]

Dr. Elizabeth E.Beyer

ProgramManager


Dr. Andrew F.Cheng

ProjectScientist


[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 befound at the PDS Small Bodies Node Archive.

Diagram showing location of NEAR science instruments

NSSDC NEAR Home Page - Links to further information on NEARImages of Eros

Images from the Earth FlybyImages from the Eros and Mathilde Flybys

Asteroid Fact SheetNSSDC Asteroid Home PageInformation on NASA's Discovery program

NEAR project home pageLow-cost innovation in spaceflight - The NEAR Shoemaker mission (3.3 Mb PDF)

Information on the NEAR Mission Profile and Trajectory


http://pdssbn.astro.umd.edu/NEARdb/neardata.html

http://nssdc.gsfc.nasa.gov/image/spacecraft/near_diagram.jpg

http://nssdc.gsfc.nasa.gov/image/spacecraft/near_diagram.jpg

http://nssdc.gsfc.nasa.gov/planetary/near.html

http://nssdc.gsfc.nasa.gov/planetary/mission/near/near_eros.html

http://nssdc.gsfc.nasa.gov/imgcat/html/mission_page/ER_NEAR_page1.html

http://nssdc.gsfc.nasa.gov/imgcat/html/mission_page/AS_NEAR_page1.html

http://nssdc.gsfc.nasa.gov/planetary/factsheet/asteroidfact.html

http://nssdc.gsfc.nasa.gov/planetary/planets/asteroidpage.html

http://nssdc.gsfc.nasa.gov/planetary/discovery.html

http://sd-www.jhuapl.edu/NEAR

http://history.nasa.gov/monograph36.pdf

http://nssdc.gsfc.nasa.gov/planetary/mission/near/near_traj.html

http://nssdc.gsfc.nasa.gov/planetary/mission/near/near_traj.html

http://www.usa.gov/





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 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 [NASA]

Near-Infrared Spectrograph (NIS) - a spectrometer covering 800-2700 nm, NIS is designed to map the mineralogical composition of Eros. Magnetometer - a three-axis fluxgate sensor that will be used to measure Eros' magnetic field. These measurements will help determine the internal composition of the asteroid.

NEAR Laser Rangefinder (NLR) - an altimeter that uses a solid-state pulsed laser to measure the distance between the spacecraft and the surface of the asteroid. It will be used to make will make accurate measurements of the asteroid's shape and detailed surface structure. Nd-YAG laser operating at 1.064 mm wavelength, 6 meter resolution, 50 km range.

Radio Science - uses the satellite's telemetry system to map Eros' gravity field.

Nation: USA Type / Application: Asteroid Orbiter / Lander Operator: NASA Contractors: Johns Hopkins University Applied Physics Laboratory (APL) Equipment: MSI, XGRS, NIS, NLR Configuration: Octagonal Prism, 1.5 m dish antenna, 4 deployed fixed solar arrays Propulsion: LEROS-1 Lifetime: Mass: 818 kg Orbit: Heliocentric, later orbit around Asteroid 433 Eros, finally landed on Eros

Satellite Date LS Launcher Remarks: NEAR (Discovery 2, Shoemaker) 17.02.1996 CC LC-17B Delta-7925-8

http://space.skyrocket.de/doc_lau_det/delta-7925.htm�




Description

OAST Flyer (NASA's Office of Aeronautical and SpaceTechnology Flyer) is an American minispacecraft that wasreleased from the shuttle STS 72. It carried 4 experimentalpackages: to measure spacecraft contamination levels at low-earth orbits, to test GPS equipment, to test amateur radiogear, and finally to determine the effects of solar radiation onthe explosives aboard satellite systems.

OAST Flyer

NSSDC ID: 1996-001B

Alternate Names

23763

Facts in Brief


Funding Agency

NASA-Office ofAeronautics and SpaceTechnology (UnitedStates)

Disciplines

Communications


Solar Physics


Launch/Orbitalinformation for OASTFlyer

Experiments on OASTFlyer

Data collections fromOAST Flyer



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=OAST Flyer

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=OAST Flyer

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=OAST Flyer

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=OAST Flyer

mailto:[email protected]?Subject=NMC Comment/Question: OAST Flyer (1996-001B)














Description

The ORFEUS-SPAS II mission followed the ORFEUS-SPAS Imission flown in 1993, motivated by improvements ininstrument performance and the critical need for additionalobservation time. The purpose of the ORFEUS-SPAS IImission was to conduct investigations of celestial sources inthe far and extreme ultraviolet spectral range, and to increaseunderstanding of the evolution of stars, the structure ofgalaxies, and the nature of the interstellar medium. ORFEUS-SPAS II was one of a series of planned joint DARA (GermanSpace Agency) /NASA missions. The name arises from thereusable Astro-Shuttle Pallet Satellite (Astro-SPAS), and theOrbiting Retrievable Far and Extreme UltravioletSpectrometers (ORFEUS) Telescope carried on Astro-SPAS.

ORFEUS-SPAS was a free-flying platform designed to bedeployed and retrieved from the space shuttle. The Astro-SPAS carrier was powered by batteries, and data from theinstruments were stored on tape. Absolute pointing wasaccurate to within a few arc seconds. ORFEUS-SPAS is 4.5min length and has a 2.5m width base. Operation of ORFEUS-SPAS was approximately 40km from the shuttle.

ORFEUS-SPAS II carried the same three spectrometers,operating over the wavelength range 400 - 1250 Angstroms, aswas carried on ORFEUS-SPAS I. The Tubingen UltravioletEchelle Spectrometer (TUES) and the Berkeley Extreme andFar-UV Spectrometer (BEFS) were housed on the primaryinstrument - the ORFEUS 1-m telescope. The InterstellarMedium Absorption Profile Spectrograph (IMAPS) wasoperated independently from ORFEUS.

The ORFEUS-SPAS II mission was flown in November-December 1996. The mission acquired spectra of numerouscelestial objects during 14 days of observations. Efficiency of62.5% for all instruments was achieved.

ORFEUS-SPAS II

NSSDC ID: 1996-065B

Alternate Names

STS 80/ ORFEUS

ORFEUS II

24661

Facts in Brief

Launch Date: 1996-11-20LaunchVehicle: ShuttleLaunch Site: CapeCanaveral, United StatesMass: 3500.0 kg

Funding Agencies


German Space Agency(Federal Republic ofGermany)

Discipline

Astronomy


Launch/Orbitalinformation for ORFEUS-SPAS II

Experiments on ORFEUS-SPAS II

Data collections fromORFEUS-SPAS II



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=ORFEUS-SPAS II

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=ORFEUS-SPAS II

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=ORFEUS-SPAS II

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=ORFEUS-SPAS II

mailto:[email protected]?Subject=NMC Comment/Question: ORFEUS-SPAS II (1996-065B)












http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=OSL[08/06/2011 23:27:07]


Description

The main objective of the Orbiting Solar Laboratory (OSL) is toacquire images of the solar surface with the high spatialresolution required for the determination of density,temperature, magnetic field, and non-thermal velocity field insolar features on the scale at which many basic physicalprocesses occur -- less than 0.2 arcsec. In addition, high-resolution spectroscopy is performed. OSL consists of fiveinstruments. The main telescope uses an f/24 on-axisGregorian configuration with primary mirror 1.1 m in diameter,useful throughout the 220 - 1000 nm range and providing a 3.9arcmin field of view with 0.15 arcsec resolution. Threeinstruments make up the Coordinated Instrument Package(CIP) and share the focal plane at the Gregorian focus. Theseinstruments obtain narrow-band and broad-band filtergrams aswell as high-resolution spectrograms. Charge-coupled Device(CCD) cameras are employed in each instrument in the CIPwhile the remaining instrument packages use self-containedtelescopes and acquire high-resolution UV spectra and XUVand X-ray images. A finder telescope provides a continuousfull-Sun image for reference by users of the other, limited field-of-view instruments. The OSL spacecraft is three-axisstabilized, with pointing accuracy of 9 arcsec in pitch/yaw and30 arcmin in roll; image motion compensation is carried outwithin the individual instruments to achieve better than 0.2arcsec stability. A polar, Sun-synchronous orbit is used toachieve more than 250 full-Sun days per year. Solar arraysprovide power. The Tracking and Data Relay Satellite System(TDRSS) contact provides 2E7 bit/s telemetry for eighthours/day on average. The mission is planned for three yearsor longer and mission operations are to include near-realtimetargeting during TDRSS contacts. Further information may beobtained through D. F. Spicer (NASA-GSFC), Project Scientist.

OSL

NSSDC ID: OSL

Alternate Names

Orbiting Solar Lab

Facts in Brief

Launch Date: 1995-12-31Launch Vehicle: DeltaIILaunch Site: CapeCanaveral, United StatesMass: 3364.0 kg

Funding Agencies



Discipline

Solar Physics


Launch/Orbitalinformation for OSL

Experiments on OSL

Data collections from OSL


Personnel


Ms. Maureen C. Project NASA Headquarters mlocke@hst-


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data



http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=OSL

http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=OSL

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=OSL

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=OSL

mailto:[email protected]?Subject=NMC Comment/Question: OSL (OSL)

mailto:[email protected]?Subject=NMC Comment/Question: OSL (OSL)










http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=OSL[08/06/2011 23:27:07]

Locke Manager popb8.gsfc.nasa.gov

Dr. J. DavidBohlin

ProgramScientist

NASA Headquarters

Dr. Daniel S.Spicer

ProjectScientist


[email protected]

Mr. Roger A.Mattson

ProjectManager



http://www.usa.gov/








Description

Palapa C-1 was an Indonesian geosynchronous spacecraftlaunched from Cape Canaveral by an Atlas 2AS rocket. It willprovide voice and TV communications to the 17,000 islands ofIndonesia, and the nearby Asian-Pacific region. It carried 24 C-band, 6 extended C-band, and 4 Ku-band transponders, mostof which were leased to several countries.

Palapa C-1

NSSDC ID: 1996-006A

Alternate Names

23779

Facts in Brief

Launch Date: 1996-01-31Launch Vehicle: Atlas-2 ASLaunch Site: CapeCanaveral, United States

Funding Agency

Unknown (Indonesia)

Discipline

Communications


Launch/Orbitalinformation for Palapa C-1

Experiments on Palapa C-1

Data collections fromPalapa C-1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Palapa C-1


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Palapa C-1


mailto:[email protected]?Subject=NMC Comment/Question: Palapa C-1 (1996-006A)











http://www.usa.gov/








Description

Palapa C-2 was an Indonesian geosynchronouscommunications satellite that was launched from Kourou,French Guiana, by an Ariane 44L rocket. With its 34transponders and parked at 113 E longitude, it is expected toprovide voice and vision communications to a large areabounded by Iran, Vlodivostok, Australia and New Zealand.

Palapa C-2

NSSDC ID: 1996-030A

Alternate Names

23864

Facts in Brief

Launch Date: 1996-05-15Launch Vehicle: Ariane44LPLaunch Site: Kourou,French Guiana

Funding Agency

Unknown (Indonesia)

Discipline

Communications


Launch/Orbitalinformation for Palapa C-2

Experiments on Palapa C-2

Data collections fromPalapa C-2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

PAMS-STU was a NASA experimental spacecraft launchedfrom STS 77 to test an attitude stabilization design. It had anunbalanced mass distribution and two magnetic rods. Theinteraction of the rods with Earth's magnetic field was expectedto damp any wobble or spin. There were some problems inascertaining the success fully because of the malfunction ofthe laser ranger. It reentered the atmosphere on October 26.

PAMS-STU

NSSDC ID: 1996-032D

Alternate Names

23876

Facts in Brief


Funding Agency


Discipline

Technology Applications


Launch/Orbitalinformation for PAMS-STU

Experiments on PAMS-STU

Data collections fromPAMS-STU



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=PAMS-STU

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=PAMS-STU

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=PAMS-STU

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=PAMS-STU

mailto:[email protected]?Subject=NMC Comment/Question: PAMS-STU (1996-032D)











http://www.usa.gov/








Description

PAS 3R, also known as PANAMSAT 3R, as an Americangeostationary communications spacecraft launched by anAriane 44L rocket from the Kourou Space Center in FrenchGuiana. After parking at 43.0 W longitude, the 2,900 kgspacecraft will provide TV and communications services toNorth and South American countries through its 16 C-bandtransponders.

PANAMSAT 3R

NSSDC ID: 1996-002A

Alternate Names

PAS 3R

Intelsat 3R

IS-3R

23764

Facts in Brief


Funding Agencies

Pan American Satellite(United States)


Discipline

Communications


Launch/Orbitalinformation forPANAMSAT 3R

Experiments onPANAMSAT 3R

Data collections fromPANAMSAT 3R



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=PANAMSAT 3R

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=PANAMSAT 3R

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=PANAMSAT 3R

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=PANAMSAT 3R

mailto:[email protected]?Subject=NMC Comment/Question: PANAMSAT 3R (1996-002A)















http://www.usa.gov/








Description

POLAR is one of four spacecraft in the Global GeospaceScience (GGS) program. These are among the six spacecraftin the International Solar Terrestrial Physics (ISTP) program.POLAR provides multi-wavelength imaging of the aurora,measuring plasma entry into the polar magnetosphere andgeomagnetic tail, the flow of plasmas to and from theionosphere, and the deposition of particle energy in theionosphere and upper atmosphere. POLAR has on-boardpropulsion 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 mfor its two despun platforms), with body-mounted solar cells,weighs 1250 kg and uses 333 W of power. The spin rate is 10rpm around an axis approximately normal to the orbital plane. Ithas long wire spin-plane antennas, inertial booms, and spin-plane appendages to support sensors. POLAR has twodespun gimbaled instrument platforms, and booms aredeployed along both Z axes. Data are stored using on-boardtape recorders and are relayed to the Deep Space Network at600 kbps maximum (250 kbps nominal) although the averagereal-time data rate for POLAR is 41.6 kbps. POLAR has a22.6-h polar orbit (90 deg inclination), with perigee and apogeeof 11,500 and 57,000 km. Polar was launched to observe thepolar magnetosphere and, as its orbit has precessed with time,has observed the equatorial inner magnetosphere and is nowcarrying out an extended period of southern hemispherecoverage. Details on the POLAR mission and instrumentationare provided in Space Science Reviews (Vol. 71, Nos. 1-4,1995) and reprinted in The Global Geospace Mission, editedby C. T. Russell (Kluwer, 1995).

Polar

NSSDC ID: 1996-013A

Alternate Names

Polar Plasma Laboratory

GGS/Polar

ISTP/Polar

23802

Facts in Brief

Launch Date: 1996-02-24Launch Vehicle: DeltaIILaunchSite: Vandenberg AFB,United StatesMass: 1300.0 kg

Funding Agency


Discipline

Space Physics


Launch/Orbitalinformation for Polar

PDMP information forPolar

Experiments on Polar

Data collections from Polar

Questions or commentsabout this spacecraft canbe directed to: Dr. TimothyE. Eastman.


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


Polar






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Polar

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Polar

mailto:[email protected]?Subject=NMC Comment/Question: Polar (1996-013A)

mailto:[email protected]?Subject=NMC Comment/Question: Polar (1996-013A)









http://nssdc.gsfc.nasa.gov/image/spacecraft/polar.jpg



Personnel


Dr. Keith W.Ogilvie

Mission PrincipalInvestigator


[email protected]

Dr. John B.Sigwarth

Project Scientist NASA Goddard SpaceFlight Center

Dr. CharlesP. Holmes

Program Scientist NASA Headquarters [email protected]

Other Sources of Polar Data/Information

ISTP Home Page

Charge and Mass Magnetospheric Ion Composition Experiment (CAMMICE) andComprehensive Energetic Particle and Pitch Angle Distribution (CEPPAD) teamsElectric Fields Investigation (EFI) teamHot Plasma Analyzer (Hydra) teamMagnetic Fields Experiment (MFE) teamPolar Ionospheric X-ray Imaging Experiment (PIXIE) teamPlasma and Radio Waves Instrument (PWI) teamThermal Ion Dynamics Experiment (TIDE) teamToroidal Imaging Mass-Angle Spectrograph (TIMAS) teamUltraviolet Imager (UVI) teamVisible Imaging System (VIS) team


http://www-istp.gsfc.nasa.gov/

http://leadbelly.lanl.gov/ccr/

http://leadbelly.lanl.gov/ccr/

http://ssed.gsfc.nasa.gov/PolarEFI/index.html

http://www-st.physics.uiowa.edu/www/hydra.html

http://www-ssc.igpp.ucla.edu/polar/

http://pixie.spasci.com/

http://www-pw.physics.uiowa.edu/plasma-wave/istp/polar/home.html

http://wwwssl.msfc.nasa.gov/ssl/pad/sppb/TIDE/

http://lasp.colorado.edu/timas/TIMAS_description.html

http://science.nasa.gov/uvi/

http://www-pi.physics.uiowa.edu/www/vis/

http://www.usa.gov/








Description

Priroda was the last of the scheduled 5 Russian modules of Mirand was launched from the Baykonur cosmodrome by aProton-K rocket to dock after 3 days rather than the usual 9days. The launch itself was 3 days earlier than the planneddate in order to facilitate an American microbiology program.Priroda carried 900 kg of American equipment to be deliveredto the American astronaut on Mir. Other cargo on boardincluded several remote sensing Russian instruments. It islikely that Priroda may later be attached to the plannedinternational space station, Alpha.

Priroda

NSSDC ID: 1996-023A

Alternate Names

23848

Facts in Brief


Funding Agency

Unknown (Russia)

Disciplines

Earth Science

Resupply/Refurbishment/Repair


Launch/Orbitalinformation for Priroda

Experiments on Priroda

Data collections fromPriroda



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Priroda

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Priroda

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Priroda

mailto:[email protected]?Subject=NMC Comment/Question: Priroda (1996-023A)











http://www.usa.gov/








Description

An improved version of cargo freighters used to supply the Mirspace station, the Progress M series had greater cargocapacity, a modernized approach/docking system and carried 2solar panels to generate electrical power. Progress M can flyfor 30 days independently and 108 days docked with Mir.Spare propellent in Progress M's tanks can be transferred toMir before it is consigned to burn up in reentry. In the past,extra fuel was abandoned with the craft. Future Progressvehicles will carry a recoverable reentry capsule for the speedyreturn of up to 150 kg of material from Mir to earth.

Progress M-31 was launched by a Soyuz U rocket from theBaykonur cosmodrome. It docked with Mir and delivered 3000kg of food, fuel and water. It undocked on August 1 at 16:45UT and was deorbited over the south Pacific later that day.

Progress M-31

NSSDC ID: 1996-028A

Alternate Names

23860

Facts in Brief

Launch Date: 1996-05-05LaunchVehicle: Soyuz-ULaunch Site: Tyuratam(Baikonur Cosmodrome),KazakhstanMass: 7250.0 kg

Funding Agency

Unknown (Russia)

Discipline



Launch/Orbitalinformation for ProgressM-31

Experiments on ProgressM-31

Data collections fromProgress M-31



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Progress M-31


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Progress M-31


mailto:[email protected]?Subject=NMC Comment/Question: Progress M-31 (1996-028A)











http://www.usa.gov/








Description


Progress M-32 was launched from the Baikonur cosmodromeaboard a Soyuz-U rocket. It delivered 2,500 kg of supplies andequipment to the Mir space station.

Progress M-32

NSSDC ID: 1996-043A

Alternate Names

24071

Facts in Brief

Launch Date: 1996-07-31LaunchVehicle: Soyuz-ULaunch Site: Tyuratam(Baikonur Cosmodrome),KazakhstanMass: 2500.0 kg

Funding Agency

Unknown (Russia)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Progress M-33 was launched by a Soyuz-Y rocket from theBaykonur cosmodrome. It delivered 2,400 kg of food, fuel andequipment.

Progress M-33

NSSDC ID: 1996-066A

Alternate Names

24633

Facts in Brief

Launch Date: 1996-11-19LaunchVehicle: Soyuz-YLaunch Site: Tyuratam(Baikonur Cosmodrome),Kazakhstan

Funding Agency

Unknown (Russia)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Raduga 33 was a Russian communications spacecraftlaunched by a Proton-K rocket from the BaykonurCosmodrome. It was intended to be geostationary but it turnedout to be a failed launch due to the explosion of the fourthstage just prior to the final maneuver.

Raduga 33

NSSDC ID: 1996-010A

Alternate Names

23794

Facts in Brief


Funding Agency


Discipline

Communications


Launch/Orbitalinformation for Raduga33

Experiments on Raduga 33

Data collections fromRaduga 33



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Raduga 33

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Raduga 33

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Raduga 33

mailto:[email protected]?Subject=NMC Comment/Question: Raduga 33 (1996-010A)











http://www.usa.gov/








Description

REX 2 (Radiation EXperiment 2) was an American militaryminispacecraft launched from Vandenberg AFB by a PegasusXL rocket. The rocket was carried aloft in the belly of a L-1011aircraft to 12 km altitude before release and ignition. It is an AirForce Rome Laboratory ionospheric research satellite whichwill test the effects of the atmosphere on radio transmissions,and will employ GPS for on-board navigation and attitudecontrol.

REX 2

NSSDC ID: 1996-014A

Alternate Names

23814

Facts in Brief

Launch Date: 1996-03-08LaunchVehicle: Pegasus XLLaunchSite: Vandenberg AFB,United StatesMass: 110.0 kg

Funding Agency

Unknown (United States)

Discipline



Launch/Orbitalinformation for REX 2

Experiments on REX 2

Data collections from REX2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=REX 2

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=REX 2

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=REX 2

mailto:[email protected]?Subject=NMC Comment/Question: REX 2 (1996-014A)











http://www.usa.gov/








Description

Satellite de Aplicaciones Cientifico-B (SAC-B) was a smallsatellite built by the Argentinean National Commission ofSpace Activities (CoNAE). SAC-B was designed to advancethe study of solar physics and astrophysics through theexamination of solar flares, gamma ray bursts, diffuse X-raycosmic background, and energetic neutral atoms. The satellitewas also designed to test and characterize the performance ofnew equipment and technologies which may be used in futureoperational or scientific missions. The satellite payloadincluded three astronomical instruments - the Hard X-raySpectrometer (HXRS), the Goddard X-ray Experiment (GXRE),and the Cosmic Unresolved X-ray Background Instrument(CUBIC). Also flying was an Italian instrument called ISENAwhich plans to measure energetic netral atoms. The spacecraftbody was a 62 x 62 cm wide by 80 cm high rectangularparallelepiped wotj 4 extended solar panels 62 cm wide by 76cm long.

SAC-B satellite was launched with the NASA satellite HETE 1.The SAC-B solar arrays did not automatically deploy due to abattery failure in the Pegasus XL rocket third stage. The solararrays were deployed via ground commands, howeverbecause of spacecraft tumbling and shadowing of the PegasusXL third stage, they were unable to generate enough power tokeep the satellite's batteries charged.

SAC-B

NSSDC ID: 1996-061B

Alternate Names

Satelite de AplicacionesCientificas - B

24645

Facts in Brief

Launch Date: 1996-11-04LaunchVehicle: Pegasus XLLaunch Site: WallopsIsland, United StatesMass: 181.0 kg

Funding Agencies


National Commission ofSpace Activities(Argentina)

Disciplines

Astronomy

Solar Physics

Space Physics


Launch/Orbitalinformation for SAC-B

Experiments on SAC-B

Data collections from SAC-B



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=SAC-B

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=SAC-B

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=SAC-B

mailto:[email protected]?Subject=NMC Comment/Question: SAC-B (1996-061B)













Personnel



http://www.usa.gov/








Description

SAX is the X-Ray Astronomy Satellite selected by the ItalianNational Space Plan for inclusion in the Science Plan. Theobjective of the mission is to perform spectroscopic and timevariability studies of celestial X-ray sources in the energy bandfrom 1 to 200 keV, including an all-sky monitoring investigationof transients in the 2-30 keV energy range. The payloadincludes the following narrow-field detectors coaligned to acommon pointing axis: (1) four X-ray imaging concentratorssensitive from 1 to 10 keV (one of them extending down to 0.1keV), (2) one gas scintillation proportional counter sensitivefrom 3 to 12 keV, and (3) a sodium iodide scintillator crystal inphoswich configuration operating from 15 to 200 keV. At 90deg to the axis of the narrow field instruments is an array ofthree identical wide field camera units sensitive from 2 to 30keV. The SAX mission payload and science program is underthe responsibility of a consortium of Italian institutes togetherwith institutes from Holland. The participation of the SpaceScience Department of ESA is also foreseen. A listing of theSAX Consortium of Institutes is given in Appendix B8.

SAX

NSSDC ID: 1996-027A

Alternate Names

Satellite for X-RayAstronomy

Beppo-SAX

23857

Facts in Brief

Launch Date: 1996-04-30Launch Vehicle: Atlas-CentaurLaunch Site: CapeCanaveral, United StatesMass: 900.0 kg

Funding Agency

Agenzia Spaziale Italiana(Italy)

Discipline

Astronomy


Launch/Orbitalinformation for SAX

Experiments on SAX

Data collections from SAX


US Active Arvhive for Beppo-SAX Information/Data

The Beppo-SAX Data Archive at HEASARC


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=SAX

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=SAX

mailto:[email protected]?Subject=NMC Comment/Question: SAX (1996-027A)



http://heasarc.gsfc.nasa.gov/docs/sax/shp_archive.html











Other Sources of SAX Information/Data

Beppo-SAX home page (Italian Space Agency)


http://www.sdc.asi.it/

http://www.usa.gov/








Description

Soyuz TM-33 was a Russian transportation spacecraft thatwas launched from the Baykonur Cosmodrome carrying 2cosmonauts. It docked with the Mir space station on February23rd.

Designed and manufactured by RKK Energiya, the Soyuz TMwas capable of carrying three cosmonauts and had a grossweight of just over seven metric tons, a length of sevenmeters, and a maximum diameter of 2.7 m. The spacecraftconsisted of three main sections: the orbital module, thecommand and reentry module, and the service module. Twosolar arrays (10.6 m span) provided electrical power for thetypical 50-hour journey to Mir and could be interconnected withthe space station's electrical system to furnish additional 1.3kW. The nominal flight time for Soyuz TM spaceship was 5-6months.

Soyuz-TM 23

NSSDC ID: 1996-011A

Alternate Names

23798

Facts in Brief

Launch Date: 1996-02-21Launch Vehicle: SoyuzLaunch Site: Tyuratam(Baikonur Cosmodrome),KazakhstanMass: 7150.0 kg

Funding Agency

Unknown (Russia)

Discipline

Human Crew


Launch/Orbitalinformation for Soyuz-TM23

Experiments on Soyuz-TM23

Data collections fromSoyuz-TM 23



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Soyuz-TM 23


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Soyuz-TM 23


mailto:[email protected]?Subject=NMC Comment/Question: Soyuz-TM 23 (1996-011A)











http://www.usa.gov/





Soyuz TM-23

Launch, orbit and landing data

Launch date: 21.02.1996 Launch time: 12:34 UT Launch site: Baikonur Launch pad: 1 Altitude: 201 - 246 km Inclination: 51,6° Landing date: 02.09.1996 Landing time: 07:41 UT Landing site: 50° 17' N, 70° 50' E

Crew No. Surname Given name Job Flight No. Duration Orbit

s

1 Onufriyenko Yuri Ivanovich Commander 1 193d 19h 07m 3066

2 Usachyov Yuri

Vladimirovich Flight Engineer 2 193d 19h 07m 3066

http://www.spacefacts.de/maps/english/e_bai_kazak_1.htm�

http://www.spacefacts.de/maps/english/e_soyuz-tm-23.htm�

http://www.spacefacts.de/bios/cosmonauts/english/onufriyenko_yuri.htm�



http://www.spacefacts.de/bios/cosmonauts/english/usachyov_yuri.htm�

http://www.spacefacts.de/mission/p_large/english/soyuz-tm-23.htm�

http://www.spacefacts.de/mission/p_large/english/soyuz-tm-23_2.htm�

http://www.spacefacts.de/mission/p_large/english/soyuz-tm-23_3.htm�

http://www.spacefacts.de/mission/large/english/soyuz-tm-23.htm�

Crew seating arrangement

Launch 1 Onufriyenko 2 Usachyov 3

Landing 1 Onufriyenko 2 Usachyov 3 André-Deshays

Double Crew

No. Surname Given name Job

1 Tsibliyev

Vasili Vasiliyevich

Commander

2 Lazutkin Aleksandr

Ivanovich 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.





http://www.spacefacts.de/bios/international/english/andre-deshays_claudie.htm�

http://www.spacefacts.de/bios/cosmonauts/english/tsibliyev_vasili.htm�



http://www.spacefacts.de/bios/cosmonauts/english/lazutkin_aleksandr.htm�

http://www.spacefacts.de/mir/english/mir-21.htm�

http://www.spacefacts.de/mission/english/sts-76.htm�

http://www.spacefacts.de/bios/astronauts/english/lucid_shannon.htm�

http://www.spacefacts.de/mission/large/english/soyuz-tm-23_2.htm�

http://www.spacefacts.de/graph/drawing/large/english/mir_1995.htm�





Description

Soyuz TM-24 carried a crew of three to the Mir space station.The crew consisted of Cosmonauts Valery Korzun andAlexander Kalery, and the first French woman in space,Claudie Andre-Deshays. They joined American astronautShannon Lucid and Mir 21 crewmates Yuri Onufriyenko andYuri Usachev. Andre-Deshays carried out biological andmedical experiments on Mir for 16 days before returning toEarth with Onufriyenko and Usachev.

Soyuz-TM 24

NSSDC ID: 1996-047A

Alternate Names

24280

Facts in Brief

Launch Date: 1996-08-18LaunchVehicle: Soyuz-ULaunch Site: Tyuratam(Baikonur Cosmodrome),Kazakhstan

Funding Agency

Unknown (Russia)

Discipline

Human Crew


Launch/Orbitalinformation for Soyuz-TM24

Experiments on Soyuz-TM24

Data collections fromSoyuz-TM 24



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/





Soyuz TM-24


Launch date: 17.08.1996 Launch time: 13:18 UT Launch site: Baikonur Launch pad: 1 Altitude: 195,8 - 242,8 km Inclination: 51,63° Landing date: 02.03.1997 Landing time: 06:44 UT Landing site: 47° 49' N, 69° 24' E

Crew

No. Surname Given name Job Flight No. Duration Orbi

ts

1 Korzun Valeri Grigoriyevich Commander 1 196d 17h

26m 3113

2 Kaleri Aleksandr Yuriyevich Flight Engineer 2 196d 17h

26m 3113

3 André-Deshays Claudie Research

Cosmonaut 1 15d 18h 23m 249

http://www.spacefacts.de/maps/english/e_bai_kazak_1.htm�

http://www.spacefacts.de/maps/english/e_soyuz-tm-24.htm�

http://www.spacefacts.de/bios/cosmonauts/english/korzun_valeri.htm�

http://www.spacefacts.de/bios/cosmonauts/english/kaleri_aleksandr.htm�



http://www.spacefacts.de/mission/p_large/english/soyuz-tm-24.htm�


Launch 1 Korzun 2 Kaleri 3 André-Deshays

Landing 1 Korzun 2 Kaleri 3 Ewald

Double Crew


3 Eyharts Léopold 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.






http://www.spacefacts.de/bios/international/english/ewald_reinhold.htm�

http://www.spacefacts.de/bios/international/english/eyharts_leopold.htm�

http://www.spacefacts.de/bios/cosmonauts/english/manakov_gennadi.htm�

http://www.spacefacts.de/bios/cosmonauts/english/vinogradov_pavel.htm�

http://www.spacefacts.de/bios/cosmonauts/english/manakov_gennadi.htm�



http://www.spacefacts.de/bios/astronauts/english/blaha_john.htm�

http://www.spacefacts.de/bios/astronauts/english/linenger_jerry.htm�






http://www.spacefacts.de/mission/english/soyuz-tm23.htm�

http://www.spacefacts.de/mission/large/english/soyuz-tm-24_original.htm�

Photos / Drawings


http://www.spacefacts.de/graph/drawing/large/english/soyuz-tm-24_pad.htm�




Description

Spartan 207 was an 850 kg module released from STS 77 asa platform from which to launch an inflatable antenna (IAE). Itwas captured back into the shuttle soon after the antennarelease.

Spartan 207

NSSDC ID: 1996-032B

Alternate Names

23871

Facts in Brief


Funding Agency


Discipline

Astronomy


Launch/Orbitalinformation for Spartan207

Experiments on Spartan207

Data collections fromSpartan 207



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Spartan 207

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Spartan 207

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Spartan 207

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Spartan 207

mailto:[email protected]?Subject=NMC Comment/Question: Spartan 207 (1996-032B)











http://www.usa.gov/








Description

STS 72 was a US shuttle spacecraft launched from CapeCanaveral. It carried, released, and retrieved the OAST Flyer.It also retrieved a long orbiting Japanese reusable spacecraft,SFU, that had amassed astronomical data and materialscience products since March 1995.

The primary objective of the STS-72 mission was to captureand return to Earth a Japanese microgravity researchspacecraft known as Space Flyer Unit (SFU). The 7,885lbsSFU spacecraft was launched by Japan's National SpaceDevelopment Agency (NASDA) from Tanegashima SpaceCenter in Japan at 8:01 UT on March 18, 1995 aboard aJapanese H-II rocket (HII-3).

The STS-72 mission also deployed (for about 50 hours) andthen retrieved the Office of Aeronautics and Space TechnologyFlyer (OAST-Flyer) spacecraft. OAST-Flyer was the seventh ina series of missions aboard reuseable free-flying Spartancarriers. It consisted of four experiments: Return FluxExperiment (REFLEX), Global Positioning System AttitudeDetermination and Control Experiment (GADACS), SolarExposure to Laser Ordnance Device (SELODE) and theUniversity of Maryland Spartan Packet Radio Experiment(SPRE).

Other experiments onboard STS-72 included the Shuttle SolarBackscatter Ultraviolet Experiment (SSBUV-8) (previouslyflown on STS-34, STS-41, STS-43, STS-45, STS-56, STS-62and STS-66), EDFT-03, Shuttle Laser Altimeter Payload (SLA-01/GAS(5)), VDA-2, National Institutes of Health NIH-R3Experiment, Space Tissue Loss Experiment (STL/NIH-C), PoolBoiling Experiment (PBE) (hardware previously flown on STS-47, STS-57 and STS-60) and the Thermal Energy Storage(TES-2) experiment (previously flown on STS-69).

Get Away Special payloads included the United States AirForce Academy G-342 Flexible Beam Experiment(FLEXBEAM-2), Society of Japanese Aerospace Companies'G-459 - Protein Crystal Growth Experiment and the JetPropulsion Laboratory GAS Ballast Can with Sample ReturnExperiment.

Endeavour's 10th flight also included two 6.5 hour spacewalksby three astronauts to test hardware and tools that will beused in the assembly of the International Space Stationstarting in late 1997. EVA-1 on flight day five consists ofCrewmembers Leroy Chiao (EV1) and Dan Barry (EV2) whileEVA-2 on Flight Day 7 consists of Leroy Chiao (EV1) andWinston Scott (EV2).

STS 72

NSSDC ID: 1996-001A

Alternate Names

23762

Facts in Brief


Funding Agency

NASA-Office of SpaceFlight (United States)

Discipline

Human Crew


Launch/Orbitalinformation for STS 72

Experiments on STS 72

Data collections from STS72



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=STS 72

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=STS 72


mailto:[email protected]?Subject=NMC Comment/Question: STS 72 (1996-001A)











STS-72 Endeavour (10)

USA


Launch date: 11.01.1996 Launch time: 09:41 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-B Altitude: 463 km Inclination: 28,45° Landing date: 20.01.1996 Landing time: 07:41 UT Landing site: Cape Canaveral (KSC)

Crew

No. Surname Given name Job Flight No. Duration Orbits

1 Duffy Brian CDR 3 8d 22h 01m 142

2 Jett Brent Ward, Jr. PLT 1 8d 22h 01m 142

3 Chiao Leroy MSP 2 8d 22h 01m 142

http://www.spacefacts.de/maps/english/39-b.htm�

http://www.spacefacts.de/maps/english/ksc_landing.htm�

http://www.spacefacts.de/bios/astronauts/english/duffy_brian.htm�

http://www.spacefacts.de/bios/astronauts/english/jett_brent.htm�

http://www.spacefacts.de/bios/astronauts/english/chiao_leroy.htm�

http://www.spacefacts.de/mission/p_large/english/sts-72.htm�

http://www.spacefacts.de/mission/p_large/english/sts-72_2.htm�

http://www.spacefacts.de/mission/large/english/sts-72.htm�

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


Launch 1 Duffy 2 Jett 3 Chiao 4 Scott 5 Wakata 6 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

http://www.spacefacts.de/bios/astronauts/english/scott_winston.htm�

http://www.spacefacts.de/bios/international/english/wakata_koichi.htm�

http://www.spacefacts.de/bios/astronauts/english/barry_daniel.htm�

















http://www.spacefacts.de/graph/drawing/large/english/shuttle.htm�

http://www.spacefacts.de/graph/sts/large_launch/english/sts-72.htm�

http://www.spacefacts.de/graph/drawing/large/english/oast-flyer.htm�

http://www.spacefacts.de/graph/drawing/large/english/sts-72_eva-scott.htm�

http://www.spacefacts.de/graph/sts/large_landing/english/sts-72.htm�




Description

The STS 75 mission was the 75th shuttle mission and the 19thflight of the Columbia orbiter. The primary tasks of this shuttleflight were to conduct experiments as part of the third flight ofthe United States Microgravity Payload (USMP-3) and todeploy the joint Italian-US Tethered Satellite System (TSS-1R).

The TSS-1R mission was a reflight of TSS-1 which was flownonboard Space Shuttle Atlantis on STS-46 in July/August of1992. During that flight, the tether was deployed a distance of860 feet. STS-75 mission scientist hope to deploy the tether toa distance of over 12 miles (20.7km).

The Tether Satellite System circled the Earth at an altitude of296 kilometers which placed the tether system within therarefied electrically charged layer of the atmosphere known asthe ionosphere. The conducting tether generated high voltageand electrical currents as it moved through the ionosphereacross the magnetic field lines of the earth. Scientists wereable to learn more about the electrodynamics of a conductingtether system to deepen our understanding of physicalprocesses in the near-Earth space environment. These studieswill help provide explanations for events such as the formationand behavior of comet tails and bursts of radio "noise"detected from other planets.

The specific TSS1-R mission objectives were: characterize thecurrent-voltage response of the TSS-orbiter system,characterize the satellites high-voltage sheath structure andcurrent collection process, demonstrate electric powergeneration, verify tether control laws and basic tetherdynamics, demonstrate the effect of neutral gas on the plasmasheath and current collection, characterize the TSS radiofrequency and plasma wave emissions and characterize theTSS dynamic-electrodynamic coupling.

TSS-1R Science Investigations include: TSS Deployer CoreEquipment and Satellite Core Equipment (DCORE/SCORE),Research on Orbital Plasma Electrodynamics (ROPE),Research on Electrodynamic Tether Effects (RETE), MagneticField Experiment for TSS Missions (TEMAG), ShuttleElectrodynamic Tether System (SETS), Shuttle Potential andReturn Electron Experiment (SPREE), Tether OpticalPhenomena Experiment (TOP), Investigation ofElectromagnetic Emissions by the Electrodynamic Tether(EMET), Observations at the Earth's Surface ofElectromagnetic Emissions by TSS (OESSE), Investigationand Measurement of Dynamic Noise in the TSS (IMDN),Theoretical and Experimental Investigation of TSS Dynamics

STS 75

NSSDC ID: 1996-012A

Alternate Names

23801

Facts in Brief


Funding Agency


Disciplines

Human Crew

Space Physics







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


STS 75


















http://nssdc.gsfc.nasa.gov/image/spacecraft/sts-75.jpg



(TEID) and the Theory and Modeling in Support of TetheredSatellite Applications (TMST).

The USMP-3 payload consisted of four major experimentsmounted on two Mission Peculiar Experiment SupportStructures (MPESS) and three Shuttle Mid-deck experiments.The experiments are: Advanced Automated DirectionalSolidification Furnace (AADSF), Material pour l'Etude desPhenomenes 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) andIsothermal Dendritic Growth Experiment (IDGE).

During this flight, the tether on TSS-1R broke after the satellitehad been deployed to a distance of 19.7 km. The shuttleended its mission after 251 orbits and a total mission durationof 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)


http://www.ksc.nasa.gov/shuttle/missions/sts-75/mission-sts-75.html

http://www.ksc.nasa.gov/shuttle/missions/sts-75/images/images.html

http://images.jsc.nasa.gov/iams/html/pao/Sts-75.htm

http://www.usa.gov/





STS-75 Columbia (19)

USA

Sour



Crew








1 Allen Andrew Michael "Andy" CDR 3 15d 17h 41m 251

2 Horowitz Scott Jay "Doc" PLT 1 15d 17h 41m 251

3 Hoffman Jeffrey Alan MSP 5 15d 17h 41m 251

4 Cheli Maurizio MSP 1 15d 17h 41m 251

5 Nicollier Claude MSP 3 15d 17h 41m 251

6 Chang-Diaz Franklin Ramon MSP 5 15d 17h 41m 251

7 Guidoni Umberto MSP 1 15d 17h 41m 251


Launch 1 Allen 2 Horowitz 3 Hoffman 4 Cheli 5 Nicollier 6 Chang-Diaz 7 Guidoni

Landing 1 Allen 2 Horowitz 3 Nicollier 4 Cheli 5 Hoffman 6 Chang-Diaz 7 Guidoni

Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC). Mission "US Microgravity Payload-3" with several experiment in different sientific fields; deploying of Italian Tethered Satellite System-1 failed, because the tether has broken after a distance of 19 km; satellite was lost; mission was extended one day due of bad weather on Cape Canaveral (KSC).

http://www.spacefacts.de/bios/astronauts/english/allen_andrew.htm�

http://www.spacefacts.de/bios/astronauts/english/horowitz_scott.htm�

http://www.spacefacts.de/bios/astronauts/english/hoffman_jeffrey.htm�

http://www.spacefacts.de/bios/international/english/cheli_maurizio.htm�

http://www.spacefacts.de/bios/international/english/nicollier_claude.htm�

http://www.spacefacts.de/bios/astronauts/english/chang-diaz_franklin.htm�

http://www.spacefacts.de/bios/international/english/guidoni_umberto.htm�















Photos / Drawings



http://www.spacefacts.de/graph/drawing/large/english/tss.htm�





Description

STS 76 was a US shuttle mission launched from CapeCanaveral. The primary mission objective was the thirddocking between the Space Shuttle Atlantis and the RussianSpace Station Mir. It included a crew transfer, anextravehicular activity (EVA), logistics operations and scientificresearch.

Rendezvous and docking with Mir was scheduled to occur onflight day three using the same approach as previously usedduring STS-74. Docking occured between the Orbiter DockingSystem in the forward area of Atlantis' payload bay and theDocking Module installed during STS-74 on Mir's Kristallmodule docking port.

The mission also featured a SPACEHAB module, middeckexperiments, a Get Away Special (GAS) canister and a 6-hourEVA. Over 1,900 pounds (862 kilograms) of equipment arebeing transfered from Atlantis to Mir including a gyrodyne,transformer, batteries, food, water, film and clothing.

Planned Experiments included the Mir Electric FieldCharacterization (MEFC) experiment, numerious EuropeanSpace Agency's (ESA) Biorack life sciences experiments, theQueen's University Experiment in Liquid Diffusion (QUELD)experiment, the Optizone Liquid Phase Sintering Experiment(OLIPSE) and a Naval Research Laboratory (NRL) Get AwaySpecial (GAS) payload Trapped Ions in Space (TRIS)experiment. TRIS measured low-energy particle radiation inthe inner magnetosphere. Another experiment conducted onMir during STS-76 was the Mir Wireless Network Experiment(WNE) which was launched on STS-74 in November 1995. Ittested the first wireless client-server network in the spaceenvironment.

The mission also included KidSat, a prototype of Earth viewingcameras and instruments that allows students in gradesKindergarden to Grade 12 (K-12) to see and direct the captureof pictures from space.

Mission Specialists Godwin and Clifford perform a six-hourspacewalk on flight day six. They attached four experiments,known collectively as the Mir Environmental Effects PayloadMEEP, onto handrails located on the Mir Docking Module.These experiments include the Polished Plate MicrometeoroidDebris (PPMD) experiment, the Orbital Debris Collector (ODC)experiment, and the Passive Optical Samples (POSA) I and IIexperiments.

STS 76

NSSDC ID: 1996-018A

Alternate Names

23831

Facts in Brief


Funding Agency


Discipline

Human Crew







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data



















STS-76 Atlantis (16)


Launch date: 22.03.1996 Launch time: 08:13 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-B Altitude: 296 km Inclination: 51,6° Landing date: 31.03.1996 Landing time: 13:28 UT Landing site: Edwards AFB


s

1 Chilton Kevin Patrick "Chily" CD

R 3 9d 05h 16m 144

2 Searfoss Richard Alan PLT 2 9d 05h 16m 144


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http://www.spacefacts.de/bios/astronauts/english/chilton_kevin.htm�

http://www.spacefacts.de/bios/astronauts/english/searfoss_richard.htm�




http://www.spacefacts.de/mir/p_large/shuttle-mir.htm�



3 Sega Ronald Michael MS

P 2 9d 05h 16m 144

4 Clifford Michael Richard Uram

"Rich" MSP 3 9d 05h 16m 144

5 Godwin Linda Maxine MS

P 3 9d 05h 16m 144

6 Lucid Matilda Shannon Wells MS

P 5 188d 04h 00m 2977


Launch 1 Chilton 2 Searfoss 3 Sega 4 Clifford 5 Godwin 6 Lucid

Landing 1 Chilton 2 Searfoss 3 Godwin 4 Clifford 5 Sega 6

Backup Crew


6 Blaha John Elmer MSP

Flight Launch from Cape Canaveral (KSC); landing on Edwards AFB; small leak of hydraulic fluid from the hydraulic system, but no Minimum Duration Flight was necessary. Docking on MIR spacestation; Shannon Lucid became member of the 21st resident crew onboard the MIR (as research cosmonaut); during the common-flight of STS-76 and MIR Godwin and Clifford performed an EVA on 27.03.1996 (6h 2m) to attach the Mir Environmental Effects Payload (MEEP), including 4 different experiments, onto handrails

http://www.spacefacts.de/bios/astronauts/english/sega_ronald.htm�

http://www.spacefacts.de/bios/astronauts/english/clifford_michael.htm�

http://www.spacefacts.de/bios/astronauts/english/godwin_linda.htm�


















http://www.spacefacts.de/bios/large/astronauts/blaha_john.htm�

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.

Photos / Drawings






http://www.spacefacts.de/graph/drawing/large/english/sts-76_mir.htm�

http://www.spacefacts.de/graph/drawing/large/english/sts-76_eva-clifford.htm�





Description

STS 77 was a Shuttle Endeavour mission launched from CapeCanaveral. The main mission was to release an inflatableantenna, IAE. The release occurred from a platform calledSpartan 207 which in turn was released from the shuttle a fewhours later. The third object released was an experimental 35kg minispacecraft, PAMS-STU. STS 77 carried the usualcomplement of crystal, metal, and biomedical experimentalgear along with 32,000 sea urchin eggs and a supply of spermto squirt on them, all in the Spacelab module. A new fizzyCoca-Cola delivering experimental device failed to performsatisfactorily.

STS 77

NSSDC ID: 1996-032A

Alternate Names

23870

Facts in Brief


Funding Agency


Disciplines

Human Crew

Life Science



Telecommunicationsinformation for STS 77





Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/





STS-77 Endeavour (11)

USA


Launch date: 19.05.1996 Launch time: 10:30 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-B Altitude: 283 km Inclination: 39° Landing date: 29.05.1996 Landing time: 11:09 UT Landing site: Cape Canaveral (KSC)

Crew


1 Casper John Howard CDR 4 10d 00h 40m 161



http://www.spacefacts.de/bios/astronauts/english/casper_john.htm�




2 Brown Curtis Lee, Jr. "Curt" PLT 3 10d 00h 40m 161

3 Thomas Andrew Sydney Withiel MSP 1 10d 00h 40m 161

4 Bursch Daniel Wheeler MSP 3 10d 00h 40m 161

5 Runco Mario, Jr. "Trooper" MSP 3 10d 00h 40m 161

6 Garneau Joseph Jean-Marie Marc MSP 2 10d 00h 40m 161


Launch 1 Casper 2 Brown 3 Thomas 4 Bursch 5 Runco 6 Garneau

Landing 1 Casper 2 Brown 3 Runco 4 Bursch 5 Thomas 6 Garneau

Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC). Mission "Spacehab-4"; deploying and retrieval of a SPARTAN-satellite and deploying of a PAMS/STU-satellite; several rendezvous-maneuvers with both satellites; various additional experiments in different fields.

Photos / Drawings

http://www.spacefacts.de/bios/astronauts/english/brown_curtis.htm�

http://www.spacefacts.de/bios/astronauts/english/thomas_andrew.htm�

http://www.spacefacts.de/bios/astronauts/english/bursch_daniel.htm�

http://www.spacefacts.de/bios/astronauts/english/runco_mario.htm�

http://www.spacefacts.de/bios/international/english/garneau_marc.htm�















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Description

STS 78 was a NASA shuttle spacecraft launched from CapeCanaveral for a 17 day mission. It carried a Spacelab (LMS-1)with many supplies and instruments for 41 microgravityexperiments involving fish embryos, rats, Bonzai plants, fluiddynamics, metallurgy, protein crystal growth, etc.

Five space agencies (NASA/USA; European SpaceAgency/Europe; French Space Agency/France; CanadianSpace Agency/Canada; and Italian Space Agency/Italy) andresearch scientists from 10 countries worked together on theprimary payload of STS-78, the Life and Microgravity Spacelab(LMS). More than 40 experiments flown were grouped into twoareas: life sciences, which included human physiology andspace biology, and microgravity science, which included basicfluid physics investigations, advanced semiconductor andmetal alloy materials processing, and medical research inprotein crystal growth.

LMS investigations were conducted via the most extensivetelescience to date. Investigators were located at four remoteEuropean and four remote U.S. locations, similar to what willhappen with the International Space Station. The mission alsomade extensive use of video imaging to help crew membersperform inflight maintenance procedures on the experimenthardware.

Previous life science investigations have delved into whatphysiological changes take place in microgravity environment;the integrated LMS experiments explored why these changesoccur. The most extensive studies ever were conducted onbone and muscle loss in space. STS-78 marked the first timeresearchers collected muscle tissue biopsy samples bothbefore and after flight. Crew members also were scheduled toundergo Magnetic Resonance Imaging (MRI) scans almostimmediately after landing. Findings from comparison of thebiopsy samples, along with various musculoskeletal testsconducted during mission, could lead to effectivecountermeasures to reduce inflight muscle atrophy.

Other life science investigations included: First evercomprehensive study of sleep cycles, 24-hour circadianrhythms and task performance in microgravity. Spacecraftorbiting Earth pass through 16 sunrises and sunsets in single24-hour period, which could disrupt normal body rhythms.During two 72-hour time blocks, crew members completedquestionnaires and measured such functions as eyemovement and muscle activity during sleep. In thePerformance Assessment Work Station, crew membersperformed a series of drills involving math problems and other

STS 78

NSSDC ID: 1996-036A

Alternate Names

23931

Facts in Brief


Funding Agency


Discipline

Human Crew







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





















mental tests to measure the microgravity effects on cognitive,or thinking, skills.

The microgravity science investigations included AdvancedGradient Heating Facility, in which samples of pure aluminumcontaining zirconia particles were solidified. This could lead tomore inexpensive ways to make mixtures of metals andceramics, particularly useful to the metal casting industry. TheAdvanced Protein Crystallization Facility is the first everdesigned to use three methods for growing protein crystals. InElectrohydrodynamics of Liquid Bridges, which focused onchanges that occur in a fluid bridge suspended between twoelectrodes. This research could finds applications in industrialprocesses 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 theBubble, Drop and Particle Unit (BDPU), designed to study fluidphysics.

The orbiter itself played a key part in a test that could helpraise the Hubble Space Telescope to a higher orbit in 1997during the second servicing mission. Columbia's vernierReaction Control System jets were gently pulsed to boost theorbiter's altitude without jarring payloads. The same exercisecould be conducted with orbiter Discovery during Mission STS-82 to raise HST's orbit without impacting its solar arrays.

No significant in-flight problems were experienced with orbiter.


http://www.usa.gov/





STS-78

Columbia (20)

USA


Launch date: 20.06.1996 Launch time: 14:49 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-B Altitude: 278 km Inclination: 39° Landing date: 07.07.1996 Landing time: 12:37 UT Landing site: Cape Canaveral (KSC)

Crew


1 Henricks Terence Thomas "Tom" CDR 4 16d 21h 48m 271

2 Kregel Kevin Richard PLT 2 16d 21h 48m 271



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http://www.spacefacts.de/groups/p_large/english/lms.htm�



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


Launch 1 Henricks 2 Kregel 3 Linnehan 4 Helms 5 Brady 6 Favier 7 Thirsk

Landing 1 Henricks 2 Kregel 3 Brady 4 Helms 5 Linnehan 6 Favier 7 Thirsk

Backup Crew


6 Duque Pedro Francisco PSP

7 Urbani Luca PSP

Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC). Mission "Life and Microgravity Spacelab"; experiments in the areas of life science and materials science; experiments for planned long-duration mission onboard the ISS; longest Shuttle-flight to date.

http://www.spacefacts.de/bios/astronauts/english/linnehan_richard.htm�

http://www.spacefacts.de/bios/astronauts/english/helms_susan.htm�

http://www.spacefacts.de/bios/astronauts/english/brady_charles.htm�

http://www.spacefacts.de/bios/international/english/favier_jean.htm�

http://www.spacefacts.de/bios/international/english/thirsk_robert.htm�















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http://www.spacefacts.de/mission/large/english/sts-78_2.htm�

Photos / Drawings


http://www.spacefacts.de/graph/drawing/large/english/sts-78_lms.htm�






Description

STS 79 was the 79th Shuttle mission, the 4th Shuttle-Mirdocking, the 1st US crew exchange, and the 32nd KSClanding. The mission was highlighted by the return to Earth ofUS astronaut Shannon Lucid after 188 days in space whichset a new US record for long-duration as well as a worldrecord for a woman. Succeeding her on Mir for anapproximately 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 insupport of the Shuttle-Mir activities and first flight of theSPACEHAB Double Module configuration. During 5 days ofmated operations, two crews transferred more than 4,000pounds (1,814 kg) of supplies to Mir, including logistics, foodand water generated by orbiter fuel cells. Three experimentsalso were transferred: Biotechnology System (BTS) for studyof cartilage development; Material in Devices asSuperconductors (MIDAS) to measure electrical properties ofhigh- temperature superconductor materials; and CommercialGeneric Bioprocessing Apparatus (CGBA), containing severalsmaller experiments, including self- contained aquatic systems.

About 2,000 pounds (907 kg) of experiment samples andequipment were transferred from Mir to Atlantis. During herapproximately six-month stay on Mir, Lucid conducted researchin the following fields: advanced technology, Earth sciences,fundamental biology, human life sciences, microgravityresearch and space sciences. Specific experiments included:Environmental Radiation Measurements to ascertain ionizingradiation levels aboard Mir; Greenhouse- Integrated PlantExperiments, to study the effects of microgravity on plants,specifically dwarf wheat; and Assessment of Humoral ImmuneFunction During Long-Duration Space flight, to gather data onthe effect of long-term spaceflight on the human immunesystem and involving the collection of blood serum and salivasamples. Some research was conducted in the newest andfinal Mir module, Priroda, which arrived at the space stationduring Lucid's stay.

Three experiments remained on Atlantis: Extreme TemperatureTranslation Furnace (ETTF), a new furnace design allowingspace-based processing up to 871 degrees F (1,600 degreesC) and above; Commercial Protein Crystal Growth (CPCG)complement of 128 individual samples involving 12 differentproteins; and Mechanics of Granular Materials, designed tofurther understanding of behavior of cohesionless granularmaterials, which could in turn lead to better understanding ofhow the Earth's surface responds during earthquakes andlandslides.

STS 79

NSSDC ID: 1996-057A

Alternate Names

24324

Facts in Brief


Funding Agency


Discipline

Human Crew







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





















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)


http://www.usa.gov/





STS-79 Atlantis (17)

USA


Launch date: 16.09.1996 Launch time: 08:54 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-A Altitude: 315 - 394 km Inclination: 51,6° Landing date: 26.09.1996 Landing time: 12:13 UT Landing site: Cape Canaveral (KSC)

Crew


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

http://www.spacefacts.de/maps/english/39-a.htm�


http://www.spacefacts.de/bios/astronauts/english/readdy_william.htm�

http://www.spacefacts.de/bios/astronauts/english/wilcutt_terrence.htm�

http://www.spacefacts.de/bios/astronauts/english/apt_jerome.htm�


http://www.spacefacts.de/mir/p_large/shuttle-mir.htm�



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


Launch 1 Readdy 2 Wilcutt 3 Apt 4 Akers 5 Walz 6 Blaha

Landing 1 Readdy 2 Wilcutt 3 Walz 4 Akers 5 Apt 6 Lucid

Backup Crew


6 Linenger Jerry Michael MSP

hi res version (880 KB)

Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC). Fourth docking with MIR space station; common mission with the 22. MIR resident crew (19. - 24.09.1996); partly crew exchange with MIR resident crew (Shannon Lucid returned to Earth, Blaha remained on MIR); supplies and equipment were also transferred between the MIR and the Shuttle including an IMAX-camera.

Note Blaha returned to Earth on 22.01.1997 at 14:23 UT with STS-81.

http://www.spacefacts.de/bios/astronauts/english/akers_thomas.htm�

http://www.spacefacts.de/bios/astronauts/english/walz_carl.htm�














http://www.spacefacts.de/bios/astronauts/english/linenger_jerry.htm�

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http://www.spacefacts.de/bios/large/astronauts/linenger_jerry.htm�

Photos / Drawings




http://www.spacefacts.de/graph/drawing/large/english/sts-79_mir.htm�





Description

The final shuttle flight of 1996 was highlighted by thesuccessful deployment, operation and retrieval of two free-flying research spacecraft. Two planned extravehicularactivities (EVAs) were cancelled.

Orbiting and Retrievable Far and Extreme UltravioletSpectrometer-Shuttle Pallet Satellite II (ORFEUS-SPAS-II)was deployed on flight day one and began approximately twoweeks of data gathering. It featured three primary scientificinstruments: the ORFEUS-Telescope with the Far Ultraviolet(FUV) Spectrometer and Extreme Ultraviolet (EUV)Spectrograph. A secondary but highly complementary payloadwas the Interstellar Medium Absorption Profile Spectrograph(IMAPS). Non-astronomy payloads included the SurfaceEffects Sample Monitor (SESAM), the ATV Rendezvous Pre-Development Project (ARP) and the Student Experiment onASTRO-SPACE (SEAS).

The Wake Shield Facility-3 (WSF-3) was deployed on flightday 4. It was a 12-foot diameter, free-flying stainless steel diskdesigned to generate an ultravacuum environment in which togrow semiconductor then films for use in advanced electronics.This third flight was successful, with a maximum of seven filmgrowths of semiconductor materials achieved and the satellitehardware performing nearly flawlessly. It was retrieved afterthree days of free-flight.

Two planned six-hour EVAs by astronauts Jernigan and Joneswere designed to evaluate equipment and procedures thatwould be used during construction and maintenance of theInternational Space Station. However, the crew could not openthe outer airlock hatch and when troubleshooting did not revealthe cause, mission managers concluded that it would not beprudent to attempt the two EVAs and risk unnecessarydamage 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 experimentsdeveloped by NASA and the National Institutes of Health, toinvestigate the role of calcium in blood pressure regulation;NASA/CCM-A, one of a series of shuttle bone cellexperiments; Biological Research in Canister (BRIC)-09experiment to study the influence of microgravity ongenetically-altered tomato and tobacco seedlings; CommercialMDA ITA experiment (CMIX-5), the last in a series of shuttleexperiments; and Visualization in an Experimental WaterCapillary Pumped Loop (VIEW-CPL), a middeck experiment toinvestigate the method for spacecraft thermal management.

STS 80

NSSDC ID: 1996-065A

Alternate Names

24660

Facts in Brief


Funding Agency


Discipline

Human Crew







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





















The crew consisted of the following:Kenneth D. Cockrell - Commander Kent V. Rominger - PilotTamara E. Jernigan - Mission Specialist Thomas D. Jones -Mission Specialist Story Musgrave - Mission Specialist


http://www.usa.gov/





STS-80 Columbia (21)

USA




s

1 Cockrell Kenneth Dale "Taco" CD

R 3 17d 15h 53m 279

2 Rominger Kent Vernon PLT 2 17d 15h 53m 279

3 Jernigan Tamara Elizabeth

"Tammy" MSP 4 17d 15h 53m 279



http://www.spacefacts.de/bios/astronauts/english/cockrell_kenneth.htm�

http://www.spacefacts.de/bios/astronauts/english/rominger_kent.htm�



http://www.spacefacts.de/bios/astronauts/english/jernigan_tamara.htm�



4 Jones Thomas David MS

P 3 17d 15h 53m 279

5 Musgrave Franklin Story MS

P 6 17d 15h 53m 279


Launch 1 Cockrell 2 Rominger 3 Jernigan 4 Jones 5 Musgrave

Landing 1 Cockrell 2 Rominger 3 Musgrave 4 Jones 5 Jernigan

Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC). Mission ORFEUS-SPAS-02; two planned EVA's were cancelled, because a hatch couldn't be opened; deploying and retrieval of German built astronomy-satellite ORFEUS-SPAS-02 and of the Wake Shield Facility (WSF 03); several secondary experiments; longest Shuttle-mission to date, landing was postponed due of bad weather at landing site; Musgrave became the oldest astronaut to date flying into space.

Photos / Drawings

http://www.spacefacts.de/bios/astronauts/english/jones_thomas.htm�

http://www.spacefacts.de/bios/astronauts/english/musgrave_story.htm�
















http://www.spacefacts.de/graph/drawing/large/english/orfeus_sts-80.htm�

http://www.spacefacts.de/graph/drawing/large/english/wsf.htm�



http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=SRL3[08/06/2011 23:42:33]


Description

The Space Radar Laboratory 3 (SRL 3) was the third in aseries of flights of this payload which was designed to (1)acquire radar imagery of the Earth's surface for studies ingeology, geography, hydrology, oceanography, agronomy, andbotony; (2) gather data for future space-borne radar systemsincluding Earth Observing System (EOS); and (3) providemeasurements of the global distribution of carbon dioxide(CO2) in the troposphere. Instruments on board included theShuttle Imaging Radar-C (SIR-C) with multi-frequency (C- andL-Bands), multi-polarization (HH, VV, HV, VH), and multi-incidence angle (15 to 55 degrees) capabilities thus lendingitself to a wide range of earth surface applications; the X-bandSynthetic Aperture Radar (X-SAR), an X-band, VV-polarizedimaging radar system, built by Dornier (Germany) and Alenia(Italy) for the German Space Agency (DARA)/GermanAerospace Research Establishment (DLR) and the ItalianSpace Agency (ASI); and, the Mapping Air Pollution fromSpace (MAPS) for the study of global air pollution. Also, on-board the SRL, was an ocean wave spectra processor,designed and built by Johns Hopkins Applied PhysicsLaboratory, which collected data on ocean surface wavelength, direction, and height. Four 45-Mbps data channelswere recorded on special high data rate tape recorders andreal-time data was transmitted to ground stations. About 50hours each of SIR-C and X-SAR data were recorded duringthe mission. The combined SIR-C/X-SAR Science Team wasmade up of 49 members and 3 associates representing 13countries. SIR-C/X-SAR data collection was focused onseveral worldwide supersites and correlated with ground andaircraft measurements. Radar data was also calibrated to allowcomparisons with other operating spaceborne radars (ERS-1SAR, JERS-1 SAR).

STS/SRL 3

NSSDC ID: SRL3

Alternate Names

SRL 3/STS

Shuttle Radar Lab 3

Space Radar Lab 3

SIR-C/X-SAR

Facts in Brief


Funding Agencies

Agenzia Spaziale Italiana(Italy)


Bundesministerium fuerForschung undTecnnologie (FederalRepublic of Germany)

Discipline

Earth Science


Launch/Orbitalinformation for STS/SRL3

PDMP information forSTS/SRL 3

Telecommunicationsinformation for STS/SRL3

Experiments on STS/SRL3


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data



http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=SRL3



http://nssdc.gsfc.nasa.gov/nmc/spacecraftPdmp.do?id=SRL3

http://nssdc.gsfc.nasa.gov/nmc/spacecraftPdmp.do?id=SRL3

http://nssdc.gsfc.nasa.gov/nmc/spacecraftTelemetry.do?id=SRL3



http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=STS/SRL 3

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=STS/SRL 3










http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=SRL3[08/06/2011 23:42:33]

Data collections fromSTS/SRL 3


Personnel


Mr. Richard M.Monson

ProgramManager

NASA Headquarters

Dr. PauloPampaloni

ProjectScientist

Consiglio Nazionale delleRicerche

[email protected]

Dr. Diane L.Evans

ProjectScientist


[email protected]

Dr. ManfredWahl

ProjectManager

Deutsche Agentur furRamfahrt-Angelegenheiten

[email protected]

Dr. Herwig Ottl ProjectScientist

Deutsche Forschungsenstaltfuer Luft-und Raumfahrt

[email protected]

Dr. PauloAmmendola

DeputyProjectManager

Italian Space Agency [email protected]

Dr. George F.Esenwein, Jr.

ProgramManager

NASA Headquarters

Mr. R. WayneRichie

ProgramManager

NASA Headquarters

Dr. Robert J.McNeal

ProgramScientist

NASA Headquarters

Mr. Michael J.Sander

ProjectManager


Selected References

Jordan, R. L., et al., SIR-C/X-SAR synthetic aperture radar system, IEEE Proc. , 79, No. 6, 827-838, June 1991.

Evans, D. L., et al., The Shuttle Imaging Radar-C and X-SAR mission, EOS, 74, No. 13, Mar.1993.


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=STS/SRL 3

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=STS/SRL 3

mailto:[email protected]?Subject=NMC Comment/Question: STS/SRL 3 (SRL3)



http://www.usa.gov/








Description

TELECOM 2D was a French geosynchronous satellitelaunched from the Kourou space center in French Guianaaboard an Ariane 44L rocket. It provided voice and videocommunications to western Europe.

TELECOM 2D

NSSDC ID: 1996-044B

Alternate Names

24209

Facts in Brief

Launch Date: 1996-08-08Launch Vehicle: Ariane44LLaunch Site: Kourou,French Guiana

Funding Agency

France Telecom (France)

Discipline

Communications


Launch/Orbitalinformation for TELECOM2D

Experiments on TELECOM2D

Data collections fromTELECOM 2D



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=TELECOM 2D

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=TELECOM 2D

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=TELECOM 2D

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=TELECOM 2D

mailto:[email protected]?Subject=NMC Comment/Question: TELECOM 2D (1996-044B)











http://www.usa.gov/








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-resolutionglobal mapping of total ozone on a daily basis (begun with theNimbus 7 SBUV/TOMS) as well as to detect global ozonetrends to verify depletion predicted by atmospheric chemistrymodels.

The TOMS-Earth Probe (TOMS-EP), the first of a series ofNASA Earth Probe missions, was one of three TOMS missionswhich included METEOR 3/TOMS2 (launched 1991) andADEOS/TOMS (launched 1995). The TOMS-EP carried onlyone instrument: the Total Ozone Mapping Spectrometer(TOMS).

The TOMS-EP spacecraft was based on the TRW/DSI Eaglebus developed under the USAF STEP program. Thespacecraft was three-axis stabilized so that the TOMSinstrument was nadir-pointed with about 0.5 degree controland about 0.1 degree knowledge from measured altitude data.The TOMS-EP spacecraft bus was designed to accomodate allof the TOMS instrument requirements to support a two-yearlifetime with a three-year lifetime goal.

TOMS-EP

NSSDC ID: 1996-037A

Alternate Names

SMEX/TOMS-EarthProbe

Small Explorer/TOMS-Earth Probe

TOMS-EP96

TOMS-Earth Probe

23940

Facts in Brief

Launch Date: 1996-07-02LaunchVehicle: Pegasus XLLaunchSite: Vandenberg AFB,United StatesMass: 248.0 kg

Funding Agency


Discipline

Earth Science


Launch/Orbitalinformation for TOMS-EP

PDMP information forTOMS-EP

Telecommunicationsinformation for TOMS-EP

Experiments on TOMS-EP

Data collections fromTOMS-EP


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data









http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=TOMS-EP

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=TOMS-EP

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=TOMS-EP












Personnel


Dr. RobertDouglasHudson

ProjectScientist


Dr. George F.Esenwein, Jr.

ProgramManager

NASA Headquarters

Mr. Donald L.Margolies

ProjectManager


[email protected]


mailto:[email protected]?Subject=NMC Comment/Question: TOMS-EP (1996-037A)



http://www.usa.gov/








Description

The TSS-1R mission is a reflight of the Tethered Satellite TSS-1 that had been flown on the Space Shuttle mission STS-46 inJuly of 1992. A protruding bolt had prevented full release ofthe tether during the TSS-1 mission. The TSS missionequipment consists of the deployer system, the Italian-buildsatellite, the electrically conductive tether (22km total length)and 6 science instruments. The TSS-1 is to be deployed from areel in the orbiter payload bay upward (away from Earth) to upto 20 Km (12.5 miles) above the Orbiter. The objectives of thismission are: (1) to verify engineering performance of theTethered Satellite System (TSS); (2) to determine and tounderstand the electro-magnetic interaction between thetether/satellite/orbiter system and the ambient space plasma;(3) to investigate and to understand the dynamical forcesacting upon a tethered satellite; (4) to demonstrate electricalpower generation; and, (5) to develop the capability for futuretether applications on the Shuttle and Space Station. Thedeploying system consists of a motor- driven tether storagereel and level wind system. A separate multipurposeequipment support structure (MPESS) carries all scienceinstruments not integrated on the satellite, with the exceptionof the Tethered Optical Phenomena (TOP) equipment, which iscarried in the crew compartment. The spherical satellite is 1.6meters in diameter and 6.5 meters in length. The S-bandantenna, magnetometers, and Research on Orbital PlasmaElectrodynamics (ROPE) equipment are mounted on stationarybooms, and the Research on Electrodynamic Tether Effects(RETE) Langmuir probe and dipole field antenna are mountedon 2.5 meter deployable/retractable booms. At the base of thesatellite, a swivel joint and a bayonet pin attache the tether tothe satellite. A connector routes the tether conductor to anammeter and then to the satellite's skin. The satellite containedcold gas (nitrogen) thrusters used for deployment, retrieval,and attitude control. The 2.54 mm diameter conducting tetherwas constructed using Kevlar and Nomex with 10 strands of34 AWG copper wire and a Teflon sheath. NASA is reponsiblefor the TSS deployer and systems integration, and Italy forbuilding the satellite. Five hours after deployment began onFebruary 25, 1996, with 19.7 km (of 20.7 planned) of tetherreleased, the tether cable suddenly snapped near the top ofthe deployment boom. The TSS satellite shot away into ahigher orbit. TSS instruments could be re-actived andproduced science data for three days until battery power ranout. An independent review panel was formed to review theTSS-1R failure.

TSS-1R

NSSDC ID: 1996-012B

Alternate Names

Tethered Satellite System1R

23805

Facts in Brief


Funding Agencies

Piano Spaziale Nazionaleof CNR (Italy)


Disciplines

Engineering

Space Physics


Launch/Orbitalinformation for TSS-1R

PDMP information forTSS-1R

Telecommunicationsinformation for TSS-1R

Experiments on TSS-1R

Data collections from TSS-1R

Questions or commentsabout this spacecraft can


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





http://nssdc.gsfc.nasa.gov/nmc/spacecraftPdmp.do?id=1996-012B

http://nssdc.gsfc.nasa.gov/nmc/spacecraftPdmp.do?id=1996-012B

http://nssdc.gsfc.nasa.gov/nmc/spacecraftTelemetry.do?id=1996-012B

http://nssdc.gsfc.nasa.gov/nmc/spacecraftTelemetry.do?id=1996-012B

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=TSS-1R

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=TSS-1R

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=TSS-1R











be directed to: Dr. Dieter K.Bilitza.

Personnel


Mr. Robert O.McBrayer

ProjectManager

NASA Marshall SpaceFlight Center

Prof. FrancoMariani

ProgramScientist


[email protected]

Dr. Michael A.Calabrese

ProgramManager


Mr. Nobie H.Stone

ProjectScientist


Mr. James M.Sisson

MissionManager


Dr. Robert A.Hoffman

ProgramScientist


[email protected]

Prof. MarinoDobrowolny

ProgramScientist


[email protected]

Dr. G. Manarini ProgramManager


Dr. Stanley D.Shawhan

ProgramScientist

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 75TSS-1

Other Sources of TSS-1R Information/Data

TSS home page


mailto:[email protected]?Subject=NMC Comment/Question: TSS-1R (1996-012B)

mailto:[email protected]?Subject=NMC Comment/Question: TSS-1R (1996-012B)

http://nssdc.gsfc.nasa.gov/space/text/tss-1r_loss.txt

http://nssdc.gsfc.nasa.gov/space/text/tss-1r_results.txt

http://nssdc.gsfc.nasa.gov/space/text/tss-1r_report.txt

http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=TSS-1

http://science.nasa.gov/ssl/pad/sppb/Tether/

http://www.usa.gov/








Description

Turksat 1C was a Turkish geosynchronous communicationssatellite that was launched by an Ariane 44L rocket from theKourou site in French Guiana. After parking at 42 deg E, thespacecraft provided radio and TV communications to Turkeyand neighboring countries.

Turksat 1C

NSSDC ID: 1996-040B

Alternate Names

23949

Facts in Brief


Funding Agency

Unknown (Turkey)

Discipline

Communications


Launch/Orbitalinformation for Turksat1C

Experiments on Turksat 1C

Data collections fromTurksat 1C



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Turksat 1C

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Turksat 1C

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Turksat 1C

mailto:[email protected]?Subject=NMC Comment/Question: Turksat 1C (1996-040B)











http://www.usa.gov/








Description

UFO 7 (UHF Follow On 7) was a US Navy satellite launched toreplace the FLTSATCOM and Leasat spacecraft currentlysupporting the Navy's global communications network, servingships at sea and a variety of other US military fixed and mobileterminals. It was compatible with ground- and sea-basedterminals already in service.

The UHF F/O satellites offered increased communicationschannel capacity over the same frequency spectrum used byprevious systems. Each spacecraft had 11 solid-state UHFamplifiers and 39 UHF channels with a total of 555 kHzbandwidth. The UHF payload compresed 21 narrow bandchannels at 5 kHz each and 17 relay channels at 25 kHz. Incomparison, FLTSATCOM offered 22 channels. The F-1through F-7 spacecraft included an SHF (super high frequency)subsystem, which provided command and ranging capabilitieswhen the satellite was on station as well as the secure uplinkfor Fleet Broadcast service, which was downlinked at UHF.

Each satellite measured more than 60 feet long from the tip ofone three-panel solar array wing to the tip of the other. Thesearrays generated a combined 2500 watts of electrical power onthe first three satellites, 2800 watts for F-4 through F-7, and3800 watts for F-8 through F-10 with GBS. The arrays werefolded against the spacecraft bus for launch, forming a cuberoughly 11 feet per side.

UFO 7

NSSDC ID: 1996-042A

Alternate Names

USA 127

UHF Follow On 7

23967

Facts in Brief

Launch Date: 1996-07-25Launch Vehicle: Atlas 2Launch Site: CapeCanaveral, United StatesMass: 3015.0 kg

Funding Agency


Disciplines

Communications



Launch/Orbitalinformation for UFO 7

Experiments on UFO 7

Data collections from UFO7



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, II




http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=UFO 7

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=UFO 7

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=UFO 7

mailto:[email protected]?Subject=NMC Comment/Question: UFO 7 (1996-042A)











http://www.usa.gov/







Description

A secondary payload launched with Cosmos 2334 was theUNAMSAT-B small satellite, for the Automonous University ofMexico (UNAM). It repaced a satellite lost in a launch failure in1995. It used the 25 cm AMSAT Microsat bus and carried anexperiment to determine the velocity of meteors using radiodoppler echo, and a communications data relay forenvironmental sensors in remote locations.

UNAMSAT-B

NSSDC ID: 1996-052B

Alternate Names

OSCAR 30

24305

Facts in Brief

Launch Date: 1996-09-05LaunchVehicle: CosmosLaunch Site: Plesetsk,RussiaMass: 10.0 kg

Funding Agency

Automonous University ofMexico (Mexico)

Disciplines

Communications

Space Physics


Launch/Orbitalinformation forUNAMSAT-B

Experiments onUNAMSAT-B

Data collections fromUNAMSAT-B



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, II





http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=UNAMSAT-B

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=UNAMSAT-B

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=UNAMSAT-B

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=UNAMSAT-B

mailto:[email protected]?Subject=NMC Comment/Question: UNAMSAT-B (1996-052B)











http://www.usa.gov/







Description

USA 118 was an American military (USAF) electronicinteligence satellite launched from Cape Canaveral aboard aTitan 4 rocket.

USA 118

NSSDC ID: 1996-026A

Alternate Names

23855

Facts in Brief

Launch Date: 1996-04-24Launch Vehicle: TitanIVLaunch Site: CapeCanaveral, United States

Funding Agency


Discipline



Launch/Orbitalinformation for USA 118

Experiments on USA 118

Data collections from USA118



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=USA 118

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=USA 118


mailto:[email protected]?Subject=NMC Comment/Question: USA 118 (1996-026A)











http://www.usa.gov/








Description

This US Navy Ocean Surveillance Satellite (NOSS) waslaunched from Vandenberg AFB aboard an Atlas E/F rocket. Itplaced a cluster of one primary satellite and three smaller sub-satellites (that trailed along at distances of several hundredkilometers) into low polar orbit. This satellite array determinedthe location of radio and radars transmitters, usingtriangulation, and the identity of naval units, by analysis of theoperating frequencies and transmission patterns.

USA 119

NSSDC ID: 1996-029A

Alternate Names

SDS-2

23893

Facts in Brief

Launch Date: 1996-05-12Launch Vehicle: TitanIVLaunch Site: CapeCanaveral, United StatesMass: 700.0 kg

Funding Agency


Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description

USA 120 was a naval reconnaisance, electronic intelligencesatellite launched from Vandenberg AFB aboard a Titan 4rocket along with USA 119, 121 - 124.

USA 120

NSSDC ID: 1996-029B

Alternate Names

23907

Facts in Brief


Funding Agency


Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data









mailto:[email protected]?Subject=NMC Comment/Question: USA 120 (1996-029B)











http://www.usa.gov/








Description

USA 121 was a US Naval reconnaisance satellite, part of theNOSS 2 series, launched from Vandenberg AFB aboard aTitan 4 rocket along with USA 119, 120, 122 - 124.

USA 121

NSSDC ID: 1996-029C

Alternate Names

23908

Facts in Brief


Funding Agency


Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data









mailto:[email protected]?Subject=NMC Comment/Question: USA 121 (1996-029C)











http://www.usa.gov/








Description

USA 122 was a US naval reconnaisance satellite, part of theNOSS 2 series, launched from Vandenberg AFB aboard aTitan 4 rocket along with USA 119 - 121, 123 and 124.

USA 122

NSSDC ID: 1996-029D

Alternate Names

23862

Facts in Brief


Funding Agency


Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data









mailto:[email protected]?Subject=NMC Comment/Question: USA 122 (1996-029D)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-029E[08/06/2011 23:50:12]


Description

USA 123 was a naval tether spacecraft launched fromVandenberg AFB aboard a Titan 4 rocket along with USA 119 -122 and 124.

USA 123

NSSDC ID: 1996-029E

Alternate Names

23936

Facts in Brief


Funding Agency


Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data









mailto:[email protected]?Subject=NMC Comment/Question: USA 123 (1996-029E)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1996-029F[08/06/2011 23:50:33]


Description

USA 124 was a naval reconnaisance satellite, part of theNOSS 2 series, launched from Vandenberg AFB aboard aTitan 4 rocket along with USA 119 - 123.

USA 124

NSSDC ID: 1996-029F

Alternate Names

23937

Facts in Brief


Funding Agency


Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data









mailto:[email protected]?Subject=NMC Comment/Question: USA 124 (1996-029F)











http://www.usa.gov/








Description

USA 125 was an Air Force surveillance satellite launched by aTitan 4 rocket from Cape Canaveral. It was part of the NOSSprogram.

USA 125

NSSDC ID: 1996-038A

Alternate Names

23945

Facts in Brief

Launch Date: 1996-07-02Launch Vehicle: TitanIVLaunch Site: CapeCanaveral, United StatesMass: 700.0 kg

Funding Agency


Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description

WSF 3 (Wake Field Facility 3) is an American microgravitymodule that was released from STS 80. The four-meterdiameter, 2,000 kg steel saucer was to grow ultra-puritysemiconductors on its rear side where the module's wake is anultra-vacuum. Its orbital parameters were very close to thoseof STS 80. It was recaptured by the shuttle on the 26November 1996.

WSF 3

NSSDC ID: 1996-065C

Alternate Names

Wake Shield Facility 3

24662

Facts in Brief


Funding Agency


Discipline

Microgravity


Launch/Orbitalinformation for WSF 3

Experiments on WSF 3

Data collections from WSF3



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=WSF 3

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=WSF 3

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=WSF 3

mailto:[email protected]?Subject=NMC Comment/Question: WSF 3 (1996-065C)











http://www.usa.gov/





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