lanzamientos.files.wordpress.com€¦ · NASA - NSSDC - Spacecraft - Query Results 15/06/2011...

Cronología de Lanzamientos Espaciales

Año 1998 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[15/06/2011 23:44:51]

Wednesday, 15 June 2011

Spacecraft Query Results

There were 156 spacecraft returned.

Spacecraft Name NSSDC ID Launch Date

Afristar 1998-063A 1998-10-27

Astra 2A 1998-050A 1998-08-29

Astrid 2 1998-072B 1998-12-09

ATEx 1998-055C 1998-10-02

BATSAT 1998-012B 1998-02-25

Bonum 1 1998-068A 1998-11-21

Brazilsat B-3 1998-006A 1998-02-03

BSAT-1B 1998-024B 1998-04-27

Capricorn 1998-005A 1998-01-28

China Star 1 1998-033A 1998-05-29

COMETS 1998-011A 1998-02-20

Cosmos 2349 1998-009A 1998-02-16

Cosmos 2350 1998-025A 1998-04-28

Cosmos 2351 1998-027A 1998-05-06

Cosmos 2352 1998-036A 1998-06-14

Cosmos 2353 1998-036B 1998-06-14

Cosmos 2354 1998-036C 1998-06-14

Cosmos 2355 1998-036D 1998-06-14

Cosmos 2356 1998-036E 1998-06-14

Cosmos 2357 1998-036F 1998-06-14

Cosmos 2358 1998-038A 1998-06-23

Cosmos 2359 1998-039A 1998-06-24

Cosmos 2360 1998-045A 1998-07-27

Cosmos 2361 1998-076A 1998-12-23

Cosmos 2362 1998-077A 1998-12-29

Cosmos 2363 1998-077B 1998-12-29

Cosmos 2364 1998-077C 1998-12-29

Deep Space 1 1998-061A 1998-10-23

Echostar 4 1998-028A 1998-05-06

EOS-Color EOS-COL 1998-05-31

Eutelsat W2 1998-056A 1998-10-04

FASAT-B 1998-043B 1998-07-09

GE 5 1998-063B 1998-10-27

GFO 1998-007A 1998-02-09

Globalstar M001 1998-008A 1998-02-13

Globalstar M002 1998-008C 1998-02-13

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



Globalstar M003 1998-008D 1998-02-13

Globalstar M004 1998-008B 1998-02-13

Globalstar M006 1998-023B 1998-04-23

Globalstar M008 1998-023D 1998-04-23

Globalstar M014 1998-023A 1998-04-23

Globalstar M015 1998-023C 1998-04-23

Hot Bird 4 1998-013A 1998-02-26

Hot Bird 5 1998-057A 1998-10-08

Inmarsat 3-F5 1998-006B 1998-02-03

Intelsat 805 1998-037A 1998-06-17

Intelsat 806 1998-014A 1998-02-27

International Space Station 1998-067A 1998-11-19

Iridium 2 1998-066A 1998-11-05

Iridium 3 1998-048A 1998-08-18

Iridium 11A 1998-074A 1998-12-18

Iridium 20A 1998-074B 1998-12-18

Iridium 50 1998-010A 1998-02-17

Iridium 51 1998-018A 1998-03-24

Iridium 52 1998-010C 1998-02-17

Iridium 53 1998-010D 1998-02-17

Iridium 54 1998-010E 1998-02-17

Iridium 55 1998-019A 1998-03-29

Iridium 56 1998-010B 1998-02-17

Iridium 57 1998-019B 1998-03-29

Iridium 58 1998-019C 1998-03-29

Iridium 59 1998-019D 1998-03-29

Iridium 60 1998-019E 1998-03-29

Iridium 61 1998-018B 1998-03-24

Iridium 62 1998-021A 1998-04-06

Iridium 63 1998-021B 1998-04-06

Iridium 64 1998-021C 1998-04-06

Iridium 65 1998-021D 1998-04-06

Iridium 66 1998-021E 1998-04-06

Iridium 67 1998-021F 1998-04-06

Iridium 68 1998-021G 1998-04-06

Iridium 69 1998-026A 1998-05-01

Iridium 70 1998-032A 1998-05-16

Iridium 71 1998-026B 1998-05-01

Iridium 72 1998-032B 1998-05-16

Iridium 73 1998-032C 1998-05-16

Iridium 74 1998-032D 1998-05-16

Iridium 75 1998-032E 1998-05-16

Iridium 76 1998-048B 1998-08-18

Iridium 77 1998-051E 1998-09-07

Iridium 79 1998-051D 1998-09-07

Iridium 80 1998-051C 1998-09-07

Iridium 81 1998-051B 1998-09-07

Iridium 82 1998-051A 1998-09-07

Iridium 83 1998-066E 1998-11-05



Iridium 84 1998-066D 1998-11-05

Iridium 85 1998-066C 1998-11-05

Iridium 86 1998-066B 1998-11-05

Lunar Prospector 1998-001A 1998-01-06

MAQSAT 3 1998-059A 1998-10-20

Mars Climate Orbiter 1998-073A 1998-12-10

Mightysat 1 1998-069C 1998-12-14

Molniya 1-91 1998-054A 1998-09-27

Molniya 3-49 1998-040A 1998-06-30

Nadezhda 5 1998-072A 1998-12-09

Nilesat 101 1998-024A 1998-04-27

NOAA 15 1998-030A 1998-05-12

Nozomi 1998-041A 1998-07-02

Orbcomm FM-03 1998-007B 1998-02-09

Orbcomm FM-04 1998-007C 1998-02-09

Orbcomm FM-13 1998-046A 1998-08-01

Orbcomm FM-14 1998-046B 1998-08-01

Orbcomm FM-15 1998-046C 1998-08-01

Orbcomm FM-16 1998-046D 1998-08-01

Orbcomm FM-17 1998-046H 1998-08-01

Orbcomm FM-18 1998-046G 1998-08-01

Orbcomm FM-19 1998-046F 1998-08-01

Orbcomm FM-20 1998-046E 1998-08-01

Orbcomm FM-21 1998-053A 1998-09-22

Orbcomm FM-22 1998-053B 1998-09-22

Orbcomm FM-23 1998-053C 1998-09-22

Orbcomm FM-24 1998-053D 1998-09-22

Orbcomm FM-25 1998-053E 1998-09-22

Orbcomm FM-26 1998-053F 1998-09-22

Orbcomm FM-27 1998-053G 1998-09-22

Orbcomm FM-28 1998-053H 1998-09-22

PANAMSAT 6B 1998-075A 1998-12-21

PANAMSAT 7 1998-052A 1998-09-15

PANAMSAT 8 1998-065A 1998-11-03

PANSAT 1998-064B 1998-10-29

Progress M-38 1998-015A 1998-03-13

Progress M-39 1998-031A 1998-05-14

Progress M-40 1998-062A 1998-10-24

Resurs-O 1 N4 1998-043A 1998-07-09

SAC-A 1998-069B 1998-12-13

SAFIR 2 1998-043F 1998-07-09

SATMEX 5 1998-070A 1998-12-05

SCD 2 1998-060A 1998-10-22

SEDSAT 1 1998-061B 1998-10-23

Sinosat 1 1998-044A 1998-07-17

Sirius 3 1998-056B 1998-10-04

Skynet 4D 1998-002A 1998-01-09

SNOE 1998-012A 1998-02-25

Soyuz-TM 27 1998-004A 1998-01-28



Soyuz-TM 28 1998-047A 1998-08-12

Spartan 201-05 1998-064C 1998-10-31

SPOT 4 1998-017A 1998-03-23

ST 1 1998-049A 1998-08-24

STEX 1998-055A 1998-10-02

STS 88 1998-069A 1998-12-03

STS 89 1998-003A 1998-01-22

STS 90 1998-022A 1998-04-16

STS 91 1998-034A 1998-06-01

STS 95 1998-064A 1998-10-28

SWAS 1998-071A 1998-12-05

Techsat 1B 1998-043D 1998-07-09

THOR 3 1998-035A 1998-06-09

TMSAT 1998-043C 1998-07-09

TRACE 1998-020A 1998-04-01

TUBSAT-N 1998-042A 1998-07-06

TUBSAT-N1 1998-042B 1998-07-06

UFO 8 1998-016A 1998-03-15

UFO 9 1998-058A 1998-10-19

Unity 1998-069F 1998-12-12

USA 139 1998-029A 1998-05-08

Westpac 1998-043E 1998-07-09

+ 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=1998-063A[16/06/2011 23:51:55]

Thursday, 16 June 2011

Description

Launched by an Ariane rocket from the Kourou Space Center,Afristar was the first WorldSpace satellite. It will broadcastdigital radio over Africa and the Middle East. Small handheldradios were able to pick up the transmissions from its three L-band beams. The satellite carried from 24 to 96 radio channelswith on-board processing to allow variable bit rates from monoto CD audio quality transmission. Broadcasters send theirprograms up to the satellite with a small X-band groundstation.

Afristar

NSSDC ID: 1998-063A

Alternate Names

25515

Facts in Brief

Launch Date: 1998-10-28Launch Vehicle: Ariane44LLaunch Site: Kourou,French Guiana

Discipline

Communications

AdditionalInformation

Launch/Orbitalinformation for Afristar

Telecommunicationsinformation for Afristar

Experiments on Afristar

Data collections fromAfristar

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=1998-063A


http://nssdc.gsfc.nasa.gov/nmc/spacecraftTelemetry.do?id=1998-063A


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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Afristar (1998-063A)











http://www.usa.gov/








Description

Astra 2A is a European (Luxembourg-registered)geosynchronous communications spacecraft that waslaunched by a Proton-K rocket from Baikonur at 00:31 UT. Itwill provide voice and video communications to Europe throughits 32 Ku-band transponders after parking over 28.2-Elongitude.

Astra 2A

NSSDC ID: 1998-050A

Alternate Names

25462

Facts in Brief

Launch Date: 1998-08-29LaunchVehicle: Proton-KLaunch Site: Tyuratam(Baikonur Cosmodrome),Kazakhstan

Funding Agency

Societe Europeenne desSatellites (Luxembourg)(Luxembourg)

Discipline

Communications


Launch/Orbitalinformation for Astra 2A

Experiments on Astra 2A

Data collections from Astra2A



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Astra 2A (1998-050A)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1998-072B[16/06/2011 23:52:42]


Description

ASTRID-2 is a Swedish scientific microsatellite. The scientificobjectives of the mission are to: make high resolution electricand magnetic field measurements in the auroral region; makeelectron density measurements; make high resolutionmeasurements of the electron and ion distribution functions;and make ultraviolet auroral imaging and atmospheric UV-absorption measurements. The spacecraft was developed bythe Swedish Space Corporation's Science Systems Division.The payload was developed by the Alfven Laboratory and theSwedish Institute of Space Physics.

The satellite was launched into a circular orbit at approximately1000 km altitude and 83 degrees inclination. The spacecraft isspin-stabilized and the spin axis will be pointed close to thesun. Solar panels and batteries provide a nominal 90 watts, at28 volts. Communication links are in the S-band, and downlinkdata rate is 128 kbps. Total mass is less than 30 kg, with about9 kg of experiments. Size with deployed solar panels is 1.7 x1.1 x 0.3 meters. Data reception and control station is atSwedish Space Corporation in Stockholm. The scientistsoperate the experiments themselves via the Internet.

For more information see the WWW page at:http://www.ssc.se/ssd/msat/astrid2.html

Astrid 2

NSSDC ID: 1998-072B

Alternate Names

25568

Facts in Brief

Launch Date: 1998-12-10LaunchVehicle: CosmosLaunch Site: Plesetsk,RussiaMass: 30.0 kg

Funding Agency

Unknown (Sweden)

Disciplines

Planetary Science

Space Physics


Launch/Orbitalinformation for Astrid 2

Telecommunicationsinformation for Astrid 2

Experiments on Astrid 2

Data collections from Astrid2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://www.ssc.se/ssd/msat/astrid2.html

http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1998-072B


http://nssdc.gsfc.nasa.gov/nmc/spacecraftTelemetry.do?id=1998-072B


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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Astrid 2 (1998-072B)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1998-055C[16/06/2011 23:53:07]


Description

The Advanced Tether Experiment (ATEx) was designed toextend the knowledge of control and survivability of tetheredspace systems. Experiments in active control were to studydeployment dynamics via a constant-speed motor andutilization of both in-plane and cross-plane thrusters to exciteand arrest librations. Additionally, ATEx was to investigate thesurvivability of long-life tether materials. The objectives ofATEx were to: (1) demonstrate tether system stability andcontrol; (2) demonstrate end-body attitude determination andcontrol; and, (3) fly a tether designed for survivability.

The tether's lower end-body was placed on top of an activespacecraft, permiting the opportunity to perform librationcontrol experiments. Such control was deemed necessary priorto developing more sophisticated tethered space systems.

The upper end-body was 0.62 x 0.52 x 0.07 m in dimensionand 11.8 kg. The lower end-body was 0.53 x 0.43 x 0.60 mand 27.6 kg. The tether was 13.4 kg. When fully deployed, thetwo masses were to be over 6 km apart.

ATEx was released from the STEX spacecraft on 16 January1999 after deploying only 22 m. The jettison was triggered byan automatic protection system designed to save STEX if thetether strayed from its expected departure angle. As a result,none of the desired goals were achieved.

ATEx

NSSDC ID: 1998-055C

Alternate Names

USA 141

Advanced TetherExperiment

25615

Facts in Brief

Launch Date: 1998-10-03LaunchVehicle: TaurusLaunchSite: Vandenberg AFB,United StatesMass: 52.8 kg

Funding Agency

US Naval ResearchLaboratory (UnitedStates)

Disciplines

Engineering

Surveillance and OtherMilitary


Launch/Orbitalinformation for ATEx

Telecommunicationsinformation for ATEx

Experiments on ATEx

Data collections from ATEx

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


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


ATEx


http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1998-055C


http://nssdc.gsfc.nasa.gov/nmc/spacecraftTelemetry.do?id=1998-055C


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

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

mailto:[email protected]?Subject=NMC Comment/Question: ATEx (1998-055C)

mailto:[email protected]?Subject=NMC Comment/Question: ATEx (1998-055C)









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




Description

The Teledesic system will provide global communication linksvia a constellation of 288 low earth orbit (LEO) spacecraft. Thesystem will provide "fiber-optic like" links to customers aroundthe world. The system will act as a network operator and willsupport communications ranging from high-quality voicechannels to broadband channels supporting video-conferencing, interactive multimedia and real-time two-waydata flow. Teledesic is backed by Microsoft Chairman BillGates and Craig McCaw, founder of McCaw CellularCommunications Inc. The system will use Ka-band to sendand receive signals from users. Each satellite will act as a nodein a large-scale packet-switching network. Service is plannedto begin in 2002. The total cost of the project is estimated at$9 billion.

BATSAT

NSSDC ID: 1998-012B

Alternate Names

Teledesic 1

T1

Broadband AdvancedTechnology Satellite

25234

Facts in Brief

Launch Date: 1998-02-26LaunchVehicle: Pegasus XLLaunchSite: Vandenberg AFB,United StatesMass: 120.0 kg

Funding Agency

Teledesic Corporation(United States)

Discipline

Communications


Launch/Orbitalinformation for BATSAT

Experiments on BATSAT

Data collections fromBATSAT



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


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




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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: BATSAT (1998-012B)
















Description

Bonum 1 was a Russian geosynchronous communicationsspacecraft. This first private sector spacecraft, owned by theRussian Bonum-1 media group, carried eight 75 W Ku-bandtransponders that enable 50 channels of direct-TV broadcaststo Russia and Eastern European countries after parking over36 degrees East longitude. Gallium arsenide solar cellsprovided power.

Bonum 1

NSSDC ID: 1998-068A

Alternate Names

25546

Facts in Brief

Launch Date: 1998-11-22Launch Vehicle: DeltaII 7925Launch Site: CapeCanaveral, United StatesMass: 620.0 kgNominalPower: 1500.0 W

Funding Agency

Russian SatelliteCommunicationsCompany (Russia)

Discipline

Communications


Launch/Orbitalinformation for Bonum 1

Telecommunicationsinformation for Bonum 1

Experiments on Bonum 1

Data collections fromBonum 1



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=Bonum 1

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Bonum 1 (1998-068A)











http://www.usa.gov/







Description

Brazilsat B3 was a Brazilian geosynchronous communicationssatellite launched from the Kourou Space Center in FrenchGuiana aboard an Ariane 4 rocket. It carried 28 C-bandtransponders to provide voice and video communications toBrazil and other countries, after parking at 70 deg Wlongitude.

Brazilsat B-3

NSSDC ID: 1998-006A

Alternate Names

Brasilsat B-3

25152

Facts in Brief

Launch Date: 1998-02-04Launch Vehicle: Ariane4Launch Site: Kourou,French Guiana

Funding Agency

Embratel (Brazil)

Discipline

Communications


Launch/Orbitalinformation for BrazilsatB-3

Experiments on BrazilsatB-3

Data collections fromBrazilsat B-3



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







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

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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Brazilsat B-3 (1998-006A)











http://www.usa.gov/








Description

B-SAT 1B was a geosynchronous communications satellitelaunched from the Kourou Space Station aboard an Ariane44LP rocket. This Hughes satellite was created for theBroadcasting Satellite System Corp of Japan and waspositioned at 109.9 deg E. It provided four-channel viewingcapabilities to homes with small, low-cost receiver dishes.Services available included NHK (Japan Broadcasting Corp),WOWOW (Japan Satellite Broadcasting Inc) and others. LikeBSAT-1A, it carried four active and four spare high-powertransponders in Ku-band, using 106-watt traveling wave tubeamplifiers. Built as a back-up to BSAT-1A, its contracted life is10 years.

BSAT-1B

NSSDC ID: 1998-024B

Alternate Names

25312

Facts in Brief

Launch Date: 1998-04-28Launch Vehicle: Ariane4Launch Site: Kourou,French GuianaMass: 1200.0 kg

Funding Agency

Broadcast SatelliteSystem Corp of Tokyo(Japan)

Discipline

Communications


Launch/Orbitalinformation for BSAT-1B

Experiments on BSAT-1B

Data collections fromBSAT-1B



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: BSAT-1B (1998-024B)











http://www.usa.gov/








Description

Capricorn was a US military photo/radar imaging spacecraftlaunched by an Atlas 2A rocket from Cape Canaveral. It wasbuilt, owned, and operated by the National ReconnaissanceOffice (NRO). It was likely that the initial apogee of about38,400 km would be at a high northern latitude, and theperigee of 320 km would be over Antarctica.

Capricorn

NSSDC ID: 1998-005A

Alternate Names

USA 137

25148

Facts in Brief

Launch Date: 1998-01-29Launch Vehicle: Atlas2ALaunch Site: CapeCanaveral, United States

Funding Agency

National ReconnaissanceOffice (United States)

Discipline



Launch/Orbitalinformation for Capricorn

Experiments on Capricorn

Data collections fromCapricorn



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Capricorn (1998-005A)











http://www.usa.gov/








Description

China Star 1 was a geosynchronous communications satelliteslaunched by the People's Republic of China from the XichangLaunch Center by a Long March 3B rocket. The spacecraftcarried 24 C-band and 24 Ku-band transponders to providevoice and video communications throughout China andneighboring countries, after parking at 87.5 deg E longitude.

China Star 1

NSSDC ID: 1998-033A

Alternate Names

Zhongwei 1

25354

Facts in Brief

Launch Date: 1998-05-30Launch Vehicle: LongMarch 3BLaunch Site: Xichang,Peoples Republic of ChinaMass: 2984.0 kg

Funding Agency

Unknown (PeoplesRepublic of China)

Discipline

Communications


Launch/Orbitalinformation for China Star1

Experiments on China Star1

Data collections fromChina Star 1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







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

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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: China Star 1 (1998-033A)











http://www.usa.gov/








Description

The Communications and Broadcasting Engineering TestSatellite (COMETS) was a research and development satelliteaimed at developing new technology in communications andbroadcasting fields such as inter-orbit communications,advanced satellite broadcasting, advanced mobile satellitecommunications, and upgrading large geostationary satellites.It was to be used for conducting experiments and verifying theabove subjects. The planned lifetime of the mission was to bethree years, but a failure in the second stage of the H-II launchvehicle resulted in a highly eccentric orbit and prevented thespacecraft from attaining its planned geostationary orbit.

COMETS

NSSDC ID: 1998-011A

Alternate Names

Communications andBroadcasting EngineeringTest Satellite

Kakehashi

25175

Facts in Brief

Launch Date: 1998-02-21Launch Vehicle: H-2LaunchSite: Tanegashima, JapanMass: 2000.0 kg

Funding Agency

National SpaceDevelopment Agency(NASDA) (Japan)

Disciplines

Communications

Engineering


Launch/Orbitalinformation for COMETS

Telecommunicationsinformation for COMETS

Experiments on COMETS

Data collections fromCOMETS



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: COMETS (1998-011A)














http://www.usa.gov/








Description

Cosmos 2349 was a Russian military photographic (2-meterresolution) satellite launched by a Soyuz-U rocket from theBaikonur cosmodrome. It provided topographical maps of theUS in accordance with a Russian-American contract.

Cosmos 2349

NSSDC ID: 1998-009A

Alternate Names

25167

Facts in Brief

Launch Date: 1998-02-17LaunchVehicle: Soyuz-ULaunch Site: Tyuratam(Baikonur Cosmodrome),Kazakhstan

Funding Agency

Unknown (Russia)

Discipline



Launch/Orbitalinformation for Cosmos2349

Experiments on Cosmos2349

Data collections fromCosmos 2349



Spacecraft

Experiments

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http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Cosmos 2349


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Cosmos 2349


mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 2349 (1998-009A)











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Description

Cosmos 2350 was a Russian military second generation globalcommand and control system (GKKRS) satellite launched fromthe Baiknour cosmodrome aboard a Proton K rocket. Thesesatellites were integrated with the Luch geostationary systemand featured retransmission of high rate data retransmission inthe centimetre wavelength range. While Luch handledcommunications between spacecraft and ground stations,Potok handled communications between fixed points anddigital data from the Yantar-4KS1 electroptical reconnaissancesatellite. Potok was the first communications spacecraft built bythe Lavochkin design bureau and used the Splav-2transponder by NPO Elas.

Potok is said by one account to have utilized the KAUR-4spacecraft bus. This had an active 3-axis orientation system,with a single central body from which extended 40 squaremetres of solar panels. Its basic structure was that of theKAUR-3, but it was equipped with completely new systems: adigital computer, plasma station-keeping engines, hydrazinemonopropellant orientation engines, and actively-scannedantennae arrays with 0.5 degrees antenna and 0.1 degreespacecraft pointing accuracy. Cosmos 2350 was stationed at73 deg E.

Cosmos 2350

NSSDC ID: 1998-025A

Alternate Names

25315

Facts in Brief


Funding Agency

Unknown (Russia)

Discipline

Communications







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Description

Cosmos 2351 was a Russian missile early warning satellitelaunched from the Plesetsk cosmodrome aboard a Molniyarocket. It was part of the Oko constellation of satellites andcovered the planes 6/7 - 129 degree longitude of ascendingnode.

Cosmos 2351

NSSDC ID: 1998-027A

Alternate Names

25327

Facts in Brief

Launch Date: 1998-05-07LaunchVehicle: Molniya-MLaunch Site: Plesetsk,Russia

Funding Agency

Unknown (Russia)

Discipline








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http://www.usa.gov/







Friday, 17 June 2011

Description

The Strela 3 system was a communications satelliteconstellation devoted to military and governmentcommunications. It was a simple store-dump repeater systemwhich were particulatly useful in relaying non-essential trafficbetween the Russian Federation and overseas stations orforces. The Strela 3 system, which began in 1985, waslaunched by the Tsyklon-3 booster from the Plesetskcosmodrome into orbits near 1400 km at inclinations of 82.6degrees with six spacecraft stacked atop each launch vehicle.Two orbital planes were spaced 90 degrees apart, apparentlyeach contained 10-12 operational spacecraft. Normally, twomissions were conducted per year, suggesting an averagespacecraft life-time of approximately 24 months. The 220 kgspacecraft had a diameter of 1.0 m and a main bus height of1.5 m. A gravity-gradient beam was extended on-orbit toprovide attitude stabilization.

Cosmos 2352

NSSDC ID: 1998-036A

Alternate Names

25363

Facts in Brief

Launch Date: 1998-06-15LaunchVehicle: Tsiklon-3Launch Site: Plesetsk,RussiaMass: 225.0 kg

Funding Agency

Unknown (Russia)

Disciplines

Communications








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http://www.usa.gov/








Description


Cosmos 2353

NSSDC ID: 1998-036B

Alternate Names

25364

Facts in Brief


Funding Agency

Unknown (Russia)

Disciplines

Communications








Spacecraft

Experiments

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Personnel

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Maps

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mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 2353 (1998-036B)











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Description


Cosmos 2354

NSSDC ID: 1998-036C

Alternate Names

25365

Facts in Brief


Funding Agency

Unknown (Russia)

Disciplines

Communications








Spacecraft

Experiments

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Personnel

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Maps

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mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 2354 (1998-036C)











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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1998-036D[17/06/2011 23:22:36]


Description


Cosmos 2355

NSSDC ID: 1998-036D

Alternate Names

25366

Facts in Brief


Funding Agency

Unknown (Russia)

Disciplines

Communications








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1998-036D







mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 2355 (1998-036D)











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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1998-036E[17/06/2011 23:23:02]


Description


Cosmos 2356

NSSDC ID: 1998-036E

Alternate Names

25367

Facts in Brief


Funding Agency

Unknown (Russia)

Disciplines

Communications








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1998-036E







mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 2356 (1998-036E)











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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1998-036F[17/06/2011 23:23:23]


Description


Cosmos 2357

NSSDC ID: 1998-036F

Alternate Names

25368

Facts in Brief


Funding Agency

Unknown (Russia)

Disciplines

Communications








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1998-036F







mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 2357 (1998-036F)











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Description

Cosmos 2358, 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.

National Space Science Data Center Header

Cosmos 2358

NSSDC ID: 1998-038A

Alternate Names

25373

Facts in Brief

Launch Date: 1998-06-24LaunchVehicle: Soyuz-ULaunch Site: Plesetsk,Russia

Funding Agency

Unknown (Russia)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

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Maps

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http://www.usa.gov/








Description

Cosmos 2359 was a Russian digital photo surveillance satellitelaunched from the Baikonur cosmodrome aboard a Soyuz 11rocket.

Cosmos 2359

NSSDC ID: 1998-039A

Alternate Names

25376

Facts in Brief


Funding Agency

Unknown (Russia)

Discipline




Telecommunicationsinformation for Cosmos2359





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http://www.usa.gov/







Description

Cosmos 2360 was a Russian military surveillance spacecraftlaunched from the Baikonur cosmodrome aboard a Zenit 2rocket. It was a member of the Tselnia series that carried"signal intelligence" instruments.

Cosmos 2360

NSSDC ID: 1998-045A

Alternate Names

25406

Facts in Brief

Launch Date: 1998-07-28Launch Vehicle: Zenit 2Launch Site: Tyuratam(Baikonur Cosmodrome),Kazakhstan

Funding Agency

Unknown (Russia)

Discipline








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Experiments

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http://www.usa.gov/








Description

Cosmos 2361 was a Russian ELINT (Electronic and SignalsIntelligence) satellite launched from the Baikonur cosmodromeaboard a Zenit 2 rocket.

Based on the first generation Tselina ELINT, TSNII-KS at thebeginning of the 1970's developed the specifications for animproved model with increased frequency range and on-boardmethod of determining the position of fixed transmitters. TheTselina-2 was authorised in March 1973 and handled by primecontractor TsNIRTI Minradioprom (M E Zaslovskiy) for theELINT equipment and KB Yuzhnoye (KB-3, B S Khimrov) forthe spacecraft bus. The launch vehicle was by OKB MEIMinvuza (A F Bogomolov) and the encrypted communicationssystem by 0-TsNII KS MO. The draft project was drawn up inthe first quarter of 1974 and the MO approved the TTZ in May1974. After a long review process the VPK issued the projectplan for development of the system in December 1976. Itwould now use the new Zenit launch vehicle. The first flighttrials system was completed in December 1980, but delays inthe development of the Zenit launch vehicle meant that the firsttwo trials flights had to be aboard Proton boosters in 1984 and1985. Zenit-boosted flights began in 1985 and the system wasaccepted into service in 1987.

Cosmos 2361

NSSDC ID: 1998-076A

Alternate Names

25590

Facts in Brief

Launch Date: 1998-12-24LaunchVehicle: CosmosLaunch Site: Plesetsk,Russia

Funding Agency

Unknown (Russia)

Discipline









Spacecraft

Experiments

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http://www.usa.gov/








Description

Cosmos 2364 was a Russian Global Navigation SatelliteSystem (GLONASS) satellite launched from the Baikonurcosmodrome aboard a Proton rocket. Originally established inorder to locate the Soviet Union's civil aircraft and its merchantand fishing vessels, the signals were used by many AmericanGPS system receivers as a complement/backup to the GPSsystem itself. The operational system contained 21 satellites in3 orbital planes, with 3 on-orbit backups. Each satellite wasidentified by its slot number, which defined the orbital plane (1-8, 9-16, 17-24) and the location within the plane. The 3 orbitalplanes were separated 120 degrees, and the satellites withinthe same orbit plane by 45 degrees. The orbits were roughlycircular with an inclination of about 64.8 degrees, a semi-axisof 25,440 km, and a period of 11h 15m 44s.

The 3-axis stabilized spacecraft possessed a mass of about1,400 kg, a slight increase over the 1,250 original model. Thediameter and height of the satellite bus were approximately 2.4m and 3.7 m, respectively, with a solar array span of 7.2 m foran electrical power generation capability of 1.6 kW atbeginning of life. The aft payload structure housed 12 primaryantennas for L-band transmissions. Laser corner-cubereflectors were also carried to aid in precise orbit determinationand geodetic research.

Cosmos 2362

NSSDC ID: 1998-077A

Alternate Names

25594

Facts in Brief

Launch Date: 1998-12-30LaunchVehicle: Proton-KLaunch Site: Tyuratam(Baikonur Cosmodrome),KazakhstanMass: 1400.0 kgNominalPower: 1600.0 W

Funding Agency

Scientific ProductionAssociation(Russia)(Russia)

Discipline

Navigation & GlobalPositioning






Questions or commentsabout this spacecraft canbe directed to: Coordinated


Spacecraft

Experiments

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Request and User SupportOffice.




http://www.usa.gov/








Description

Cosmos 2363 was a Russian Global Navigation SatelliteSystem (GLONASS) satellite launched from the Baikonurcosmodrome aboard a Proton rocket. Originally established inorder to locate the Soviet Union's civil aircraft and its merchantand fishing vessels, the signals were used by many AmericanGPS system receivers as a complement/backup to the GPSsystem itself. The operational system contained 21 satellites in3 orbital planes, with 3 on-orbit backups. Each satellite wasidentified by its slot number, which defined the orbital plane (1-8, 9-16, 17-24) and the location within the plane. The 3 orbitalplanes were separated 120 degrees, and the satellites withinthe same orbit plane by 45 degrees. The orbits were roughlycircular with an inclination of about 64.8 degrees, a semi-axisof 25,440 km, and a period of 11h 15m 44s.

The 3-axis stabilized spacecraft possessed a mass of about1,400 kg, a slight increase over the 1,250 original model. Thediameter and height of the satellite bus were approximately 2.4m and 3.7 m, respectively, with a solar array span of 7.2 m foran electrical power generation capability of 1.6 kW atbeginning of life. The aft payload structure housed 12 primaryantennas for L-band transmissions. Laser corner-cubereflectors were also carried to aid in precise orbit determinationand geodetic research.

Cosmos 2363

NSSDC ID: 1998-077B

Alternate Names

25595

Facts in Brief


Funding Agency

Scientific ProductionAssociation(Russia)(Russia)

Discipline









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http://www.usa.gov/







Cosmos 2364

NSSDC ID: 1998-077C

Description

Cosmos 2362 was a Russian Global Navigation Satellite System (GLONASS) satellite launched from the Baikonurcosmodrome aboard a Proton rocket. Originally established in order to locate the Soviet Union's civil aircraft and itsmerchant and fishing vessels, the signals were used by many American GPS system receivers as acomplement/backup to the GPS system itself. The operational system contained 21 satellites in 3 orbital planes, with 3on-orbit backups. Each satellite was identified by its slot number, which defined the orbital plane (1-8, 9-16, 17-24) andthe location within the plane. The 3 orbital planes were separated 120 degrees, and the satellites within the same orbitplane by 45 degrees. The orbits were roughly circular with an inclination of about 64.8 degrees, a semi-axis of 25,440km, and a period of 11h 15m 44s.

The 3-axis stabilized spacecraft possessed a mass of about 1,400 kg, a slight increase over the 1,250 original model.The diameter and height of the satellite bus were approximately 2.4 m and 3.7 m, respectively, with a solar array spanof 7.2 m for an electrical power generation capability of 1.6 kW at beginning of life. The aft payload structure housed 12primary antennas for L-band transmissions. Laser corner-cube reflectors were also carried to aid in precise orbitdetermination and geodetic research.

Alternate Names25593

Facts in Brief

Launch Date: 1998-12-30Launch Vehicle: Proton-KLaunch Site: Tyuratam (Baikonur Cosmodrome), KazakhstanMass: 1400.0 kgNominal Power: 1600.0 W

Funding AgencyScientific Production Association(Russia) (Russia)

DisciplineNavigation & Global Positioning

Additional InformationLaunch/Orbital information for Cosmos 2364Telecommunications information for Cosmos 2364

Experiments on Cosmos 2364

Data collections from Cosmos 2364

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


Spacecraft











ExperimentsData CollectionsPersonnelPublicationsMapsNew/Updated DataLunar/Planetary Events

+ Privacy Policy and Important Notices

NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.16, 26 April 2011








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Description

The Deep Space 1 (DS1) is the first of a series of technologydemonstration probes being developed by NASA's NewMillennium Program. The spacecraft flew by the Mars-crossingnear-Earth asteroid 9969 Braille (formerly known as 1992 KD)in July, 1999 and flew by comet Borrelly on 22 September2001. As part of the technology demonstrations, the probecarries the Miniature Integrated Camera-Spectrometer(MICAS), an instrument combining two visible imagingchannels with UV and IR spectrometers. MICAS is used tostudy the chemical composition, geomorphology, size, spin-state, and atmosphere of the target objects. It also carries thePlasma Experiment for Planetary Exploration (PEPE), an ionand electron spectrometer which measures the solar windduring cruise, the interaction of the solar wind with targetbodies during encounters, and the composition of the cometarycoma.

Spacecraft and SubsystemsThe Deep Space 1 spacecraft is built on an octagonalaluminum frame bus which is 1.1 x 1.1 x 1.5 m in size. Withinstruments and systems attached, the spacecraft measures2.5 m high, 2.1 m deep, and 1.7 m wide. The launch mass ofthe spacecraft is about 486.3 kg, which includes 31.1 kg ofhydrazine and 81.5 kg of xenon gas. The probe is powered bybatteries and two solar panel "wings" attached to the sides ofthe frame which span roughly 11.75 m when deployed. Thesolar panels, designated SCARLET II (Solar ConcentratorArrays with Refractive Linear Element Technology) constituteone of the technology tests on the spacecraft. A cylindricallens concentrates sunlight on a strip of GaInP2/GaAs/Gephotovoltaic cells and acts to protect the cells. Each solararray consists of four 160 cm x 113 cm panels. The array willfurnish 2500 W at 100 volts at the beginning of the mission,and less as the spacecraft moves further from the Sun and asthe solar cells age. Communications are via a high-gainantenna, three low-gain antennas, and a Ka-band antenna, allmounted on top of the spacecraft except one low gain antennamounted on the bottom.

Propulsion is provided by a xenon ion engine mounted in thepropulsion unit on the bottom of the frame. The 30 cm diameterengine consists of an ionization chamber into which xenon gasis injected. Electrons are emitted by a cathode traversedischarge tube and collide with the xenon gas, stripping offelectrons and creating positive ions. The ions are acceleratedthrough a 1280 volt grid at to 31.5 km/sec and ejected from thespacecraft as an ion beam, producing 0.09 Newtons (0.02pounds) of thrust at maximum power (2300 W) and 0.02 N atthe minimum operational power of 500 W. The excess

Deep Space 1

NSSDC ID: 1998-061A

Alternate Names

New Millennium DS1

DS1

25508

Facts in Brief


Funding Agency

National Aeronautics andSpace Administration(United States)

Disciplines

Engineering

Planetary Science

Technology Applications


Launch/Orbitalinformation for DeepSpace 1

PDMP information forDeep Space 1

Telecommunicationsinformation for DeepSpace 1

Experiments on DeepSpace 1

Data collections from DeepSpace 1


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


Deep Space 1





http://nssdc.gsfc.nasa.gov/nmc/spacecraftPdmp.do?id=1998-061A





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

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

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

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









http://nssdc.gsfc.nasa.gov/image/spacecraft/nm_ds_1.gif



electrons are collected and injected into the ion beam toneutralize the electric charge. Of the 81.5 kg of xenon,approximately 17 kg were consumed during the primarymission.

Other technologies which will be tested on this mission includea solar concentrator array, autonomous navigation plus twoother autonomy experiments, small transponder, Ka-band solidstate power amplifier, and experiments in low powerelectronics, power switching, and multifunctional structures (inwhich electronics, cabling, and thermal control are integratedinto a load bearing element).

Mission ProfileDeep Space 1 was launched from Pad 17-A at the CapeCanaveral Air Station at 12:08 UT (8:08 a.m. EDT), 24 October1998, the first launch under NASA's Med-Lite booster program,on a Delta 7326-9.5 (a Delta II Lite launch vehicle with threestrap-on solid-rocket boosters and a Star 37FM third stage). At13:01 UT the third stage burn put DS1 into its solar orbittrajectory. DS1 separated from the Delta II about 550 kmabove the Indian Ocean. Telemetry was received by the NASADeep Space Network 1 hour, 37 minutes after launch, a 13minute delay from the expected time. The reason for the delayis not known. All critical spacecraft systems were performingwell.

DS1 flew by the near-Earth asteroid 9969 Braille at 04:46 UT(12:46 a.m. EDT) on 29 July 1999 at a distance of about 26 kmat approximately 15.5 km/sec relative velocity. A softwareproblem caused the spacecraft to go into a safing mode atapproximately 12:00 UT on 28 July, but the problem wassolved an the spacecraft returned to normal operations at18:00 UT. Up to six minor trajectory correction maneuverswere scheduled in the 48 hours prior to the flyby. Thespacecraft made its final pre-encounter transmission about 7hours before closest approach, after which it turned its high-gain antenna away from Earth to point the MICAScamera/spectrometer camera towards the asteroid. Thespacecraft had a target-tracking problem and the MICASinstrument was not pointed towards the asteroid as itapproached, so no images or spectra were obtained. MICASturned off about 25 seconds before closest approach at adistance of about 350 km and measurements were taken withthe PEPE plasma instrument. The spacecraft then turned afterthe encounter to obtain images and spectra of the oppositeside of the asteroid as it receded from view, but due to thetarget-tracking problem only two black and white images and adozen spectra were obtained. The images were taken at 915and 932 seconds after closest approach from 14,000 km andthe spectra were taken about 3 minutes later. The data weretransmitted back to Earth over the next few days. The diameterof Braille is estimated at 2.2 km at its longest and 1 km at itsshortest. The spectra showed it to be similar to the asteroidVesta.

The primary mission lasted until 18 September 1999, thespacecraft is now in an extended mission. By the end of 1999approximately 22 kg of xenon had been used by the ion engineto impart a total delta V of 1300 m/s to the spacecraft. Theoriginal plan was to fly by the dormant comet Wilson-Harrington in January 2001 and comet Borrelly in September2001. The star tracker failed on 11 November 1999 and a newextended mission to fly by comet Borrely (using techniquesdeveloped to operate the spacecraft without the star tracker)was planned. On 22 September 2001, Deep Space 1 enteredthe coma of comet Borrelly and made its closest approach(2171 km) to the nucleus at 22:29:33 UT ( 6:29:33 p.m. EDT).It was travelling at 16.58 km/s relative to the nucleus. At the

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

mailto:[email protected]?Subject=NMC Comment/Question: Deep Space 1 (1998-061A)

mailto:[email protected]?Subject=NMC Comment/Question: Deep Space 1 (1998-061A)



time of the flyby the spacecraft and comet were 1.36 AU fromthe Sun. The PEPE instrument was turned on throughout theencounter. MICAS started making measurements and imaging80 minutes before encounter and operated until a few minutesbefore encounter as planned. Both instruments successfullyreturned data and images from the encounter. The ion engineson DS1 were commanded off on 18 December 2001 at about20:00 UT (3:00 p.m. EST) to end the mission. The radioreciever was left on in case future contact with the spacecraftis desired. All new technologies on board DS1 weresuccessfully tested during the primary mission.

Deep Space 1 has a total mission cost of $152.3 millioncomprised of $94.8 million for development, $43.5 million forlaunch, $10.3 million for operations, and $3.7 million forscience.

Personnel

Name Role Original Affiliation E-mail

Mr. David H.Lehman

ProjectManager

NASA Jet PropulsionLaboratory

[email protected]

Mr. E. KaneCasani

ProgramManager


Dr. Robert M.Nelson

MissionScientist


[email protected]

Selected References

Nelson, R. M., Deep space One: Preparing for space exploration in the 21st century, EOS, Tran.Amer. Geophys. Union, 79, No. 41, Oct. 1998.

Rayman, M. D., and D. H. Lehman, Deep Space One: NASA's first Deep-Space technologyvalidation mission, Acta Astronautica, 41, No. 4, 289-299, 1997.

Rayman, M. D., The Deep Space 1 extended mission: Challenges in preparing for an encounterwith mission Borrelly, Acta Astronaut., 51, No. 1-9, 507-516, 2002.

Results from the flyby - Press Release, 5 August 1999

Deep Space 1 Status Report

Composite color-enhanced mosaic of Comet BorrellyImages and spectra from the flybyNASA bids farewell to the successful Deep Space 1 mission - Press Release, 17 December2001Aging NASA spacecraft captures best-ever view of comet's core - Press Release, 25 September2001NASA's Deep Space 1 succeeds in close asteroid flyby - Press Release, 29 July 1999Closest-ever Asteroid Flyby Set for July 29 - Press Release, 28 July 1999DS-1 Asteroid named for Louis Braille Computer Program Assumes Spacecraft Command - Press Release, 17 May 1999Deep Space 1 Technologies Tested - Press Release, 6 April 1999Deep Space 1 Press Briefing on Tuesday, 6 April - Press Release, 1 April 1999Deep Space 1 Ion Propulsion System Starts Up - Press Release, 25 November 1998Deep Space 1 Prelaunch Briefing - Press Release, 16 September 1998

http://nssdc.gsfc.nasa.gov/planetary/text/ds1_pr_19990805.txt

http://nssdc.gsfc.nasa.gov/planetary/text/ds1_status.txt

http://nssdc.gsfc.nasa.gov/planetary/image/ds1_labelled.gif

http://nssdc.gsfc.nasa.gov/planetary/image/borrelly_ds1.jpg

http://www.jpl.nasa.gov/ds1news





http://planetary.org/news/articlearchive/headlines/1999/headln-072699.html








New DS1 target chosen - Press Release, 5 June 1998DS1 launch delayed until October - Press Release, 17 April 1998Science Team chosen for DS1 - Press Release, 29 September 1997

Comets and Asteroids PageAsteroid Fact SheetComet Fact Sheet

NM Deep Space 1 Home PageNew Millenium Program Home PageThe History of Ion Propulsion





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

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

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

http://nmp.jpl.nasa.gov/ds1/

http://nmp.jpl.nasa.gov/

http://science.nasa.gov/newhome/headlines/prop06apr99_2.htm

http://www.usa.gov/





Deep Space 1

La misión Deep Space 1 de la NASA consistió en una sonda equipada con 12 sistemas tecnológicos avanzados de alto riesgo que debían ser probados y validados en el espacio, incluyéndose entre ellos un motor de propulsión iónica NSTAR. El vehículo fue lanzado en otoño de 1998 y tenía previsto realizar una misión de 11 meses, pero el desarrollo de ésta fue tan bueno que se decidió su prolongación durante unos pocos años más para proseguir con el estudio del funcionamiento del motor iónico y realizar otras investigaciones científicas (sobrevuelos del asteroide Braille y del cometa Borrelly).

El combustible empleado por el motor iónico de la Deep Space 1 es xenón, un gas químicamente inerte, incoloro, inodoro e insípido, cuatro veces más ligero que el aire y que suele ser empleado en los flashes de las cámaras fotográficas y en muchos sistemas de iluminación. Además, no es explosivo ni corrosivo, por lo que no supone un riesgo añadido a la vida del satélite o al personal que lo almacena en tierra. Cuando el motor se halla trabajando, los electrones son emitidos por un tubo hueco denominado cátodo. Dichos electrones entran en una cámara de anillos magnéticos, golpeando los átomos de xenón y arrancándoles uno de sus 54 electrones, con lo cual estos átomos de xenón adquieren carga positiva: se ionizan.

En la parte trasera de la cámara, un par de redes de metal se cargan positiva y negativamente, generando una diferencia de potencial que imprime un empuje electrostático en los átomos de xenón ionizados, siendo estos expulsados del motor a unos 100.000 Km/h. A su máxima potencia, el motor iónico consume 2500 watios y proporciona un empuje muy bajo, comparable a los cohetes químicos más ligeros. El empuje de un motor iónico es tan suave como el de una hoja de papel en la palma de la mano. La ventaja es que el motor iónico puede funcionar durante meses o años y ser hasta 10 veces más eficiente que uno químico, o sea desarrollar 10 veces más potencia por kilogramo de combustible que un motor químico tradicional.

La clave de esta tecnología también es que

el motor iónico es ligero: emplea sólo unos pocos cientos de gramos de combustible al día. Por otra parte, la electricidad necesaria para acelerar los iones mediante campos magnéticos se consigue empleando paneles solares de gran eficiencia: como ejemplo, señalar que los paneles solares necesarios para hacer trabajar el motor NSTAR tienen una eficiencia del 93%, generan 2500 watios de potencia y pesan unos 15 Kg.

Un mes después de su lanzamiento al espacio, el 24 de

noviembre de 1998, los controladores pusieron en marcha el motor iónico de la sonda, cuando ésta se hallaba a 4.8 millones de kilómetros de la Tierra. Dicho motor funcionó durante 14 días, llevando al vehículo a las cercanías del asteroide Braille el 29 de julio de 1999, a una distancia de sólo 26 Km del mismo y con una velocidad relativa de 15.5 Km/s. Después de esta exitosa misión principal la NASA decidió extender la misión de la Deep Space 1 y los operadores de la sonda planificaron el sobrevuelo del cometa Wilson-Harrington para enero de 2001 y del Borrelly para septiembre de ese año. Los problemas con el rastreador estelar obligaron a los planificadores a revisar la misión, de tal modo que desistieron de realizar el primer encuentro. Así, el sobrevuelo del Borrelly sería todo un éxito: se obtuvieron fotografías detalladas de su núcleo y coma, espectros infrarrojos y mediciones del medio ambiente en torno a éste. El motor de la Deep Space 1 se había convertido además en el sistema de propulsión de más largo uso continuado hasta el momento (ocho meses de operación). La misión finalizó el 18 de diciembre de 2001, habiendo demostrado el correcto funcionamiento de las nuevas tecnologías puestas a prueba.

Imagen del motor iónico de la Deep

Space 1

Una vista más

detallada de dicho motor

Tests de prueba con el

motor de la Deep Space 1

Imagen alta resolución (6,7 MB)

http://technology.jpl.nasa.gov/gallery/gl_high/p49722bc_high.tif�

http://technology.jpl.nasa.gov/gallery/gl_high/p49722bc_high.tif�

http://www.astroenlazador.com/especiales/propionica/98pc1191.gif�

http://www.astroenlazador.com/especiales/propionica/98pc1192.gif�

http://www.astroenlazador.com/especiales/propionica/p49722bc_browse.jpg�

Imagen del asteroide Braille tomada

poco después del sobrevuelo de éste (28 de julio de 1999).

Imagen del cometa Borrelly obtenida

el 25 de septiembre de 2001 por la Deep Space 1, la toma más detallada

de un núcleo cometario hasta la fecha.

http://www.astroenlazador.com/especiales/propionica/braile.jpg�

http://www.astroenlazador.com/especiales/propionica/borrelly_1.jpg�




Description

Echostar 4, a Lockheed Martin A2100 satellite, was launchedsuccessfully from the Baikonur cosmodrome aboard a Protonrocket. Along with Echostar 3, it will become the primaryservice satellites for the DISH Network providing video, audioand data services throughout the continental US, Hawaii andAlaska. It will be positioned at 148 deg W.

Echostar 4

NSSDC ID: 1998-028A

Alternate Names

25331

Facts in Brief


Funding Agency

EchostarCommunicationsCorporation (UnitedStates)

Discipline

Communications


Launch/Orbitalinformation for Echostar 4

Experiments on Echostar 4

Data collections fromEchostar 4



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Echostar 4

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Echostar 4

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Echostar 4

mailto:[email protected]?Subject=NMC Comment/Question: Echostar 4 (1998-028A)











http://www.usa.gov/





http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=EOS-COL[17/06/2011 23:33:01]


Description

The Earth Observing System (EOS) is a science andobservation program that will provide long-term (15-year) datasets for Earth system science in order to gain anunderstanding of the interactions between Earth's land,atmosphere, oceans, and biology. The EOS Program is thecenterpiece of NASA's Mission to Planet Earth (MTPE). TheEOS program was restructured in response to direction fromthe EOS Engineering Review Committee, U.S. Congress, andthe EOS Payload Advisory Panel to fly EOS instruments onintermediate-sized and smaller spacecraft instead of on largespace platforms. The EOS-COLOR spacecraft will carry onlyone sensor, an Ocean Color Instrument similar in design andfunction to the Sea-viewing Wide Field of View Sensor(SeaWiFS) launched in 1993 on SeaStar. The EOS OceanColor Instrument will monitor variations in ocean absorption ofsolar radiation caused by changes in bio-optical properties.The EOS-COLOR platform is designed specifically to continueocean color measurements begun by SeaWiFS until the launchof the EOS-AM1 platform (which will carry the MODISinstrument with similar spectral channels for ocean colormonitoring). The EOS-COLOR platform will be launched with aPegasus-class commercial launch vehicle into a near-polarorbit in 1998 and will not involve a series of launches. As withSeaStar/SeaWiFS, NASA will enter a data purchaseagreement with a commercial data provider.

EOS-Color

NSSDC ID: EOS-COL

Alternate Names

Color

Color-1

Facts in Brief

Launch Date: 1998-05-31LaunchVehicle: PegasusLaunch Site: UnitedStatesMass: 236.0 kg

Funding Agency

NASA-Office of SpaceScience Applications(United States)

Discipline

Earth Science


Launch/Orbitalinformation for EOS-Color

PDMP information forEOS-Color

Telecommunicationsinformation for EOS-Color

Experiments on EOS-Color

Data collections from EOS-Color



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data



http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=EOS-COL

http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=EOS-COL

http://nssdc.gsfc.nasa.gov/nmc/spacecraftPdmp.do?id=EOS-COL

http://nssdc.gsfc.nasa.gov/nmc/spacecraftPdmp.do?id=EOS-COL

http://nssdc.gsfc.nasa.gov/nmc/spacecraftTelemetry.do?id=EOS-COL

http://nssdc.gsfc.nasa.gov/nmc/spacecraftTelemetry.do?id=EOS-COL

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=EOS-Color

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=EOS-Color

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=EOS-Color

mailto:[email protected]?Subject=NMC Comment/Question: EOS-Color (EOS-COL)












http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=EOS-COL[17/06/2011 23:33:01]

Personnel


Dr. Michael D.King

MissionScientist

NASA Goddard SpaceFlight Center

[email protected]

Dr. Charles R.McClain

ProjectScientist


[email protected]

Dr. Raymond R.Roberts

ProgramManager

NASA Headquarters

Mr. Thomas Y.Yi

ProjectManager


[email protected]

Mr. Jeremiah J.Madden

ProjectManager


Dr. GhassemAsrar

ProgramScientist

NASA Headquarters


http://www.usa.gov/








Description

EUTELSAT W2 is a geosynchronous communicationsspacecraft of that consortium. The satellite will provide direct-to-home voice and video communications to North Africa, theMiddle East, and Europe through its 24 Ku-band transpondersafter parking over 16 deg-E longitude.

Eutelsat W2

NSSDC ID: 1998-056A

Alternate Names

25491

Facts in Brief

Launch Date: 1998-10-05Launch Vehicle: Ariane44LLaunch Site: Kourou,French GuianaMass: 2900.0 kg

Funding Agency

EuropeanTelecommunicationsSatellite Consortium(International)

Discipline

Communications


Launch/Orbitalinformation for EutelsatW2

Telecommunicationsinformation for EutelsatW2

Experiments on EutelsatW2

Data collections fromEutelsat W2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data









http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Eutelsat W2

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Eutelsat W2

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Eutelsat W2

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Eutelsat W2

mailto:[email protected]?Subject=NMC Comment/Question: Eutelsat W2 (1998-056A)














Description

FASAT-B was a microsatellite for the Chilean Air Force,launched from the Baikonur cosmodrome aboard a Zenitrocket. It was launched to replace the ill-fated FASAT-A andwas similar in appearance to earlier ones in the series andcarried Earth Imaging for Ozone monitoring, digitalcommunications and GPS orbit determination experiments.

FASAT-B

NSSDC ID: 1998-043B

Alternate Names

25395

Facts in Brief

Launch Date: 1998-07-10Launch Vehicle: Zenit 2Launch Site: Tyuratam(Baikonur Cosmodrome),KazakhstanMass: 55.0 kg

Funding Agency

Unknown (Chile)

Discipline

Earth Science


Launch/Orbitalinformation for FASAT-B

Experiments on FASAT-B

Data collections fromFASAT-B



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: FASAT-B (1998-043B)











http://www.usa.gov/








Description

GE 5 is an American geosynchronous communicationsspacecraft that was launched to provide voice and videocommunications to North America. It was launched by anAriane 44L rocket from Kourou at 22:16 UT.

GE 5

NSSDC ID: 1998-063B

Alternate Names

25516

Facts in Brief

Launch Date: 1998-10-28Launch Vehicle: Ariane44LLaunch Site: Kourou,French Guiana

Funding Agency

GE AmericanCommunications, Inc.(United States)

Discipline

Communications


Launch/Orbitalinformation for GE 5

Telecommunicationsinformation for GE 5

Experiments on GE 5

Data collections from GE 5



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data








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

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

mailto:[email protected]?Subject=NMC Comment/Question: GE 5 (1998-063B)











http://www.usa.gov/








Description

GFO (Geosat Follow On) was an American military spacecraftlaunched by a Taurus rocket from Vandenberg AFB. The 410kg satellite carried a radio altimeter and a water vaporradiometer to measure sea levels and glacial heights. Themission followed the 1985 Johns Hopkins Applied Physics Labbuilt Geosat mission. The spacecraft had 96 Mbytes of on-board storage, and generated up to 126 W orbit averagepower. Early on in the mission, momentum wheel directionswere found to be reversed, although that was rectified insoftware.

GFO

NSSDC ID: 1998-007A

Alternate Names

Geosat Follow On

25157

Facts in Brief


Funding Agency

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

Discipline

Earth Science


Launch/Orbitalinformation for GFO

Experiments on GFO

Data collections from GFO



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

mailto:[email protected]?Subject=NMC Comment/Question: GFO (1998-007A)











http://www.usa.gov/








Description

Globalstar FM1 was the first of a planned 52 (48 operationaland 4 on-orbit spares) satellites in the Space Systems Loral"Big LEO" global mobile communications network offeringglobal real time voice, data and fax, was launched on a Delta IIrocket from Cape Canaveral. The satellite was 3-axis stabilizedand employed magnetometers on a deployable boom, sunsensors, GPS as attitude sensors, and carried two deployablesolar arrays delivering 1100 W. The satellites in the first-generation constellation were designed to operate at fullperformance for a minimum of 7.5 years.

The satellites in the system will be placed into low earth orbit ineight operational planes of six satellites each with a 1,414kilometer circular orbit inclined at 52 degrees.

Globalstar M001

NSSDC ID: 1998-008A

Alternate Names

Globalstar U1

25162

Facts in Brief


Funding Agency

Globalstar (International)

Discipline

Communications


Launch/Orbitalinformation for GlobalstarM001

Experiments on GlobalstarM001

Data collections fromGlobalstar M001



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Globalstar M001


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Globalstar M001


mailto:[email protected]?Subject=NMC Comment/Question: Globalstar M001 (1998-008A)











http://www.usa.gov/








Description

Globalstar FM3 was the third of a planned 52 (48 operationaland 4 on-orbit spares) satellites in the Space Systems Loral"Big LEO" global mobile communications network offeringglobal real time voice, data and fax, was launched on a Delta IIrocket from Cape Canaveral. The satellite was 3-axis stabilizedand employed magnetometers on a deployable boom, sunsensors, GPS as attitude sensors, and carried two deployablesolar arrays delivering 1100 W. The satellites in the first-generation constellation were designed to operate at fullperformance for a minimum of 7.5 years.


Globalstar M002

NSSDC ID: 1998-008C

Alternate Names

Globalstar L1

25164

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data











mailto:[email protected]?Subject=NMC Comment/Question: Globalstar M002 (1998-008C)











http://www.usa.gov/








Description

Globalstar FM4 was the fourth of a planned 52 (48 operationaland 4 on-orbit spares) satellites in the Space Systems Loral"Big LEO" global mobile communications network offeringglobal real time voice, data and fax, was launched on a Delta IIrocket from Cape Canaveral. The satellite was 3-axis stabilizedand employed magnetometers on a deployable boom, sunsensors, GPS as attitude sensors, and carried two deployablesolar arrays delivering 1100 W. The satellites in the first-generation constellation were designed to operate at fullperformance for a minimum of 7.5 years.


Globalstar M003

NSSDC ID: 1998-008D

Alternate Names

Globalstar L2

25165

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data











mailto:[email protected]?Subject=NMC Comment/Question: Globalstar M003 (1998-008D)











http://www.usa.gov/








Description

Globalstar FM2 was the second of a planned 52 (48operational and 4 on-orbit spares) satellites in the SpaceSystems Loral "Big LEO" global mobile communicationsnetwork offering global real time voice, data and fax, waslaunched on a Delta II rocket from Cape Canaveral. Thesatellite was 3-axis stabilized and employed magnetometerson a deployable boom, sun sensors, GPS as attitude sensors,and carried two deployable solar arrays delivering 1100 W.The satellites in the first-generation constellation weredesigned to operate at full performance for a minimum of 7.5years.


Globalstar M004

NSSDC ID: 1998-008B

Alternate Names

Globalstar U2

25163

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data











mailto:[email protected]?Subject=NMC Comment/Question: Globalstar M004 (1998-008B)











http://www.usa.gov/








Description

Globalstar FM8 was the sixth of a planned 52 (48 operationaland 4 on-orbit spares) satellites in the Space Systems Loral"Big LEO" global mobile communications network offeringglobal real time voice, data and fax, was launched on a Delta IIrocket from Cape Canaveral. The satellite was 3-axis stabilizedand employed magnetometers on a deployable boom, sunsensors, GPS as attitude sensors, and carried two deployablesolar arrays delivering 1100 W. The satellites in the first-generation constellation were designed to operate at fullperformance for a minimum of 7.5 years.


Globalstar M006

NSSDC ID: 1998-023B

Alternate Names

25307

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Globalstar FM15 was the eighth of a planned 52 (48operational and 4 on-orbit spares) satellites in the SpaceSystems Loral "Big LEO" global mobile communicationsnetwork offering global real time voice, data and fax, waslaunched on a Delta II rocket from Cape Canaveral. Thesatellite was 3-axis stabilized and employed magnetometerson a deployable boom, sun sensors, GPS as attitude sensors,and carried two deployable solar arrays delivering 1100 W.The satellites in the first-generation constellation weredesigned to operate at full performance for a minimum of 7.5years.


Globalstar M008

NSSDC ID: 1998-023D

Alternate Names

25309

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Globalstar FM6 was the fifth of a planned 52 (48 operationaland 4 on-orbit spares) satellites in the Space Systems Loral"Big LEO" global mobile communications network offeringglobal real time voice, data and fax, was launched on a Delta IIrocket from Cape Canaveral. The satellite was 3-axis stabilizedand employed magnetometers on a deployable boom, sunsensors, GPS as attitude sensors, and carried two deployablesolar arrays delivering 1100 W. The satellites in the first-generation constellation were designed to operate at fullperformance for a minimum of 7.5 years.


Globalstar M014

NSSDC ID: 1998-023A

Alternate Names

25306

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Globalstar FM14 was the seventh of a planned 52 (48operational and 4 on-orbit spares) satellites in the SpaceSystems Loral "Big LEO" global mobile communicationsnetwork offering global real time voice, data and fax, waslaunched on a Delta II rocket from Cape Canaveral. Thesatellite was 3-axis stabilized and employed magnetometerson a deployable boom, sun sensors, GPS as attitude sensors,and carried two deployable solar arrays delivering 1100 W.The satellites in the first-generation constellation weredesigned to operate at full performance for a minimum of 7.5years.


Globalstar M015

NSSDC ID: 1998-023C

Alternate Names

25308

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Hot Bird 4 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 deliving over 320 analogue anddigital 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. In addition to the basicWidebeam and Superbeam, Hot Bird 3 and 4 were equippedwith a Steerable Beam which could be oriented anywherevisible from 13 degrees E, either northern or southernhemispheres. Hot Birds 4 and 5 were the first in the world tobe equipped with SKYPLEX for on-board multiplexing of digitalsignals into a single DVB stream which could be received inthe downlink by standard IRDs.

Hot Bird 4

NSSDC ID: 1998-013A

Alternate Names

Atlantic Bird 4

25237

Facts in Brief

Launch Date: 1998-02-27Launch Vehicle: Ariane42PLaunch Site: Kourou,French GuianaMass: 1310.0 kg

Funding Agency


Discipline

Communications


Launch/Orbitalinformation for Hot Bird 4

Experiments on Hot Bird 4

Data collections from HotBird 4



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Hot Bird 4

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Hot Bird 4


mailto:[email protected]?Subject=NMC Comment/Question: Hot Bird 4 (1998-013A)











http://www.usa.gov/








Description

Hot Bird 5 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 Birds 4 and 5 were thefirst in the world to be equipped with SKYPLEX for on-boardmultiplexing of digital signals into a single DVB stream whichcould be received in the downlink by standard IRDs.

Hot Bird 5

NSSDC ID: 1998-057A

Alternate Names

Eurobird 2

25495

Facts in Brief

Launch Date: 1998-10-09Launch Vehicle: Atlas2ALaunch Site: CapeCanaveral, United StatesMass: 1310.0 kg

Funding Agency


Discipline

Communications


Launch/Orbitalinformation for Hot Bird 5

Telecommunicationsinformation for Hot Bird 5

Experiments on Hot Bird 5

Data collections from HotBird 5



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data








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



















Description

Inmarsat 3-F5 was the fifth in a series of five third generationsatellites. Launched from the Kourou Space Center aboard anAriane rocket, it is currently service over the Atlantic Ocean. Itused the latest spot-beam technology and higher power tosupply voice and data communications services worldwide tomobile terminals as small as pocket-size messaging units onships, aircraft 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-F5

NSSDC ID: 1998-006B

Alternate Names

25153

Facts in Brief


Funding Agency

InternationalTelecommunicationsSatellite Corporation(International)

Discipline

Communications


Launch/Orbitalinformation for Inmarsat3-F5

Experiments on Inmarsat3-F5

Data collections fromInmarsat 3-F5



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Inmarsat 3-F5

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Inmarsat 3-F5

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Inmarsat 3-F5

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Inmarsat 3-F5

mailto:[email protected]?Subject=NMC Comment/Question: Inmarsat 3-F5 (1998-006B)











http://www.usa.gov/








Description

INTELSAT 805 is the latest member of the INTELSAT fleet ofgeosynchronous satellites and was launched by an Atlas 2ASrocket from Cape Canaveral at 22:48 UT. It will provide voice,video, and internet services between Europe and the Americasafter parking over at about 40-W longitude.

Intelsat 805

NSSDC ID: 1998-037A

Alternate Names

25371

Facts in Brief

Launch Date: 1998-06-18Launch Vehicle: Atlas2ASLaunch Site: CapeCanaveral, United States

Funding Agency


Discipline

Communications


Launch/Orbitalinformation for Intelsat805

Experiments on Intelsat805

Data collections fromIntelsat 805



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Intelsat 805


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Intelsat 805


mailto:[email protected]?Subject=NMC Comment/Question: Intelsat 805 (1998-037A)











http://www.usa.gov/








Description

Intelsat 806 was a geosynchronous communicationsspacecraft of the 142-nation consortium launched by an Atlas2AS rocket from Cape Canaveral. It was the latest member ofthe current Intelsat fleet, now totalling 26 spacecraft. It wasparked over the Atlantic ocean enabling voice and videocommunications to Europe and the Americas by means of its28 C-band and 6 Ku-band transponders after parking at 40degrees W.

Intelsat 806

NSSDC ID: 1998-014A

Alternate Names

25239

Facts in Brief

Launch Date: 1998-02-27Launch Vehicle: Atlas2ASLaunch Site: CapeCanaveral, United StatesMass: 1595.0 kg

Funding Agency


Discipline

Communications


Launch/Orbitalinformation for Intelsat806

Telecommunicationsinformation for Intelsat806

Experiments on Intelsat806

Data collections fromIntelsat 806



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data



























Description

Zarya (Dawn) is the Russian-built, American-financed modulethat was the first-launched of numerous planned modules ofthe International Space Station (ISS), which is beingassembled in earth orbit. The ISS orbit is approximatelycircular at 386 km, with an inclination of 52.6 degrees. Zarya,the initial control module, also known as the Functional CargoBlock (FGM when the Russian equivalent acronym istransliterated), was linked together with Unity, the Americansix-port habitable connection module, in the first assembly stepof the ISS. Because Zarya was the first-orbited element of theISS, its international spacecraft ID (1998-067A) will also be theID used for the International Space Station, and thecontinually-evolving brief description of the ISS will also bemaintained here. References to other information are given atthe end of this description.

The International Space Station is a large multi-module earth-orbiting space station, intended to be a long-term mannedstation for various research and development uses. It will beconstructed in earth orbit, using STS shuttle flights (U.S.A.)and Proton and Soyuz rocket flights (Russia) for ferryingcomponents into orbit and for later resupply flights.

In 1984, President Ronald Reagan gave NASA the go-aheadto build a space station, and invited the participation ofinternational partners. There was a series of proposed plansfor a large manned earth-orbiting space station, at lowinclination, to be coordinated with related platforms, such asthe ESA Columbus Polar Platform, Columbus Attached Lab,and Columbus Free-flying Platform. Over time, each proposedstation and alternative version in turn failed to gain acceptanceand budget approval, and was dropped during re-scoping anddown-sizing of the plan. Those rejected items included SpaceStation Alpha and Space Station Freedom, the last of thegroup. The ESA Columbus platforms underwent a similar re-scoping and down-sizing, and the principal ESA module will bethe laboratory Columbus Orbital Facility (COF), to be flownafter the year 2002.

Eventually the multi-nation US-led international station, namedInternational Space Station, or ISS, was accepted and gainedU.S. budget approval. By launch time the mission had evolved,due largely to financial constraints, to include a variety oflevels of involvement by additional other nations. As ofNovember, 1998 the global participants, in addition to theUnited States, included Russia, Canada, Japan, Brazil, andESA (Belgium, Britain, Denmark, France, Germany, Italy, TheNetherlands, Norway, Spain, Sweden, and Switzerland).

International Space Station

NSSDC ID: 1998-067A

Alternate Names

ISS

MKS

Space Station

Zarya

Unity

FGB

25544

Facts in Brief

Launch Date: 1998-11-20LaunchVehicle: Proton-KLaunch Site: Tyuratam(Baikonur Cosmodrome),KazakhstanMass: 31100.0 kg

Funding Agencies

Russian Space Agency(Russia)


Disciplines

Engineering

Human Crew


Launch/Orbitalinformation forInternational SpaceStation

Experiments onInternational Space Station

Data collections from


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


International SpaceStation






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=International Space Station

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=International Space Station

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=International Space Station









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



In the first phase of the project, seven U.S. astronauts spentalmost 27 months aboard the Russian Mir, gaining technical,operational and risk management experience. In the nextphase (November 1998 - January 2000) the station will expandfrom its first two sections to include labs, larger solar wings, aSoyuz return vehicle, communications systems and a robotarm. After that (March 2000 - January 2004), labs from Japanand ESA will be added, as well as a centrifuge module forexperiments requiring gravity, and finally a U.S.-built habitationmodule big enough for a permanent crew of seven.

Once the station becomes habitable, perhaps early in 2000,three-person crews will begin living aboard and conductinglong-term experiments. Anticipated projects for ISS includezero-gravity research in processing of materials andpharmaceuticals, and biological research.

The first two modules of the ISS, Zarya (1998-067A) and Unity(1998-069F, also called Node 1), were attached together inorbit at 02:49 GMT on December 7, 1998. Zarya, a 43,000-pound (~19,500 kg) control module launched November 20 bya Russian Proton rocket, and Unity, a 25,500-pound (~11,600kg) six-port habitable connection module launched aboard theU.S. STS-88 Space Shuttle on December 3, were linkedtogether by the international crew of STS-88. With thesubsequent connection of various power, communication, anddata cables, the International Space Station becameoperational. For further details of the component modules, seetheir separate descriptions in the NSSDC information system,and/or see the URLs below.

For more information, see the following NASA and ESA WWWpages: http://spaceflight.nasa.gov/

(A search page)http://station.nasa.gov/station/assembly/index.html

Zarya (1998-067A)http://station.nasa.gov/station/assembly/elements/fgb/

Unity (1998-069F)http://station.nasa.gov/station/assembly/elements/node1/

http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1998-069F

http://www.estec.esa.int/spaceflight/index.htmISShttp://www.estec.esa.int/spaceflight/zarya.htmColumbushttp://www.estec.esa.nl/spaceflight/cof.htm

International Space Station


Personnel


Dr. Donald A.Thomas

ProgramScientist

NASA Johnson SpaceCenter

[email protected]


http://spaceflight.nasa.gov/

http://station.nasa.gov/station/assembly/index.html

http://station.nasa.gov/station/assembly/elements/fgb/

http://station.nasa.gov/station/assembly/elements/node1/

http://www.estec.esa.int/spaceflight/index.htm

http://www.estec.esa.int/spaceflight/zarya.htm

http://www.estec.esa.nl/spaceflight/cof.htm

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=International Space Station

mailto:[email protected]?Subject=NMC Comment/Question: International Space Station (1998-067A)



http://www.usa.gov/








Description

Iridium 2 was part of a planned commercial communicationsnetwork comprised of a constellation of 66 LEO spacecraft.The system will use L-Band to provide global communicationsservices through portable handsets. A total of 125 spacecraftwill be built by Lockheed for more than $700M. Commercialservice is planned to begin in 1998. The system will employ15-20 ground stations with a master control complex inLandsdowne, VA, a backup in Italy, and a third engineeringcenter in Chandler, AZ. The spacecraft was 3-axis stabilized,with a hydrazine propulsion system. It had 2 solar panels with1-axis articulation. The system employed L-Band usingFDMA/TDMA to provide voice at 4.8 kbps and data at 2400bps with 16 dB margin. Each satellite had 48 spot beams forEarth coverage and used Ka-Band for crosslinks and groundcommanding.

Iridium 2

NSSDC ID: 1998-066A

Alternate Names

25527

Facts in Brief

Launch Date: 1998-11-06Launch Vehicle: DeltaII 7920LaunchSite: Vandenberg AFB,United StatesMass: 556.0 kg

Funding Agency

Iridium (United States)

Discipline

Communications


Launch/Orbitalinformation for Iridium 2

Telecommunicationsinformation for Iridium 2

Experiments on Iridium 2

Data collections fromIridium 2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data








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

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


mailto:[email protected]?Subject=NMC Comment/Question: Iridium 2 (1998-066A)











http://www.usa.gov/








Description


Iridium 3

NSSDC ID: 1998-048A

Alternate Names

25431

Facts in Brief

Launch Date: 1998-08-19Launch Vehicle: LongMarch 2CLaunch Site: Taiyuan,Peoples Republic of China

Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description

Iridium 11A was part of a planned commercial communicationsnetwork comprised of a constellation of 66 LEO spacecraft. Itreplaced Iridium 11 in the constellation. The system will use L-Band to provide global communications services throughportable handsets. A total of 125 spacecraft will be built byLockheed for more than $700M. Commercial service isplanned to begin in 1998. The system will employ 15-20ground stations with a master control complex in Landsdowne,VA, a backup in Italy, and a third engineering center inChandler, AZ. The spacecraft was 3-axis stabilized, with ahydrazine propulsion system. It had 2 solar panels with 1-axisarticulation. The system employed L-Band using FDMA/TDMAto provide voice at 4.8 kbps and data at 2400 bps with 16 dBmargin. Each satellite had 48 spot beams for Earth coverageand used Ka-Band for crosslinks and ground commanding.

Iridium 11A

NSSDC ID: 1998-074A

Alternate Names

25577

Facts in Brief

Launch Date: 1998-12-19Launch Vehicle: LongMarch 2CLaunch Site: Taiyuan,Peoples Republic of ChinaMass: 556.0 kg

Funding Agency


Discipline

Communications


Launch/Orbitalinformation for Iridium11A

Telecommunicationsinformation for Iridium11A

Experiments on Iridium11A

Data collections fromIridium 11A



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data










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


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


mailto:[email protected]?Subject=NMC Comment/Question: Iridium 11A (1998-074A)











http://www.usa.gov/








Description

Iridium 20A was part of a planned commercial communicationsnetwork comprised of a constellation of 66 LEO spacecraft. Itreplaced Iridium 20 in the constellation. The system will use L-Band to provide global communications services throughportable handsets. A total of 125 spacecraft will be built byLockheed for more than $700M. Commercial service isplanned to begin in 1998. The system will employ 15-20ground stations with a master control complex in Landsdowne,VA, a backup in Italy, and a third engineering center inChandler, AZ. The spacecraft was 3-axis stabilized, with ahydrazine propulsion system. It had 2 solar panels with 1-axisarticulation. The system employed L-Band using FDMA/TDMAto provide voice at 4.8 kbps and data at 2400 bps with 16 dBmargin. Each satellite had 48 spot beams for Earth coverageand used Ka-Band for crosslinks and ground commanding.

Iridium 20A

NSSDC ID: 1998-074B

Alternate Names

25578

Facts in Brief

Launch Date: 1998-12-19Launch Vehicle: LongMarch 2CLaunch Site: Taiyuan,Peoples Republic of ChinaMass: 556.0 kg

Funding Agency


Discipline

Communications


Launch/Orbitalinformation for Iridium20A

Telecommunicationsinformation for Iridium20A

Experiments on Iridium20A

Data collections fromIridium 20A



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data














mailto:[email protected]?Subject=NMC Comment/Question: Iridium 20A (1998-074B)











http://www.usa.gov/








Description


Iridium 50

NSSDC ID: 1998-010A

Alternate Names

25169

Facts in Brief

Launch Date: 1998-02-18Launch Vehicle: DeltaII 7920LaunchSite: Vandenberg AFB,United States

Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 51

NSSDC ID: 1998-018A

Alternate Names

25262

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 52

NSSDC ID: 1998-010C

Alternate Names

25171

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data









mailto:[email protected]?Subject=NMC Comment/Question: Iridium 52 (1998-010C)











http://www.usa.gov/







Iridium 53

NSSDC ID: 1998-010D

Description

Iridium 53 was part of a planned commercial communications network comprised of a constellation of 66 LEOspacecraft. The system will use L-Band to provide global communications services through portable handsets. A totalof 125 spacecraft will be built by Lockheed for more than $700M. Commercial service is planned to begin in 1998. Thesystem will employ 15-20 ground stations with a master control complex in Landsdowne, VA, a backup in Italy, and athird engineering center in Chandler, AZ. The spacecraft was 3-axis stabilized, with a hydrazine propulsion system. Ithad 2 solar panels with 1-axis articulation. The system employed L-Band using FDMA/TDMA to provide voice at 4.8kbps and data at 2400 bps with 16 dB margin. Each satellite had 48 spot beams for Earth coverage and used Ka-Bandfor crosslinks and ground commanding.


Facts in Brief

Launch Date: 1998-02-18Launch Vehicle: Delta II 7920Launch Site: Vandenberg AFB, United States

Funding AgencyIridium (United States)

DisciplineCommunications

Additional InformationLaunch/Orbital information for Iridium 53


Data collections from Iridium 53



SpacecraftExperimentsData CollectionsPersonnelPublicationsMapsNew/Updated DataLunar/Planetary Events






mailto:[email protected]?Subject=NMC Comment/Question: Iridium 53 (1998-010D)













http://www.usa.gov/








Description


Iridium 55

NSSDC ID: 1998-019A

Alternate Names

25272

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 56

NSSDC ID: 1998-010B

Alternate Names

25170

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data









mailto:[email protected]?Subject=NMC Comment/Question: Iridium 56 (1998-010B)











http://www.usa.gov/








Description


Iridium 57

NSSDC ID: 1998-019B

Alternate Names

25273

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 58

NSSDC ID: 1998-019C

Alternate Names

25274

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 59

NSSDC ID: 1998-019D

Alternate Names

25275

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 60

NSSDC ID: 1998-019E

Alternate Names

25276

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data









mailto:[email protected]?Subject=NMC Comment/Question: Iridium 60 (1998-019E)











http://www.usa.gov/








Description


Iridium 61

NSSDC ID: 1998-018B

Alternate Names

25263

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 62

NSSDC ID: 1998-021A

Alternate Names

25285

Facts in Brief

Launch Date: 1998-04-06LaunchVehicle: Proton-KLaunch Site: Kourou,French Guiana

Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 63

NSSDC ID: 1998-021B

Alternate Names

25286

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 64

NSSDC ID: 1998-021C

Alternate Names

25287

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 65

NSSDC ID: 1998-021D

Alternate Names

25288

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 66

NSSDC ID: 1998-021E

Alternate Names

25289

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/







Iridium 67

NSSDC ID: 1998-021F

Description

Iridium 67 was part of a planned commercial communications network comprised of a constellation of 66 LEOspacecraft. The system will use L-Band to provide global communications services through portable handsets. A totalof 125 spacecraft will be built by Lockheed for more than $700M. Commercial service is planned to begin in 1998. Thesystem will employ 15-20 ground stations with a master control complex in Landsdowne, VA, a backup in Italy, and athird engineering center in Chandler, AZ. The spacecraft was 3-axis stabilized, with a hydrazine propulsion system. Ithad 2 solar panels with 1-axis articulation. The system employed L-Band using FDMA/TDMA to provide voice at 4.8kbps and data at 2400 bps with 16 dB margin. Each satellite had 48 spot beams for Earth coverage and used Ka-Bandfor crosslinks and ground commanding.


Facts in Brief

Launch Date: 1998-04-06Launch Vehicle: Proton-KLaunch Site: Kourou, French Guiana

Funding AgencyIridium (United States)

DisciplineCommunications

Additional InformationLaunch/Orbital information for Iridium 67











mailto:[email protected]?Subject=NMC Comment/Question: Iridium 67 (1998-021F)













http://www.usa.gov/







Saturday, 18 June 2011

National Space Science Data Center Header

Iridium 54NSSDC ID: 1998-010E

Description

Iridium 54 was part of a planned commercial communications network comprised of a constellation of 66 LEOspacecraft. The system will use L-Band to provide global communications services through portable handsets. Atotal of 125 spacecraft will be built by Lockheed for more than $700M. Commercial service is planned to begin in1998. The system will employ 15-20 ground stations with a master control complex in Landsdowne, VA, a backupin Italy, and a third engineering center in Chandler, AZ. The spacecraft was 3-axis stabilized, with a hydrazinepropulsion system. It had 2 solar panels with 1-axis articulation. The system employed L-Band usingFDMA/TDMA to provide voice at 4.8 kbps and data at 2400 bps with 16 dB margin. Each satellite had 48 spotbeams for Earth coverage and used Ka-Band for crosslinks and ground commanding.

Alternate Names

25173

Facts in Brief

Launch Date: 1998-02-18Launch Vehicle: Delta II 7920Launch Site: Vandenberg AFB, United States

Funding Agency


Discipline

Communications

Additional Information

Launch/Orbital information for Iridium 54









NSSDC Master Catalog Search














http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1998-021G[18/06/2011 0:20:56]


Description


Iridium 68

NSSDC ID: 1998-021G

Alternate Names

25291

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1998-021G





mailto:[email protected]?Subject=NMC Comment/Question: Iridium 68 (1998-021G)











http://www.usa.gov/








Description


Iridium 69

NSSDC ID: 1998-026A

Alternate Names

25319

Facts in Brief

Launch Date: 1998-05-02Launch Vehicle: LongMarch 2C/SDLaunch Site: Taiyuan,Peoples Republic of China

Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 70

NSSDC ID: 1998-032A

Alternate Names

25342

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 71

NSSDC ID: 1998-026B

Alternate Names

25230

Facts in Brief

Launch Date: 1998-05-02Launch Vehicle: LongMarch 2C/SDLaunch Site: Taiyuan,Peoples Republic of China

Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 72

NSSDC ID: 1998-032B

Alternate Names

25343

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 73

NSSDC ID: 1998-032C

Alternate Names

25344

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 74

NSSDC ID: 1998-032D

Alternate Names

25345

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 75

NSSDC ID: 1998-032E

Alternate Names

25346

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 76

NSSDC ID: 1998-048B

Alternate Names

25432

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 77

NSSDC ID: 1998-051E

Alternate Names

25471

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 79

NSSDC ID: 1998-051D

Alternate Names

25470

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 80

NSSDC ID: 1998-051C

Alternate Names

25469

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 81

NSSDC ID: 1998-051B

Alternate Names

25468

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 82

NSSDC ID: 1998-051A

Alternate Names

24467

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 83

NSSDC ID: 1998-066E

Alternate Names

25531

Facts in Brief


Funding Agency


Discipline

Communications








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/spacecraftTelemetry.do?id=1998-066E

http://nssdc.gsfc.nasa.gov/nmc/spacecraftTelemetry.do?id=1998-066E















http://www.usa.gov/








Description


Iridium 84

NSSDC ID: 1998-066D

Alternate Names

25530

Facts in Brief


Funding Agency


Discipline

Communications








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/spacecraftTelemetry.do?id=1998-066D

http://nssdc.gsfc.nasa.gov/nmc/spacecraftTelemetry.do?id=1998-066D















http://www.usa.gov/








Description


Iridium 85

NSSDC ID: 1998-066C

Alternate Names

25529

Facts in Brief


Funding Agency


Discipline

Communications








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Iridium 86

NSSDC ID: 1998-066B

Alternate Names

25528

Facts in Brief


Funding Agency


Discipline

Communications








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

The Lunar Prospector was designed for a low polar orbitinvestigation of the Moon, including mapping of surfacecomposition and possible deposits of polar ice, measurementsof magnetic and gravity fields, and study of lunar outgassingevents. Data from the 19 month mission will allow constructionof a detailed map of the surface composition of the Moon, andwill improve our understanding of the origin, evolution, currentstate, and resources of the Moon. The spacecraft carries 6experiments: a Gamma Ray Spectrometer (GRS), a NeutronSpectrometer (NS), a Magnetometer (MAG), an ElectronReflectometer (ER), an Alpha Particle Spectrometer (APS),and a Doppler Gravity Experiment (DGE). The instruments areomnidirectional and require no sequencing. The normalobservation sequence is to record and downlink datacontinuously.

Spacecraft and SubsystemsThe spacecraft is a graphite-epoxy drum, 1.37 meters indiameter and 1.28 meters high with three radial 2.5 minstrument booms. A 1.1 m extension boom at the end of oneof the 2.5 m booms holds the magnetometer. Total initial mass(fully fueled) was 296 kg. It is spin-stabilized (nominal spin rate12 rpm) with its spin axis normal to the ecliptic plane. Thespacecraft is controlled by 6 hydrazine monopropellant 22-Newton thrusters, two aft, two forward, and two tangential.Three fuel tanks mounted inside the drum hold 138 kg ofhydrazine pressurized by helium. The power system consistsof body mounted solar cells which produce an average of 186W and a 4.8 amp-hr rechargeable NiCd battery.Communications are through two S-band transponders, aslotted, phased-array medium gain antenna for downlink, andan omnidirectional low-gain antenna for downlink and uplink.There is no on-board computer, all control is from the ground,commanding a single on-board command and data handlingunit. Data are downlinked directly and also stored on a solid-state recorder and downlinked after 53 minutes, to ensure alldata collected during communications blackout periods arereceived.

Mission ProfileFollowing launch on 7 January 1998 UT (6 January EST)aboard a three-stage Athena 2 rocket, the Lunar Prospectorhad a 105 hour cruise to the Moon. During the cruise, thethree instrument booms were deployed. The MAG and APScollected calibration data, while the GRS, NS, and ERoutgassed for one day, after which they also collectedcalibration data in cis-lunar space. The craft was inserted intoan 11.6-hour period capture orbit about the Moon at the end ofthe cruise phase. After 24 hours Lunar Prospector wasinserted into a 3.5-hour period intermediate orbit, followed 24hours later (on 13 January 1998) by tranfer into a 92 x 153 km

Lunar Prospector

NSSDC ID: 1998-001A

Alternate Names

Lunar Prospector Orbiter

25131

Facts in Brief

Launch Date: 1998-01-06LaunchVehicle: Athena 2Launch Site: CapeCanaveral, United StatesMass: 158.0 kgNominalPower: 202.0 W

Funding Agency

NASA-Office of SpaceScience (United States)

Discipline

Planetary Science


Launch/Orbitalinformation for LunarProspector

PDMP information forLunar Prospector

Telecommunicationsinformation for LunarProspector

Experiments on LunarProspector

Data collections from LunarProspector



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


Lunar Prospector










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

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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Lunar Prospector (1998-001A)

mailto:[email protected]?Subject=NMC Comment/Question: Lunar Prospector (1998-001A)









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



preliminary mapping orbit, and then on 16 January by insertioninto the near-circular 100 km altitude nominal lunar polarmapping orbit with an inclination of 90 degrees and a period of118 minutes. Lunar calibration data was collected during the11.6- and 3.5-hour orbits. Lunar mapping data collectionstarted shortly after the 118 minute orbit was achieved. Thedata collection was periodically interrupted during the missionas planned for orbital maintenance burns, which took place torecircularize the orbit whenever the periselene or aposelenewas more than 20 to 25 km from the 100 km nominal orbit,about once a month. On 19 December 1998, a maneuverlowered the orbit to 40 km to perform higher resolution studies.The orbit was altered again on 28 January to a 15 x 45 kmorbit, ending the 1 year primary mission and beginning theextended mission. The mission ended on 31 July 1999 at9:52:02 UT (5:52:02 EDT) when Lunar Prospector wasdeliberately targeted to impact in a permanently shadowedarea of a crater near the lunar south pole. It was hoped thatthe impact would liberate water vapor from the suspected icedeposits in the crater and that the plume would be detectablefrom Earth, however, no plume was observed.

The Lunar Prospector mission was the third mission selectedby NASA for full development and construction as part ofNASA's Discovery Program. Total cost for the mission was$62.8 million including development ($34 million), launchvehicle (~$25 million) and operations (~$4 million).

Personnel


Dr. MarkA.Saunders

ProgramManager

NASA Headquarters

Mr. G.ScottHubbard

MissionManager

NASA AmesResearch Center

[email protected]

Dr. AlanB. Binder

MissionPrincipalInvestigator

Lockheed [email protected]

Dr.DomenickJ.Tenerelli

ProjectManager

Lockheed [email protected]

Mr. HenryC. Brinton

ProgramScientist

NASA Headquarters

Selected References

Binder, A. B., Lunar Prospector: Overview, Science, 281, No. 5382, 1475-1476, Sept. 1998.

Hubbard, G. S., et al., The Lunar Prospector Discovery mission: Mission and measurementdescription, IEEE Trans. Nuclear Sci., 45, No. 3, 880-887, June 1998.

Experiment and Engineering Raw Data on CD-WO

NSSDC Lunar Prospector Home PageSummary of Current Lunar Prospector Science ResultsLunar Science Home PageMoon PageMoon Fact SheetThe Search for Ice on the MoonLunar Prospector Orbital Dynamics - Flight Dynamics DivisionLunar Prospector Home Page - NASA AmesLunar Prospector Spectrometers - Los Alamos National Laboratory

http://nssdc.gsfc.nasa.gov/database/MasterCatalog?ds=PSPG-00057

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

http://nssdc.gsfc.nasa.gov/planetary/lunar/lp_science.html

http://nssdc.gsfc.nasa.gov/planetary/lunar/apollo_25th.html

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

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

http://nssdc.gsfc.nasa.gov/planetary/ice/ice_moon.html

http://fdd.gsfc.nasa.gov/lp/

http://lunar.arc.nasa.gov/

http://nis-www.lanl.gov/nis-projects/lunar/

Lunar Prospector

· Otros nombres: 1998-001A, Lunar Prospector Orbiter, 25131 · Fecha de lanzamiento: 7 de enero de 1.998 a las 02:28:44 GMT · Masa seca en órbita: 158 kg · Potencia máxima: 186 W · Objetivos e instrumentos La sonda Lunar Prospector fue diseñada para realizar investigaciones en la Luna, incluida la realización de mapas de la composición de la superficie y posibles depósitos de hielo polar, medidas de los campos magnéticos y gravitatorios y posibles eventos de expulsión de gases. Los datos de esta misión de 19 meses de duración permitirán conocer la composición, origen, estado actual y de recursos disponibles en la Luna. La nave portaba seis instrumentos: - Espectrómetro de rayos gamma (GRS) - Espectrómetro de neutrones (NS) - Magnetómetro (MAG) - Reflectómetro de electrones (ER) - Espectrómetro de partículas alfa (APS) - Experimento Doppler de gravedad (DGE) Todos los instrumentos eran omnidireccionales y no necesitaban ni apuntado de la nave ni órdenes para funcionar. Los datos eran grabados abordo y transmitidos de manera continua. Los espectrómetros GRS y NS debían obtener datos globales de abundancia de elementos lo que permitiría comprender la evolución de la corteza lunar y la duración del vulcanismo basáltico y para cononcer los recursos lunares. Además el NS debía localizar la situación y la cantidad del agua helada presente en las zonas sombrías cerca de los polos lunares. Los experimentos MAG y ER darían datos del campo magnético de la corteza y del dipolo magnético inducido lunar. Estos datos permitirían conocer el origen del paleomagnetismo lunar y la influencia de los impactos en él, así como para conocer el tamaño y composición del posible núcleo lunar.

La nave lista para ser lanzada

El espectrómetro APS permitiría conocer las zonas donde se produce expulsión de gas radón, detectando las partículas alfa emitidas por el radón y su producto de decaimiento, el polonio. Observando la frecuencia y localización de estas emisiones permitiría conocer las fuentes de la tenue atmósfera lunar. También se relacionarían la expulsión de gases con la edad de los cráteres y las estructuras tectónicas y su nivel de actividad actual. El experimento Doppler DGE usaría la banda S de radio. Se seguiría la señal de la sonda para caracterizar la órbita y de esta manera conocer el campo de gravedad. Los datos recogidos permitirían conocer el interior de la Luna al ser combinados con los datos de topografía. · La nave La sonda estaba construida con un compuesto de Epoxi reforzado con fibra de carbono, con un tamaño de 1,37 x 1,28 metros y con tres brazos desplegables radiales de 2,5 metros de longitud. Otra extensión de 1,1 metros al final de uno de los brazos mantenía el magnetómetro. La masa inicial incluyendo el combustible era de 296 kilogramos. Su giro estaba estabilizado en un eje con un ritmo de rotación de 12 revoluciones por minuto y

con el eje perpendicular al plano de la eclíptica. La nave controlaba su orientación con 6 toberas de hidracina con una potencia de 22 Newtons. Para el combustible la sonda portaba tres tanques montados en el interior que tenían capacidad para 138 kilogramos, siendo presurizados por helio.

La nave rumbo a la Luna Para la alimentación eléctrica, la nave estaba rodeada por células solares que daban una energía media de 186 vatios y cargaban una batería de 4,8 amperios-hora de Ni/Cd. Las comunicaciones se establecían a través de dos transpondedores de banda S, una antena de media ganancia para envío de datos a la Tierra y una antena omnidireccional de baja ganancia para envío y recepción de datos y telemetría. La nave no llevaba ningún tipo de ordenador y todo era controlado desde la Tierra, de tal forma que la nave solo tenía una unidad receptora de comandos y manejo de datos. Los datos se enviaban directamente a nuestro planeta y si esto no era posible se almacenaban en un grabador de datos de estado sólido y se retransmitían tras 53 minutos para asegurar que todos los datos recogidos durante los periodos de bloqueo de comunicación eran recibidos.

· La misión La nave fue lanzada el 7 de enero de 1998 a bordo de un cohete Athena 2 rumbo a la Luna en un crucero de 105 horas hasta llegar a nuestro satélite. Durante el viaje se desplegaron tres

brazos de los instrumentos. Lanzamiento Al llegar a la Luna, la nave fue insertada en una órbita de captura con un periodo de 11,6 horas. Tras 24 horas la sonda Lunar Prospector fue insertada en una órbita intermedia de 3,5 horas de duración y otras 24 horas después (13 de enero) se colocó en una órbita de 92 x 153 kilómetros para realizar la fase preliminar de fotografía. El 16 de enero quedó por fin colocada en una órbita polar circular de 100 kilómetros de altura con una inclinación de 90º y un

periodo de 118 minutos. En las órbitas de 11,6 y 3,5 horas se recogieron datos de calibración y los datos científicos ya fueron obtenidos en la órbita circular de 100 kilómetros. La recogida de datos fue interrumpida periódicamente durante la misión para la realización de maniobras para mantener la altura respecto al suelo lunar lo que permitía recircularizar la órbita para que tanto el perilunio como el apolunio nunca estuvieran a más de 25 kilómetros de la órbita prefijada, lo que ocurría una vez al mes. El 19 de diciembre una maniobra bajó la órbita hasta los 40 kilómetros para realizar estudios con más resolución. El 28 de enero de 1999 se volvió a mover la órbita hasta los 15 x 45 kilómetros, finalizando de esta forma el año primario de misión y comenzando la misión extendida. La misión concluyó de forma definitiva el 31 de julio de 1999 a las 09:52:02 GMT cuando la nave fue estrellada de forma deliberada contra la superficie lunar en una zona que se encuentra en sombra de forma permanente, en un cráter cerca del polo sur. Se esperaba que el impacto liberara vapor de agua de los depósitos de hielo en el cráter y que el material fuera detectado desde la Tierra. Sin embargo no se pudo detectar nada desde nuestro planeta. · Descubrimientos - Hielo en la Luna: El espectrómetro de neutrones mostró un aumento de las concentraciones

de hidrógeno en los polos norte y sur de la Luna, indicando una presencia significativa de grandes cantidades de agua que se encuentra atrapada en los cráteres que están permanentemente en sombra.

Presencia de neutrones en los polos - Composición de la superficie: El espectrómetro de neutrones es además sensible al hierro y al titanio en el suelo y rocas lunares. Con los mapas realizados con este instrumento se mostraron tres zonas diferenciadas: mares de basalto ricos en hierro y titanio, terrenos elevados pobres en hierro y titanio y los suelos de la cuenca Aitken en el Polo Sur y los bordes de los mares circulares en los alrededores que tienen concentraciones intermedias. - Datos de gravedad: Los resultados del seguimiento en banda S y los cálculos del Doppler daban información de la gravedad lunar. Los datos mostraron que la luna tenía un pequeño núcleo denso con una masa de entre el 1 y el 4% del total lunar y un radio de entre 220 y 590 kilómetros, en función de su posible composición. Además se descubrieron 7 nuevos mascones. - Radón: El Espectrómetro APS estaba diseñado para detectar radón en la superficie. Los análisis iniciales fueron complicados debido a la presencia de las partículas energéticas del sol pero mostraron que el gas radón emana actualmente en las cercanías de los cráteres Aristarco y Kepler. Además se detectó torio, lo que implica la presencia de uranio.




Description

MAQSAT 3 was a dummy payload to test the performance ofthe latest model of the Ariane series, Ariane 5. The rocket alsoreleased an atmospheric reentry demonstrator (ARD).

MAQSAT 3

NSSDC ID: 1998-059A

Alternate Names

25503

Facts in Brief


Funding Agency

European Space Agency(International)

Discipline

Engineering


Launch/Orbitalinformation for MAQSAT3

Experiments on MAQSAT3

Data collections fromMAQSAT 3



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







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

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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: MAQSAT 3 (1998-059A)











http://www.usa.gov/








Description

The Mars Surveyor '98 program is comprised of two spacecraftlaunched separately, the Mars Climate Orbiter (formerly theMars Surveyor '98 Orbiter) and the Mars Polar Lander(formerly the Mars Surveyor '98 Lander). The two missionswere to study the Martian weather, climate, and water andcarbon dioxide budget, in order to understand the reservoirs,behavior, and atmospheric role of volatiles and to search forevidence of long-term and episodic climate changes. The MarsClimate Orbiter was destroyed when a navigation error causedit to miss its target altiude at Mars by 80 to 90 km, insteadentering the martian atmosphere at an altitude of 57 km duringthe orbit insertion maneuver.

Science ObjectivesThe Orbiter has as its primary science objectives to: 1) monitorthe daily weather and atmospheric conditions; 2) recordchanges on the martian surface due to wind and otheratmospheric effects; 3) determine temperature profiles of theatmosphere; 4) monitor the water vapor and dust content ofthe atmosphere and 5) look for evidence of past climatechange. Specifically it will observe and study dust storms,weather systems, clouds and dust hazes, ozone, distributionand transport of dust and water, the effects of topography onatmospheric circulation, atmospheric response to solarheating, and surface features, wind streaks, erosion, and colorchanges. The orbiter will use two instruments to carry outthese investigations. The Mars Climate Orbiter Color Imager(MARCI) will acquire daily atmospheric weather images andhigh resolution surface images and the Pressure ModulatedInfrared Radiometer (PMIRR) will allow measurement of theatmospheric temperature, water vapor abundance, and dustconcentration. The orbiter will also serve as a data relaysatellite for the Mars Polar Lander and other future NASA andinternational lander missions to Mars.

Spacecraft and SubsystemsThe Mars Climate Orbiter is a box shaped spacecraft about 2.1m high, 1.6 m wide, and 2 m deep, consisting of stackedpropulsion and equipment modules. The total spacecraftlaunch mass of 629 kg includes 291 kg of propellant. An 11square meter solar array wing, measuring 5.5 m tip-to-tip, isattached by 2-axis gimbal to one side and a 1.3 m diameterhigh-gain dish antenna is attached by 2-axis gimbal to a mastat the top of the propulsion module. The MARCI and PMIRRinstruments, as well as a UHF antenna and battery enclosure,are mounted to the bottom of the equipment module.

Propulsion is achieved via a 640-N bi-propellant(hydrazine/nitrogen tetroxide) main engine, mounted with the

Mars Climate Orbiter

NSSDC ID: 1998-073A

Alternate Names

Mars Surveyor 98 Orbiter

Mars '98 Orbiter

25571

Facts in Brief


Funding Agency


Discipline

Planetary Science


Launch/Orbitalinformation for MarsClimate Orbiter

PDMP information forMars Climate Orbiter

Telecommunicationsinformation for MarsClimate Orbiter

Experiments on MarsClimate Orbiter

Data collections from MarsClimate Orbiter

Questions or comments


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


Mars Climate Orbiter










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

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

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

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









http://nssdc.gsfc.nasa.gov/image/spacecraft/mars98orb.jpg



propellant tanks in the propulsion module, and hydrazinethrusters. The orbiter is 3-axis stabilized. Attitude control andmaneuvering capability is provided by four 7-Nm thrusters(pitch/yaw) and four 0.3-Nm thrusters (roll) in combination withreaction wheels. Attitude is determined using an inertialmeasurement unit, a star tracker, and analog Sun sensors withknowledge of 25 mrad and stability of 1.5 mrad/(1 sec) and 3mrad/(3 sec).

Spacecraft power is provided by 3 panels of GaAs/Ge solarcells on the 5.5 meter long single-wing solar array whichprovide 1000 W of power at Earth and 500 W at Mars. Poweris stored in nickel hydride (NiH2) common pressure vesselbatteries. Thermal control is achieved through a combination oflouvers, MLI, Kapton, paints, radiators and heater circuits.Communications with Earth are in X-band using Cassini DeepSpace Transponders and 15 W RF solid state power amplifiersthrough the 1.3 m high gain antenna for both uplink anddownlink, a medium gain transmitting antenna, and a low-gainreceiving antenna. A 10 W UHF system is used for 2-waycommunications with the Mars Polar Lander. A RAD6000processor is used for on-board command and data handling.

Mission ProfileMars Climate Orbiter was launched on a Delta 7425 (a Delta IILite launch vehicle with four strap-on solid-rocket boosters anda Star 48 (PAM-D) third stage). Launch was at 18:45:51 UT(1:45:51 p.m. EST) on 11 December 1998 from Pad A ofLaunch Complex 17 at Cape Canaveral Air Station, Florida.After a brief cruise in Earth orbit, the Delta II 3rd stage put thespacecraft into trans-Mars trajectory and about 15 days afterlaunch the largest trajectory correction maneuver (TCM) wasexecuted using the hydrazine thrusters. During cruise to Mars,three additional TCM's using the hydrazine thrusters wereperformed on 4 March, 25 July, and 15 September 1999.

The spacecraft reached Mars and executed a 16 minute 23second orbit insertion main engine burn on 23 September1999 at 09:01 UT (5:01 a.m. EDT) Earth received time (ERT,signal travel time from Mars will be 10 minutes 55 seconds).The spacecraft passed behind Mars at 09:06 UT ERT and wasto re-emerge and establish radio contact with Earth at 09:27UT ERT, 10 minutes after the burn was completed. However,contact was never re-established and no signal was everreceived from the spacecraft. Findings of the failure reviewboard indicate that a navigation error resulted from somespacecraft commands being sent in English units instead ofbeing converted to metric. This caused the spacecraft to missits intended 140 - 150 km altitude above Mars during orbitinsertion, instead entering the martian atmosphere at about 57km. The spacecraft would have been destroyed byatmospheric stresses and friction at this low altitude.

The burn would have slowed the spacecraft and put it into a 14hour elliptical (~150 x 21,000 km) capture orbit. The orbiterwas to begin aerobraking, using the solar panel to provideresistance and continue until a 90 x 405 km orbit wasachieved, nominally on 22 November 1999, with periapsis at89 N. The hydrazine thrusters would be used to change theorbit to a 2-hour, 421 km near-circular polar science mappingorbit on 1 December 1999. The orbit was to be nearly Sun-synchronous, crossing the daytime equator at about 4:30 p.m.local time. The first phase of the mission was to support theMars Polar Lander from its landing on Mars on 3 December1999 to the end of the lander primary mission on 29 February2000. The orbiter would pass over the lander site 10 times permartian day for 5-6 minutes each time, communicating via theUHF 2-way relay link at 128 kbits/s. Mars science operations

about this spacecraft canbe directed to: Dr. David R.Williams.

mailto:[email protected]?Subject=NMC Comment/Question: Mars Climate Orbiter (1998-073A)

mailto:[email protected]?Subject=NMC Comment/Question: Mars Climate Orbiter (1998-073A)



and mapping, involving operation of the MARCI and PMIRR,would initiate on 3 March 2000 and continue for one martianyear (687 days). At the end of the mapping mission on 15January 2002, the orbiter was to be placed in a stable orbitand function as a UHF relay for the Mars 2001 mission.

The Mars Surveyor '98 program spacecraft development cost193.1 million dollars. Launch costs are estimated at 91.7million dollars and mission operations at 42.8 million dollars.The Mars Climate Orbiter is part of NASA's 10-year MarsSurveyor Program, which will feature launches every 26months when the Earth and Mars are favorably aligned.

Personnel


Mr. John B.McNamee

ProjectManager


[email protected]

Dr. RichardW. Zurek

ProjectScientist


[email protected]

Dr. Joseph M.Boyce

ProgramScientist

NASA Headquarters [email protected]

The report of the failure review board investigating the loss of Mars ClimateOrbiter was discussed at a press briefing on Wednesday, November 10 at2:00 p.m. EST. The findings and recommendations of the review board aredetailed in a NASA Press Release.

Findings of the Failure Review Board on the loss of Mars Climate OrbiterDetails on the Loss of Mars Climate OrbiterPress Release on Probable Cause of Loss

Mars Surveyor '98 Status Report

(2046 K JPG)

Other Mars Climate Orbiter Information

http://nssdc.gsfc.nasa.gov/planetary/text/mco_pr_19991110.txt


http://nssdc.gsfc.nasa.gov/planetary/news/mco_19990923.html


http://nssdc.gsfc.nasa.gov/planetary/text/mars98_status.txt

http://nssdc.gsfc.nasa.gov/planetary/image/mco-text_sm.jpg

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

http://nssdc.gsfc.nasa.gov/planetary/image/mco-text.jpg



Mars Orbit Insertion Timeline - Schedule of events on 23 September 1999NASA Press Release on mission, 11 February 1998 - Mission details and MGS images of thesouth polar cap1998 Mars Orbiter, Lander, Microprobes set for launch - Prelaunch press release (November1998).

Mars Polar LanderMars Home PageMars Global Surveyor

Mars Climate Orbiter Home PageMars Surveyor 98 Project Press Kit - PDF fileMars Climate Orbiter Orbit Insertion Press Kit - PDF fileColor Imager Home Page - Malin Space Science Systems

Mars Climate Orbiter images at top right and bottom left created by CorbyWaste


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

http://nssdc.gsfc.nasa.gov/planetary/text/nasa_pr_19980211.txt

http://nssdc.gsfc.nasa.gov/planetary/text/mars98_pr_19981116.txt

http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1999-001A

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

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

http://mpfwww.jpl.nasa.gov/msp98/orbiter/

http://www.jpl.nasa.gov/files/misc/mars98launch.pdf

http://www.jpl.nasa.gov/files/misc/mcoarrivehq.pdf

http://barsoom.msss.com/mars/surveyor/marci.html

http://www.usa.gov/





Mars Climate Orbiter NSSDC ID: 1998-073A Other Names Mars '98 Orbiter Mars Surveyor 98 Orbiter 25571 Launch Date/Time: 1998-12-11 at 18:45:51 UTC On-orbit Dry Mass: 338 kg Nominal Power Output: 500 W

Description The Mars Surveyor '98 program is comprised of two spacecraft launched separately, the Mars Climate Orbiter (formerly the Mars Surveyor '98 Orbiter) and the Mars Polar Lander (formerly the Mars Surveyor '98 Lander). The two missions were to study the Martian weather, climate, and water and carbon dioxide budget, in order to understand the reservoirs, behavior, and atmospheric role of volatiles and to search for evidence of long-term and episodic climate changes. The Mars Climate Orbiter was destroyed when a navigation error caused it to miss its target altiude at Mars by 80 to 90 km, instead entering the martian atmosphere at an altitude of 57 km during the orbit insertion maneuver. Science Objectives The Orbiter has as its primary science objectives to: 1) monitor the daily weather and atmospheric conditions; 2) record changes on the martian surface due to wind and other atmospheric effects; 3) determine temperature profiles of the atmosphere; 4) monitor the water vapor and dust content of the atmosphere and 5) look for evidence of past climate change. Specifically it will observe and study dust storms, weather systems, clouds and dust hazes, ozone, distribution and transport of dust and water, the effects of topography on atmospheric circulation, atmospheric response to solar heating, and surface features, wind streaks, erosion, and color changes. The orbiter will use two instruments to carry out these investigations. The Mars Climate Orbiter Color Imager (MARCI) will acquire daily atmospheric weather images and high resolution surface images and the Pressure Modulated Infrared Radiometer (PMIRR) will allow measurement of the atmospheric temperature, water vapor abundance, and dust concentration. The orbiter will also serve as a data relay satellite for the Mars Polar Lander and other future NASA and international lander missions to Mars. Spacecraft and Subsystems The Mars Climate Orbiter is a box shaped spacecraft about 2.1 m high, 1.6 m wide, and 2 m deep, consisting of stacked propulsion and equipment modules. The total spacecraft launch mass of 629 kg includes 291 kg of propellant. An 11 square meter solar array wing, measuring 5.5 m tip-to-tip, is attached by 2-axis gimbal to one side and a 1.3 m diameter high-gain dish antenna is attached by 2-axis gimbal to a mast at the top of the propulsion module. The MARCI and PMIRR instruments,

as well as a UHF antenna and battery enclosure, are mounted to the bottom of the equipment module. Propulsion is achieved via a 640-N bi-propellant (hydrazine/nitrogen tetroxide) main engine, mounted with the propellant tanks in the propulsion module, and hydrazine thrusters. The orbiter is 3-axis stabilized. Attitude control and maneuvering capability is provided by four 7-Nm thrusters (pitch/yaw) and four 0.3-Nm thrusters (roll) in combination with reaction wheels. Attitude is determined using an inertial measurement unit, a star tracker, and analog Sun sensors with knowledge of 25 mrad and stability of 1.5 mrad/(1 sec) and 3 mrad/(3 sec). Spacecraft power is provided by 3 panels of GaAs/Ge solar cells on the 5.5 meter long single-wing solar array which provide 1000 W of power at Earth and 500 W at Mars. Power is stored in nickel hydride (NiH2) common pressure vessel batteries. Thermal control is achieved through a combination of louvers, MLI, Kapton, paints, radiators and heater circuits. Communications with Earth are in X-band using Cassini Deep Space Transponders and 15 W RF solid state power amplifiers through the 1.3 m high gain antenna for both uplink and downlink, a medium gain transmitting antenna, and a low-gain receiving antenna. A 10 W UHF system is used for 2-way communications with the Mars Polar Lander. A RAD6000 processor is used for on-board command and data handling. Mission Profile Mars Climate Orbiter was launched on a Delta 7425 (a Delta II Lite launch vehicle with four strap-on solid-rocket boosters and a Star 48 (PAM-D) third stage). Launch was at 18:45:51 UT (1:45:51 p.m. EST) on 11 December 1998 from Pad A of Launch Complex 17 at Cape Canaveral Air Station, Florida. After a brief cruise in Earth orbit, the Delta II 3rd stage put the spacecraft into trans-Mars trajectory and about 15 days after launch the largest trajectory correction maneuver (TCM) was executed using the hydrazine thrusters. During cruise to Mars, three additional TCM's using the hydrazine thrusters were performed on 4 March, 25 July, and 15 September 1999. The spacecraft reached Mars and executed a 16 minute 23 second orbit insertion main engine burn on 23 September 1999 at 09:01 UT (5:01 a.m. EDT) Earth received time (ERT, signal travel time from Mars will be 10 minutes 55 seconds). The spacecraft passed behind Mars at 09:06 UT ERT and was to re-emerge and establish radio contact with Earth at 09:27 UT ERT, 10 minutes after the burn was completed. However, contact was never re-established and no signal was ever received from the spacecraft. Findings of the failure review board indicate that a navigation error resulted from some spacecraft commands being sent in English units instead of being converted to metric. This caused the spacecraft to miss its intended 140 - 150 km altitude above Mars during orbit insertion, instead entering the martian atmosphere at about 57 km. The spacecraft would have been destroyed by atmospheric stresses and friction at this low altitude. The burn would have slowed the spacecraft and put it into a 14 hour elliptical (~150 x 21,000 km) capture orbit. The orbiter was to begin aerobraking, using the solar panel to provide resistance and continue until a 90 x 405 km orbit was achieved, nominally on 22 November 1999, with periapsis at 89 N. The hydrazine thrusters would be used to change the orbit to a 2-hour, 421 km near-circular polar science mapping orbit on 1 December 1999. The orbit was to be nearly Sun-synchronous, crossing the daytime equator at about 4:30 p.m. local time. The first phase of the mission was to support the Mars Polar Lander from its landing on Mars on 3 December 1999 to the end of the lander primary mission on 29 February 2000. The orbiter would pass over the lander site 10 times per martian day for 5-6 minutes each time, communicating via the UHF 2-way relay link at 128 kbits/s. Mars science operations and mapping, involving operation of the MARCI and PMIRR, would initiate on 3 March 2000 and continue for one martian year (687 days). At the end of the mapping mission on 15 January 2002, the orbiter was to be placed in a stable orbit and function as a UHF relay for the Mars 2001 mission. The Mars Surveyor '98 program spacecraft development cost 193.1 million dollars. Launch costs are estimated at 91.7 million dollars and mission operations at 42.8 million dollars. The Mars Climate Orbiter is part of NASA's 10-year Mars Surveyor Program, which will feature launches every 26 months when the Earth and Mars are favorably aligned.




Description

Mightysat 1 was an American minisatellite that was ejectedfrom STS 88 on 12 December 1998. It carried equipment forfive advanced technology demonstrations/tests: anew/improved Advanced Composition (spacecraft) Structure, anew solar cell with Gallium Indium Phosphide layer on aGallium Arsenide layer, a "MAPLE" experiment to testadvanced microelectronic packaging, a "SMARD" payload toenable/test low-shock ejection devices, and a "MPID" packageto provide indications of natural and man-made space debris.For further details see:

http://sspp.gsfc.nasa.gov/hh/hh.html

Mightysat 1

NSSDC ID: 1998-069C

Alternate Names

25551

Facts in Brief

Launch Date: 1998-12-15LaunchVehicle: ShuttleLaunch Site: CapeCanaveral, United StatesMass: 320.0 kg

Funding Agency

Unknown (United States)

Discipline

Engineering


Launch/Orbitalinformation for Mightysat1

Experiments on Mightysat1

Data collections fromMightysat 1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://sspp.gsfc.nasa.gov/hh/hh.html




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

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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Mightysat 1 (1998-069C)











http://www.usa.gov/








Description

Molniya 1/91 was a first-generation Russian communicationssatellite (COMSAT) orbited to test and perfect a system ofradio communications 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 1/91, 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 1/91 remained relatively stationary with respect to theearth below for nearly 8 of every 12 hr. By placing three ofmore 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 1-91

NSSDC ID: 1998-054A

Alternate Names

25485

Facts in Brief


Funding Agency

Unknown (Russia)

Discipline

Communications


Launch/Orbitalinformation for Molniya 1-91

Experiments on Molniya 1-91

Data collections fromMolniya 1-91



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Molniya 1-91


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Molniya 1-91


mailto:[email protected]?Subject=NMC Comment/Question: Molniya 1-91 (1998-054A)











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 3-49

NSSDC ID: 1998-040A

Alternate Names

25379

Facts in Brief


Funding Agency

Unknown (Russia)

Discipline

Communications


Launch/Orbitalinformation for Molniya 3-49

Experiments on Molniya 3-49

Data collections fromMolniya 3-49



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Nadezhda 5 is a Russian navigational (search/rescue)spacecraft in the Tsikada system. It is part of the Russian fleetof "Kospas-Sarsat System" to search for ships and aircraft indistress, and to enable rescue missions.

Nadezhda 5

NSSDC ID: 1998-072A

Alternate Names

25567

Facts in Brief

Launch Date: 1998-12-10LaunchVehicle: CosmosLaunch Site: Plesetsk,RussiaMass: 825.0 kg

Funding Agency

Unknown (Russia)

Discipline



Launch/Orbitalinformation for Nadezhda5

Telecommunicationsinformation for Nadezhda5

Experiments on Nadezhda5

Data collections fromNadezhda 5



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data










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

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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Nadezhda 5 (1998-072A)











http://www.usa.gov/







Description

The Egyptian Satellite Company's first satellite of the firstgeneration, Nilesat-101 will be operated in a geostationaryorbit with a payload of 12 operating transponders optimized forDigital Multimedia DTH applications. It was positioned at 7degrees W and transmitted at 105 W. Its expected life time is15 years.

Nilesat 101

NSSDC ID: 1998-024A

Alternate Names

25311

Facts in Brief

Launch Date: 1998-04-28Launch Vehicle: Ariane4Launch Site: Kourou,French GuianaMass: 795.0 kgNominalPower: 105.0 W

Funding Agency

Egypt Satellite Company(Arab Republic of Egypt)

Discipline

Communications


Launch/Orbitalinformation for Nilesat101

Experiments on Nilesat101

Data collections fromNilesat 101



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Nilesat 101

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Nilesat 101

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Nilesat 101

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Nilesat 101

mailto:[email protected]?Subject=NMC Comment/Question: Nilesat 101 (1998-024A)











http://www.usa.gov/








Description

NOAA 15, also known as NOAA-K before launch, was anoperational, polar orbiting, meteorological satellite operated bythe National Oceanic and Atmospheric Administration (NOAA).It was the latest in the Advanced TIROS-N (ATN) series andthe design was based on the Defense Meteorological SatelliteProgram (DMSP). Launched by the Titan II rocket fromVandenberg AFB, NOAA-K replaced the decommissionedNOAA 12 in an afternoon equator-crossing orbit. It providedsupport to environmental monitoring by complementing theNOAA/NESS geostationary meteorological satellite program(GOES). Instruments were flown for imaging andmeasurement of the Earth's atmosphere, its surface, and cloudcover, including Earth radiation, atmospheric ozone, aerosoldistribution, sea surface temperature, vertical temperature andwater profiles in the troposphere and stratosphere;measurement of proton and electron flux at orbit altitude, andremote platform data collection, and for SARSAT. Theyincluded: (1) an improved six-channel Advanced Very HighResolution Radiometer/3 (AVHRR/3); (2) an improved HighResolution Infrared Radiation Sounder (HIRS/3); (3) theSearch and Rescue Satellite Aided Tracking System (S&R),which consists of the Search and Rescue Repeater (SARR)and the Search and Rescue Processor (SARP-2); (4) theFrench/CNES-provided improved ARGOS Data CollectionSystem (DCS-2); and (5) the Advanced Microwave SoundingUnits (AMSUs), which replaced the previous MSU and SSUinstruments to become the first in the NOAA series to supportdedicated microwave measurements of temperature, moisture,surface and hydrological studies in cloudy regions wherevisible and infrared instruments have decreased capability.Further information can be found at http://poes2.gsfc.nasa.govand http://www2.ncdc.noaa.gov/docs/intro.htm

NOAA 15

NSSDC ID: 1998-030A

Alternate Names

Polar OperationalEnvironmental Satellite

POES 15

Advanced TIROS-N(ATN)

25338

Facts in Brief

Launch Date: 1998-05-13Launch Vehicle: Titan IILaunchSite: Vandenberg AFB,United StatesMass: 1457.0 kgNominalPower: 330.0 W

Funding Agencies

NASA-Office of SpaceScience Applications(United States)

NOAA NationalEnvironmental SatelliteService (United States)

Disciplines

Engineering

Earth Science

Solar Physics

Space Physics


Launch/Orbitalinformation for NOAA 15

PDMP information forNOAA 15

Telecommunicationsinformation for NOAA 15


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data



http://poes2.gsfc.nasa.gov/

















Experiments on NOAA 15

Data collections fromNOAA 15


Personnel


Mr. Harry G. McCain Project Manager NASA Goddard Space Flight Center


http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=NOAA 15

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=NOAA 15

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=NOAA 15

mailto:[email protected]?Subject=NMC Comment/Question: NOAA 15 (1998-030A)



http://www.usa.gov/








Description

Efforts to put the Nozomi spacecraft into martian orbit havebeen abandoned. An attempt to fire thrusters to orient the craftfor a Mars orbit insertion burn failed on December 9. Thesmaller thrusters were successfully fired and Nozomi flew pastMars at a distance of 1000 km on 14 December and went intoa heliocentric orbit with a period of roughly two years.

Nozomi (Japanese for Hope and known before launch asPlanet-B) was planned as a Mars orbiting aeronomy missiondesigned to study the martian upper atmosphere and itsinteraction with the solar wind and to develop technologies foruse in future planetary missions. Specifically, instruments onthe spacecraft were to measure the structure, composition anddynamics of the ionosphere, aeronomy effects of the solarwind, the escape of atmospheric constituents, the intrinsicmagnetic field, the penetration of the solar-wind magnetic field,the structure of the magnetosphere, and dust in the upperatmosphere and in orbit around Mars. The mission would havealso returned images of Mars' surface.

Spacecraft and SubsystemsThe Nozomi orbiter is a 0.58 meter high, 1.6 meter squareprism with truncated corners. Extending out from two oppositesides are solar panel wings containing silicon solar cells whichprovide power to the spacecraft directly or via Ni-MH (nickelmetal hydride) batteries. On the top surface is a dish antenna,and a propulsion unit protrudes from the bottom. A five meterdeployable mast and a 1 meter boom extend from the sides,along with two pairs of thin wire antennas which measure 50 mtip to tip. Other instruments are also arranged along the sidesof the spacecraft. Spacecraft communications are via X-bandat 8410.93 MHz and S-band at 2293.89 MHz. The 14instruments carried on Nozomi are an imaging camera, neutralmass spectrometer, dust counter, thermal plasma analyzer,magnetometer, electron and ion spectrum analyzers, ion massspectrograph, high energy particles experiment, VUV imagingspectrometer, sounder and plasma wave detector, LF waveanalyzer, electron temperature probe, and a UV scanner. Thetotal mass budgeted for the science instruments is 33 kg.Radio science experiments will also be possible using theexisting radio equipment and an ultrastable oscillator. The totalmass of Nozomi at launch including 282 kg of propellant was540 kg.

Mission ProfileAfter launch on an M-V-3 launch vehicle Nozomi was put intoan elliptical geocentric parking orbit with a perigee of 340 kmand an apogee of 400,000 km. The spacecraft used a lunarswingby on 24 September and another on 18 December, 1998

Nozomi

NSSDC ID: 1998-041A

Alternate Names

Planet-B

25383

Facts in Brief

Launch Date: 1998-07-03Launch Vehicle: M-5Launch Site: UchinouraSpace Center, JapanMass: 258.0 kg

Funding Agency

Institute of Space andAeronautical Science, Uof Tokyo (Japan)

Disciplines

Planetary Science

Space Physics


Launch/Orbitalinformation for Nozomi

PDMP information forNozomi

Telecommunicationsinformation for Nozomi

Experiments on Nozomi

Data collections fromNozomi



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


Nozomi








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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Nozomi (1998-041A)

mailto:[email protected]?Subject=NMC Comment/Question: Nozomi (1998-041A)









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



to increase the apogee of its orbit. It swung by Earth on 20December 1998 at a perigee of about 1000 km. Thegravitational assist from the swingby coupled with a 7 minuteburn of the bipropellant engine put Nozomi into an escapetrajectory towards Mars. It was scheduled to arrive at Mars on11 October 1999 at 7:45:14 UT, but a malfunctioning valveduring the Earth swingby resulted in a loss of fuel and left thespacecraft with insufficient acceleration to reach its plannedtrajectory. Two course correction burns on 21 December usedmore propellant than planned, leaving the spacecraft short offuel.

The new plan was for Nozomi to remain in heliocentric orbit foran additional four years, including two Earth flybys inDecember 2002 and June 2003, and encounter Mars at aslower relative velocity in December 2003. On 21 April 2002 asNozomi was approaching Earth for the gravity assistmaneuver, powerful solar flares damaged the spacecraft'sonboard communications and power systems. An electricalshort was caused in a power cell used to control the attitudecontrol heating system which allowed the hydrazine fuel tofreeze. The fuel thawed out as the craft approached Earth andmaneuvers to put the craft on the correct trajectory for its Earthflyby were successful. Another Earth flyby within 11000 kmoccurred on 19 June 2003. The fuel had completely thawedout for this manuever because of the spacecraft's proximity tothe Sun. However, on 9 December 2003, efforts to orient thecraft to prepare it for a 14 December main thruster orbitalinsertion burn failed, and efforts to save the mission wereabandoned. The small thrusters were fired on December 9moving the closest approach distance to 1000 km. Thespacecraft flew by Mars on 14 December 2003 and went into aroughly 2-year heliocentric orbit.

Nozomi was to be inserted into a highly eccentric Mars orbitwith a periapsis 300 km above the surface, an apoapsis of 15Mars radii, and an inclination of 170 degrees with respect tothe ecliptic plane. Shortly after insertion the mast and antennaswere to be deployed. The periapsis would have been loweredto 150 km, the orbital period to about 38.5 hours. Thespacecraft was to be spin stabilized at 7.5 RPM with its spinaxis (and the dish antenna) pointed towards Earth. Theperiapsis portion of the orbit would have allowed in-situmeasurements of the thermosphere and lower exosphere andremote sensing of the lower atmosphere and surface. Themore distant parts of the orbit would be for study of the ionsand neutral gas escaping from Mars and their interactions withthe solar wind. The nominal mission was planned for onemartian year (approximately two Earth years). An extendedmission might have allowed operation of the mission for threeto five years. The spacecraft was also to point its cameras atthe martian moons Phobos and Deimos.

Personnel


Dr. KoichiroTsuruda

MissionManager

Institute of Space andAeronautical Science

[email protected]

Dr. IchiroNakatani

MissionManager

Institute of Space andAeronautical Science

[email protected]

Selected References

Yamamoto, T., and K. Tsuruda, The PLANET-B mission, Earth Planet. Space, 50, No. 3, 175-181, 1998.



Tsuruda, K., et al., PLANET-B mission to Mars - 1998, Adv. Space Res., 17, No. 12, (12)21-(12)29, 1996.

Yoshikawa, M., et al., Summary of the orbit determination of NOZOMI spacecraft for all themission period, Acta Astronaut., 57, No. 2-8, 510-519, 2005.

The first image taken by the Nozomi camera, of the Earth and Moon

Press Release on Nozomi/Planet-B launch and TPA - 3 July 1998U.S. experiments on Nozomi/Planet-B - Press Release, 01 July 1998Article on Nozomi science goals - Planetary SocietyNozomi/Planet-B undergoing final tests - Press Release, 26 November 1997Mars Home PageMars Fact Sheet

Nozomi Home Page (ISAS)Nozomi Description (ISAS)ISAS Home Page


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

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

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

http://nssdc.gsfc.nasa.gov/planetary/image/planet-b_diag.jpg

http://nssdc.gsfc.nasa.gov/planetary/text/planetb_pr_19980703.txt


http://www.planetary.org/gsp-pr-111296-10.html


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

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

http://www.planet-b.isas.ac.jp/index-e.html

http://www.isas.ac.jp/e/enterp/missions/nozomi/cont.html

http://www.isas.ac.jp/

http://www.usa.gov/





Nozomi

DESCRIPCIÓN: Nozomi, también conocida como Planet-B, es una sonda de la Agencia Espacial Japonesa ISAS cuyo objetivo principal es estudiar la interacción entre el viento solar y la atmósfera de Marte, el campo magnético y el polvo en suspension en la atmósfera, así como el desarrollo de tecnologías para su uso en futuras misiones al planeta. La llegada a Marte de esta sonda tuvo que ser aplazada durante 4 años debido a que durante una correción de su trayectoria el 21 de diciembre de 1.998 tras un sobrevuelo de la Tierra, se gastó mucho más combustible del esperado por lo que se optó por dejar a la sonda en una órbita heliocéntrica para poder realizar un par de sobrevuelos más de nuestro planeta y poder llegar a Marte en diciembre del año 2.003. FECHAS PRINCIPALES: - Lanzamiento: 4 de julio de 1.998 - Sobrevuelo lunar 1: 24 de septiembre de 1.998 - Sobrevuelo lunar 2: 18 de diciembre de 1.998 - Sobrevuelo Tierra 1: 20 de diciembre de 1.998 - Sobrevuelo Tierra 2: 30 de diciembre de 2.002 - Sobrevuelo Tierra 3: 20 de junio de 2.003 - Llegada a Marte: diciembre de 2.003

Nuevo recorrido y definitivo

LA NAVE: Tiene forma de prisma con una altura de 60cm. con un ancho de 1.6m. En uno de los extremos soporta una antena de comunicaciones de 1.5m y en el otro extremo un motor de propulsión. Posee dos paneles solares que alimentan unas baterías de Ni-MH. Su peso total es

de unos 540kg de los cuales 282kg. son de combustible. A bordo lleva 14 instrumentos científicos, algunos de ellos fruto de la colaboración con otros paises.

INSTRUMENTOS: Hay 14 instrumentos en la sonda: NMS - Espectrómetro de masas PET - Sonda para la temperatura de los electrones TPA - Analizador termal de plasma de iones PWS - Estudio de la ionosfera LFA - Estudio de ondas de plasma OCLT - Experimentos de radio MIC - Cámara de Imágenes de Marte MDC - Contador de polvo de Marte ISA - Analizador de iones de baja energía ESA - Analizador de electrones de baja energía EIS - Analizador electrones e iones de alta energía XUV - Espectrómetro del UV extremo MGF - Medidor del campo magnético UVS - Espectrómetro ultravioleta IMI - Analizador de masa de iones

ORGANISMOS: Esta misión está desarrollada por la Agencia Espacial Japonesa ISAS . Algunos instrumentos han sido desarrollados en colaboración con la Agencia Espacial Canadiense, la NASA, Francia, Suecia y Alemania.




Description

ORBCOMM FM-3 was part of a commercial venture to provideglobal messaging services using a constellation of 26 low-Earth orbiting satellites. The planned system is designed tohandle up to 5 million messages from users utilizing small,portable terminals to transmit and receive messages directly tothe satellites. The first 2 satellites of the constellation (95-017A+ B) experienced communication problems after launch, butwere recovered and placed into operational status. Thenominal 26 satellite constellation will be deployed by 1997, withthe potential for an additional 8 satellite plane and 2 more polarorbiters depending on demands for increased coverage. Thevehicles will be controlled from a single control center locatedin Dulles, VA.

The spacecraft was a circular shaped disk. Circular panelshinged from each side after launch to expose solar cells.These panels articulated in 1-axis to track the sun and provide160W. Deployed spacecraft measured 3.6 m from end to endwith 2.3 m span across the circular disks. VHF telemetry wasat 57.6 kbps. The spacecraft contained an on-board GPSnavigation and timing system, and 14 volt power system.Gravity gradient stabilization provided 4 degs control withmagnetic torques for damping cold gas (nitrogen) propulsionsystem.

The spacecraft carried 17 data processors and 7 antennas andwas designed to handle 50,000 messages per hour. The longboom was a 2.6 meter VHF/UHF gateway antenna. Receive:2400 bps at 148 - 149.9 MHz. Transmit: 4800 bps at 137 - 138MHz and 400.05 to 400.15 MHz. The system used X.400(CCITT 1988) addressing. Message size was 6 to 250 bytestypical (no maximum).

Orbcomm FM-03

NSSDC ID: 1998-007B

Alternate Names

Orbcomm FM-3

25158

Facts in Brief

Launch Date: 1998-02-10LaunchVehicle: TaurusLaunchSite: Vandenberg AFB,United StatesMass: 41.0 kgNominalPower: 160.0 W

Funding Agency

ORBCOMM (UnitedStates)

Discipline

Communications


Launch/Orbitalinformation for OrbcommFM-03

Experiments on OrbcommFM-03

Data collections fromOrbcomm FM-03



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Orbcomm FM-03


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Orbcomm FM-03


mailto:[email protected]?Subject=NMC Comment/Question: Orbcomm FM-03 (1998-007B)















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

http://www.usa.gov/






Description

ORBCOMM FM-4 was part of a commercial venture to provideglobal messaging services using a constellation of 26 low-Earth orbiting satellites. The planned system is designed tohandle up to 5 million messages from users utilizing small,portable terminals to transmit and receive messages directly tothe satellites. The first 2 satellites of the constellation (95-017A+ B) experienced communication problems after launch, butwere recovered and placed into operational status. Thenominal 26 satellite constellation will be deployed by 1997, withthe potential for an additional 8 satellite plane and 2 more polarorbiters depending on demands for increased coverage. Thevehicles will be controlled from a single control center locatedin Dulles, VA.



Orbcomm FM-04

NSSDC ID: 1998-007C

Alternate Names

Orbcomm FM-4

25159

Facts in Brief

Launch Date: 1998-02-10LaunchVehicle: TaurusLaunchSite: Vandenberg AFB,United StatesMass: 41.0 kgNominalPower: 160.0 W

Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data











mailto:[email protected]?Subject=NMC Comment/Question: Orbcomm FM-04 (1998-007C)
















Description

ORBCOMM FM-13 was part of a commercial venture toprovide global messaging services using a constellation of 26low-Earth orbiting satellites. The planned system is designedto handle up to 5 million messages from users utilizing small,portable terminals to transmit and receive messages directly tothe satellites. The first 2 satellites of the constellation (95-017A+ B) experienced communication problems after launch, butwere recovered and placed into operational status. Thenominal 26 satellite constellation will be deployed by 1997, withthe potential for an additional 8 satellite plane and 2 more polarorbiters depending on demands for increased coverage. Thevehicles will be controlled from a single control center locatedin Dulles, VA.



Orbcomm FM-13

NSSDC ID: 1998-046A

Alternate Names

25413

Facts in Brief

Launch Date: 1998-08-02LaunchVehicle: Pegasus XLLaunch Site: WallopsIsland, United StatesMass: 41.0 kgNominalPower: 160.0 W

Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data











mailto:[email protected]?Subject=NMC Comment/Question: Orbcomm FM-13 (1998-046A)











http://www.usa.gov/








Description




Orbcomm FM-14

NSSDC ID: 1998-046B

Alternate Names

25414

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description




Orbcomm FM-15

NSSDC ID: 1998-046C

Alternate Names

25415

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description




Orbcomm FM-16

NSSDC ID: 1998-046D

Alternate Names

25416

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data











mailto:[email protected]?Subject=NMC Comment/Question: Orbcomm FM-16 (1998-046D)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1998-046H[23/06/2011 0:06:59]


Description




Orbcomm FM-17

NSSDC ID: 1998-046H

Alternate Names

25420

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1998-046H







mailto:[email protected]?Subject=NMC Comment/Question: Orbcomm FM-17 (1998-046H)











http://www.usa.gov/








Description




Orbcomm FM-18

NSSDC ID: 1998-046G

Alternate Names

25419

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data











mailto:[email protected]?Subject=NMC Comment/Question: Orbcomm FM-18 (1998-046G)











http://www.usa.gov/








Description




Orbcomm FM-19

NSSDC ID: 1998-046F

Alternate Names

25418

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data











mailto:[email protected]?Subject=NMC Comment/Question: Orbcomm FM-19 (1998-046F)











http://www.usa.gov/








Description




Orbcomm FM-20

NSSDC ID: 1998-046E

Alternate Names

25417

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data











mailto:[email protected]?Subject=NMC Comment/Question: Orbcomm FM-20 (1998-046E)











http://www.usa.gov/








Description




Orbcomm FM-21

NSSDC ID: 1998-053A

Alternate Names

25475

Facts in Brief

Launch Date: 1998-09-23LaunchVehicle: PegasusLaunch Site: WallopsIsland, United StatesMass: 41.0 kg

Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description




Orbcomm FM-22

NSSDC ID: 1998-053B

Alternate Names

25476

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description




Orbcomm FM-23

NSSDC ID: 1998-053C

Alternate Names

25477

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description




Orbcomm FM-24

NSSDC ID: 1998-053D

Alternate Names

25478

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description




Orbcomm FM-25

NSSDC ID: 1998-053E

Alternate Names

25479

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description




Orbcomm FM-26

NSSDC ID: 1998-053F

Alternate Names

25480

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description




Orbcomm FM-27

NSSDC ID: 1998-053G

Alternate Names

25481

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1998-053H[23/06/2011 0:12:17]


Description




Orbcomm FM-28

NSSDC ID: 1998-053H

Alternate Names

25482

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

PANAMSAT 6B will provide direct-to-home televisiontransmissions in South America. The satellite carried a 7-kilowatt payload consisting of 32 active Ku-band transponderspowered by a combination of 105-watt and 140-watt travelingwave-tuve amplifiers. It also carried Hughes' xenon ionpropulsion system, 'XIPS". Its solar arrays generated morethan 8 kW of power through the use of dual-junction galliumarsenide solar cells, which provided a significant increase inpower over silicon cells. The satellite was designed to providea minimum of 15 years of service from its geostationaryposition at 43 degrees W.

PANAMSAT 6B

NSSDC ID: 1998-075A

Alternate Names

PAS 6B

Intelsat 6B

IS-6B

25585

Facts in Brief

Launch Date: 1998-12-21Launch Vehicle: Ariane44LLaunch Site: Kourou,French GuianaMass: 2102.0 kgNominalPower: 8000.0 W

Funding Agencies

Pan American Satellite(United States)


Discipline

Communications


Launch/Orbitalinformation forPANAMSAT 6B

Telecommunicationsinformation forPANAMSAT 6B

Experiments onPANAMSAT 6B

Data collections fromPANAMSAT 6B


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data









http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=PANAMSAT 6B

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=PANAMSAT 6B

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=PANAMSAT 6B

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=PANAMSAT 6B













mailto:[email protected]?Subject=NMC Comment/Question: PANAMSAT 6B (1998-075A)



http://www.usa.gov/








Description

PAS 7 (PanAmSat 7) is an American geostationarycommunications spacecraft that was launched by an Ariane44LP rocket from Kourou at 06:31 UT. The 3,838 kg satellitecarries 40 Ku-band and 18 C-band transponders to providevoice and video communications to Europe and West Asia,after parking at 68.5-E longitude.

PANAMSAT 7

NSSDC ID: 1998-052A

Alternate Names

PAS 7

Intelsat 7

IS-7

25473

Facts in Brief

Launch Date: 1998-09-16Launch Vehicle: Ariane44LPLaunch Site: Kourou,French GuianaMass: 3838.0 kg

Funding Agencies



Discipline

Communications


Launch/Orbitalinformation forPANAMSAT 7

Experiments onPANAMSAT 7

Data collections fromPANAMSAT 7



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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


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


mailto:[email protected]?Subject=NMC Comment/Question: PANAMSAT 7 (1998-052A)















http://www.usa.gov/








Description

PANAMSAT 8 was an American geosynchronouscommunications spacecraft. It carries 24 C-band and 24 Ku-band transponders to provide digital television channels afterparking over 166 degrees E longitude. It was based on theSpace Systems/Loral three-axis, body-FS-1300 bus, whosemodular design has proven its worth during some 275 years ofcumulative on-orbit service. Solar arrays and nickel-hydrogenbatteries provided uninterrupted electrical power.

PANAMSAT 8

NSSDC ID: 1998-065A

Alternate Names

PAS 8

IS-8

Intelsat 8

25522

Facts in Brief

Launch Date: 1998-11-04LaunchVehicle: Proton-KLaunch Site: Tyuratam(Baikonur Cosmodrome),KazakhstanMass: 2100.0 kg

Funding Agencies



Discipline

Communications


Launch/Orbitalinformation forPANAMSAT 8

Telecommunicationsinformation forPANAMSAT 8

Experiments onPANAMSAT 8

Data collections fromPANAMSAT 8


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




























http://www.usa.gov/








Description

The Petite Amateur Navy Satellite (PANSAT) was a smallsatellite designed and built by officer students, faculty, andstaff at the Naval Postgraduate School (NPS). The mainobjective was to support the Space Systems and Engineeringand Space Systems Operations curricula by providing a"hands-on" hardware project where exposure to the manyfacets of a space system development and life cycle could beexperienced. PANSAT provided educational training while inorbit through a space-based laboratory for officer students atNPS. PANSAT was launched from the Shuttle into a low-Earthorbit on the STS-95 Discovery mission as part of the thirdInternational Extreme Ultraviolet Hitchhiker (IEH-3) experiment.The spacecraft provided store-and-forward (packet radio)digital communications using direct sequence spread spectrummodulation. PANSAT operated in the amateur radio 70 cmband with center frequency at 436.5 MHz, a bit rate of 9842bits per second and 9 MB of message storage. Amateur radioground stations were able to utilize PANSAT via a bulletin-board type user interface.

PANSAT

NSSDC ID: 1998-064B

Alternate Names

Petite Amateur NavySatellite

OSCAR 34

25520

Facts in Brief

Launch Date: 1998-10-30LaunchVehicle: ShuttleLaunch Site: CapeCanaveral, United States

Funding Agency


Disciplines

Communications



Launch/Orbitalinformation for PANSAT

Experiments on PANSAT

Data collections fromPANSAT



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: PANSAT (1998-064B)
















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-38 was launched from the Baikonur cosmodromeaboard a Soyuz-V rocket. It carried a 900 kg propulsion unit toattach to the Quantum module of Mir, and 1,500 kg of repairtools, replacement parts, food and water. It had to be dockedmanually with Mir after a slight misalignment was noticed whenit was about 15 meters from the space station.

Progress M-38

NSSDC ID: 1998-015A

Alternate Names

25256

Facts in Brief

Launch Date: 1998-03-14Launch Vehicle: SoyuzLaunch Site: Tyuratam(Baikonur Cosmodrome),Kazakhstan

Funding Agency


Discipline

Resupply/Refurbishment/Repair


Launch/Orbitalinformation for ProgressM-38

Experiments on ProgressM-38

Data collections fromProgress M-38



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Progress M-38


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Progress M-38


mailto:[email protected]?Subject=NMC Comment/Question: Progress M-38 (1998-015A)











http://www.usa.gov/








Description


Progress M-39 was launched from the Baikonur cosmodromeaboard a Soyuz-U rocket. It docked with and delivered goodsto the Mir space station at 23:50 UT on May 17, 1998 anddelivered 1,500 kg of fuel and another 1,500 kg of food,equipment and gifts. In late June, Progress M-39 will give ajerk to to Mir to initiate progressively lower orbits, leading to itsdemise in the ocean in December 1999.

Progress M-39

NSSDC ID: 1998-031A

Alternate Names

25340

Facts in Brief


Funding Agency

Unknown (Russia)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Progress M-40 was launched by a Soyuz-U rocket fromBaykonur at 04:15 UT to carry cargo to the Mir station. Itcarried 7,285 kg of cargo including 400 kg of fuel, 2,500 kg offood, water, and scientific/engineering equipment required forthe experiment (Znamia 2.5) to reflect Sun light toward Earth.It docked with Mir on 27 October, 1998.

Progress M-40

NSSDC ID: 1998-062A

Alternate Names

25512

Facts in Brief


Funding Agency


Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

RESURS-O 1N4 is a Russian natural resources sensingsatellite that was launched by a Zenit 2 rocket from Baykonurat 05:45 UT. It will also do ecological and meteorologicalmonitoring.

Resurs-O 1 N4

NSSDC ID: 1998-043A

Alternate Names

25394

Facts in Brief

Launch Date: 1998-07-10Launch Vehicle: Zenit 2Launch Site: Tyuratam(Baikonur Cosmodrome),Kazakhstan

Funding Agency

Unknown (Russia)

Discipline

Earth Science


Launch/Orbitalinformation for Resurs-O1 N4

Experiments on Resurs-O1 N4

Data collections fromResurs-O 1 N4



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Resurs-O 1 N4

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Resurs-O 1 N4

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Resurs-O 1 N4

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Resurs-O 1 N4

mailto:[email protected]?Subject=NMC Comment/Question: Resurs-O 1 N4 (1998-043A)











http://www.usa.gov/








Description

Satellite de Aplicaciones Cientifico-A (SAC-A) was a smallnon-recoverable satellite built by the Argentinean NationalCommission of Space Activities (CoNAE). The satellite will testand characterize the performance of new equipment andtechnologies which may be used in future operational orscientific missions.

The satellite payload included a Differential Global PositioningSystems (DGPS) to provide real-time autonomous attitudemeasurements for the satellite, a CCD camera to performdigital space photography, Argentinean built silicon solar cells,a magnetometer to take scalar measurements of the Earth'smagnetic field, and an Argentinean experiment to trackendangered whale population migrations in the southernhemisphere.

SAC-A

NSSDC ID: 1998-069B

Alternate Names

Satelite de AplicacionesCientificas-A

25550

Facts in Brief


Funding Agency

Unknown (Argentina)

Disciplines

Earth Science

Space Physics


Launch/Orbitalinformation for SAC-A

Experiments on SAC-A

Data collections from SAC-A



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: SAC-A (1998-069B)











http://www.usa.gov/








Description

OHB System and the German Space Agency (DARA) haveundertaken a program of small communications satellitesnamed SAFIR (Satellite for Information Relay). SAFIR 2 waslaunched along with RESURS-O aboard a Zenit rocket fromthe Baikonur cosmodrome. It had a mass of 55 kg in the formof a 0.45-m cube and a gravity-gradient stabilization system.Communications was in the 400 MHz band.

SAFIR 2

NSSDC ID: 1998-043F

Alternate Names

25399

Facts in Brief


Funding Agency

German Space Agency(Federal Republic ofGermany)

Discipline

Communications


Launch/Orbitalinformation for SAFIR 2

Experiments on SAFIR 2

Data collections fromSAFIR 2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: SAFIR 2 (1998-043F)











http://www.usa.gov/








Description

SATMEX 5 was a Mexican communications satellite launchedfrom the Kourou space center in French Guiana aboard anAriane rocket. It offered nearly 8,000 watts of power andcarried 48 transponders, 24 in C-band and 24 in Ku-band. Itwas the fifth satellite Hughes Space and CommunicationsCompany built that used XIPS. It provided improved services,such as business communications, television distribution,educational programming, and others, with high reliability. Thesatellite beams expanded to include the whole Americancontinent, providing services to countries such as Argentina,Brazil, Chile, Colombia, El Salvador, Peru, Venezuela, the US,among others.

SATMEX 5

NSSDC ID: 1998-070A

Alternate Names

25558

Facts in Brief

Launch Date: 1998-12-05Launch Vehicle: Ariane44LLaunch Site: Kourou,French GuianaMass: 1950.0 kg

Funding Agency

Unknown (Mexico)

Discipline

Communications


Launch/Orbitalinformation for SATMEX5

Telecommunicationsinformation for SATMEX5

Experiments on SATMEX 5

Data collections fromSATMEX 5



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data










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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: SATMEX 5 (1998-070A)











http://www.usa.gov/








Description

SCD-2 (Satellite de Coleta de Dados-2), INPE's follow onmission on SCD-1, was launched on a Pegasus-XL rocket. Itssister satellite was to be launched on the first Brazilian VLS butunfortunately failed. The spacecraft was cylindrical in shapeand measured 1.45 m high and 1 m in diameter. It delivered 70W of power. Uplinks were at 401.635MHz and 2033.200MHz,and downlinks were at 2208.0000MHz and 2267.5150MHz. Itwas spin stabilized and carried a reaction wheel experimentand magnetorquers to control the spacecraft spin rate. Itcarried S-band and UHF communications systems. Thespacecraft was employed for data collection from smallstations over the Brazilian territory. In particular it studiedhydrology of the Amazon basin, atmospheric chemistry andwas employed in oceanography and weather forecasting.

SCD 2

NSSDC ID: 1998-060A

Alternate Names

Satelite de Coleta deDados 2

Data Collection Satellite 2

25504

Facts in Brief

Launch Date: 1998-10-22LaunchVehicle: PegasusLaunch Site: CapeCanaveral, United StatesMass: 115.0 kgNominal Power: 70.0 W

Funding Agency

Instituto Nacional dePesquisas Espaciais,Brazil (Brazil)

Disciplines

Communications

Earth Science


Launch/Orbitalinformation for SCD 2

Experiments on SCD 2

Data collections from SCD2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: SCD 2 (1998-060A)














http://www.usa.gov/








Description

SEDSAT 1 (Students for the Exploration and Development ofSpace) is an American mini-spacecraft. It will obtain images ofthe Earth and distribute them through the Internet from theUniversity of Alabama. It will also serve as a relay for amateurradio communications.

SEDSAT 1

NSSDC ID: 1998-061B

Alternate Names

OSCAR 33

25509

Facts in Brief

Launch Date: 1998-10-24Launch Vehicle: DeltaII 7326Launch Site: CapeCanaveral, United StatesMass: 36.0 kg

Funding Agency

Students for theExploration andDevelopment of Space(United States)

Disciplines

Communications

Earth Science


Launch/Orbitalinformation for SEDSAT 1

Telecommunicationsinformation for SEDSAT 1

Experiments on SEDSAT 1

Data collections fromSEDSAT 1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: SEDSAT 1 (1998-061B)














Description

Sinosat 1 (also known as Zhongwei 1) was launched from theXichang space conplex aboard a Long March 3B rocket. It wasa Chinese geosynchronous communications spacecraft thatcarried 24 C-band and 14 Ku-band transponders to providevoice and video communications to the Asia-Pacific regionafter parking at 110.5 deg E.

Sinosat 1

NSSDC ID: 1998-044A

Alternate Names

Zhongwei 1

25404

Facts in Brief

Launch Date: 1998-07-18Launch Vehicle: LongMarch 3BLaunch Site: Xichang,Peoples Republic of ChinaMass: 2820.0 kg

Funding Agency

Unknown (PeoplesRepublic of China)

Discipline

Communications


Launch/Orbitalinformation for Sinosat 1

Experiments on Sinosat 1

Data collections fromSinosat 1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Sinosat 1 (1998-044A)











http://www.usa.gov/








Description

Sirius 3 is a Swedish geosynchronous communicationsspacecraft. The spacecraft will provide voice and videocommunications to Northern Europe and Scandinavia through15 Ku-band 44 watt transponders after parking at about 5degrees E longitude.

The satellite is cylindrical in shape, 2.16 m in diameter and7.76 m in height when deployed. It has two telescopingcylindrical solar panels and antennas that fold for compactnessduring launch. The Sirius 3 antenna has shaped surfaceoctagonal reflectors, approximately 2 m in diameter, with singleoffset feeds. This antenna has three surfaces: one forhorizontally polarized signals, one for vertically polarizedsignals, and one for on-station tracking and command.

Sirius 3 carries 15 Ku-band transponders powered by 44 watttraveling-wave tube amplifiers (TWTAs). The spacecraft usesgallium arsenide solar cells to generate a minimum of 1400watts of spacecraft power at end of life and relies on nickel-hydrogen batteries for power through eclipses. The plannedservice life is 12 years.

Sirius 3 is used primarily for direct-to-home and cabletelevision services as well as data distribution in Scandinaviaand neighboring countries, but is also capable of providingtelevision distribution and high-speed internet data toGreenland. The Ku-band effective isotropic radiated power(EIRP) will be minimum 54 dBW in the primary zone.

Sirius 3

NSSDC ID: 1998-056B

Alternate Names

25492

Facts in Brief

Launch Date: 1998-10-05Launch Vehicle: Ariane44LLaunch Site: Kourou,French GuianaMass: 815.0 kgNominalPower: 1400.0 W

Funding Agency

Nordic Satellite Company(Sweden)

Discipline

Communications


Launch/Orbitalinformation for Sirius 3

Telecommunicationsinformation for Sirius 3

Experiments on Sirius 3

Data collections from Sirius3



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data








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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Sirius 3 (1998-056B)











http://www.usa.gov/








Description

Skynet 4D was a British military geosynchronouscommunications satellite launched by a Delta 2 rocket fromCape Canaveral. The spacecraft was the first in the new seriesthat is expected to replace the aging 1988-era series. Theparking longitude was expected to be in western Europe.

Skynet 4D

NSSDC ID: 1998-002A

Alternate Names

25134

Facts in Brief

Launch Date: 1998-01-09Launch Vehicle: DeltaII 7925Launch Site: CapeCanaveral, United StatesMass: 1150.0 kg

Funding Agency

Ministry of Defence, UK(United Kingdom)

Discipline

Communications


Launch/Orbitalinformation for Skynet 4D

Experiments on Skynet 4D

Data collections fromSkynet 4D



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Skynet 4D

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Skynet 4D

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Skynet 4D

mailto:[email protected]?Subject=NMC Comment/Question: Skynet 4D (1998-002A)











http://www.usa.gov/








Description

The Student Nitric Oxide Explorer (SNOE) project was the firstsatellite to be launched in NASA's Student ExplorerDemonstration Initiative (STEDI) program. STEDI, managedfor NASA by USRA, is a pilot program to demonstrate thathigh-quality space science can be carried out with small, low-cost (<$4.4 Million) free-flying satellites on a time scale of twoyears from go-ahead to launch. The scientific objectives of theStudent Nitric Oxide Explorer were a detailed study ofvariations in nitric oxide (NO) in the Earth thermosphere. NO isan important minor constituent that strongly affects the ioncomposition of the ionosphere and the thermal structure of thethermosphere. Specific objectives were to: (1) determine howvariations in the solar soft X-radiation produce changes in thedensity of nitric oxide in the lower thermosphere; and, (2)determine how auroral activity produces increased nitric oxidein the polar regions. The spacecraft is a compact hexagonalstructure, approximately 0.9 m high and 1 m across it widestdimension, weighing a maximum of 100 kg. It was launchedinto a sun-synchronous circular orbit at 530-580 km altitudeand 97.7 degrees inclination. It span at 5 rpm with the spinaxis normal to the orbit plane and carried three instruments: anultraviolet spectrometer to measure nitric oxide altitudeprofiles, a two-channel auroral photometer to measure auroralemissions beneath the spacecraft, and a five-channel solarsoft X-ray photometer. SNOE also carried a GPS receiver foraccurate orbit and attitude determination.

The SNOE spacecraft and its instrument complement weredesigned, built, and operated entirely at the Laboratory forAtmospheric and Space Physics (LASP) of the University ofColorado at Boulder.

SNOE re-entered the atmosphere on 12/13/03 at 09:34Z +/- 6minutes, descending over 2.9 deg S, 273.8 deg E, on orbit32248, after 5 years and 290 days.

SNOE

NSSDC ID: 1998-012A

Alternate Names

Explorer 72

STEDI-SNOE

Student Nitric OxideExplorer

UNEX/SNOE

25233

Facts in Brief

Launch Date: 1998-02-26LaunchVehicle: Pegasus XLLaunchSite: Vandenberg AFB,United StatesMass: 120.0 kgNominal Power: 37.0 W

Funding Agency


Disciplines

Solar Physics

Space Physics


Launch/Orbitalinformation for SNOE

Experiments on SNOE

Data collections fromSNOE

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


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: SNOE (1998-012A)

mailto:[email protected]?Subject=NMC Comment/Question: SNOE (1998-012A)











Personnel


Dr. CharlesA. Barth

Mission PrincipalInvestigator

University of Colorado [email protected]

Dr. Scott M.Bailey

Deputy MissionPrincipal Investigator

University of Alaska [email protected]

Other SNOE Data/Information at NSSDCSNOE data

Other Sources of SNOE Data/InformationSNOE Project


http://nssdcftp.gsfc.nasa.gov/spacecraft_data/snoe/

http://lasp.colorado.edu/snoe/

http://www.usa.gov/








Description

Soyuz TM-27 was a Russian transportation spacecraftlaunched from the Baikonur cosmodrome to dock with the MIRspace station. The 7,000 kg spacecraft carried threecosmonauts and food supplies to MIR.

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 27

NSSDC ID: 1998-004A

Alternate Names

25146

Facts in Brief

Launch Date: 1998-01-29Launch Vehicle: SoyuzLaunch Site: Tyuratam(Baikonur Cosmodrome),KazakhstanMass: 7000.0 kg

Funding Agency

Unknown (Russia)

Discipline

Human Crew


Launch/Orbitalinformation for Soyuz-TM27

Experiments on Soyuz-TM27

Data collections fromSoyuz-TM 27



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Soyuz-TM 27


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Soyuz-TM 27


mailto:[email protected]?Subject=NMC Comment/Question: Soyuz-TM 27 (1998-004A)











http://www.usa.gov/





Soyuz TM-27

Russia

Launch, orbit and landing data Launch date: 29.01.1998 Launch time: 16:33 UT Launch site: Baikonur Launch pad: 1 Altitude: 193,46 - 237,76 km Inclination: 51,62° Landing date: 25.08.1998 Landing time: 05:24 UT Landing site: 47° 57' 07'' N, 69° 37' 50'' E

© CNES/ Christian

BARDOU, 1997

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

s

1

Musabayev

Talgat Amangeldyyevich Commander 2 207d 12h

51m 3284

2

Budarin Nikolai Mikhailovich Flight Engineer 2 207d 12h 51m

3284

3

Eyharts Léopold Research Cosmonaut 1 20d 16h

37m 325

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Crew seating arrangement Launch

1 Musabayev 2 Budarin 3 Eyharts

Landing 1 Musabayev 2 Budarin 3 Baturin

Double Crew No. Surname Given name Job

1 Afanasiyev Viktor Mikhailovich Commander

2 Treshchyov

Sergei Yevgeniyevich Flight Engineer

3 Haigneré Jean-Pierre Research

Cosmonaut

Flight Launch from Baikonur; landing 40 km southeast of Dzheskasgan. Docking on MIR spacestation; Musabayev and Budarin together with astronaut Andy Thomas became the 25th resident crew of MIR; French mission "PEGASE"; common scientific experiments; a planned EVA of Musabayev and Budarin at 03.03.1998 was cancelled, because the hatch could not be opened and all wrenches broke. Later five EVA's by both cosmonauts on 01.04.1998 (6h 40m), 06.04.1998 (4h 23m), 11.04.1998 (6h 25m), 17.04.1998 (6h 32m), 22.04.1998 (6h 21m), repairing the damaged Spektr solar panel and installing the new VDU station orientation engine into the Sofora boom.

Note Eyharts landed on 19.02.1998 at 09:10 UT with Soyuz TM-26-spacecraft.






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Description

Soyuz-TM 28 is a Russian cosmonaut-transporting vehicle thatwas launched to carry three cosmonauts to the MIR station;two of them will stay in Mir for 201 days. It was launched by aSoyuz-U rocket from Baykonur at 09:43 UT. It was dockedmanually with Mir at 10:56 UT on 15 August 1998, afterautomatically moving within 10 meters from the station.

Soyuz-TM 28

NSSDC ID: 1998-047A

Alternate Names

25429

Facts in Brief


Funding Agency

Unknown (Russia)

Discipline

Human Crew


Launch/Orbitalinformation for Soyuz-TM28

Experiments on Soyuz-TM28

Data collections fromSoyuz-TM 28



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/





Soyuz TM-28

Russia

Launch, orbit and landing data

Launch date: 13.08.1998 Launch time: 09:43 UT Launch site: Baikonur Launch pad: 1 Altitude: 190 - 237,7 km Inclination: 50,64° Landing time: 28.02.1999 Landing date: 02:14 UT Landing site: 50° 42' N, 67° 12' E

Crew No. Surnam

e Given name Job Flight No. Duration Orbits

1 Padalka

Gennadi Ivanovich Commander 1 198d 16h 31m 3144

2 Avdeyev

Sergei Vasiliyevich Flight Engineer 3 379d 14h 52m 6007

3 Baturin Yuri Mikhailovich Research

Cosmonaut 1 11d 19h 41m 186

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Crew seating arrangement

Launch 1 Padalka 2 Avdeyev 3 Baturin

Landing 1 Padalka 2 Bella 3

Double Crew

No. Surname Given name Job

1 Zalyotin Sergei Viktorovich Commander

2 Kaleri Aleksandr Yuriyevich Flight Engineer

3 Kotov Oleg Valeriyevich Research Cosmonaut

Flight Launch from Baikonur; landing of Padalka and Bella (launched with Soyuz TM-29) 59 km northeast of Arkalyk. Docking on MIR space station; Padalka and Avdeyev became 26th resident crew of MIR; Baturin, the first Russian politician in space, performed an inspection-mission; Padalka and Avdeyev performed an EVA on 15.09.1998 (30m) into the module Spektr (new cabels connected for solar structures).

Note Baturin landed on 25.08.1998 (5:24 UT with Soyuz TM-27). Avdeyev returned to Earth on 28.08.1999 (0:41 UT) with Soyuz TM-29-spacecraft.





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Photos / Drawings

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Description

Spartan 201-05 is an American solar observatory that wasreleased and recaptured by the shuttle (STS 95). It made 43hours of solar corona monitoring with its white light (WLC) andultraviolet (UVCS) cameras.

The images may be seen via the URL:http://thalia.gsfc.nasa.gov/~gibson/SPARTAN/spartan.html

The data will assist in the recalibration of the SOHO spacecraftinstruments.

Spartan 201-05 was retrieved by STS 95 at 08:48 UT on 03November 1998.

Spartan 201-05

NSSDC ID: 1998-064C

Alternate Names

25521

Facts in Brief


Funding Agency


Discipline

Solar Physics


Launch/Orbitalinformation for Spartan201-05

Telecommunicationsinformation for Spartan201-05

Experiments on Spartan201-05

Data collections fromSpartan 201-05



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://thalia.gsfc.nasa.gov/~gibson/SPARTAN/spartan.html







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Spartan 201-05

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Spartan 201-05

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Spartan 201-05

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Spartan 201-05

mailto:[email protected]?Subject=NMC Comment/Question: Spartan 201-05 (1998-064C)











http://www.usa.gov/








Description

SPOT 4 (Systeme Probatoire d'Observation de la Terre) was aFrench remote sensing/reconnoissance spacecraft launchedfrom the Kourou space center aboard an Ariane 40 rocket. Itcarried multispectral cameras to monitor vegitation at 1 kmresolution and other cameras to provide 10 to 20 meterresolution pictures. Also on board was a DORIS package toascertain the spacecraft coordinates, and a SILEX instrumentto enable laser transmission of the data to an Artemis satellite.

SPOT 4

NSSDC ID: 1998-017A

Alternate Names

25260

Facts in Brief


Funding Agency

Centre National d'EtudesSpatiales (France)

Discipline

Earth Science


Launch/Orbitalinformation for SPOT 4

Experiments on SPOT 4

Data collections fromSPOT 4



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=SPOT 4

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=SPOT 4

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=SPOT 4

mailto:[email protected]?Subject=NMC Comment/Question: SPOT 4 (1998-017A)











http://www.usa.gov/








Description

ST 1 is a Singapore/Taiwan (ROC) geosynchronouscommunications spacecraft that was launched by an Ariane44P rocket from Kourou at 11:07 UT. The 3,200 kg satellitecarries 16 Ku-band and 14 C-band transponders to providevoice and video communications to the Pacific rim and East-Asian countries, after parking at 88-E longitude.

ST 1

NSSDC ID: 1998-049A

Alternate Names

25460

Facts in Brief

Launch Date: 1998-08-25Launch Vehicle: Ariane44PLaunch Site: Kourou,French GuianaMass: 3200.0 kg

Discipline

Communications


Launch/Orbitalinformation for ST 1

Experiments on ST 1

Data collections from ST 1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

mailto:[email protected]?Subject=NMC Comment/Question: ST 1 (1998-049A)











http://www.usa.gov/








Description

The STEX (Space Technology Experiments) satellite carried29 new technologies intended to result in lower cost andhigher performance spacecraft for future missions. Among thetechnologies were Russian-derived Xenon Hall-effect electricthrusters capable of delivering 40 mN of thrust, a 51 Gbit solid-state data recorder, and high-density NiH batteries designed tolast longer and provide more energy with less weight. ATEx(Advanced Tether Experiment), a 6 km tether with TiPSheritage, was to be deployed as a separate sub-satellite.Frangibolts were used on the mission for shocklessdeployment of the spacecraft and tether. Experimental solarpanels with high-efficiency solar cells were also carried. Theplanned lifetime of STEX was two years.

The spacecraft was comprised of a body shell and two trackingsolar panels. A blowdown liquid propulsion system wascarried. The spacecraft was three-axis stablized. A lightweightprecision star tracker was used to determine satellite pointing.

On January 16, 1999, ATEx was deployed, but failed. It wasdeployed but its two masses separated only by 22 m. It is nowtracked as a separate object (USA 141, 1998-055C).

STEX

NSSDC ID: 1998-055A

Alternate Names

Space TechnologyExperiments

USA 140

25489

Facts in Brief


Funding Agency

National ReconnaissanceOffice (United States)

Disciplines

Engineering



Launch/Orbitalinformation for STEX

Telecommunicationsinformation for STEX

Experiments on STEX

Data collections fromSTEX



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


STEX






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: STEX (1998-055A)










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



Office.



http://www.usa.gov/








Description

STS 88 is an American shuttle spacecraft. It carried Unity (alsoknown as Node 1) module for the International Space Station(ISS), two minisatellites (SAC-A and Mightysat 1) for a laterday ejection, and some other experimental items of interest toK-14 level students. The shuttle crew (of six) hoisted the Unitymodule over the open cargo bay on 05 December andpositioned it perpendicular to the shuttle. Thrusters were thenfired to black flip the shuttle and reach ISS-Zarya within 3 mwhen the robotic arm of the shuttle captured Zarya (that wasbelow STS) on 06 December. Zarya's and Unity's ports werethen aligned with a separation of only a few centimeters whenthe shuttle's thrusters fired again to dovetail them tight.

After several days of extravehicular activities (EVAs) to securethe joints, and interconnect the power lines and computer linksand, after raising the shuttle's altitude by about 10 km, thejoined modules were released from the shuttle for free flight on13 December 1998.

STS 88

NSSDC ID: 1998-069A

Alternate Names

25549

Facts in Brief


Funding Agency

NASA-Office of SpaceFlight (United States)

Discipline

Human Crew


Launch/Orbitalinformation for STS 88

Telecommunicationsinformation for STS 88

Experiments on STS 88

Data collections from STS88



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data








http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=STS 88

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=STS 88


mailto:[email protected]?Subject=NMC Comment/Question: STS 88 (1998-069A)











http://www.usa.gov/





STS-88 Endeavour (13)

USA


Launch date: 04.12.1998 Launch time: 08:35 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-A Altitude: 388 - 401 km Inclination: 51,6° Landing date: 15.12.1998 Landing time: 13:53 UT Landing site: Cape Canaveral (KSC)

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alternate crew photo

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Crew

No. Surname Given name Job Flight No. Duration Orbits

1 Cabana Robert Donald CDR 4 11d 19h 18m 185

2 Sturckow Frederick Wilford "Rick" PLT 1 11d 19h 18m 185

3 Ross Jerry Lynn MSP 6 11d 19h 18m 185

4 Currie Nancy Jane Sherlock MSP 3 11d 19h 18m 185

5 Newman James Hansen MSP 3 11d 19h 18m 185

6 Krikalyov Sergei Konstantinovich MSP 4 11d 19h 18m 185


Launch 1 Cabana 2 Sturckow 3 Ross 4 Currie 5 Newman 6 Krikalyov

Landing 1 Cabana 2 Sturckow 3 Newman 4 Currie 5 Ross 6 Krikalyov

Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC). First USA Space Station Assembly Flight (ISS-01-2A); docking of U.S.-built Node (Unity) on the Russian-built FGB (Zarya); Ross and Newman performed then two EVA's on 7.12.1998 (7h 21m) and 9.12.1998 (7h 2m) to connect cables between the Node and the FGB; then Cabana and Krikalyov turned over for the first time into the ISS; later third EVA by Ross and Newman on 12.12.1998 (6h 59m) to check the connected cables und to test the SAFER. Later the crew deployed the small argentinian-built test-satellite SAC-A (Satelite de

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Aplicaciones/Cientifico).

Photos / Drawings

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Description

STS 89 was a US Shuttle launch intended to reach and dockwith the MIR space station to deliver a new Americanastronaut for endurance and experience in MIR, and to bringback an earlier astronaut after his four months of stay. It alsocarried 1,500 kg of supplies and docked at 20:14 UT onJanuary 24. STS 89 also carried resources for somemicrogravity experiments with names like Closed EquilibratedBiological Aquatic System (CEBAS), Microgravity PlantNutrient Experiment (MPNE), and Interferometer ProteinCrystal Growth (IPCG). It unlocked from MIR at 16:56 UT onJanuary 29. More information can be found at:

http://shuttle.nasa.gov/sts-89/orbit/payloads

STS 89

NSSDC ID: 1998-003A

Alternate Names

25143

Facts in Brief


Funding Agency


Disciplines

Human Crew

Microgravity







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://shuttle.nasa.gov/sts-89/orbit/payloads

















http://www.usa.gov/





STS-89 Endeavour (12)

USA


Crew


Launch date: 23.01.1998 Launch time: 02:48 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-A Altitude: 277 km Inclination: 28,45° Landing date: 31.01.1998 Landing time: 22:36 UT Landing site: Cape Canaveral (KSC)




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1 Wilcutt Terrence Wade CDR 3 8d 19h 48m 138

2 Edwards Joe Frank, Jr. PLT 1 8d 19h 48m 138

3 Reilly James Francis II "J.R." MSP 1 8d 19h 48m 138

4 Anderson Michael Philip MSP 1 8d 19h 48m 138

5 Dunbar Bonnie Jeanne MSP 5 8d 19h 48m 138

6 Sharipov Salizhan Shakirovich MSP 1 8d 19h 48m 138

7 Thomas Andrew Sydney Withiel MSP 2 140d 15h 13m 2213

Crew seating arrangement Launch

1 Wilcutt 2 Edwards 3 Reilly 4 Anderson 5 Dunbar 6 Sharipov 7 Thomas

Landing 1 Wilcutt 2 Edwards 3 Dunbar 4 Anderson 5 Reilly 6 Sharipov 7 Wolf

Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC). 8th MIR-Docking-Mission; supplies and equipment were brought to MIR (i.e. two computers, a cooling system and a compressor); common flight of 4d 20h 43m (24. - 29.01.1998) with the 24. MIR resident crew; Thomas replaced Dave Wolf as a member of MIR resident crew.

Note Thomas returned to Earth on 12.06.1998 at 18:01 UT with STS-91.

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Photos / Drawings







Description

The primary mission of STS 90 was to conduct acomprehensive list of neurobiological experiments andobservations on a number of species: seven humans, 18pregnant mice, 152 rats (including 12 females with prenatallitters of eight each, and two with litters of seven each), 229swordtail fish, 60 snails, 75 snail pawn packs, 824 crickets,and 680 cricket eggs. According to a principal investigator (ofrat research), "the findings from the microgravity experimentsmay help gain some more insight into the best way to treatneurologic patients with Parkinson's disease, and balancedisorders." According to the project scientist of the mission, "itis important to note that the sensory and motor developmentevents and processes under study in the various species onNeurolab are essentially the same as those that occur inhumans, although with a different time frame."

STS 90

NSSDC ID: 1998-022A

Alternate Names

25297

Facts in Brief


Funding Agency


Disciplines

Human Crew

Life Science








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/





STS-90 Columbia (25)

USA


Launch date: 17.04.1998 Launch time: 18:19 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-B Altitude: 278 km Inclination: 39,01° Landing date: 03.05.1998 Landing time: 16:09 UT Landing site: Cape Canaveral (KSC)

h

a

Crew


1 Searfoss Richard Alan CDR 3 15d 21h 50m 256

2 Altman Scott Douglas "Scooter" PLT 1 15d 21h 50m 256

3 Linnehan Richard Michael MSP 2 15d 21h 50m 256

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4 Hire Kathryn Patricia "Kay" MSP 1 15d 21h 50m 256

5 Williams Daffyd Rhys "Dave" MSP 1 15d 21h 50m 256

6 Buckey Jay Clark, Jr. PSP 1 15d 21h 50m 256

7 Pawelczyk James Anthony "Jim" PSP 1 15d 21h 50m 256


Launch 1 Searfoss 2 Altman 3 Williams 4 Hire 5 Linnehan 6 Buckey 7 Pawelczyk

Landing 1 Searfoss 2 Altman 3 Linnehan 4 Hire 5 Williams 6 Buckey 7 Pawelczyk

Backup Crew

No. Surname Given name Job

6 Dunlap Alexander

William PSP

7 Mukai Chiaki PSP

hi res version (1,09 MB)

Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC). Final mission of Spacelab; mission Neurolab 31 experiments for researching the effects of microgravity on the nervous system (e.g. with rats); first operation in space on living animals.

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Photos / Drawings


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Description

STS 91 was an American Shuttle spacecraft launched fromCape Canaveral. The main mission was to dock with anddeliver goods to the Mir space station. It also carried the 3.5ton international Alpha Magnetic Spectrometer to measure veryhigh energy cosmic rays, and some resources for microgravityexperiments. It docked with Mir on June 4 at 20:58 UT,undocked on June 8 at 16:02 UT and returned to Earth onJune 12 at 18:00 UT.

This mission was the first to use of the super lightweightexternal tank (SLWT) which is the same size (154ft long and27ft in diameter) as the external tank used on previouslaunches but 7,500 lbs lighter. The tank is made of analuminum lithium alloy and the tank's structural design also hasbeen improved making it 30% stronger and 5% less dense.The walls of the redesigned hydrogen tank are machined in anorthogonal waffle-like pattern, providing more strength andstability than the previous design. These improvements willprovide additional payload capacity to the International SpaceStation.

STS 91

NSSDC ID: 1998-034A

Alternate Names

25356

Facts in Brief


Funding Agency


Disciplines

Human Crew

Microgravity








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/





STS-91 Discovery (24)

USA


Launch date: 02.06.1998 Launch time: 22:06 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-A Altitude: 239 - 328 km Inclination: 51,60° Landing date: 12.06.1998 Landing time: 18:01 UT Landing site: Cape Canaveral (KSC)

Crew


1 Precourt Charles Joseph CDR 4 9d 19h 54m 155

2 Gorie Dominic Lee Pudwill PLT 1 9d 19h 54m 155



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

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



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


3 Chang-Diaz Franklin Ramon MSP 6 9d 19h 54m 155

4 Lawrence Wendy Barrien MSP 3 9d 19h 54m 155

5 Kavandi Janet Lynn MSP 1 9d 19h 54m 155

6 Ryumin Valeri Viktorovich MSP 4 9d 19h 54m 155


Launch 1 Precourt 2 Gorie 3 Chang-Diaz 4 Lawrence 5 Kavandi 6 Ryumin 7

Landing 1 Precourt 2 Gorie 3 Kavandi 4 Lawrence 5 Chang-Diaz 6 Ryumin 7 Thomas

Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC). 9th and final MIR-Docking-Mission; common flight with the 25. MIR resident crew (04. - 08.06.1998); supplies and equipment were brought to MIR and several experiments were brought from the MIR back to Earth; Andrew Thomas (final U.S. astronaut on MIR) returned to Earth with Discovery; experiment to find the leak in the module Spektr failed; several secondary payloads.

Photos / Drawings

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

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

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

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



















http://www.spacefacts.de/graph/drawing/large/english/sts-91_mir.htm�





Description

The STS-95 mission conducted a variety of experimentsaboard the Space Shuttle Discovery, including the Spartan 201free-flyer, the HST Orbiting Systems Test, the InternationalExtreme Ultraviolet Hitchhiker, four Get Away Special (GAS)experiment packages, six other Hitchhiker experiments, andexperiments conducted in the SPACEHAB module. The crewof STS-95 consisted of commander Curt Brown, pilot SteveLindsey, mission specialists Scott Parazynski, Steve Robinson,and Pedro Duque, and payload specialists Chiaki Mukai andJohn Glenn. The shuttle Discovery landed at Kennedy SpaceCenter on 07 November 1998 at 17:04 UT (12:04 p.m. EST)after a duration of 8 days, 22 hours, 44 minutes.

Spartan 201The Spartan 201 platform was released on the fourth day ofthe flight by the shuttle's deployable arm and retrieved twodays later and returned to Earth. The platform containedinstruments including two telescopes to study the solar coronaand solar wind. This was a reflight of the Spartan payloadflown on Mission STS-87 in November 1997 which developedproblems shortly after being deployed from the shuttle. TheSpartan also carried tests of a system to transmit real-time tothe ground to correct orientation and a video guidance sensorfor automated docking systems.

HOSTThe Hubble Space Telescope Orbiting Systems Test (HOST)was a platform on the shuttle designed for on-orbit testing offour of the components planned for the third Hubble servicingmission. The NICMOS Cooling System test involved zero-gverification of a Reverse Turbo Brayton Cycle Cooler. The HST486 Computer test studied radiation effects on the DF-224replacement parts. The Solid State Recorder test comparedon-orbit performance of the flight spare solid state recorderwith the current HST unit. The Fiber Optic Line test comparedthe 4 kbps data stream sent over fiber optic cables to the samestream sent over traditional electric wire.

IEHThe International Extreme Ultraviolet Hitchhiker (IEH) iscomprised of six experiments mounted in the shuttle payloadbay. These experiments are: (1) the Solar Extreme UltravioletHitchhiker (SEH) designed to measure EUV and FUV fluxesrequired to study the Earth's upper atmosphere; (2) theUltraviolet Spectrograph Telescope for Astronomical Research(UVSTAR) which measures EUV fluxes in order to produceimages of extended plasma sources; (3) the STAR-LITEpayload for observations of extended and diffuse astrophysicaltargets; (4) the CONCAP-IV payload designed to grow thin

STS 95

NSSDC ID: 1998-064A

Alternate Names

25519

Facts in Brief


Funding Agency


Disciplines

Astronomy

Engineering

Earth Science

Human Crew

Life Science

Microgravity

Planetary Science








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


STS 95


















http://nssdc.gsfc.nasa.gov/image/spacecraft/sts-95_takeoff_1.jpg



films by physical vapor transport; (5) the Petite Amateur NavySatellite (PANSAT), a small deployable satellite from the DODSpace Test Program which stores and transmits digitalcommunications to ground stations; and, (6) two Get AwaySpecial (GAS) packages.

SpacehabA Spacehab Module, a 10 x 13.5 foot pressurized laboratory ismounted in the payload bay connected by a tunnel to theshuttle mid-deck. The laboratory provides room for some 30experiments including plant growth, materials science,microgravity, and medications. Among these experiments arean aerogel production test, the Advanced Gradient HeatingFacility (AGHF), the Advanced Protein Crystallization Facility(APCF), the BIOBOX human bone and cell growth experiment,Oceaneering SPACEHAB Refrigerator Freezer (OSRF), theVestibular Function Experiment Unit (VFEU), the ProteinCrystallization Apparatus for Microgravity (PCAM), OrganicCrystal Growth (OCC), and the NHK Camera.

Other Hitchhiker and GAS ExperimentsIn addition to the hitchhiker experiments discussed above(SEH, UVSTAR, STAR-LITE, and PANSAT) the shuttle carriedthe Solar Constant Experiment (SOLCON), a radiometerdesigned to measure solar irradiance for calibration of satellitemeasurements; the Cosmic Dust Aggregate experiment(CODAG) which simulates the aggregation and dynamics ofdust particles during early solar system formation; and theRoach Experiment which used a camcorder to monitor the lifecycle of cockroaches in space. The two Get Away Specials inaddition to the two carried on IEH are the Capillary PumpedLoop (CPL) experiment to demonstrate the performance of atwo-phase capillary pumped loop in space, and the Hearts inSpace experiment to study why astronauts' hearts becomesmaller while in space.

Human Crew Life SciencesLife science experiments on the crew included experiments ofthe effects of space on a crew member of advanced age (77-year-old John Glenn). Studies on Glenn included wearingelectrodes and ingesting a miniature thermometer to studysleep disturbances in space, giving blood and urine samples tolearn about protein breakdown in space, monitoring of heartactivity in microgravity, and long term effects of weightlessnesson balance and muscle loss. Other astronauts also took part insome of these experiments. Additionally, Chiaki Mukai tookpart in a study on sleep patterns and melatonin.

John GlennThis shuttle mission received much public attention due to theinclusion of John Glenn as payload specialist. Glenn was oneof the original Mercury 7 astronauts and the first American toorbit the Earth on 20 February 1962 on the Mercury Atlascapsule Friendship 7. At 77 years of age, he becomes on thisshuttle flight the oldest person to go into space.


Related Information/Data at NSSDC

John Glenn's Mercury flight

Other Sources of STS 95 Information/Data

STS 95 information (NASA Shuttle Web)STS 95 information (NASA KSC)




http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1962-003A

http://spaceflight.nasa.gov/shuttle/archives/sts-95/

http://www.ksc.nasa.gov/shuttle/missions/sts-95/mission-sts-95.html



STS-95 Discovery (25)

USA


Launch date: 29.10.1998 Launch time: 19:19 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-B Altitude: 574 km Inclination: 28,45° Landing date: 07.11.1998 Landing time: 17:04 UT Landing site: Cape Canaveral (KSC)

Crew


1 Brown Curtis Lee, Jr. "Curt" CDR 5 8d 21h 44m 134

2 Lindsey Steven Wayne PLT 2 8d 21h 44m 134

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


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

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




3 Robinson Stephen Kern MSP 2 8d 21h 44m 134

4 Parazynski Scott Edward MSP 3 8d 21h 44m 134

5 Duque Pedro Francisco MSP 1 8d 21h 44m 134

6 Mukai Chiaki PSP 2 8d 21h 44m 134

7 Glenn John Herschel, Jr. PSP 2 8d 21h 44m 134


Launch 1 Brown 2 Lindsey 3 Duque 4 Parazynski 5 Robinson 6 Glenn 7 Mukai

Landing 1 Brown 2 Lindsey 3 Robinson 4 Parazynski 5 Duque 6 Glenn 7 Mukai

Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC). Mission Spacehab-SM; astronaut-veteran John Glenn (77) returned into space after more than 36 years; experiments on and with John Glenn (how do older humans work and feel in space?); deploying and retrieval (after two days) of the free-flyer SPARTAN 201-05; during launch the orbiter lost a flap of the parachute-box; landing without using the Drag Chute.

Photos / Drawings

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

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

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


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



















http://www.spacefacts.de/graph/drawing/large/english/spartan_sts-95.htm�

http://www.spacefacts.de/graph/drawing/large/english/sts-95_florida.htm�





Description

SWAS (Submillimeter Wave Astronomy Satellite) is part ofNASA's Small Explorer (SMEX) program. The SWASinstrument is a submillimeter wave telescope launched onDecember 2, 1998 and operated in a 600 km circular orbit with70° inclination. Scientific objectives of SWAS are to study thechemical composition, energy balance and structure ofinterstellar clouds, both galactic and extragalactic, and theprocesses that lead to the formation of stars and planets.SWAS focuses on the following spectral lines: (1) watermolecule at 556.936 GHz; (2) oxygen molecule at 487.249GHz; (3) CI at 492.161 GHz; (4) carbon 13 monoxide moleculeat 550.927 GHz; and, (5) oxygen 18 water molecule at548.676 GHz). Detailed 1 degree x 1 degree maps of giantmolecular and dark cloud cores are generated from a grid ofmeasurements taken at 3.7 arc-min spacings. SWAS'ssubmillimeter radiometers are a pair of passively cooledsubharmonic Schottky diode receivers, with receiver noisefigures of 2500-3000 K. An acousto-optical spectrometer(AOS) was provided by the University of Cologne. Outputs ofthe two SWAS receivers are combined to form a finalintermediate frequency, which extends from 1.4 to 2.8 GHzand is dispersed into 1400 1 MHz channels by the AOS.SWAS has a 55 x 71 cm elliptical off-axis Cassegraintelescope with a beam width of 4 arc-min at operatingfrequencies. SWAS is designed to make pointed observationsstabilized on three axes, with a position accuracy of about 38arc-s, and jitter of about 24 arc-s. Attitude information isobtained from gyros whose drift is corrected via a star tracker.Momentum wheels are used to maneuver the spacecraft.Information on the SMEX program is provided by Baker, D., etal., NASA's Small Explorer program, Phys. Today, 45, No. 12,44-51, Dec. 1991.

SWAS

NSSDC ID: 1998-071A

Alternate Names

SMEX/SWAS

Small Explorer/SWAS

Submillimeter WaveAstronomy Satellite

Explorer 74

25560

Facts in Brief

Launch Date: 1998-12-05LaunchVehicle: Pegasus XLLaunchSite: Vandenberg AFB,United StatesMass: 288.0 kgNominalPower: 230.0 W

Funding Agency


Discipline

Astronomy


Launch/Orbitalinformation for SWAS

PDMP information forSWAS

Telecommunicationsinformation for SWAS

Experiments on SWAS

Data collections fromSWAS


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data









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

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

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












Personnel


Dr. Gary J.Melnick


Smithsonian AstrophysicalObservatory

[email protected]

Dr. GordonChin

Mission Scientist NASA Goddard SpaceFlight Center

[email protected]

Selected References

Baker, D., et al., NASA's Small Explorer program, Phys. Today, 45, No. 12, 44-51, Dec. 1991.

US Active Archive for SWAS Information/Data

The SWAS Archive at LAMBDA

Other Sources of SWAS Information/Data

SWAS Project Page at SAO

Small Explorer Project


mailto:[email protected]?Subject=NMC Comment/Question: SWAS (1998-071A)



http://lambda.gsfc.nasa.gov/product/swas/

http://sao-www.harvard.edu/cfa/oir/Research/swas/swas.html

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

http://www.usa.gov/








Description

Techsat-1B was a 70 kg microsatellite built by the Haifa basedTechnion Institute of Technology in Israel to replace Techsat-1A which failed to reach orbit in 1995. The three axis stabilizedsatellite has as its primary payload a multispectral push-broomCCD scanner offering 12 m ground resolution. It was launchedfrom the Baikonur cosmodrome aboard a Zenit rocket into a821 km sun-synchronous orbit with FASAT-B, TMSAT, SAFIR,WESTPAC and Resurs O2-1. The satellite transmitted a 9600-baud burst every 30 seconds lasting 3 seconds on one of thetwo downlinks at 435.225 MHz or 435.325 MHz.

Techsat 1B

NSSDC ID: 1998-043D

Alternate Names

OSCAR 32

25397

Facts in Brief


Funding Agency

Technion Institute ofTechnology, Israel (Israel)

Disciplines

Communications

Earth Science


Launch/Orbitalinformation for Techsat1B

Experiments on Techsat1B

Data collections fromTechsat 1B



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







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

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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Techsat 1B (1998-043D)











http://www.usa.gov/







Description

Thor 3 was a Norwegian geosynchronous communicationsspacecraft launched from Cape Canaveral aboard a Delta 2rocket. It carried 14 Ku-band transponders to provide voiceand video communications to Europe after parking at 1 deg Wlongitude.

THOR 3

NSSDC ID: 1998-035A

Alternate Names

25358

Facts in Brief

Launch Date: 1998-06-09Launch Vehicle: DeltaII 7925Launch Site: CapeCanaveral, United States

Funding Agency

Unknown (Norway)

Discipline

Communications


Launch/Orbitalinformation for THOR 3

Experiments on THOR 3

Data collections fromTHOR 3



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: THOR 3 (1998-035A)











http://www.usa.gov/








Description

TMSAT was a microsatellite built for the Thai MicrosatelliteCompany. It was similar in appearance to earlier ones in theseries and carried Earth Imaging and digital communicationsand GPS orbit determination experiments. It was launchedfrom the Baikonur cosmodrome aboard a Zenit rocket into a821 km sun-synchronous (21h37m) orbit. It has returned manymulti-spectral images of approximately 90m ground samplingdistance, in three spectral bands.

TMSAT

NSSDC ID: 1998-043C

Alternate Names

Thai Microsatellite

OSCAR 31

25396

Facts in Brief


Funding Agency

Thai MicrosatelliteCompany, Thailand(Thailand)

Disciplines

Communications

Earth Science


Launch/Orbitalinformation for TMSAT

Experiments on TMSAT

Data collections fromTMSAT



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: TMSAT (1998-043C)











http://www.usa.gov/







Description

The Transition Region and Coronal Explorer (TRACE) is aNASA small explorer mission designed to examine the three-dimensional magnetic structures which emerge through theSun's photosphere (the visible surface of the Sun) and defineboth the geometry and dynamics of the upper solaratmosphere (the transition region and corona). Its primaryscience objectives are to: (1) follow the evolution of magneticfield structures from the solar interior to the corona; (2)investigate the mechanisms of the heating of the outer solaratmosphere; and, (3) determine the triggers and onset of solarflares and mass ejections. TRACE is a single-instrument,three-axis stabilized spacecraft. The spacecraft attitude controlsystem (ACS) utilizes three magnetic-torquer coils, a digitalsun sensor, six coarse sun sensors, a three-axismagnetometer, four reaction wheels, and three two-axis inertialgyros to maintain pointing. In science mode the spacecraftuses an instrument-provided guide telescope as a fineguidance sensor to provide a pointing accuracy of less than 5arc-seconds. Power is provided to the spacecraft through theuse of four panels of Ga-As solar cells with a total area of 2.0square-meters. The solar array actually produces power ofaround 220 W, 85 W of which is used each orbit by thespacecraft and 35 W of which is used by the instrument eachorbit. The remaining power is used for operational anddecontamination heating of the spacecraft and telescope. A 9A-hour Ni-Cd battery provides energy during time when thespacecraft is in the Earth's shadow. Communications areprovided via a 5 W S-band transponder, providing up to 2.25Mbps downlink data transmission and 2 kbps uplink. Data aretransmitted up to six times daily. Data are stored on-boardusing a solid-state recorder capable of holding up to 300 MB.The command and data handling system uses a 32-bit80386/80387 processor.

TRACE

NSSDC ID: 1998-020A

Alternate Names

SMEX/TRACE

Small Explorer/TRACE

Transition Region andCoronal Explorer

Explorer 73

25280

Facts in Brief

Launch Date: 1998-04-01LaunchVehicle: Pegasus XLLaunchSite: Vandenberg AFB,United StatesMass: 250.0 kgNominalPower: 200.0 W

Funding Agency


Disciplines

Solar Physics

Space Physics


Launch/Orbitalinformation for TRACE

PDMP information forTRACE

Telecommunicationsinformation for TRACE

Experiments on TRACE

Data collections fromTRACE


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


TRACE








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

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

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









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




Personnel


Dr. AlanM. Title


Lockheed Palo Alto [email protected]

Ms.DawnMyers

Project Manager NASA Goddard SpaceFlight Center

[email protected]

Other Sources of TRACE Information/Data

TRACE Project page (NASA GSFC)TRACE Project page (Lockheed Martin)

Small Explorer program


mailto:[email protected]?Subject=NMC Comment/Question: TRACE (1998-020A)



http://sunland.gsfc.nasa.gov/smex/trace/index.html

http://vestige.lmsal.com/TRACE/

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

http://www.usa.gov/








Description

TUBSAT-N/TUBSAT-N1 were two nanosatellites launched asa satellite cluster from a submarine with a Russian SS-23military rocket in the Barents Sea. The satellites wereseparated in orbit via telecommand. Each contained threedifferent experimental payloads provided by the TechnicalUniversity of Berlin (TUB): reaction wheel performance, starsensor performance, and store and forward communication.The latter payload consisted of four independentcommunication transceivers for store and forwardcommunication with a baud rate of 1200 and 2400 baud. Twotransceivers worked in the 2m frequency band, the other two inthe 70 cm frequency band with FFSK (Fask Frequency ShiftKeying) modulation. An additional downlink transmitter with9600 Baud GMSK (Gaussian Minimum Shift Keying)modulation was available.

The attitude control of TUBSAT-N consisted of two magneticcoils, a magnetometer, a reaction wheel and a star sensor. Allattitude control devices were also developments of theTechnical University of Berlin. Electrical power was providedby 9 NiCd-battery cells of 5 Ah (SANYO). The battery cellswere connected serially and provided an unregulated busvoltage from 9 to 13 V.

It will be used from tracking medium-sized and largemammals, stolen cars and to collect data from autonomousbuoys for earth environmental observation. These buoys arelocated in the northern Atlantic ocean near the Canary Islands.

TUBSAT-N

NSSDC ID: 1998-042A

Alternate Names

25389

Facts in Brief

Launch Date: 1998-07-06Launch Vehicle: Shtil 1Launch Site: RussianSubmarine in Barents Sea,GermanyMass: 8.5 kg

Funding Agency

Technical University ofBerlin (Federal Republicof Germany)

Discipline

Earth Science


Launch/Orbitalinformation for TUBSAT-N

Experiments on TUBSAT-N

Data collections fromTUBSAT-N



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







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

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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: TUBSAT-N (1998-042A)











http://www.usa.gov/








Description

TUBSAT-N/TUBSAT-N1 were two nanosatellites launched asa satellite cluster from a submarine with a Russian SS-23military rocket in the Barents Sea. The satellites wereseparated in orbit via telecommand. Each contained threedifferent experimental payloads provided by the TechnicalUniversity of Berlin (TUB): reaction wheel performance, starsensor performance, and store and forward communication.The latter payload consisted of four independentcommunication transceivers for store and forwardcommunication with a baud rate of 1200 and 2400 baud. Twotransceivers worked in the 2m frequency band, the other two inthe 70 cm frequency band with FFSK (Fask Frequency ShiftKeying) modulation. An additional downlink transmitter with9600 Baud GMSK (Gaussian Minimum Shift Keying)modulation was available.

The attitude control of TUBSAT-N1 consisted of two magneticcoils, a magnetometer, a reaction wheel and a star sensor. Allattitude control devices were also developments of theTechnical University of Berlin. Electrical power was providedby 9 NiCd-battery cells of 5 Ah (SANYO). The battery cellswere connected serially and provided an unregulated busvoltage from 9 to 13 V.

It will be used from tracking medium-sized and largemammals, stolen cars and to collect data from autonomousbuoys for earth environmental observation. These buoys arelocated in the northern Atlantic ocean near the Canary Islands.

TUBSAT-N1

NSSDC ID: 1998-042B

Alternate Names

25390

Facts in Brief

Launch Date: 1998-07-06Launch Vehicle: Shtil 1Launch Site: RussianSubmarine in Barents Sea,GermanyMass: 8.5 kg

Funding Agency

Technical University ofBerlin (Federal Republicof Germany)

Discipline

Earth Science


Launch/Orbitalinformation for TUBSAT-N1

Experiments on TUBSAT-N1

Data collections fromTUBSAT-N1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=TUBSAT-N1

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=TUBSAT-N1

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=TUBSAT-N1

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=TUBSAT-N1

mailto:[email protected]?Subject=NMC Comment/Question: TUBSAT-N1 (1998-042B)











http://www.usa.gov/








Description

UFO 8 (UHF Follow On 8) 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 compressed 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. Onthe F-8 through F-10 missions, the SHF payload was replacedby the GBS (Global Broadcast Service) package thatrevolutionized communications for the full range of the DefenseDepartment's high-capacity requirements, from intelligencedissemination to quality-of-life programming.

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 8

NSSDC ID: 1998-016A

Alternate Names

UHF Follow On 8

USA 138

UHF F8

25258

Facts in Brief

Launch Date: 1998-03-16Launch Vehicle: Atlas2ASLaunch Site: CapeCanaveral, United StatesMass: 1000.0 kgNominalPower: 1200.0 W

Funding Agency


Disciplines

Communications



Launch/Orbitalinformation for UFO 8

Experiments on UFO 8

Data collections from UFO8



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=UFO 8

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=UFO 8


mailto:[email protected]?Subject=NMC Comment/Question: UFO 8 (1998-016A)












Office.



http://www.usa.gov/








Description

UFO 9 (UHF Follow On 9) 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. Onthe F-8 through F-10 missions, the SHF payload was replacedby the GBS (Global Broadcast Service) package thatrevolutionized communications for the full range of the DefenseDepartment's high-capacity requirements, from intelligencedissemination to quality-of-life programming.

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 9

NSSDC ID: 1998-058A

Alternate Names

UHF Follow On 9

25501

Facts in Brief

Launch Date: 1998-10-20Launch Vehicle: Atlas2ALaunch Site: CapeCanaveral, United States

Funding Agency


Disciplines

Communications



Launch/Orbitalinformation for UFO 9

Telecommunicationsinformation for UFO 9

Experiments on UFO 9

Data collections from UFO9



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data








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



















Description

Unity (also known as Node 1) is a six-sided aluminumconnecting passageway to living and work areas of theInternational Space Station. It is the first major U.S.-builtcomponent of the station, and was delivered by the spaceshuttle STS-88. The shuttle crew docked Unity with Zarya,then conducted spacewalks to attach various power,communication, and data lines between Zarya, the PMAs, andUnity, thereby making the ISS an operational entity. Later,before releasing Unity from its connection to the shuttle, theshuttle Endeavor fired thrusters and climbed to about 248miles, 5-1/2 miles higher than before. During the lifetime of theISS, other such boosts will be needed to maintain the station inthe desired orbit. The initial orbital parameters of the ISS(Zarya + Unity combined) were approximately: period 93 min,apogee 410 km, perigee 390 km, and inclination 51.6 deg. Thesize of the combination is approximately 77,000 pounds(35,000 kg) and 77 feet (23 m) tip-to-tip.

Unity has two Pressurized Mating Adapters (PMAs), oneattached to either end. Including the PMAs, it is about 11 m(36 feet) long, and has a diameter of about 5 m (16 feet). PMA1 is now permanently mated to the FGB and PMA 2 will beused for orbiter dockings and crew access to the station. Unityalso will contain an International Standard Payload Rack usedto support on-orbit activities once activated after the fifthShuttle/Station assembly flight.

In addition to its connection to Zarya and its shuttle dockingport, Unity has six other hatches that will eventually provideconnecting points for the Z1 truss exterior framework, the U.S.laboratory module; an airlock; the cupola; Node 3; and a Multi-Purpose Logistics Module (MPLM). For further details of thecomponent modules, see their separate descriptions in theNSSDC information system, the NASA web sitehttp://spaceflight.nasa.gov/ and the URLs below.

http://station.nasa.gov/station/assembly/index.html (A searchpage)

http://station.nasa.gov/station/assembly/elements/fgb/ (Zarya -1998-067A)

http://station.nasa.gov/station/assembly/elements/node1/ (Unity- 1998-069F)

http://www.estec.esa.int/spaceflight/index.htmhttp://www.estec.esa.int/spaceflight/zarya.htm (ISS)

Unity

NSSDC ID: 1998-069F

Alternate Names

25575

Facts in Brief


Funding Agency


Discipline

Engineering


Launch/Orbitalinformation for Unity

PDMP information forUnity

Experiments on Unity

Data collections from Unity



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data



http://spaceflight.nasa.gov/

http://station.nasa.gov/station/assembly/index.html

http://station.nasa.gov/station/assembly/elements/fgb/

http://station.nasa.gov/station/assembly/elements/node1/

http://www.estec.esa.int/spaceflight/index.htm

http://www.estec.esa.int/spaceflight/zarya.htm



http://nssdc.gsfc.nasa.gov/nmc/spacecraftPdmp.do?id=1998-069F

http://nssdc.gsfc.nasa.gov/nmc/spacecraftPdmp.do?id=1998-069F

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Unity (1998-069F)














Description

USA 139 is an American (National Reconnoissance Office)military reconnoissance spacecraft in the MILSTAR 3 seriesthat was launched from Cape Canaveral Air Station by a Titan4B rocket.

USA 139

NSSDC ID: 1998-029A

Alternate Names

25336

Facts in Brief

Launch Date: 1998-05-08Launch Vehicle: Titan4BLaunch Site: CapeCanaveral, United States

Funding Agency

Unknown (United States)

Discipline



Launch/Orbitalinformation for USA 139

Experiments on USA 139

Data collections from USA139



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=USA 139

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=USA 139

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=USA 139

mailto:[email protected]?Subject=NMC Comment/Question: USA 139 (1998-029A)











http://www.usa.gov/








Description

Formerly known as WPLTN-1, Westpac was an Australiageodetic satellite for the joint venture between Australia'sElectro Optics and the Russian Space Agency. It wasspherical in shape with laser reflectors. It served as a target forthe Western Pacific Laser Tracking Network.

Westpac

NSSDC ID: 1998-043E

Alternate Names

25398

Facts in Brief


Funding Agency

Unknown (Australia)

Discipline

Earth Science


Launch/Orbitalinformation for Westpac

Experiments on Westpac

Data collections fromWestpac



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Westpac (1998-043E)











http://www.usa.gov/





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