NASA - NSSDC - Master Catalog - Spacecraft Query · Navstar 43 1997-035A 1997-07-22 ... Historia...

Cronología de Lanzamientos Espaciales

Año 1997 Recopilación de datos Ing. Eladio Miranda Batlle. Los textos, imágenes y tablas fueron obtenidos de la National Space Science. Data Center. NASA

NASA - NSSDC - Spacecraft - Query Results

http://nssdc.gsfc.nasa.gov/nmc/spacecraftSearch.do;jsessionid=8957C6EF953AF82B9FF4FB6AABC49796[13/06/2011 22:59:00]

Monday, 13 June 2011

Spacecraft Query Results

There were 154 spacecraft returned.

Spacecraft Name NSSDC ID Launch Date

ACE 1997-045A 1997-08-24

Agila 2 1997-042A 1997-08-18

Apstar 2R 1997-062A 1997-10-15

AsiaSat 3 1997-086A 1997-12-23

Astra 1G 1997-076A 1997-12-01

BSAT-1A 1997-016B 1997-04-15

Cakrawarta 1 1997-071B 1997-11-11

Cassini 1997-061A 1997-10-14

Celestis 1997-018B 1997-04-20

Cosmos 2337 1997-006D 1997-02-13

Cosmos 2338 1997-006E 1997-02-13

Cosmos 2339 1997-006F 1997-02-13

Cosmos 2340 1997-015A 1997-04-08

Cosmos 2341 1997-017A 1997-04-16

Cosmos 2342 1997-022A 1997-05-13

Cosmos 2343 1997-024A 1997-05-14

Cosmos 2344 1997-028A 1997-06-05

Cosmos 2345 1997-041A 1997-08-13

Cosmos 2346 1997-052A 1997-09-22

Cosmos 2347 1997-079A 1997-12-08

Cosmos 2348 1997-080A 1997-12-14

CRISTA-SPAS 2 1997-039B 1997-08-06

DMSP 5D-2/F14 1997-012A 1997-04-03

Dongfanghong 3 1997-021A 1997-05-10

DSCS III-B13 1997-065A 1997-10-24

Dummy S1 1997-048A 1997-08-31

Dummy S2 1997-048B 1997-08-31

Early Bird 1 1997-085A 1997-12-23

Echostar 3 1997-059A 1997-10-04

Equator-S 1997-075B 1997-12-01

FAISAT 2V 1997-052B 1997-09-22

Fengyun 2B 1997-029A 1997-06-09

FORTE 1997-047A 1997-08-28

Foton 11 1997-060A 1997-10-08

Galaxy 8 1997-078A 1997-12-07

GE 2 1997-002A 1997-01-29

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



GE 3 1997-050A 1997-09-03

GOES 10 1997-019A 1997-04-24

GOES-K GOES-K 1997-04-23

Gonets D1-4 1997-006A 1997-02-13

Gonets D1-5 1997-006B 1997-02-13

Gonets D1-6 1997-006C 1997-02-13

HALCA 1997-005A 1997-02-11

Hot Bird 3 1997-049A 1997-09-01

Inmarsat 3-F4 1997-027A 1997-06-02

INSAT 2D 1997-027B 1997-06-02

Inspektor 1997-058D 1997-12-16

Intelsat 801 1997-009A 1997-02-28

Intelsat 802 1997-031A 1997-06-24

Intelsat 803 1997-053A 1997-09-22

Intelsat 804 1997-083A 1997-12-21

Iridium 4 1997-020E 1997-05-04

Iridium 5 1997-020D 1997-05-04

Iridium 6 1997-020C 1997-05-05

Iridium 7 1997-020B 1997-05-04

Iridium 8 1997-020A 1997-05-04

Iridium 9 1997-030C 1997-06-17

Iridium 10 1997-030D 1997-06-17

Iridium 11 1997-030G 1997-06-17

Iridium 12 1997-030B 1997-06-17

Iridium 13 1997-030E 1997-06-17

Iridium 14 1997-030A 1997-06-17

Iridium 15 1997-034A 1997-07-08

Iridium 16 1997-030F 1997-06-17

Iridium 17 1997-034B 1997-07-08

Iridium 18 1997-034C 1997-07-08

Iridium 19 1997-056A 1997-09-26

Iridium 20 1997-034D 1997-07-08

Iridium 21 1997-034E 1997-07-08

Iridium 22 1997-043E 1997-08-20

Iridium 23 1997-043D 1997-08-20

Iridium 24 1997-043C 1997-08-20

Iridium 25 1997-043B 1997-08-20

Iridium 26 1997-043A 1997-08-20

Iridium 27 1997-051D 1997-09-13

Iridium 28 1997-051E 1997-09-13

Iridium 29 1997-051A 1997-09-13

Iridium 30 1997-051F 1997-09-13

Iridium 31 1997-051G 1997-09-13

Iridium 32 1997-051B 1997-09-13

Iridium 33 1997-051C 1997-09-13

Iridium 34 1997-056E 1997-09-26

Iridium 35 1997-056D 1997-09-26

Iridium 36 1997-056C 1997-09-26

Iridium 37 1997-056B 1997-09-26



Iridium 38 1997-069E 1997-11-08

Iridium 39 1997-069D 1997-11-08

Iridium 40 1997-069C 1997-11-08

Iridium 41 1997-069B 1997-11-08

Iridium 42 1997-077A 1997-12-07

Iridium 43 1997-069A 1997-11-08

Iridium 44 1997-077B 1997-12-07

Iridium 45 1997-082A 1997-12-19

Iridium 46 1997-082B 1997-12-19

Iridium 47 1997-082C 1997-12-19

Iridium 48 1997-082D 1997-12-19

Iridium 49 1997-082E 1997-12-19

IRS-1D 1997-057A 1997-09-28

JCSAT 4 1997-007A 1997-02-17

JCSAT 5 1997-075A 1997-12-01

Kiku 7 Chaser 1997-074B 1997-11-26

Kiku 7 Target 1997-074E 1997-11-26

Kupon 1997-070A 1997-11-11

LANL 97A LANL-97 1996-12-31

MAQSAT-B 1997-066B 1997-10-29

MAQSAT-H 1997-066A 1997-10-29

Meteosat 7 1997-049B 1997-09-01

Minisat 01 1997-018A 1997-04-20

Molniya 1-90 1997-054A 1997-09-23

Nahuel 1A 1997-002B 1997-01-29

Navstar 38 1997-067A 1997-11-05

Navstar 43 1997-035A 1997-07-22

Orbcomm FM-05 1997-084F 1997-12-22

Orbcomm FM-06 1997-084G 1997-12-22

Orbcomm FM-07 1997-084H 1997-12-22

Orbcomm FM-08 1997-084A 1997-12-22

Orbcomm FM-09 1997-084E 1997-12-22

Orbcomm FM-10 1997-084B 1997-12-22

Orbcomm FM-11 1997-084C 1997-12-22

Orbcomm FM-12 1997-084D 1997-12-22

PANAMSAT 5 1997-046A 1997-08-27

PANAMSAT 6 1997-040A 1997-08-06

Progress M-34 1997-014A 1997-04-05

Progress M-35 1997-033A 1997-07-04

Progress M-36 1997-058A 1997-10-04

Progress M-37 1997-081A 1997-12-19

Resurs F-1M 1997-072A 1997-11-17

Seastar 1997-037A 1997-07-31

Sirius 2 1997-071A 1997-11-11

Soyuz-TM 25 1997-003A 1997-02-09

Soyuz-TM 26 1997-038A 1997-08-04

Spartan 201-4 1997-073B 1997-11-20

Sputnik Jr 1997-058C 1997-11-02

SSTI-LEWIS 1997-044A 1997-08-22



STEP 4 1997-063A 1997-10-21

STS 81 1997-001A 1997-01-11

STS 82 1997-004A 1997-02-10

STS 83 1997-013A 1997-04-03

STS 84 1997-023A 1997-05-14

STS 85 1997-039A 1997-08-06

STS 86 1997-055A 1997-09-25

STS 87 1997-073A 1997-11-18

STS 94 1997-032A 1997-06-30

Superbird-C 1997-036A 1997-07-27

Telstar 5 1997-026A 1997-05-23

Tempo 2 1997-011A 1997-03-07

THAICOM 3 1997-016A 1997-04-15

THOR 2A 1997-025A 1997-05-19

TRMM 1997-074A 1997-11-26

USA 130 1997-008A 1997-02-23

USA 133 1997-064A 1997-10-23

USA 136 1997-068A 1997-11-06

YES 1997-066C 1997-10-29

Zeya 1997-010A 1997-03-03

+ 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=1997-045A[13/06/2011 23:21:52]


Description

The objective of the Advanced Composition Explorer (ACE) isto collect observations of particles of solar, interplanetary,interstellar, and galactic origins, spanning the energy rangefrom that of KeV solar wind ions to galactic cosmic ray nucleiup to 600 MeV/nucleon. Definitive studies will be made of theabundances of essentially all isotopes from H to Zn (Z = 1-30),with exploratory isotope studies extending to Zr (Z = 40). TheACE payload includes six high resolution spectrometers, eachdesigned to provide the optimum charge, mass, or charge-state resolution in its particular energy range. Eachspectrometer has a geometry factor optimized for the expectedflux levels, so as to provide a collecting power greater by afactor of 10-1000 times that of previous or plannedexperiments. The payload also includes three additionalinstruments of standard design to monitor energetic electrons,H and He ions, and a magnetometer. The ACE spacecraft isbased on the design of the Charge Composition Explorer, builtat JHU/APL for the Active Magnetospheric Particle TracerExplorer (AMPTE) program. The spacecraft spin axis ispointed towards the Sun to within +/- 20 degrees, and itoccupies a halo orbit about the L1 Earth-Sun libration point.Powered by solar cells, the spacecraft has a design life of atleast five years, and it returns data in daily tape recorderdumps, received through NASA JPL's Deep Space Networkand initially processed at NASA-GSFC. The average datatelemetry rate is 6.7 Kbs.

ACE

NSSDC ID: 1997-045A

Alternate Names

Advanced CompositionExplorer

Explorer 71

24912

Facts in Brief

Launch Date: 1997-08-25Launch Vehicle: DeltaII 7920Launch Site: CapeCanaveral, United StatesMass: 596.0 kgNominalPower: 464.0 W

Funding Agency

NASA-Office of SpaceScience (United States)

Discipline

Space Physics

AdditionalInformation

Launch/Orbitalinformation for ACE

PDMP information forACE

Telecommunicationsinformation for ACE

Experiments on ACE

Data collections from ACE

Questions or commentsabout this spacecraft canbe directed to: Dr. John F.Cooper.


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


ACE


http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1997-045A


http://nssdc.gsfc.nasa.gov/nmc/spacecraftPdmp.do?id=1997-045A


http://nssdc.gsfc.nasa.gov/nmc/spacecraftTelemetry.do?id=1997-045A


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

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

mailto:[email protected]?Subject=NMC Comment/Question: ACE (1997-045A)

mailto:[email protected]?Subject=NMC Comment/Question: ACE (1997-045A)









http://nssdc.gsfc.nasa.gov/image/spacecraft/ace1.jpg

(ACE)Advanced Composition Explorer

Advanced Composition Explorer

Advanced Composition Explorer (ACE) es un satélite de la NASA cuyo objetivo primordial es comparar y determinar la composición elemental e isotópica de distintos tipos de materia, entre los que se incluyen el viento solar, el medio interestelar y otra materia de origen galáctico. Con una masa de 596 kg, fue lanzado el 25 de agosto de 1997 a bordo de un Delta II y actualmente esta operando en las ceranías del Punto de Lagrange L1, situado entre el Sol y la Tierra, a una distancia de unos 1,5 millones de kilómetros de esta última.

Instrumentación [editar

• Cosmic Ray Isotope Spectrometer (CRIS): Estudia y determina la composición

]

isotópica de los rayos cósmicos en un intento de esclarecer su origen • ACE Real Time Solar Wind (RTSW) • Solar Wind Ion Mass Spectrometer (SWIMS) y Solar Wind Ion Composition

Spectrometer (SWICS): Estos dos instrumentos son espectrómetros de masas cada uno destinado para diferentes medidas. Analizan la composición química e isotópica del viento solar y la materia interestelar.

• Ultra-Low Energy Isotope Spectrometer (ULEIS): Este instrumento mide el flujo de iones en el rango del helio hasta el níquel para determinar las características de las partículas energéticas solares y el mecanismo por el cual las mismas se cargan por el sol.

• Solar Energetic Particle Ionic Change analyzer (SEPICA) • Solar Isotope Spectrometer (SIS) • Solar Wind Electron, Proton and Alpha Monitor (SWEPAM) • Magnetometer (MAG)

Historia [editar

La misión fue concebida en un encuentro el

]

19 de junio de 1983 en la Universidad de Maryland, aunque se venía gestando la propuesta de un satélite que estudiara en profundidad el viento solar y las radiaciones intergalácticas bajo el nombre de Cosmic Composition Explorer. En 1986 la NASA retomó la idea, pero no sería hasta 1988 cuando el ACE fue seleccionado para un estudio conceptual conocido como la Fase A del diseño.

http://es.wikipedia.org/wiki/NASA�

http://es.wikipedia.org/wiki/Viento_solar�

http://es.wikipedia.org/w/index.php?title=Interestelar&action=edit&redlink=1�

http://es.wikipedia.org/wiki/25_de_agosto�

http://es.wikipedia.org/wiki/1997�

http://es.wikipedia.org/wiki/Delta_II�

http://es.wikipedia.org/wiki/Puntos_de_Lagrange�

http://es.wikipedia.org/w/index.php?title=Advanced_Composition_Explorer&action=edit&section=1�

http://es.wikipedia.org/wiki/Is%C3%B3topo�

http://es.wikipedia.org/wiki/Rayos_c%C3%B3smicos�

http://es.wikipedia.org/wiki/Espectr%C3%B3metro_de_masas�

http://es.wikipedia.org/wiki/Helio�

http://es.wikipedia.org/wiki/N%C3%ADquel�

http://es.wikipedia.org/w/index.php?title=Advanced_Composition_Explorer&action=edit&section=2�

http://es.wikipedia.org/wiki/19_de_junio�


http://es.wikipedia.org/wiki/Universidad_de_Maryland�



Finalmente el 22 de abril de 1991 la misión dio comienzo oficialmente con la firma de un contrato entre NASA/GSFC y el California Institute of Technology. Tras varios meses con el planeamiento de las operaciones, dio comienzo la Fase B de definición de la misión en agosto de 1992.

El diseño preeliminar comenzó en noviembre de 1993, y las Fases C y D de implementación de los instrumentos comenzaron poco después.

http://es.wikipedia.org/wiki/22_de_abril�


http://es.wikipedia.org/wiki/California_Institute_of_Technology�





Personnel

Name Role Original Affiliation E-mail

Dr. JohnLintott

ProgramManager

NASA Headquarters

Mr. Louis J.Demas

ProgramScientist

NASA Headquarters

Prof. EdwardC. Stone, Jr.

MissionPrincipalInvestigator

California Institute ofTechnology

[email protected]

Dr. W.VernonJones

ProgramScientist

NASA Headquarters [email protected]

Mr. DonaldL. Margolies

ProjectManager

NASA Goddard SpaceFlight Center

[email protected]

Mr. Frank E.Snow

MissionOperationsManager


[email protected]

Dr. JonathanF. Ormes

ProjectScientist


[email protected]

Mr. James S.Barrowman

ProjectManager


[email protected]

Other ACE Data/Information at NSSDC

DataNSSDC Anonymous FTP (HDF and ASCII data)CDAWeb (MAG, SIS, EPAM, SWEPAM, and ULEIS data)SSCWeb (SSC ephemeris plots and data)

Archiving StatusDate Coverage Chart for ACE Data Sets at NSSDC and on CDAWeb

Press ReleasesACE arrives at KSC (06/13/97)

Other Sources of ACE Data/Information

ACE Science Center DataACE Fact Sheet


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

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

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

http://nssdc.gsfc.nasa.gov/space/image/ACE_data_barchart.gif

http://nssdc.gsfc.nasa.gov/space/text/ace_arrives.txt

http://www.srl.caltech.edu/ACE/ASC/

http://sd-www.jhuapl.edu/ACE/ACE_FactSheet.html

http://www.usa.gov/








Description

Agila 2 was a Philippine communications satellite launchedfrom the Xichang facility in the Peoples Republic of China forthe Mabuhay Communications Corporation of Manila. It wasput into a geostationary orbit at 140 deg E.

Agila 2

NSSDC ID: 1997-042A

Alternate Names

Mabuhay 1

24901

Facts in Brief

Launch Date: 1997-08-19Launch Vehicle: LongMarch 3BLaunch Site: Xichang,Peoples Republic of China

Funding Agency

Unknown (Philippines)

Discipline

Communications


Launch/Orbitalinformation for Agila 2

Experiments on Agila 2

Data collections from Agila2

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/experimentSearch.do?spacecraft=Agila 2

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Agila 2 (1997-042A)











http://www.usa.gov/








Description

APSTAR 2R was a Hong Kong geostationary communicationssatellite launched by a Long March 3B rocket from the Xichanglaunch center in the PRC. It carried 28 C-band and 15 Ku-bandtransponders to provide voice and video communications toChina after parking at 76.5 deg E. It had an expected life spanof 15 years.

Apstar 2R

NSSDC ID: 1997-062A

Alternate Names

25010

Facts in Brief

Launch Date: 1997-10-16Launch Vehicle: LongMarch 3BLaunch Site: Xichang,Peoples Republic of ChinaMass: 3700.0 kg

Funding Agency

APT Satellite CompanyLtd (Hong Kong)

Discipline

Communications


Launch/Orbitalinformation for Apstar 2R

Experiments on Apstar 2R

Data collections fromApstar 2R



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Apstar 2R (1997-062A)











http://www.usa.gov/








Description

Asiasat 3 was a communications satellite launched by HongKong, People's Republic of China. It was to be used primarilyfor television distribution and telecommunications servicesthroughout Asia, the Middle East, and Australasia, with multiplespot beams for selected areas.

The body-stabilized satellite was 26.2 m tip-to-tip along theaxis of the solar arrays and 10 m across the axis of theantennas. The bus was essentially a cube, roughly 4 m on aside.

Power to the spacecraft was generated using two sun-tracking,four-panel solar wings covered with Ga-As solar cells,providing up to 9900 watts A 29-cell Ni-H battery providedpower to the spacecraft during eclipse operations. Abipropellant propulsion system, consisting of twelveconventional bi-propellant thrusters, was used forstationkeeping.

Two 2.72 m diameter Gregorian shaped-surface antennaswere mounted on opposing sides of the bus, perpendicular tothe axis along which the solar arrays were mounted. One ofthese antennas operated in C-band, the other in Ku-band.Focused area coverage was provided by a 1.3 m diameter,dual-gridded shaped reflector operating in the Ku-band. A 1 mdiameter Ku-band steerable spot-beam antenna provided thespacecraft with the ability to direct 5 degree coverage of anyarea on the Earth's surface visible to the spacecraft from itsorbit location. Both of these antennas were mounted on thenadir side of the spacecraft.

The satellite was to be placed into a geosynchronous orbit, buta malfunction in the fourth (DM 3) stage resulted in a short lifeand a dysfunctional orbit. Later investigation revealed that theDM 3 may have been designed only for a maximum payload of2.4 metric tonnes and had previously mislaunched two earlierpayloads which exceeded this limit (as did Asiasat 3).

Following its failure to achieve the proper orbit, themanufacturer (Hughes Global Services) purchased thespacecraft back from the insurers and renamed it HGS 1. HGS1 was then successfully maneuvered into two successive flybysof the Moon to place it into geosynchronous orbit, the first timesuch a maneuver was performed by a commercial satellite.

In early 1999, the satellite was acquired by PanAmSat,renamed PAS 22, and moved to a new location.

AsiaSat 3

NSSDC ID: 1997-086A

Alternate Names

HGS 1

PAS 22

25126

Facts in Brief

Launch Date: 1997-12-24LaunchVehicle: Proton-KLaunch Site: Tyuratam(Baikonur Cosmodrome),KazakhstanMass: 2534.0 kgNominalPower: 9900.0 W

Funding Agencies

Asia SatelliteTelecommunications Co.Ltd. (AsiaSat) (PeoplesRepublic of China)

Pan American Satellite(United States)

Discipline

Communications


Launch/Orbitalinformation for AsiaSat 3

Telecommunicationsinformation for AsiaSat 3

Experiments on AsiaSat 3

Data collections fromAsiaSat 3

Questions or comments


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







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

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

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











about this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.

Personnel



mailto:[email protected]?Subject=NMC Comment/Question: AsiaSat 3 (1997-086A)



http://www.usa.gov/





Asiasat 3 - HGS 1

· Otros nombres: 1997-086A, HGS 1, 25126 · Fecha de lanzamiento: 24 de diciembre de 1997 a las 23:19:00 GMT · Masa seca en órbita: 2.534 kg · Potencia máxima: 9.900 W Asiasat 3 es un satélite de comunicaciones lanzado por una empresa de Hong Kong, de la República Popular de China. Su función principal era la distribución de televisión y servicios de telecomunicaciones a través de toda Asia, el Medio Este, Australasia y otras zonas cercanas. El satélite está estabilizado en los 3 ejes y tenía una longitud de 26,2 metros con los paneles solares plenamente desplegados y 10 metros de anchura en la zona de las antenas. El bus tenía forma de cubo de 4 metros de lado. La energía era proporcionada por 4 paneles solares de Ga-As que se alineaban de forma continua hacia el Sol gracias a 2 sensores solares y se almacenaba en baterías de Ni-H que proporcionaban un total de 9.900 vatios a 29 amperios. El sistema de propulsión por bipropelente tenía 12 toberas que eran usadas para mantener la posición en todo momento. La nave tenía dos antenas de 2,72 metros que estaban colocadas en cara opuestas del bus y de forma perpendicular al eje donde estaban los paneles solares. Estas antenas operaban en banda C y banda Ku. Además la nave portaba otras antenas menores y redireccionables.

Satélite Asiasat-3, el primer satélite comercial en sobrevolar la Luna El satélite tenía que ser colocado en órbita geoestacionaria pero un fallo en la cuarta etapa DM3 del cohete Proton K, dio como resultado una órbita incorrecta de 203 x 36.000 kilómetros y por tanto quedaba inutilizado. La investigación posterior concluyó que la etapa DM3 había sido diseñada para un máximo de 2,4 toneladas métricas y ya había dado problemas en dos lanzamientos anteriores que habían excedido los límites…………………………………………………………………. Tras el fallo, el manufacturador Hughes Global Services adquirió el satélite y lo renombró HGS-1. Los técnicos programaron varias maniobras con sus propios motores de tal manera que se aumentara el apogeo durante 11 encendidos. El 13 de mayo la nave sobrevoló la Luna a tan sólo 6.300 kilómetros de distancia y subió su perigeo a los 42.000 kilómetros y reujo su inclinación. El 3 de junio se produjo el segundo sobrevuelo lunar a 34.300 kilómetros de distancia, lo que terminó situando al satélite en una órbita geoestacionaria. Era la primera vez en la Historia que un satélite comercial realizaba una maniobra de este tipo.




Description

Astra 1G was a European communications satellite launchedfrom the Baikonur cosmodrome aboard a Proton rocket. It wasinitially parked in a geostationary orbit at 23.9 deg E but wasto be operated at 19.2 deg E. Its planned operational lifetimewas a minimum of 15 years.

Astra 1G

NSSDC ID: 1997-076A

Alternate Names

25071

Facts in Brief

Launch Date: 1997-12-02LaunchVehicle: Proton-KLaunch Site: Tyuratam(Baikonur Cosmodrome),KazakhstanMass: 23000.0 kg

Funding Agency

Societe Europeenne desSatellites (Luxembourg)(Luxembourg)

Discipline

Communications


Launch/Orbitalinformation for Astra 1G

Experiments on Astra 1G

Data collections from Astra1G



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Astra 1G (1997-076A)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1997-016B[13/06/2011 23:26:47]


Description

B-SAT 1A 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 110 deg E. It provided direct broadcast analogTV to over 12 million customers throughout Japan. It wasthree-axis stabilized and generated 2 kW of electrical power. Itwas equipped with eight Ku-band transponders.

BSAT-1A

NSSDC ID: 1997-016B

Alternate Names

24769

Facts in Brief

Launch Date: 1997-04-16Launch Vehicle: Ariane44LLaunch Site: Kourou,French GuianaMass: 723.0 kgNominalPower: 1200.0 W

Funding Agency

Broadcast SatelliteSystem Corp of Tokyo(Japan)

Discipline

Communications


Launch/Orbitalinformation for BSAT-1A

Experiments on BSAT-1A

Data collections fromBSAT-1A



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1997-016B


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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: BSAT-1A (1997-016B)











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Description

Cakrawarta was an Indonesian communications satellitelaunched from the Kourou Space Center in French Guianaaboard an Ariane 44L rocket. It was place in ageosynchronous orbit at 100.6 deg E.

Cakrawarta 1

NSSDC ID: 1997-071B

Alternate Names

25051

Facts in Brief

Launch Date: 1997-11-12Launch Vehicle: Ariane4Launch Site: Kourou,French Guiana

Funding Agency

Unknown (Indonesia)

Discipline

Communications


Launch/Orbitalinformation forCakrawarta 1

Experiments onCakrawarta 1

Data collections fromCakrawarta 1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

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

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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Cakrawarta 1 (1997-071B)











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Description

The Cassini Orbiter's mission consists of delivering a probe(called Huygens, provided by ESA) to Titan, and thenremaining in orbit around Saturn for detailed studies of theplanet and its rings and satellites. The principal objectives areto: (1) determine the three-dimensional structure anddynamical behavior of the rings; (2) determine the compositionof the satellite surfaces and the geological history of eachobject; (3) determine the nature and origin of the dark materialon Iapetus' leading hemisphere; (4) measure the three-dimensional structure and dynamical behavior of themagnetosphere; (5) study the dynamical behavior of Saturn'satmosphere at cloud level; (6) study the time variability ofTitan's clouds and hazes; and, (7) characterize Titan's surfaceon a regional scale.

Spacecraft and SubsystemsThe spacecraft was originally planned to be the second three-axis stabilized, RTG-powered Mariner Mark II, a class ofspacecraft developed for missions beyond the orbit of Mars.However, various budget cuts and rescopings of the projectforced a more specialized design, postponing indefinitely anyimplementation of the Mariner Mark II series.

Cassini is the largest interplanetary spacecraft everconstructed by NASA. It measures 6.8 m in length with a 4 mhigh gain antenna. At launch the spacecraft had a mass of5,655 kg, of which 3,132 kg were propellant.

Cassini is three-axis stabilized. Orientation is maintainedthrough the use of either three reaction wheel assembliesmounted along orthogonal axes on the spacecraft (for finepointing control) or via 16 0.5 N thrusters (for coarse pointingcontrol). The thrusters are arranged in four groups of four anduse hydrazine. Orientation is determined through the use ofeither three inertial reference units (using solid-stategyroscopes) or a star tracker (which detects stars in its field ofview and compares them with an on-board catalog of 5,000stars). The thrusters are also used in the alteration of thespacecraft trajectory of <5 m/s. For trajectory corrections >5m/s, one of two identical main engines (one serves as abackup) is used. The engines are gimbaled so that thrust canbe maintained through the spacecraft center of mass and burnthe bipropellants nitrogen tetroxide and monomethyl hydrazine.

Power is provided to the spacecraft through the use of threeradioisotope thermoelectric generators (RTGs). Each RTGuses the heat generated by the decay of 10.9 kg of plutoniumdioxide (PuO2) to generate electrical power to be usedthroughout the spacecraft. At the beginning of the mission,

Cassini

NSSDC ID: 1997-061A

Alternate Names

Cassini Orbiter

25008

Facts in Brief

Launch Date: 1997-10-15Launch Vehicle: TitanIV-CentaurLaunch Site: CapeCanaveral, United StatesMass: 2523.0 kgNominalPower: 640.0 W

Funding Agencies

NASA-Office of SpaceScience Applications(United States)

European Space Agency(International)

Agenzia Spaziale Italiana(Italy)

Disciplines

Astronomy

Planetary Science

Space Physics


Launch/Orbitalinformation for Cassini

PDMP information forCassini

Telecommunicationsinformation for Cassini

Experiments on Cassini

Data collections fromCassini


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


Cassini








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

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

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











each RTG was capable of producing 300 W of electricalpower. By the end of the nominal 11 year mission, the outputis expected to degrade to around 210 W per RTG. Theresultant electricity, a regulated 30 V DC, is used not only toprovide power to the various science instruments andspacecraft subsystems, but also to one-time pyrotechnicdevices used in the course of the mission, such as to separatethe the spacecraft from the Centaur launch vehicle or toseparate the Huygens probe from Cassini.

Although some data will be transmitted in real time, muchscience data and spacecraft health and status information arerecorded on a solid-state data recorder. Although suchsystems had been used previously on other missions, Cassiniis the first to use one in deep space. The spacecraft isequipped with two recorders, each of which has a capacity of 2Gb (gigabits) in the form of dynamic random access memory(DRAM). Because such memory is vulnerable to radiationeffects, the recorders are encased in half-inch thick aluminum.Nonetheless, degradation of the recorders (due to solar andcosmic ray activity) is expected to reduce their capacity byabout 10% by the end of the mission. Recorded data are thenperiodically transmitted to Earth via the HGA and erased.

Mission ProfileUnable to be launched directly to Saturn with the propulsionsystems available at the time, Cassini took a roundabout routeto reach the ringed planet. Referred to as a VVEJGA (Venus-Venus-Earth-Jupiter Gravity Assist) trajectory, Cassini madetwo flybys of Venus (April 1998 and June 1999), one of theEarth (August 1999), and one of Jupiter (December 2000).Various observations were made at each of these encountersin order to verify instrument and spacecraft systems as well asto perform calibration observations. At Jupiter, numeroussimultaneous observations were made using Cassini, Galileo,and the Hubble Space Telescope, among other missions.

The first object in the Saturnian system to receive closeexamination will be its satellite Phoebe. This will be the onlyopportunity the Cassini will have to examine Phoebe at closerange because of its distance from the planet, but will be muchcloser than any previous mission has come to the satellite. Thetrajectory of Cassini during this initial orbit will be the closest ofthe entire mission, 1.3 Rs (1 Rs = 60,330 km) from the centerof the planet. The only other orbits which will come nearly asclose will occur late in the mission, around 2.7 Rs. Althoughthis close initial pass will cause Cassini to pass through therings, a region known to be relatively free of particles, thespacecraft has been designed to withstand such exposure. Aburn of the engine will slow the spacecraft sufficiently to placeit into a highly elongated orbit.

The first two orbits around Saturn are designed to set up thenecessary trajectory for deployment of the Huygens probe onthe third orbit. Currently planned for December 2004, amaneuver will place the paired spacecraft on an intersectcourse with Titan. A few days later the probe will be released.The two spacecraft will separate with a relative velocity of 0.3-0.4 m/s but remain in the same orbit for about three weeks. Atthat time, Cassini will execute a deflection maneuver to enableit to fly by Titan at an altitude of 60,000 km and positioning it toreceive transmissions from Huygens as it enters Titan'satmosphere, some 2.1 hours prior to Cassini's closestapproach.

After relaying the Huygens data, Cassini is expected to makeat least 76 loose elliptical orbits of the planet, each optimizedfor a different set of observations of the rings, varioussatellites, and the magnetosphere.

Questions or commentsabout this spacecraft canbe directed to: Dr. Edwin V.Bell, II.

mailto:[email protected]?Subject=NMC Comment/Question: Cassini (1997-061A)

mailto:[email protected]?Subject=NMC Comment/Question: Cassini (1997-061A)



Cassini's instrumentation consists of: a radar mapper, a CCDimaging system, a visible/infrared mapping spectrometer, acomposite infrared spectrometer, a cosmic dust analyzer, aradio and plasma wave experiment, a plasma spectrometer, anultraviolet imaging spectrograph, a magnetospheric imaginginstrument, a magnetometer, an ion/neutral massspectrometer. Telemetry from the communications antenna aswell as other special transmitters (an S-band transmitter and adual frequency Ka-band system) will also be used to makeobservations of the atmospheres of Titan and Saturn and tomeasure the gravity fields of the planet and its satellites.

Personnel


Mr. Robert T.Mitchell

ProgramManager

NASA Jet PropulsionLaboratory

[email protected]

Mr. Henry C.Brinton

ProgramScientist

NASA Headquarters

Dr. Dennis L.Matson

ProjectScientist

NASA Jet PropulsionLaboratory

[email protected]

Selected References

Jaffe, L. D., and L. M. Herrell, Cassini/Huygens science instruments, spacecraft, and mission,J. Spacecr. Rockets, 34, No. 4, 509-521, July-August 1997.

Matson, D. L., et al., The Cassini/Huygens mission to the Saturnian System, Space Sci. Rev.,104, No. 1-4, 1-58, doi:10.1023/A:1023609211620, 2002.

Other Cassini Information/Data at NSSDC

Information about Huygens

Related Information/Data at NSSDC

Venus pageEarth pageMoon pageAsteroid & Comets pageJupiter pageSaturn page

Other Sources of Cassini Information/Data

Cassini Project page (JPL)

Cassini Plasma Spectrometer (CAPS)Cosmic Dust Analyzer (CDA)Composite Infrared Spectrometer (CIRS)Ion and Neutral Mass Spectrometer(INMS)Imaging Science Subsystem (ISS)Magnetometer (MAG)Magnetospheric Imaging Instrument(MIMI)Radio and Plasma Wave Science (RPWS)Ultraviolet Imaging Spectrograph (UVIS)Visual and Infrared Mapping Spectrometer (VIMS)

Radioisotope Thermal Generators (RTGs) (Answers to questions about Cassini's use ofradioactive materials for power generation)

+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, II

http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1997-061C

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

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

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

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

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

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

http://saturn.jpl.nasa.gov/

http://caps.space.swri.edu/

http://www.mpi-hd.mpg.de/dustgroup/cassini/

http://cirs.gsfc.nasa.gov/

http://sprg.ssl.berkeley.edu/inms/

http://ciclops.lpl.arizona.edu/

http://www.sp.ph.ic.ac.uk/cassini/

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

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

http://lasp.colorado.edu/cassini/

http://wwwvims.lpl.arizona.edu/

http://saturn.jpl.nasa.gov/spacecraft/safety.cfm

http://www.usa.gov/




Cassini- Huygens

DESCRIPCIÓN:

La misión principal de la sonda Cassini es el estudio del planeta Saturno, su sistema de anillos y sus satélites. Va acompañada de la sonda de descenso europea Huygens que penetrará en Titán, el mayor satélite del planeta y el más interesante desde el punto de vista científico y biológico de todo el Sistema Solar. Este proyecto es fruto de la cooperación entre la agencia espacial norteamericana NASA y la agencia espacial europea ESA y es el mayor proyecto jamás emprendido por ambas agencias. Las naves son las mejor equipadas y preparadas de todas las lanzadas hasta la fecha y se han diseñado y construido para disminuir al mínimo las posibilidades de fallos de componentes. El número de piezas mecánicas es ínfimo y la mayoría han sido sustituidas por elementos fijos y que no requieran mecanismos, dado que son los que mayores fallos presentan. PREPARACIÓN:

Todo comenzó en el año 1.982, cuando los comités científicos de la Academia Nacional de Ciencias de los Estados Unidos y la Fundación Europea de Ciencia propusieron, como siguiente paso en la exploración de nuestro Sistema Solar, el envío de una sonda a Titán y Saturno para estudiarlos en profundidad. Otras sondas ya habían pasado por allí o estaban a punto de hacerlo y ya estaba en desarrollo una misión a Júpiter (la misión Galileo), por lo que el próximo objetivo debía de ser Saturno y Titán. En 1.983, el Comité de Exploración del Sistema Solar propone a la NASA el envío de una misión a Saturno y una sonda de descenso a Titán y en 1.985 una reunión conjunta de la NASA y la ESA perfila los detalles del proyecto. En 1.988 la NASA realiza el estudio completo del orbitador de Saturno mientras la Agencia Europea desarrolla los planos del módulo de descenso a Titán. Poco después comenzará la construcción de ambas sondas. EL LANZAMIENTO:

La sonda Cassini/Huygens fue lanzada desde Cabo Cañaveral el 15 de octubre de 1.997 a las 08:43 GMT. usando para ello un cohete Titan IV/B de dos etapas, con una 3ª etapa superior Centaur. Para llegar a su destino, la nave ha usado la técnica de sobrevuelo de planetas para aumentar su velocidad y tomar la dirección final hacia Saturno. En total se realizaron cuatro sobrevuelos, dos a Venus, uno a la Tierra y otro a Júpiter. En todo este tiempo, desde el lanzamiento hasta varios meses después de sobrevolar nuestro planeta, la nave se ha mantenido orientada con su antena principal hacia el Sol para proteger a los instrumentos del calor, ya que la nave se acercará hasta los 90 millones de kilómetros de nuestra estrella. Los sobrevuelos de Venus tuvieron lugar en abril de 1.998 y en junio de 1.999 a una velocidad de 13,6 km/s y en ambos se 'despertaron' algunos de los instrumentos para tomar datos científicos que serían posteriormente enviados a la Tierra. Cincuenta y cinco días después del segundo sobrevuelo de Venus, el 18 de agosto, la nave llegó a la Tierra sobrevolándola a unos 1.000 kilómetros de distancia con una velocidad de 19 km/s (68.000 km/h !!!) y en esta ocasión nueve de los instrumentos fueron activados y realizaron observaciones del sistema Tierra-Luna. Fotografías del sobrevuelo tomadas desde la Tierra. Por último tuvo lugar el esperado encuentro con Júpiter a más de 9,7 millones de kilómetros de distancia del planeta. A pesar de tan lejana distancia, la nave obtuvo datos muy valiosos sobre la atmósfera de Júpiter y otros datos de la magnetosfera que serán contrastados con los obtenidos por la Galileo y que realizó observaciones simultaneamente. Después del encuentro algunos de los instrumentos de la nave Cassini permanecerán encendidos durante algunos meses

para intentar detectar las ondas de los campos gravitatorios y realizar otros experimentos de campos magnéticos. FECHAS PRINCIPALES DE LA MISIÓN:

- Fecha de Lanzamiento: 15-octubre-1.997 (08:43 GMT) - Sobrevuelo de Venus 1: 26-abril-1.998 - Sobrevuelo de Venus 2: 24-junio-1.999 (20:30 GMT a 598 km) - Sobrevuelo de La Tierra: 18-agosto-99 (03:28 GMT a 1.166 km) - Sobrevuelo Masursky: 23-enero-00 (09:35 GMT a 1.6 mill.km) - Sobrevuelo de Jupiter: 30-dic-2.000 (03:00 GMT a 9.7 mill. km) - Llegada a Saturno: 01-julio-2.004 - Sobrevuelo de Titán 1: 26-octubre-2.004 - Sobrevuelo de Titán 2: 13-diciembre-2004 - Suelta de la sonda Huygens: 25-diciembre-2.004 - Descenso de Huygens en Titán: 14-enero-2.005 ENCUENTRO CON EL ASTEROIDE 2685 MASURSKY - 23.01.00:

La sonda Cassini pasó el día 23 de enero de 2.000 a una distancia de 1,6 millones de km. del asteroide Masursky lo que aprovechó para tomar dos imágenes, una de ellas con alta resolución. Dada la lejanía de la sonda, las imágenes no revelan ningún detalle pero permiten a los científicos calcular su diámetro y algunas propiedades de los materiales que componen su superficie. Además ha permitido probar el sistema de guiado

automático de la cámara y comprobar que funciona tal y como estaba previsto. Las 2 imágenes fueron tomadas 7 y 5 horas antes del máximo acercamiento y nos darán algunas pistas sobre que tipo de asteroide es y su periodo de rotación. Las estimaciones indican que su tamaño oscila entre los 15 y 20 km. ENCUENTRO CON JÚPITER - 30.12.00 - WEBS: JUPITER MILLENNIUM FLYBY y CASSINI JUPITER

FLYBY SCIENCE PAGE: En su camino hacia Saturno, la sonda Cassini/Huygens pasó por las cercanías de Júpiter a finales del año 2.000. Además de la importancia del acercamiento al planeta, este encuentro tuvo especial significado no sólo por el hecho de servir como tests a los instrumentos de la Cassini, sino que permitió comparar los datos obtenidos con los de la sonda Galileo que se encontraba en órbita de Júpiter en aquel momento. Era la primera vez que dos sondas obtenían datos simultáneamente de un planeta que no fuese la Tierra. El equipo científico de Cassini programó toda una serie de experimentos y puso a funcionar los equipos de la nave desde octubre de 2.000 hasta marzo de 2.001 para tomar los máximos datos posibles. En total 12 instrumentos tomaron datos durante estos días, entre los cuales destacan las cámaras de la Cassini que tomaron miles de fotografías, componiendo mosaicos y animaciones de la atmósfera y los satélites del planeta. Además se estudió el comportamiento dinámico de la atmósfera, su composición, los campos magnéticos y su interacción con los satélites y los volcanes de Io.

La sombra de Io.

Las bandas de Júpiter.

Júpiter en color verdadero y falso color.

Volcanes en Io. LA MISIÓN HUYGENS REVISADA. JUNIO 2.001.

La alarma saltó en el otoño del año 2.000. Un fallo en el diseño del sistema de comunicaciones de la sonda Huygens hacía imposible la comunicación con la nave Cassini y por tanto el envío de los datos que pudiera tomar durante el descenso y el aterrizaje. Al alejarse la sonda Huygens de la nave Cassini y aumentar las distancias entre ellas, se producía un efecto Doppler en las señales de radio que la sonda de descenso era incapaz de compensar. Un 'grupo de recuperación' de la sonda Huygens se puso a trabajar durante seis meses y rediseñó por completo la fase inicial de la misión orbital incluyendo las fechas de descenso y el recorrido de ambas sondas. El descenso original planeado para noviembre de 2.004 tuvo que ser aplazado siete semanas hasta el 14 de enero de 2.005. Desde la llegada a Saturno en julio de 2.004 hasta febrero de 2.005, la sonda Cassini realizará tres sobrevuelos de Titán en vez de los dos previstos antes de soltar la sonda, de manera que las dos primeras órbitas serán acortadas para dar lugar a una tercera órbita antes de febrero, que permite una nueva geometría en el descenso de forma que Cassini sobrevolará Titán a 65.000 kilómetros de altura en vez de los 1.300 km. previstos. Estos cambios suponen consumir entre un cuarta y una tercera parte del combustible de reserva de la nave para la extensión de la misión más allá del año 2.008. De esta forma el primer sobrevuelo de Titán será el 26 de octubre y el segundo el 13 de diciembre. La sonda

será soltada el 25 de diciembre para su entrada 22 días después. A partir de febrero continuará la misión tal y como estaba prevista. LA NAVE CASSINI:

Su peso en el lanzamiento era de 5.600 kg. de los cuales 2.500 kg. corresponden a la nave en sí y el resto es combustible. Sus dimensiones son 6,8 metros de altura y 4 metros de ancho. Para la propulsión posee dos motores de 450 Newtons de empuje cada uno. La energía es proporcionada por tres generadores termoeléctricos de radioisótopos. Sus múltiples instrumentos se clasifican en dos grandes grupos: ópticos de sensores remotos, formados por las cámaras y espectrómetros y el grupo de instrumentos de campos y partículas que medirán la magnetosfera, las radiaciones y las partículas del entorno. INSTRUMENTOS CASSINI:

Sensores de óptica remotos: - Composite Infrared Spectrometer (CIRS): es un espectrómetro doble evolucionado del instrumento IRIS de la nave Voyager pero con una resolución 10 veces mayor. Su objetivo es medir la radiación infrarroja de las atmósferas, los anillos y las superficies de los satélites en el rango de longitudes de onda del milímetro a los 7 micrones, es decir, el infrarrojo lejano y medio. Con ello se obtendrán mapas de temperaturas de Titán y

Saturno, las composiciones de sus atmósferas, nubes, procesos energéticos, composición de los anillos de Saturno y temperaturas de la superficie de Titán. - Imaging Science Subsystems (ISS): Es un conjunto de dos cámaras en luz visible, una de campo ancho para tomas amplias y otra de campo estrecho con mayor resolución, ambas con sensores CCD de 1.024x1.024. Su objetivos son fotografiar el movimiento de las atmósferas de Titán y Saturno, estudiar la composición y características de las nubes y aerosoles, hacer mapas de las superficies de los satélites, estudiar los anillos de Saturno y determinar la composición y rotación de los satélites menores del planeta. Más información e imágenes en CICLOPS - Universidad de Arizona. - Ultraviolet Imaging Spectrograph (UVIS): Es un espectrómetro ultravioleta encargado de medir la luz en esa longitud de onda de las atmósferas, los anillos y las lunas de Saturno. De esta forma se podrá determinar la composición de las atmósferas, la distribución de elementos, la circulación atmosférica, la estructura de los anillos y las lunas heladas. Más información en la Universidad de Colorado. - Visual and Infrared Mapping Spectrometer (VIMS): espectrómetro en infrarrojo cercano y luz visible. Servirá para medir la composición, estructuras y temperaturas de las atmósferas de Saturno y sus lunas, sirviendo para observar la superficie de Titán, la estructura de los anillos, las tormentas en Saturno y volcanes en Titán. Sensores de microondas remotos: - Cassini Radar (RADAR): Este experimento se basará en el uso de la antena de alta ganancia de la nave ( la antena principal ), para realizar las transmisiones de radar contra la superficie de Titán y averiguar si está se encuentra en estado sólido o líquido y su distribución, además de trazar un mapa topográfico y geológico del satélite. Más información en la página Cassini-Radar. - Radio Science Subsystem (RSS): Usa los sistemas de comunicación por radio para medir la composición, presiones y temperaturas de las atmósferas y estructuras de los anillos. Campos, partículas y ondas: - Cassini Plasma Spectrometer (CAPS): Mide el flujo de iones y electrones en función de su masa y su carga. Es uno de los instrumentos más completos y servirá para medir la composición de las moléculas ionizadas, la magnetosfera, las auroras y el plasma del medio interestelar, de Saturno y de Titán. - Cosmic Dust Analyzer (CDA): Analizador de Polvo Cósmico. Dará datos directos de las partículas que se encuentran en el entorno del planeta, para investigar la física, la química y las propiedades dinámicas de estas partículas y su interacción con los satélites, la magnetosfera y los anillos. Más información: Max Planck Institute. - Ion and Neutral Mass Spectrometer (INMS): Medirá los iones positivos y las moléculas neutras de las capas altas de la atmósfera de Titán y la magnetosfera de Saturno. - Dual Technique Magnetometer (MAG): Su principal objetivo es determinar los campos magnéticos planetarios para hacer modelos en tres dimensiones y su interacción con el polvo y los anillos de Saturno. - Magnetospheric Imaging Instrument (MIMI): Está diseñado para medir la composición, cargas eléctricas y energías de los iones y electrones de la magnetosfera y el plasma. Más información. - Radio & Plasma Wave Science (RPWS): Medirá los campos eléctricos y magnéticos, la densidad de electrones y la temperatura en el medio interplanetario y la magnetosfera. Más información. Además existen una serie de grupos llamados de 'ciencia interdisciplinaria' cuya misión es sacar conclusiones sobre los anillos, satélites, atmósferas y magnetosferas usando los datos de varios de los instrumentos simultáneamente. SONDA DE DESCENSO HUYGENS.

La sonda ha sido diseñada y construida por la Agencia Espacial Europea y tiene un peso total de 350 kg. Su misión principal será descender por la atmósfera de Titán en paracaídas durante 150 minutos como máximo para posarse en la superficie y permanecer en ella funcionando un mínimo de tres minutos (y es posible que dure hasta media hora). Durante este periodo de tiempo analizará la atmósfera tomando muestras de los aerosoles presentes en ella y hará mediciones espectrales, analizando su composición y propiedades. También tomará fotografías de la superficie y características del suelo ya que hasta ahora no conocemos la composición ni el estado de la superficie y si hay océanos de metano líquido en ella. La nave Cassini apuntará directamente hacia la superficie de Titán durante el tiempo que dure el descenso y la media hora posterior para volverse a girar de nuevo hacia la Tierra y retransmitir los datos tomados por Huygens. El descenso. El 6 de noviembre de 2.004, unos pequeños explosivos separarán a Huygens de la sonda Cassini y en esos momentos comenzará a distanciarse a una velocidad de 30 cms por segundo y realizando 7 giros sobre si misma por minuto para estabilizarse. Entonces se dirigirá a su punto de aterrizaje en el hemisferio norte de Titán en una zona de la cara iluminada en esos momentos por el Sol. La entrada se realizará el día 14 de enero a una velocidad de 6,1 km/s a una altitud de 1.270 km. sobre la superficie. Para protegerse de las altas temperaturas en esta fase (hasta 12.000ºC) lleva un escudo protector que la protege y ayuda al frenado de la sonda. A unos 300 km. de altura la velocidad desciende hasta 20 veces la velocidad del sonido. Poco después a 180 km. de altura y a 2 veces la velocidad del sonido (600 m/s), se abre un paracaidas auxiliar que tirará hacia afuera del paracaidas principal que quedará completamente abierto en menos de 3 segundos. A 170 km. de altura la velocidad ha quedado reducida a 80 m/s, sólo 30 segundos después de abrirse el paracaidas. En ese instante se desprende el escudo protector y se despliegan los instrumentos y pies de aterrizaje. Tras 15 minutos descendiendo por las capas bajas de la atmósfera y a 110 km. de la superficie y a una velocidad de 40 m/s, se desprende el paracaidas principal, quedando solamente uno más pequeño que sirve para estabilizar la nave. Unas dos horas después (como máximo), la sonda hará contacto con la supeficie y tomará datos de ella durante un periodo que puede oscilar entre los 3 y los 30 minutos.

La sonda porta en total seis instrumentos entre los que se encuentran cámaras y espectrómetros que medirán la neblina de la atmósfera, su composición y los vientos. INSTRUMENTOS DE HUYGENS: - Huygens Atmospheric Structure Instrument (HASI): Consiste en una serie de sensores que miden las propiedades eléctricas y físicas de la atmósfera de Titán. Unos acelerómetros medirán las fuerzas en las 3 direcciones para conocer los movimientos de la sonda durante el descenso. Si la superficie fuese líquida se apreciaría el movimiento ondulatorio con este sistema. Además lleva sensores de presión y temperatura que permitirán conocer la estructura de la atmósfera. Un analizador de ondas electromagnéticas y permitividad medirá la conductividad de los electrones e iones de la atmósfera. También detectará los posibles relámpagos y truenos mediante un micrófono. Este instrumento ha sido construido y diseñado en parte en el Instituto de Astrofísica de Andalucía y supone la primera participación española en una sonda interplanetaria. Más información.

- Doppler Wind Experiment (DWE): Usará un oscilador ultraestable para permitir que la frecuencia en la que transmite la sonda permanezca estable y contrarrestar el efecto Doppler debido a los movimientos de la sonda empujada por los vientos de Titán y los balanceos del paracaídas y se podrán deducir características de la atmósfera. Más información. - Aerosol Collector and Pyrolyser (ACP): A través de unos filtros cogerá muestras de la atmósfera que serán calentadas para conocer su composición. Las muestras se tomarán a diferentes alturas. Más información. - Descent Imager/Spectral Radiometer (DISR): Tomará imágenes y espectros durante el descenso de la sonda. Unos sensores de luz determinarán la intensidad de la radiación solar en cada momento y la absorción de la luz por los aerosoles, lo que permitirá determinar el número y tamaño de esas partículas. Una cámara en luz visible y otra en infrarrojo tomarán imágenes durante las últimas fases del descenso y se podrá construir un mosaico de imágenes de la zona de aterrizaje al ir girando la nave al bajar. Además se harán tomas del horizonte y las nubes. En caso de que la luz sea baja, la sonda lleva una lampara para iluminar el terreno. Más información. - Gas Chromatograph Mass Spectrometer (GCMS): Es un analizador químico de gases que identificará los constituyentes de la atmósfera. Tiene unas cápsulas que se irán llenado con los gases de la atmósfera durante la fase inicial del descenso, para ser analizados en la última fase del mismo. En caso de un aterrizaje (¿atitanzaje?) seguro, analizará también la composición del terreno o líquido que la rodee. - Surface-Science Package (SSP): Es el conjunto de nueve instrumentos que comenzarán a funcionar en el momento de tomar tierra (o 'líquido'). Un sónar empezará a funcionar 100 metros antes de llegar al suelo y determinará la distancia al mismo para seguridad de la sonda y averiguará la rugosidad de la superficie. Si la superficie es líquida medirá la velocidad del sonido en dicho líquido y su profundidad. Las medidas de la velocidad del sonido durante el descenso permitirá conocer más datos de la atmósfera y su temperatura. Una vez en tierra diversos sensores medirán densidades, temperaturas, índices de refracción, conductividad térmica, capacidad calorífica y permitividad eléctrica.




Description

Celestis was a microcapsule launched along with Minisat fromthe Spanish Canary Islands. It was developed by OrbitalSciences Corporation for the Celestis Inc of Florida and carriedashes of some long-deceased people into space. More suchcapsules may be available for past and future ashes.

Celestis

NSSDC ID: 1997-018B

Alternate Names

24780

Facts in Brief

Launch Date: 1997-04-21LaunchVehicle: Pegasus XLLaunch Site: CanaryIslands, Spain

Funding Agency

Unknown (United States)

Discipline

Other


Launch/Orbitalinformation for Celestis

Experiments on Celestis

Data collections fromCelestis



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Celestis (1997-018B)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1997-006D[13/06/2011 23:30:49]


Description

Cosmos 2337 was a Russian military spacecraft launched fromthe Plesetsk cosmodrome aboard a Tsyklon 3 rocket. It waslaunched along with Gonets D1-4, D1-5, D1-6, and Cosmos2338 and 2339. It provided military data messaging and photoreconnaissance for the Russian Federation Ministry ofDefense.

Cosmos 2337

NSSDC ID: 1997-006D

Alternate Names

24728

Facts in Brief

Launch Date: 1997-02-13LaunchVehicle: Cyclone 3Launch Site: Plesetsk,RussiaMass: 225.0 kg

Funding Agency

Unknown (Russia)

Discipline

Surveillance and OtherMilitary


Launch/Orbitalinformation for Cosmos2337

Experiments on Cosmos2337

Data collections fromCosmos 2337



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1997-006D



http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Cosmos 2337


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Cosmos 2337


mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 2337 (1997-006D)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1997-006E[13/06/2011 23:31:10]


Description


Cosmos 2338

NSSDC ID: 1997-006E

Alternate Names

24729

Facts in Brief


Funding Agency

Unknown (Russia)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1997-006E







mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 2338 (1997-006E)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1997-006F[13/06/2011 23:31:42]


Description


Cosmos 2339

NSSDC ID: 1997-006F

Alternate Names

24730

Facts in Brief


Funding Agency

Unknown (Russia)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1997-006F







mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 2339 (1997-006F)











http://www.usa.gov/








Description

Cosmos 2340 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 8/9 - 217 degree longitude of ascendingnode.

Cosmos 2340

NSSDC ID: 1997-015A

Alternate Names

24761

Facts in Brief

Launch Date: 1997-04-09LaunchVehicle: Molniya-MLaunch Site: Plesetsk,Russia

Funding Agency

Russian Space Agency(U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data











mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 2340 (1997-015A)











http://www.usa.gov/








Description

Cosmos 2341 was part of a 6-satellite Russian militarynavigation system distributed in orbital planes spaced 30degrees apart, and launched from the Plesetsk cosmodromeaboard a Cosmos rocket. Navigation information was derivedfrom Doppler-shifted VHF transmissions (approximately 150and 400 MHz) of the satellite position and orbital data. Byacquiring fixes from several satellite, a user's location could becalculated with an accuracy of 100 m. The time needed toascertain a position was dependent upon the user's latitudeand the number of operational spacecraft in orbit. Normally,accurate location determination could be made within 1-2hours.

Cosmos 2341

NSSDC ID: 1997-017A

Alternate Names

24772

Facts in Brief

Launch Date: 1997-04-17LaunchVehicle: CosmosLaunch Site: Plesetsk,U.S.S.R

Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 2342 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 2342

NSSDC ID: 1997-022A

Alternate Names

24800

Facts in Brief


Funding Agency

Russian Space Agency(Russia)

Discipline








Spacecraft

Experiments

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Personnel

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Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 2343 was the sixth of the sixth generation photoreconnaisance satellites launched from the Baikonurcosmodrome using the Soyuz-U2 launch vehicle, which hadotherwise been restricted to supporting Soyuz-TM andProgress-M missions. The spacecraft was inserted into anorbital inclination of 64.8 degrees with mean operationalaltitudes normally between 240 and 260 km. The sixthgeneration spacecraft, believed to carry both film returncapsules and digital transmission capabilities, have only flownsix times; once each year during 1989-1993 and once in 1997.After returning multiple film capsules, the spacecraft wasdeorbited. This satellite provided Russia with the photoresonnaisance capability after a break of 7 1/2 months. Thislaunch came on the 40th anniversary of the first successfullaunch of the R-7 rocket, from which the Soyuz-U was derived.It was the 250th launch of the Soyuz-U from Baikonur, the350th launch from Launch Complex 31, and the 666th launchof a Soyuz-U.

Cosmos 2343

NSSDC ID: 1997-024A

Alternate Names

24805

Facts in Brief

Launch Date: 1997-05-15LaunchVehicle: Soyuz-ULaunch Site: Tyuratam(Baikonur Cosmodrome),Kazakhstan

Funding Agency

Unknown (Russia)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Launched from the Baikonur cosmodrome on a Proton rocket,Cosmos 2344 was a new advanced Russian 20 ton imagingreconnaissance satellite the size of a school bus andresembling the Hubble Space Telescope. It was placed in anorbit of 2740 x 1500 km, with an inclination of 63.4 degrees. Itrepeated its ground track every 24 hours. The orbit provided awider field of view and a slower overflight time. It supposedlywas designed to provide wide area surveillance at 2-5 meterresolution. The spacecraft's powerful telescope could bepointed to multiple targets as far as 1000 km off its track. Itused folded optics to achieve a 27 meter imaging focal length.It's reported to work in the visible and near infrared spectrum.

Cosmos 2344

NSSDC ID: 1997-028A

Alternate Names

24827

Facts in Brief

Launch Date: 1997-06-06LaunchVehicle: Proton-KLaunch Site: Tyuratam(Baikonur Cosmodrome),Kazakhstan

Funding Agency

Unknown (Russia)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 2345 is a Russian military geosynchronouscommunications spacecraft that was launched by a Proton-Krocket from Baykonur cosmodrome at 20:49 UT. Parkinglongitude is not available.

Cosmos 2345

NSSDC ID: 1997-041A

Alternate Names

24895

Facts in Brief


Funding Agency

Unknown (Russia)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 2346 was part of a 6-satellite Russian militarynavigation system distributed in orbital planes spaced 30degrees apart, and launched from the Plesetsk cosmodromeaboard a Cosmos rocket. Navigation information was derivedfrom Doppler-shifted VHF transmissions (approximately 150and 400 MHz) of the satellite position and orbital data. Byacquiring fixes from several satellite, a user's location could becalculated with an accuracy of 100 m. The time needed toascertain a position was dependent upon the user's latitudeand the number of operational spacecraft in orbit. Normally,accurate location determination could be made within 1-2hours.

Cosmos 2346

NSSDC ID: 1997-052A

Alternate Names

24953

Facts in Brief

Launch Date: 1997-09-23LaunchVehicle: CosmosLaunch Site: Plesetsk,Russia

Funding Agency

Unknown (Russia)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 2347 was a Russian naval reconnaisance satellitelaunched from the Baikonur cosmodrome aboard a Tsyklon 2rocket. This naval forces monitoring spacecraft was used todetermine the position of enemy naval forces through detectionand triangulation of their electromagnetic emissions (radio,radar, etc).

Cosmos 2347

NSSDC ID: 1997-079A

Alternate Names

25088

Facts in Brief

Launch Date: 1997-12-09LaunchVehicle: Tsiklon-2Launch Site: Tyuratam(Baikonur Cosmodrome),KazakhstanMass: 6500.0 kg

Funding Agency

Unknown (Russia)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 2348 was a Russian military photo reconnaissancespacecraft in the Yantar-4K class ("Kobalt") subseries, a fourthgeneration close-look photo reconnaissance satellite. It carrieda main descent module and two smaller externally mounteddata return capsules which could be ejected and returned toEarth while the main payload remained in orbit. The mainvehicle returned the camera system at the end of the mission,typically 2-3 months.

Cosmos 2348

NSSDC ID: 1997-080A

Alternate Names

25095

Facts in Brief

Launch Date: 1997-12-15LaunchVehicle: Soyuz-ULaunch Site: Plesetsk,RussiaMass: 6500.0 kg

Funding Agency

Unknown (Russia)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

CHRISTA-SPAS 2 (Cryogenic Infrared Spectrometers andTelescopes for the Atmosphere-Shuttle Pallet Satellite 2) wasa German-American free-flying module that was released fromthe Shuttle Remote Manipulator System (RMS) on STS 85 tomonitor atmospheric constituents (ozone, etc.) of the middleatmosphere by means of infrared spectrometers. It wasretrieved by the Shuttle RMS after nine days of free flying inthe vicinity of the Shuttle. During its free flight about 66minirockets and balloons were launched by the United Statesand Germany to concurrently monitor the same regions of theatmosphere as the spacecraft did. Initial orbital parameters ofthe spacecraft were close to those of the Shuttle.

The primary experiment was the CRISTA, a system of threetelescopes and four spectrometers to measure infraredradiation emitted by the Earth's middle atmosphere. Acomplementary instrument called MAHRSI (MiddleAtmosphere High Resolution Spectrograph Investigation) wasalso carried on the payload together with a passive experimentcalled SESAM (Surface Effects Sample Monitor). MAHRSImeasured ultraviolet radiation emitted and scattered by theEarth's atmosphere.

Two additional experiments were mounted on the SPAS andwere activated during free-flight. The Mini Dual Earth Sensor(MiDES) was used to gather operational data of the Earthhorizon positions, and the Interferometry Program Experiment-II (IPEX-II) to measure the vibration of the SPAS structure.

CRISTA-SPAS 2

NSSDC ID: 1997-039B

Alternate Names

Cryogenic IRSpectrometers andTelescopes for theAtmosphere

Shuttle Palette Satellite 2

24890

Facts in Brief

Launch Date: 1997-08-07LaunchVehicle: ShuttleLaunch Site: CapeCanaveral, United States

Funding Agencies

German Space Agency(Federal Republic ofGermany)

NASA Office of Mission toPlanet Earth (UnitedStates)

Discipline

Earth Science


Launch/Orbitalinformation for CRISTA-SPAS 2

Experiments on CRISTA-SPAS 2

Data collections fromCRISTA-SPAS 2

Questions or commentsabout this spacecraft canbe directed to: Coordinated


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


CRISTA-SPAS 2





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

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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: CRISTA-SPAS 2 (1997-039B)









http://nssdc.gsfc.nasa.gov/image/spacecraft/crista-spas2.jpg



Request and User SupportOffice.


STS 85 (CRISTA-SPAS 2 deployment mission)

Other sources of CRISTA-SPAS 2 data/information

CRISTA home page (U. of Wuppertal)MAHRSI home page (NRL)




http://www.crista.uni-wuppertal.de/crista_index.shtml

http://uap-www.nrl.navy.mil/mahrsi/mahrsi.html

http://www.usa.gov/








Description

DMSP 5D-2/F14, also named USA 131, is one of a series ofmeteorological satellites developed and operated by the AirForce under the Defense Meteorological Satellite Program(DMSP). This program, previously known as DAPP (DataAcquisition and Processing Program), was classified untilMarch 1973. The objective of this program is to provide globalvisual and infrared cloudcover data and specializedenvironmental data to support Department of Defenseoperational weather analysis and forecasting requirements.Operationally, the program consists of two satellites in sun-synchronous polar orbits, with the ascending node of onesatellite in early morning and the other at local noon.

The 6.4-m-long spacecraft is separated into four sections: (1) aprecision mounting platform for sensors and equipmentrequiring precise alignment; (2) an equipment support modulecontaining the electronics, reaction wheels, and somemeteorological sensors; (3) a reaction control equipmentsupport structure containing the third-stage rocket motor andsupporting the ascent phase reaction control equipment; and(4) a 9.29-sq-m solar cell panel. The spacecraft stabilization iscontrolled by a combination flywheel and magnetic control coilsystem so that sensors are maintained in the desired earth-looking mode. One feature is the precision-pointing accuracyof the primary imager to 0.01 deg provided by a star sensorand an updated ephemeris navigation system. This allowsautomatic geographical mapping of the digital imagery to thenearest picture element.

The operational linescan system is the primary data acquisitionsystem and provides real-time or stored, multi-orbit, day-and-night, visual and infrared imagery of clouds. A supplementarysensor package contains: (1) a microwave imager; (2) amicrowave temperature sounder; (3) a microwave water vaporprofiler; (4) an ion and electron scintillation monitor; (5) aprecipitating electron/ion spectrometer; (6) a gamma/X-raydetector; (7) a magnetometer; and (8) a static earth-viewingsensor monitoring electromagnetic radiation.

Additional information concerning the satellite can be found inthe report by D. A. Nichols, "The Defense MeteorologicalSatellite Program," Optical Engineering, v. 14, n. 4, p. 273,July-August 1975.

DMSP 5D-2/F14

NSSDC ID: 1997-012A

Alternate Names

DMSP-F14

USA 131

24753

Facts in Brief

Launch Date: 1997-04-04Launch Vehicle: Titan IILaunchSite: Vandenberg AFB,United States

Funding Agency

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

Disciplines

Earth Science


Space Physics


Launch/Orbitalinformation for DMSP 5D-2/F14

Telecommunicationsinformation for DMSP 5D-2/F14

Experiments on DMSP 5D-2/F14

Data collections fromDMSP 5D-2/F14

Questions or commentsabout this spacecraft can


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data









http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=DMSP 5D-2/F14

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=DMSP 5D-2/F14

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=DMSP 5D-2/F14

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=DMSP 5D-2/F14











be directed to: Dr. Dieter K.Bilitza.

Other Sources of DMSP Data/Information

SSIES ion data (U. Texas - Dallas)DMSP data (National Geophysical Data Center)DMSP F14 summary (NASA MSFC)


mailto:[email protected]?Subject=NMC Comment/Question: DMSP 5D-2/F14 (1997-012A)

mailto:[email protected]?Subject=NMC Comment/Question: DMSP 5D-2/F14 (1997-012A)

http://cindispace.utdallas.edu/DMSP/

http://dmsp.ngdc.noaa.gov/dmsp.html

http://microwave.msfc.nasa.gov:5721/source_documents/dmsp_f14.html

http://www.usa.gov/








Description

DFH-3 was a Chinese communications satellite launched intogeosynchronous orbit at 125 deg E. It was built by the ChineseTelecomms Broadcast Satellite Company of Beijing.

Dongfanghong 3

NSSDC ID: 1997-021A

Alternate Names

DFH 3

24798

Facts in Brief

Launch Date: 1997-05-11Launch Vehicle: LongMarchLaunch Site: Xichang,Peoples Republic of ChinaMass: 2266.0 kg

Funding Agency

Unknown (PeoplesRepublic of China)

Discipline

Communications


Launch/Orbitalinformation forDongfanghong 3

Experiments onDongfanghong 3

Data collections fromDongfanghong 3



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







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

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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Dongfanghong 3 (1997-021A)











http://www.usa.gov/








Description

Defense Satellite Communications System (DSCS III-B13) waspart of a US military satellite constellation place ingeosynchronous orbit to provide high-volume, secure voiceand data communications. Phase II was a successor to theIDSCS (Initial Defense Satellite Communications System)program which began in 1966 with the launch of the first 8satellites of this constellation. The DSCS III system was usedfor high priority communications such as the exchange ofwartime information between defense officials and battlefieldcommanders. The military also used DSCS to transmit spaceoperations and early warning data to various systems andusers.

Each satellite orbits the earth at an altitude of more than23,000 miles. They carried a single channel transponder usedfor disseminating emergency action and force directionmessages to nuclear capable forces. Each satellite utilized sixsuper high frequency transponder channels capable ofproviding worldwide secure voice and high rate datacommunications.

DSCS III-B13

NSSDC ID: 1997-065A

Alternate Names

Defense Sat CommunSystem III-B13

25019

Facts in Brief

Launch Date: 1997-10-24Launch Vehicle: Atlas2ALaunch Site: CapeCanaveral, United States

Funding Agency


Discipline

Communications


Launch/Orbitalinformation for DSCS III-B13

Experiments on DSCS III-B13

Data collections fromDSCS III-B13



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=DSCS III-B13

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=DSCS III-B13

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=DSCS III-B13

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=DSCS III-B13

mailto:[email protected]?Subject=NMC Comment/Question: DSCS III-B13 (1997-065A)











http://www.usa.gov/








Description

Dummy S1 is one of two dummies simulating IRIDIUMspacecraft. They were launched by a (newly developed) LongMarch 2-3 rocket from the new Taiyuan launch center. Thegoal was to offer the Long March 2-3 as a potential carrier forfuture launches of IRIDIUMs.

Dummy S1

NSSDC ID: 1997-048A

Alternate Names

24925

Facts in Brief

Launch Date: 1997-09-01Launch Vehicle: LongMarch 2-3Launch Site: Taiyuan,Peoples Republic of ChinaMass: 680.0 kg

Funding Agency


Discipline

Communications


Launch/Orbitalinformation for DummyS1

Experiments on Dummy S1

Data collections fromDummy S1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Dummy S1

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Dummy S1


mailto:[email protected]?Subject=NMC Comment/Question: Dummy S1 (1997-048A)











http://www.usa.gov/








Description

Dummy S2 is one of two dummies simulating IRIDIUMspacecraft. They were launched by a (newly developed) LongMarch 2-3 rocket from the new Taiyuan launch center. Thegoal was to offer the Long March 2-3 as potential carrier forfuture launches of IRIDIUMs.

Dummy S2

NSSDC ID: 1997-048B

Alternate Names

24926

Facts in Brief

Launch Date: 1997-09-01Launch Vehicle: LongMarch 2-3Launch Site: Taiyuan,Peoples Republic of ChinaMass: 680.0 kg

Funding Agency


Discipline

Communications


Launch/Orbitalinformation for DummyS2

Experiments on Dummy S2

Data collections fromDummy S2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Dummy S2



mailto:[email protected]?Subject=NMC Comment/Question: Dummy S2 (1997-048B)











http://www.usa.gov/








Description

Early Bird 1 was an imaging satellite developed for theEarthWatch, Inc remote sensing company. It contained apanchronmatic (93 m resolution) and a multispectral scanner(15 m resolution). The Vector receiver was used for on-boardattitude, positioning, and timing, and the Viceroy for on-boardpositioning and timing. Both receivers provided rawpsuedorange and carrier phase data for precise postprocessed orbit determination.

Early Bird 1

NSSDC ID: 1997-085A

Alternate Names

25123

Facts in Brief

Launch Date: 1997-12-24Launch Vehicle: ICBMRS-12M Topol or SS-25Sickle, 3-stage SRMLaunch Site: Svobodniy,Russia

Funding Agency

Earth Watch, Inc (UnitedStates)

Discipline

Earth Science


Launch/Orbitalinformation for Early Bird1

Experiments on Early Bird1

Data collections from EarlyBird 1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







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

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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Early Bird 1 (1997-085A)











http://www.usa.gov/








Description

Echostar 3 was an American geosynchronous communicationssatellite that was launched by an Atlas 2AS rocket from CapeCanaveral. The 4,000 kg satellite carried 16 (or more) Ku-bandtransponders to provide direct voice and videocommunications to small dishes in North America after parkingover 79 W or 135 W longitude.

Echostar 3

NSSDC ID: 1997-059A

Alternate Names

25004

Facts in Brief

Launch Date: 1997-10-05Launch Vehicle: Atlas-2 ASLaunch Site: CapeCanaveral, United StatesMass: 4000.0 kg

Funding Agency

EchostarCommunicationsCorporation (UnitedStates)

Discipline

Communications


Launch/Orbitalinformation for Echostar 3

Experiments on Echostar 3

Data collections fromEchostar 3



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Echostar 3 (1997-059A)











http://www.usa.gov/








Description

Equator-S is an element of the International Solar-TerrestrialPhysics (ISTP) program. Spacecraft design, manufacturingand testing were provided by the Max-Planck-Institut furExtraterrestrische Physik (MPE). The project was financiallysupported by DARA (Deutsche Agentur fur RaumfahrtAngelegenheiten). Some assistance and in-kind contributionswere received from ESA/ESTEC and NASA. Mission analysisand operations are the responsibility of the German SpaceOperations Center (GSOC) of the DLR. The spacecraft waslaunched December 2, 1997, as a secondary payload on anAriane IV vehicle from Kourou (French Guiana). Equator-S isdifferent from NASA's ISTP/EQUATOR spacecraft, which wasdropped when the ISTP mission was re-scoped in late 1989.

The Equator-S objectives are to provide high-resolutionplasma, magnetic, and electric field measurements in severalregions not adequately covered by the existing ISTP missions,namely the low-latitude dayside magnetopause and itsboundary layer, the equatorial ring current region, and thenear-earth equatorial plasma sheet. These regions play keyroles for our understanding of the global perspective of solar-terrestrial relations as well as the detailed plasmaphysicalprocesses.

The orbit is near-equatorial, with 500 km perigee altitude and11 Re geocentric apogee distance. The payload consists ofseven scientific instruments provided by international groups tostudy the solar wind and charged particles trapped in theearth's magnetosphere. For reasons of cost and schedule,these instruments are largely derived from engineering orspare units from other ISTP missions. Innovative sub-systemsfor solar power and orbit measurement are tested on Equator-S for the benefit of future spacecraft designs. Furthermore,some technological experiments have been added that exploitthe hard radiation environment of the Equator-S orbit or makeuse of its orbital features. These include a GaAs solar cell tocheck on temperature and I/V - characteristics, anddegradation by radiation; and a GPS receiver to study the GPScapabilities as a function of spacecraft altitude. There is also amass memory of 192 MBytes of CMOS RAM for temporarydata storage.

The rapid spacecraft spin rate (60 rpm) allows unprecedentedhigh temporal resolution of the measurements.

At the regular telemetry contact with the Weilheim ground-station on 1 May 1998, EQUATOR-S stopped sending data,although the TM-signal was unchanged. This is attributed to afailure of the redundant processor, similar to the failure of the

Equator-S

NSSDC ID: 1997-075B

Alternate Names

ISTP/Equator-S

25068

Facts in Brief

Launch Date: 1997-12-02Launch Vehicle: Ariane4Launch Site: Kourou,French GuianaMass: 250.0 kgNominal Power: 80.0 W

Funding Agency

German Space Agency(Federal Republic ofGermany)

Disciplines

Engineering

Space Physics


Launch/Orbitalinformation for Equator-S

PDMP information forEquator-S

Telecommunicationsinformation for Equator-S

Experiments on Equator-S

Data collections fromEquator-S

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


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


Equator-S




http://nssdc.gsfc.nasa.gov/nmc/spacecraftPdmp.do?id=1997-075B

http://nssdc.gsfc.nasa.gov/nmc/spacecraftPdmp.do?id=1997-075B

http://nssdc.gsfc.nasa.gov/nmc/spacecraftTelemetry.do?id=1997-075B


http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Equator-S

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Equator-S

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Equator-S

mailto:[email protected]?Subject=NMC Comment/Question: Equator-S (1997-075B)

mailto:[email protected]?Subject=NMC Comment/Question: Equator-S (1997-075B)









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



first processor on 17 December 1997. All attempts tocommand the spacecraft failed. However, GSOC will continuethis effort. If a latch-up caused by penetrating particle radiationwas the cause of the failure, there is hope that it may heal itselfupon the next eclipse (August 1998) because of the completetemporary switch-off of the electrical system.

Further information is available on WWW at the followinglocations.

http://www.mpe-garching.mpg.de/www_plas/EQS/eq-s-home.html

http://www.op.dlr.de/wt-rm/eqs_mb_e.htm

Personnel


Dr. Roy B.Torbert

Deputy MissionPrincipal Investigator

University of New Hampshire [email protected]

Dr. GerhardHaerendel

Mission PrincipalInvestigator

Max-Planck-Institut furExtraterrestrische Physik

[email protected]

Dr. GoetzPaschmann

Project Scientist Max-Planck-Institut furExtraterrestrische Physik

[email protected]

Other Sources of Equator-S Data/Information

Prime and Summary parameters (CDAWeb)




http://www.op.dlr.de/wt-rm/eqs_mb_e.htm

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

http://www.usa.gov/








Description

FAISAT-2V was a systems verification (test) satellite launchedfrom the Plesetsk cosmodrome aboard a Cosmos rocket. It is aprecursor to a joint venture between Final Analysis, Inc andPolyot Design Bureau of Russia to launch a constellation of 36commercial communications satellites.

FAISAT 2V

NSSDC ID: 1997-052B

Alternate Names

24954

Facts in Brief

Launch Date: 1997-09-23LaunchVehicle: CosmosLaunch Site: Plesetsk,Russia

Funding Agencies

Final Analysis, Inc(United States)

Polyot Design Bureau ofRussia (Russia)

Discipline

Communications


Launch/Orbitalinformation for FAISAT2V

Experiments on FAISAT2V

Data collections fromFAISAT 2V



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







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

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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: FAISAT 2V (1997-052B)











http://www.usa.gov/








Description

China began its geostationay meteorological satellite FY-2program in 1980. Feng Yun 2 was built by the ShanghaiInstitute of Satellite Engineering. The spin-stabilized spacecraftwas quite similar to the Japanese GMS-5 satellite originallybuilt by Hughes. The FY-2 was operationally similar to GMSwith high resolution stretched VISSR data (5 km IR, 5 km WV,1.25 km VIS), low resolution Wefax (analog), DCP capabilityand a new digital S-band fax service (CCITT G3) for domesticdistribution of charts and imagery. The attitude of the satellitewas spin stabilized with a speed of 100 rotation/min. Thespacecraft was slightly more massive than PRC's DFH-2communications satellite. The Feng Yun 2 spacecraft busdiameter was 2.1 m, and the total height on-station was about4.5 m.

In 1994 the long-awaited Feng Yun 2 GEO meteorologicalspacecraft was to be launched and positioned at 105 deg E.The first FY-2 satellite was undergoing final check-out on April2, 1994 before being mated to its launch vehicle when a fireand explosion erupted, destroying the vehicle, killing oneworker, and injuring 20 or more others. Feng Yun 2B waslaunched on June 10, 1997 to 105 deg E longitude on a CZ-3booster from Xichang, and the satellite began regular servicelate in 1997. On April 8, 1998, FY-2B ceased transmission ofimages due to a problem with the S-band antenna on thespacecraft.

Fengyun 2B

NSSDC ID: 1997-029A

Alternate Names

FY-2B

Fengyuan 2B

24834

Facts in Brief

Launch Date: 1997-06-10Launch Vehicle: LongMarch 3Launch Site: Xichang,Peoples Republic of ChinaMass: 593.0 kg

Funding Agency

Chinese MeteorologicalAdministration (PeoplesRepublic of China)

Discipline

Earth Science


Launch/Orbitalinformation for Fengyun2B

Experiments on Fengyun2B

Data collections fromFengyun 2B



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=Fengyun 2B

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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Fengyun 2B (1997-029A)
















Description

FORTE (Fast On-orbit Recording of Transient Events) waslaunched from Vandenberg AFB on a Pegasus-XL rocket into a800 x 807 km x 70.0 degree orbit. FORTE was a small satelliteprogram by the Los Alamos National Laboratory and SandiaNational Laboratories for the Department of Energy. It carriedsophisticated electronic equipment for detecting, analyzing andrecording bursts of radion energy (monitoring of violations ofnuclear test ban treaties) arising from near Earth's surface. Thesatellite used a completely graphite epoxy composite structureweighing only 41 kg. It carried a 10m depolyable antenna. Theattitude mode employed was momentum bias with gravitygradient stabilization. It carried 3x2 axis magnetometers andan Earth horizon sensor, momentum wheel and 3-axismagnetic torque rods.

FORTE

NSSDC ID: 1997-047A

Alternate Names

24920

Facts in Brief

Launch Date: 1997-08-29LaunchVehicle: Pegasus XLLaunchSite: Vandenberg AFB,United StatesMass: 215.0 kg

Funding Agency


Discipline



Launch/Orbitalinformation for FORTE

Experiments on FORTE

Data collections fromFORTE



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: FORTE (1997-047A)











http://www.usa.gov/








Description

Beginning in 1985 the USSR/CIS conducted annual unmannedspace missions dedicated to materials science research. ThePhoton (Foton) spacecraft used for these flights was aderivative of the 1960's era Vostok/Voskhod mannedspacecraft and the Zenit military reconnaissance satellites andwere very similar to the operational Bion and Resurs-Fsatellites. Prototype Photon satellites were launched during1985-1987 as Cosmos 1645, Cosmos 1744, and Cosmos1841. Since 1988, the spacecraft have been officiallydesignated as Photon.

The 6,200-kg spacecraft was 6.2 m in length with a maximumdiameter of 2.5 m and was divided into three major sections:the service/retro module, the payload capsule, and anequipment block. The 2.3 m diameter recoverable capsulehandled a payload of up to 700 kg and a volume of 4.7 mcubed. Electrical power was supplied entirely by storagebatteries with 400 W average per day allocated to the payload(up to 700 W for 90 minutes each day). Mission durations forthe 8 Photon flights to the end of 1992 were 13-16 days.

To minimize perturbation forces, thereby maximizingmicrogravity conditions, Photon spacecraft were placed in amildly eccentric orbit at 62.8 degrees inclination and were notmaneuvered during the mission. Prior to 1991 the annualPhoton missions had always been launched in April or May.Launches were performed by the Soyuz booster from thePlesetsk cosmodrome, and recoveries made in Kazakhstan inthe primary manned recovery region northeast of the Baikonurcosmodrome.

Photon 11 carried and released a 154 kg German capsulenamed Mirka.

Foton 11

NSSDC ID: 1997-060A

Alternate Names

Photon 11

25006

Facts in Brief

Launch Date: 1997-10-09LaunchVehicle: Soyuz-ULaunch Site: Plesetsk,RussiaMass: 5800.0 kg

Funding Agency

Unknown (Russia)

Discipline

Microgravity


Launch/Orbitalinformation for Foton 11

Experiments on Foton 11

Data collections from Foton11



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Foton 11 (1997-060A)











http://www.usa.gov/








Description

Galaxy 8 is an American geosynchronous communicationsspacecraft that was launched by an Atlas 2AS rocket fromCape Canaveral Air Station. The 3,560 kg satellite carries 32Ku-band transponders that will beam 200 digital television andmusic channels to South America after parking at W-95 deglongitude.

Galaxy 8

NSSDC ID: 1997-078A

Alternate Names

25086

Facts in Brief

Launch Date: 1997-12-08Launch Vehicle: Atlas-2 ASLaunch Site: CapeCanaveral, United StatesMass: 1962.0 kg

Funding Agency


Discipline

Communications


Launch/Orbitalinformation for Galaxy 8

Experiments on Galaxy 8

Data collections fromGalaxy 8



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Galaxy 8

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Galaxy 8

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Galaxy 8

mailto:[email protected]?Subject=NMC Comment/Question: Galaxy 8 (1997-078A)











http://www.usa.gov/








Description

GE 2 was a General Electric American Communicationssatellite launched from the Kourou Space Center in FrenchGuiana aboard an Ariane 44L rocket. It was placed in ageostationary orbit at 84.9 deg W.

GE 2

NSSDC ID: 1997-002A

Alternate Names

24713

Facts in Brief

Launch Date: 1997-01-30Launch Vehicle: Ariane44LLaunch Site: Kourou,French Guiana

Funding Agency

GE AmericanCommunications, Inc.(United States)

Discipline

Communications


Launch/Orbitalinformation for GE 2

Experiments on GE 2

Data collections from GE 2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

mailto:[email protected]?Subject=NMC Comment/Question: GE 2 (1997-002A)











http://www.usa.gov/







Tuesday, 14 June 2011

Description

GE 3 was a General Electric American Communicationssatellite launched from Cape Canaveral aboard an Atlas 2ASrocket. It was placed into a geostationary orbit at 87.1 deg W.

GE 3

NSSDC ID: 1997-050A

Alternate Names

24936

Facts in Brief

Launch Date: 1997-09-04Launch Vehicle: Atlas2ASLaunch Site: CapeCanaveral, United States

Funding Agency

GE AmericanCommunications, Inc.(United States)

Discipline

Communications


Launch/Orbitalinformation for GE 3

Experiments on GE 3

Data collections from GE 3



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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












http://www.usa.gov/








Description

The Geostationary Operational Environmental Satellite GOES10 is the third satellite in a series of next generationgeosynchronous spacecraft, referred to as GOES-NEXT andrepresented by the GOES I through GOES M spacecraft. TheGOES-NEXT series is a joint effort on the part of NASA andNOAA to provide continued operational monitoring of weathersystems primarily over the United States, distributemeteorological data to regional and national weather officeswithin the USA, contribute to the development of anenvironmental data collection network, contribute to the searchand rescue program, improve the capability for forcasting andprovide real-time warnings of solar distrubances, and toextend knowledge and understanding of atmosphericprocesses to improve short and long-term weather forecasts.

The GOES-NEXT series extends the capabilities of theprevious GOES 1-7 spacecraft. The GOES I-M spacecraft willbe placed over the equator at 135 deg West or 75 deg West.The design allows unobstructed views of the Earth foroperational coverage by the spacecraft sensors. Thespacecraft configuration is a compact box-shaped main bodythat carries the Earth-observing instruments, a continuous-drive solar array attached to the south panel through a yokeassembly, and a solar pointing instrument gimbal mounted onthe solar panel yoke. The main body accomodates thesensors, electronics, and support subsystems. Thecommunication antennas, except the Tracking, Telemetry, andCommand (TT&C) antenna, are hard-mounted to the Earth-facing panel. The Propulsion Module consists of the fuel andoxidizer tanks for the bipropellant propulsion subsystemmounted on the central cylinder. The Attitude and Orbit ControlSubstem (AOCS) provides attitude control of the spacecraft.The AOCS consists of the sensors, electronics, and theactuators. The GOES power is generated from the solar arrayand two 12 A-hr batteries. Power is automatically regulatedduring solar eclipses. A conical shaped solar sail at the end ofa 58-foot boom balances torque caused by solar radiation. Themain body of the spacecraft is a 2-meter cube. In its deployedorbit configuration, the overall length is about 27 meters. Initialmass was about 4640 pounds, including fuel. Design lifetime isabout five years.

The Image Navigation/Registration (INR) system providesImager and Sounder data products in real-time to users. TheCommunications, Command, and Data Handling subsystem iscomprised of antennas, receivers, transponders, transmitters,data encoders and encryptors and multiplexers. The TrackingTelemetry and Command (TT&C) subsystem provides thenecessary monitor and command link between the spacecraft

GOES 10

NSSDC ID: 1997-019A

Alternate Names

24786

Facts in Brief

Launch Date: 1997-04-25Launch Vehicle: Atlas-CentaurLaunch Site: CapeCanaveral, United StatesMass: 2109.0 kg

Funding Agency

National Oceanic andAtmosphericAdministration (UnitedStates)

Discipline

Earth Science


Launch/Orbitalinformation for GOES 10

Experiments on GOES 10

Data collections fromGOES 10



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=GOES 10

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=GOES 10

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=GOES 10

mailto:[email protected]?Subject=NMC Comment/Question: GOES 10 (1997-019A)













and the ground stations.

The GOES-NEXT instruments consist of the following: (1)Earth Imaging System, a 5-channel visible and infraredradiometer which provides Earth imagery 24 hours a day; (2)Sounding System, a 19-channel discrete-filter radiometer forobtaining atmospheric temperature and moisture soundings;(3) a Space Environment Monitor (SEM), which consists of amagnetic field sensor, a solar X-ray sensor, an energeticparticle sensor (EPS), and a High Energy Proton and AlphaDetector (HEPAD); (4) a Search and Rescue subsystem(SARSAT), which receives signals from 406 MHz distressbeacons and relays them to the ground; (5) a Data CollectionSystem (DCS) for collecting and relaying real-time informationfrom Data Collection Platforms (DCPs) such as buoys,balloons, remote weather stations, ships, and aircraft; and (6)a Weather Facsimile (WEFAX) system which relays processedweather imagary from the Wallops Island station to the usercommunity. The SEC package has been frequently eraticduring 2003.


http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=GOES-K[14/06/2011 23:56:40]


Description

The Geostationary Operational Environmental Satellite (GOES-K) is the third satellite in a series of next generationgeosynchronous spacecraft, referred to as GOES-NEXT andrepresented by the GOES I through GOES M spacecraft. TheGOES-NEXT series is a joint effort on the part of NASA andNOAA to provide continued operational monitoring of weathersystems primarily over the United States, distributemeteorological data to regional and national weather officeswithin the USA, contribute to the development of anenvironmental data collection network, contribute to the searchand rescue program, improve the capability for forcasting andprovide real-time warnings of solar distrubances, and toextend knowledge and understanding of atmosphericprocesses to improve short and long-term weather forecasts.The GOES-NEXT series, extends the capabilities of theprevious GOES 1-7 spacecraft. The GOES I-M spacecraft willbe placed over the equator at 135 deg West or 75 deg West.The spacecraft structure is based on the Space TransportationSystem (STS)-launched, three-axis stabilized Insat(geostationary satellite for India) meteorological satellitedesign. The design allows unobstructed views of the Earth foroperational coverage by the spacecraft sensors. Thespacecraft configuration is a compact box-shaped main bodythat carries the Earth-observing instruments, a continuous-drive solar array attached to the south panel through a yokeassembly, and a solar pointing instrument gimbal mounted onthe solar panel yoke. The main body accomodates thesensors, electronics, and support subsystems. Thecommunication antennas, except the Tracking, Telemetry, andCommand (TT&C) antenna, are hard-mounted to the Earth-facing panel. The Propulsion Module consists of the fuel andoxidizer tanks for the bipropellant propulsion subsystemmounted on the central cylinder. The Attitude and Orbit ControlSubstem (AOCS) provides attitude control of the spacecraft.The AOCS consists of the sensors, electronics, and theactuators. The GOES power is generated from the solar arrayand two 12 A-hr batteries. Power is automatically regulatedduring solar eclipses. The Image Navigation/Registration (INR)system provides Imager and Sounder data products in real-time to users. The Communications, Command, and DataHandling subsystem is comprised of antennas, receivers,transponders, transmitters, data encoders and encryptors andmultiplexers. The Tracking Telemetry and Command (TT&C)subsystem provides the necessary monitor and command linkbetween the spacecraft and the ground stations. The GOES-NEXT instruments consist of the following: (1) Earth ImagingSystem, a 5-channel visible and infrared radiometer whichprovides Earth imagery 24 hours a day; (2) Sounding System,a 19-channel discrete-filter radiometer for obtaining

GOES-K

NSSDC ID: GOES-K

Alternate Names

GOES-NEXT

Facts in Brief

Launch Date: 1997-04-24Launch Vehicle: Atlas ILaunch Site: CapeCanaveral, United StatesMass: 980.0 kgNominalPower: 973.0 W

Funding Agencies


NOAA NationalEnvironmental SatelliteService (United States)

Disciplines

Engineering

Earth Science

Solar Physics

Space Physics


Launch/Orbitalinformation for GOES-K

PDMP information forGOES-K

Telecommunicationsinformation for GOES-K

Experiments on GOES-K

Data collections fromGOES-K


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data



http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=GOES-K

http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=GOES-K

http://nssdc.gsfc.nasa.gov/nmc/spacecraftPdmp.do?id=GOES-K

http://nssdc.gsfc.nasa.gov/nmc/spacecraftPdmp.do?id=GOES-K

http://nssdc.gsfc.nasa.gov/nmc/spacecraftTelemetry.do?id=GOES-K

http://nssdc.gsfc.nasa.gov/nmc/spacecraftTelemetry.do?id=GOES-K

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=GOES-K

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=GOES-K

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=GOES-K










http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=GOES-K[14/06/2011 23:56:40]

atmospheric temperature and moisture soundings; (3) a SpaceEnvironment Monitor (SEM), which consists of a magnetic fieldsensor, a solar X-ray sensor, an energetic particle sensor(EPS), and a High Energy Proton and Alpha Detector(HEPAD); (4) a Search and Rescue subsystem (SARSAT),which receives signals from 406 MHz distress beacons andrelays them to the ground; (5) a Data Collection System (DCS)for collecting and relaying real-time information from DataCollection Platforms (DCPs) such as buoys, balloons, remoteweather stations, ships, and aircraft; and (6) a WeatherFacsimile (WEFAX) system which relays processed weatherimagary from the Wallops Island station to the user community.


Personnel


Mr. James R.Greaves

ProgramManager

NASA Headquarters [email protected]

Mr. Arthur F.Obenschain

ProjectManager


[email protected]


mailto:[email protected]?Subject=NMC Comment/Question: GOES-K (GOES-K)



http://www.usa.gov/








Description

Gonets D-1 6, Gonets D-1 5, and Gonets D-1 4 were Russianspacecraft that were launched by a Cyclone 3 rocket fromPlesetsk cosmodrome at 03:47 UT. Like the earlier Gonetslaunched last year, these are to provide urgent alerts onnatural and man-made disasters or emergencies.

Gonets D1-4

NSSDC ID: 1997-006A

Alternate Names

24725

Facts in Brief

Launch Date: 1997-02-13LaunchVehicle: Cyclone 3Launch Site: Plesetsk,Russia

Funding Agency

Unknown (Russia)

Discipline

Communications


Launch/Orbitalinformation for GonetsD1-4

Experiments on GonetsD1-4

Data collections fromGonets D1-4



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Gonets D1-4


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Gonets D1-4


mailto:[email protected]?Subject=NMC Comment/Question: Gonets D1-4 (1997-006A)











http://www.usa.gov/








Description


Gonets D1-5

NSSDC ID: 1997-006B

Alternate Names

24726

Facts in Brief


Funding Agency

Unknown (Russia)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data











mailto:[email protected]?Subject=NMC Comment/Question: Gonets D1-5 (1997-006B)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1997-006C[14/06/2011 23:58:05]


Description


Gonets D1-6

NSSDC ID: 1997-006C

Alternate Names

24727

Facts in Brief


Funding Agency

Unknown (Russia)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1997-006C







mailto:[email protected]?Subject=NMC Comment/Question: Gonets D1-6 (1997-006C)











http://www.usa.gov/








Description

Haruka (meaning "far away") is the post-launch name of theJapanese Muses-B radio astronomy satellite. The spacecraftcarries a wire mesh dish antenna 8 m in diameter as one partof a radio astronomy interferometer, with the other part beingany one of a number of ground-based radio telescopes. Itcarries detectors which operate at 1.6, 5 and 22 GHz (18, 6,and 1.3 cm, respectively), and will be able to make radioimages with very high spatial resolution (the highest yet invery-long baseline interferometry) and permit precisemeasurements of quasar jets and galactic maser sources. Itsplanned lifetime is 3-5 years.

HALCA

NSSDC ID: 1997-005A

Alternate Names

Muses-B

Highly AdvancedLaboratory forCommunications andAstronomy

Haruka

24720

Facts in Brief

Launch Date: 1997-02-11Launch Vehicle: M-5Launch Site: UchinouraSpace Center, JapanMass: 830.0 kgNominal Power: 2.5 W

Funding Agency

Institute of Space andAeronautical Science, Uof Tokyo (Japan)

Discipline

Astronomy


Launch/Orbitalinformation for HALCA

Telecommunicationsinformation for HALCA

Experiments on HALCA

Data collections fromHALCA



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: HALCA (1997-005A)












Other Sources of HALCA Information/Data

HALCA mission page at ISASThe VLBI Space Observatory Programme




http://www.isas.ac.jp/e/enterp/missions/halca/

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

http://www.usa.gov/








Description

Hot Bird 3 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 southernhemisphere.

Hot Bird 3

NSSDC ID: 1997-049A

Alternate Names

Eurobird 4

24931

Facts in Brief


Funding Agency

EuropeanTelecommunicationsSatellite Consortium(International)

Discipline

Communications


Launch/Orbitalinformation for Hot Bird 3

Experiments on Hot Bird 3

Data collections from HotBird 3



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Hot Bird 3 (1997-049A)











http://www.usa.gov/








Description

Inmarsat 3-F4 was the fourth in a series of five third generationsatellites. Launched from the Kourou Space Center aboard anAriane rocket, it is currently in service over the Atlantic Ocean.It used 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-F4

NSSDC ID: 1997-027A

Alternate Names

24819

Facts in Brief

Launch Date: 1997-06-03Launch Vehicle: Ariane44LLaunch Site: Kourou,French GuianaMass: 2400.0 kg

Funding Agency

InternationalTelecommunicationsSatellite Corporation(International)

Discipline

Communications


Launch/Orbitalinformation for Inmarsat3-F4

Experiments on Inmarsat3-F4

Data collections fromInmarsat 3-F4



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Inmarsat 3-F4

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Inmarsat 3-F4

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Inmarsat 3-F4

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Inmarsat 3-F4

mailto:[email protected]?Subject=NMC Comment/Question: Inmarsat 3-F4 (1997-027A)











http://www.usa.gov/








Description

Stationed at 74.1 deg E, INSAT 2D was a multipurposesatellite that provided the following services to India: domesticlong range communications, meteorological earth observationand data collection services, direct satellite TV broadcasting tocommunity TV receivers in rural and remote areas, radio andTV program distribution, satellite aided search and rescueservices.

INSAT 2D

NSSDC ID: 1997-027B

Alternate Names

Indian National Satellite2D

24820

Facts in Brief

Launch Date: 1997-06-03Launch Vehicle: Ariane44LLaunch Site: Kourou,French GuianaMass: 2079.0 kg

Funding Agency

Indian Space ResearchOrganization (India)

Discipline

Communications


Launch/Orbitalinformation for INSAT 2D

Experiments on INSAT 2D

Data collections fromINSAT 2D



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: INSAT 2D (1997-027B)











http://www.usa.gov/








Description

Inspektor was a small remote camera satellite that was carriedon the Progress M36 cargo ship to the Mir space station. Itwas released from the Progress spacecraft shortly afterProgress undocked from the station in order to take images ofthe station's exterior, but it failed shortly after deployment,failing to orient itself properly and not responding tocommands.

Inspektor

NSSDC ID: 1997-058D

Alternate Names

Inspector

25100

Facts in Brief


Funding Agencies

DeutscheForschunganstalt fuerLuft- und Raumfahrt(DLR, nee DFVLR)(Federal Republic ofGermany)


Discipline

Technology Applications


Launch/Orbitalinformation for Inspektor

Experiments on Inspektor

Data collections fromInspektor



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Inspektor (1997-058D)














http://www.usa.gov/








Description

INTELSAT 801 is a geosynchronous communicationsspacecraft that was launched by an Ariane 44L rocket fromKourou in French Guiana to provide voice and videocommunications to the member countries in that consortiumafter parking at 174-E longitude. It carries six transponders inthe Ku-band.

Intelsat 801

NSSDC ID: 1997-009A

Alternate Names

24742

Facts in Brief

Launch Date: 1997-02-28Launch Vehicle: Ariane44LLaunch Site: Kourou,French Guiana

Funding Agency


Discipline

Communications


Launch/Orbitalinformation for Intelsat801

Experiments on Intelsat801

Data collections fromIntelsat 801



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Intelsat 801


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Intelsat 801


mailto:[email protected]?Subject=NMC Comment/Question: Intelsat 801 (1997-009A)











http://www.usa.gov/








Description

INTELSAT 802 is a geosynchronous communicationsspacecraft of that international consortium that was launchedby an Ariane 44-P rocket from Kourou in French Guiana. Itcarries 38 C-band transponders to provide voice and videocommunications after parking over 175 deg-E longitude.

Intelsat 802

NSSDC ID: 1997-031A

Alternate Names

24846

Facts in Brief

Launch Date: 1997-06-25Launch Vehicle: Ariane44PLaunch Site: Kourou,French Guiana

Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

INTELSAT 803 is a geosynchronous communicationsspacecraft of that consortium that was launched by an Ariane 4rocket from Kourou. The 3,455 kg satellite carries six Ku-bandtransponders to provide voice and video communications afterparking at 175-E longitude.

Intelsat 803

NSSDC ID: 1997-053A

Alternate Names

24957

Facts in Brief

Launch Date: 1997-09-23Launch Vehicle: Ariane4Launch Site: Kourou,French GuianaMass: 3455.0 kg

Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Intelsat 804 is a geosynchronous communications spacecraftof that consortium and was launched by an Ariane 4 rocketfrom Kourou at 00:17 UT. The 1,600 kg satellite carries sixtransponders in Ku-band and 38 in C-band to provide voice,data, and video communications after parking at E-64 degover the Indian Ocean.

Intelsat 804

NSSDC ID: 1997-083A

Alternate Names

25110

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Iridium 4 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 4

NSSDC ID: 1997-020E

Alternate Names

24796

Facts in Brief

Launch Date: 1997-05-05Launch Vehicle: DeltaII 7920LaunchSite: Vandenberg AFB,United States

Funding Agency

Iridium (United States)

Discipline

Communications


Launch/Orbitalinformation for Iridium 4

Telecommunicationsinformation for Iridium 4

Experiments on Iridium 4

Data collections fromIridium 4



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/spacecraftTelemetry.do?id=1997-020E


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

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


mailto:[email protected]?Subject=NMC Comment/Question: Iridium 4 (1997-020E)











http://www.usa.gov/








Description


Iridium 5

NSSDC ID: 1997-020D

Alternate Names

24795

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=1997-020D





mailto:[email protected]?Subject=NMC Comment/Question: Iridium 5 (1997-020D)











http://www.usa.gov/







Wednesday, 15 June 2011

Description


Iridium 6

NSSDC ID: 1997-020C

Alternate Names

24794

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=1997-020C





mailto:[email protected]?Subject=NMC Comment/Question: Iridium 6 (1997-020C)











http://www.usa.gov/








Description


Iridium 7

NSSDC ID: 1997-020B

Alternate Names

24793

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 7 (1997-020B)











http://www.usa.gov/








Description


Iridium 8

NSSDC ID: 1997-020A

Alternate Names

24792

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 8 (1997-020A)











http://www.usa.gov/








Description


Iridium 9

NSSDC ID: 1997-030C

Alternate Names

24838

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 10

NSSDC ID: 1997-030D

Alternate Names

24839

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=1997-030G[15/06/2011 0:06:07]


Description


Iridium 11

NSSDC ID: 1997-030G

Alternate Names

24842

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=1997-030G





mailto:[email protected]?Subject=NMC Comment/Question: Iridium 11 (1997-030G)











http://www.usa.gov/








Description


Iridium 12

NSSDC ID: 1997-030B

Alternate Names

24837

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 13

NSSDC ID: 1997-030E

Alternate Names

24840

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 14

NSSDC ID: 1997-030A

Alternate Names

24836

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 15

NSSDC ID: 1997-034A

Alternate Names

24869

Facts in Brief


Funding Agency


Discipline

Communications








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Iridium 16

NSSDC ID: 1997-030F

Alternate Names

24841

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 16 (1997-030F)











http://www.usa.gov/








Description


Iridium 17

NSSDC ID: 1997-034B

Alternate Names

24870

Facts in Brief


Funding Agency


Discipline

Communications








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Iridium 18

NSSDC ID: 1997-034C

Alternate Names

24871

Facts in Brief


Funding Agency


Discipline

Communications








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Iridium 19

NSSDC ID: 1997-056A

Alternate Names

24965

Facts in Brief


Funding Agency


Discipline

Communications








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Iridium 20

NSSDC ID: 1997-034D

Alternate Names

24872

Facts in Brief


Funding Agency


Discipline

Communications








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Iridium 21

NSSDC ID: 1997-034E

Alternate Names

24873

Facts in Brief


Funding Agency


Discipline

Communications








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Iridium 22

NSSDC ID: 1997-043E

Alternate Names

24907

Facts in Brief


Funding Agency


Discipline

Communications








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Iridium 23

NSSDC ID: 1997-043D

Alternate Names

24906

Facts in Brief


Funding Agency


Discipline

Communications








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Iridium 24

NSSDC ID: 1997-043C

Alternate Names

24905

Facts in Brief


Funding Agency


Discipline

Communications








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Iridium 25

NSSDC ID: 1997-043B

Alternate Names

24904

Facts in Brief


Funding Agency


Discipline

Communications








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Iridium 26

NSSDC ID: 1997-043A

Alternate Names

24903

Facts in Brief


Funding Agency


Discipline

Communications








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Iridium 27

NSSDC ID: 1997-051D

Alternate Names

24947

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 28

NSSDC ID: 1997-051E

Alternate Names

24948

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 29

NSSDC ID: 1997-051A

Alternate Names

24944

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 30

NSSDC ID: 1997-051F

Alternate Names

24949

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 31

NSSDC ID: 1997-051G

Alternate Names

24950

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 32

NSSDC ID: 1997-051B

Alternate Names

24945

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


On 10 February 2009 at approximately 16:56 UT the Iridium 33satellite collided with Cosmos 2251 (1993-036A). The collisiontook place at about 800 km altitude.

Iridium 33

NSSDC ID: 1997-051C

Alternate Names

24946

Facts in Brief


Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 34

NSSDC ID: 1997-056E

Alternate Names

24969

Facts in Brief


Funding Agency


Discipline

Communications








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Iridium 35

NSSDC ID: 1997-056D

Alternate Names

24968

Facts in Brief


Funding Agency


Discipline

Communications








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Iridium 36

NSSDC ID: 1997-056C

Alternate Names

24967

Facts in Brief


Funding Agency


Discipline

Communications








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Iridium 37

NSSDC ID: 1997-056B

Alternate Names

24966

Facts in Brief


Funding Agency


Discipline

Communications








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Iridium 38

NSSDC ID: 1997-069E

Alternate Names

25043

Facts in Brief


Funding Agency


Discipline

Communications








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Iridium 39

NSSDC ID: 1997-069D

Alternate Names

25042

Facts in Brief


Funding Agency


Discipline

Communications








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Iridium 40

NSSDC ID: 1997-069C

Alternate Names

25041

Facts in Brief


Funding Agency


Discipline

Communications








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Iridium 41

NSSDC ID: 1997-069B

Alternate Names

25040

Facts in Brief


Funding Agency


Discipline

Communications








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Iridium 42

NSSDC ID: 1997-077A

Alternate Names

25077

Facts in Brief

Launch Date: 1997-12-08Launch Vehicle: LongMarch 2CLaunch Site: Taiyuan,Peoples Republic of ChinaMass: 1445.0 kg

Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 43

NSSDC ID: 1997-069A

Alternate Names

25039

Facts in Brief


Funding Agency


Discipline

Communications








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Iridium 44

NSSDC ID: 1997-077B

Alternate Names

25078

Facts in Brief

Launch Date: 1997-12-08Launch Vehicle: LongMarch 2CLaunch Site: Taiyuan,Peoples Republic of ChinaMass: 1445.0 kg

Funding Agency


Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


Iridium 45

NSSDC ID: 1997-082A

Alternate Names

25104

Facts in Brief

Launch Date: 1997-12-20Launch Vehicle: DeltaII 7920LaunchSite: Vandenberg AFB,United StatesMass: 556.0 kg

Funding Agency


Discipline

Communications








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Iridium 46

NSSDC ID: 1997-082B

Alternate Names

25105

Facts in Brief


Funding Agency


Discipline

Communications








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Iridium 47

NSSDC ID: 1997-082C

Alternate Names

25106

Facts in Brief


Funding Agency


Discipline

Communications








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Iridium 48

NSSDC ID: 1997-082D

Alternate Names

25107

Facts in Brief


Funding Agency


Discipline

Communications








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Iridium 49

NSSDC ID: 1997-082E

Alternate Names

25108

Facts in Brief


Funding Agency


Discipline

Communications








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

IRS-1D is an Indian remote sensing Sun-synchronous orbiterthat was launched by a PSLV-1C (Polar Satellite LaunchVehicle) rocket from Shriharikota (in southeast India) at 04:47UT. (The 44.4 meter, four-stage, 468 ton PSLV-1C complex isnow an operational vehicle, after earlier test launches.) It is thefourth of the IRS series. The 1,200 kg orbiter carries threemain instruments: a panchromatic camera (PAN), a linearimaging self-scanner (LISS-3), and a wide field sensor (WIFS).PAN has reflective optics and the other have two refractiveoptics. The color imagery will have a resolution of 23.5 metersand the black and white, 5 meters. An on-board tape recorderstores data over unreachable intervals. Sensed data on Indianand foreign terrains will be sold through an American company(after the usual clearance by Indian military). Orbit maneuversmay be planned to raise the perigee.

IRS-1D

NSSDC ID: 1997-057A

Alternate Names

Indian Remote SensingSatellite 1D

24971

Facts in Brief

Launch Date: 1997-09-29Launch Vehicle: PSLVLaunch Site: Sriharikota,IndiaMass: 920.0 kg

Funding Agency

Indian Space ResearchOrganization (India)

Discipline

Earth Science


Launch/Orbitalinformation for IRS-1D

Experiments on IRS-1D

Data collections from IRS-1D



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: IRS-1D (1997-057A)











http://www.usa.gov/








Description

The Japanese Communications Satellite 4 (JCSAT 4) waslaunched to relay voice, data and television signals to Japan,with multiple beams for international coverage west to India,south to Australia and New Zealand, and east to Hawaii.JCSAT-4 carried four octagonal communications antennas andtwo wings with four solar panels each. The payload consistedof 12 active C-band transponders and 28 active Ku-bandtransponders with an expected lifetime of at least 12 years. Itwas launched as a replacement for JCSAT 1 after a small fuelleak rendered it inoperable.

JCSAT 4

NSSDC ID: 1997-007A

Alternate Names

JapaneseCommunications Satellite4

24732

Facts in Brief

Launch Date: 1997-02-17Launch Vehicle: Atlas2ASLaunch Site: CapeCanaveral, United StatesNominalPower: 5000.0 W

Funding Agency

Japan Satellite Systems,Inc. (Japan)

Discipline

Communications


Launch/Orbitalinformation for JCSAT 4

Experiments on JCSAT 4

Data collections fromJCSAT 4



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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


mailto:[email protected]?Subject=NMC Comment/Question: JCSAT 4 (1997-007A)











http://www.usa.gov/








Description

The Japanese Communications Satellite 5 (JCSat 5) waslaunched to relay voice, data and television signals to Japan,with multiple beams for international coverage west to India,south to Australia and New Zealand, and east to Hawaii.JCSat-5 carried four octagonal communications antennas andtwo wings with four solar panels each. The payload consistedof 12 active C-band transponders and 28 active Ku-bandtransponders with an expected lifetime of at least 12 years. Itwas placed in a geosynchronous orbit at 139.4 deg E initially,but was planned to be operated over 150 deg E.

JCSAT 5

NSSDC ID: 1997-075A

Alternate Names

JapaneseCommunications Satellite5

25067

Facts in Brief

Launch Date: 1997-12-02Launch Vehicle: Ariane44PLaunch Site: Kourou,French GuianaMass: 1841.0 kg

Funding Agency

Japan Satellite Systems,Inc. (Japan)

Discipline

Communications


Launch/Orbitalinformation for JCSAT 5

Experiments on JCSAT 5

Data collections fromJCSAT 5



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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














http://www.usa.gov/








Description

Kiku 7 (ETS 7) was a dual spacecraft mission designed to testand develop robotic technologies to be used in future spaceactivities (such as the International Space Station and in-orbitsateliite servicing).

Kiku 7 Chaser

NSSDC ID: 1997-074B

Alternate Names

ETS-7 Chaser

Hikoboshi

Engineering TestSatellite-7 Chaser

Chaser

25064

Facts in Brief

Launch Date: 1997-11-27Launch Vehicle: H-2LaunchSite: Tanegashima, JapanMass: 2540.0 kg

Funding Agency

National SpaceDevelopment Agency(NASDA) (Japan)

Discipline

Engineering


Launch/Orbitalinformation for Kiku 7Chaser

Telecommunicationsinformation for Kiku 7Chaser

Experiments on Kiku 7Chaser

Data collections from Kiku7 Chaser



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


Kiku 7 Chaser








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

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

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

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









http://nssdc.gsfc.nasa.gov/image/spacecraft/ets-7.jpg



be directed to: Dr. Edwin V.Bell, II.


ETS-7 Target

Other Sources of ETS-7 Information/Data

ETS-7 home page (NASDA)


mailto:[email protected]?Subject=NMC Comment/Question: Kiku 7 Chaser (1997-074B)

mailto:[email protected]?Subject=NMC Comment/Question: Kiku 7 Chaser (1997-074B)

http://oss1.tksc.nasda.go.jp/ets-7/index_e.html

http://www.usa.gov/








Description

Kiku 7 (ETS 7) was a dual spacecraft mission designed to testand develop robotic technologies to be used in future spaceactivities (such as the International Space Station and in-orbitsateliite servicing).

Kiku 7 Target

NSSDC ID: 1997-074E

Alternate Names

Engineering TestSatellite-7 Target

Orihime

ETS-7 Target

Target

25424

Facts in Brief


Funding Agency


Discipline

Engineering


Launch/Orbitalinformation for Kiku 7Target

Telecommunicationsinformation for Kiku 7Target

Experiments on Kiku 7Target

Data collections from Kiku7 Target



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


Kiku 7 Target








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

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

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

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









http://nssdc.gsfc.nasa.gov/image/spacecraft/ets-7.jpg



be directed to: Dr. Edwin V.Bell, II.


ETS-7 Chaser

Other Sources of ETS-7 Information/Data

ETS-7 home page (NASDA)


mailto:[email protected]?Subject=NMC Comment/Question: Kiku 7 Target (1997-074E)

mailto:[email protected]?Subject=NMC Comment/Question: Kiku 7 Target (1997-074E)

http://oss1.tksc.nasda.go.jp/ets-7/index_e.html

http://www.usa.gov/








Description

Kupon was a Russian geostationary communicationsspacecraft that was intended to facilitate banking transactionsin Russia and elsewhere, as part of a fleet of the "Bankir"system. The spacecraft carried enough transponders to handle10,000 transactions simultaneously. The on-board computerfailed after the spacecraft achieved orbit rendering itinoperable.

Kupon

NSSDC ID: 1997-070A

Alternate Names

25045

Facts in Brief


Funding Agency

Unknown (Russia)

Discipline

Communications


Launch/Orbitalinformation for Kupon

Experiments on Kupon

Data collections fromKupon



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Kupon (1997-070A)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=LANL-97[15/06/2011 0:32:27]


Description

This spacecraft is classified. It is known to carry aMagnetospheric Plasma Analyzer (MPA) similar to that LANLinstrument on other spacecraft, many of which are in the USAseries of spacecraft. Data sets from the MPA are included aspart of the Key Parameters in the extended ISTP KeyParameters data set available at NSSDC.

LANL 97A

NSSDC ID: LANL-97

Facts in Brief

Launch Date: 1996-12-31Launch Vehicle: nullLaunch Site: UnitedStates

Funding Agency

Department of Defense(United States)

Disciplines


Space Physics


Launch/Orbitalinformation for LANL 97A

Experiments on LANL 97A

Data collections from LANL97A



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=LANL-97

http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=LANL-97

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=LANL 97A

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=LANL 97A

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=LANL 97A

mailto:[email protected]?Subject=NMC Comment/Question: LANL 97A (LANL-97)











http://www.usa.gov/








Description

MAQSAT-B was launched from the Kourou Space Center inFrench Guiana aboard the same Ariane 5 rocket withMAQSAT-H. It was a smaller dummy satellite stored in thelower bay of the SPELTRA dual launch adapter. It was built byKayser-Threde of Germany for the European Space Agency.

MAQSAT-B

NSSDC ID: 1997-066B

Alternate Names

25024

Facts in Brief


Funding Agency


Discipline

Engineering


Launch/Orbitalinformation for MAQSAT-B

Experiments on MAQSAT-B

Data collections fromMAQSAT-B



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







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

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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: MAQSAT-B (1997-066B)











http://www.usa.gov/








Description

MAQSAT-H was a dummy communications satelliteinstrumented to report the actual payload bay environmentduring launch of the Ariane 5 booster. It also included theTEAMSAT technology experiment payload, developed byESTEC. It ejected a subsatellite, the Young Engineers Satellite(YES), also with several experiments. The MAQSATs werebuilt by Kayser-Threde of Germany for the European SpaceAgency.

MAQSAT-H

NSSDC ID: 1997-066A

Alternate Names

25023

Facts in Brief


Funding Agency


Discipline

Engineering


Launch/Orbitalinformation for MAQSAT-H

Experiments on MAQSAT-H

Data collections fromMAQSAT-H



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







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

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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: MAQSAT-H (1997-066A)











http://www.usa.gov/








Description

Meteosat 7, a European meteorological satellites, waslaunched from the Kourou space center in French Guianaaboard an Ariane 44LP rocket. It was placed in ageosynchronous orbit at 10.2 deg W.

Meteosat 7

NSSDC ID: 1997-049B

Alternate Names

24932

Facts in Brief


Funding Agency

European MeteorologicalSatellite Agency(International)

Discipline

Earth Science


Launch/Orbitalinformation for Meteosat7

Experiments on Meteosat 7

Data collections fromMeteosat 7



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Meteosat 7 (1997-049B)











http://www.usa.gov/








Description

Minisat 1 was a Spanish technology satellite launched aboarda Pegasus rocket along with Celestis. It was three-axisstabilized and carried deployable solar arrays. It was contolledby the Maspalomas ground station. One of the payloads of thismaiden Minisat mission was an extreme ultraviolet telescopefor astrophysical studies.

Minisat 01

NSSDC ID: 1997-018A

Alternate Names

24779

Facts in Brief

Launch Date: 1997-04-21LaunchVehicle: Pegasus XLLaunch Site: CanaryIslands, SpainMass: 200.0 kg

Funding Agency

Unknown (Spain)

Disciplines

Astronomy

Engineering


Launch/Orbitalinformation for Minisat 01

Experiments on Minisat 01

Data collections fromMinisat 01



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Minisat 01

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Minisat 01

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Minisat 01

mailto:[email protected]?Subject=NMC Comment/Question: Minisat 01 (1997-018A)











http://www.usa.gov/








Description

Molniya 1/90 was a first-generation Russian communicationsatellite orbited to test and perfect a system of radiocommunications and television broadcasting using earthsatellites as active transponders and to experiment with thesystem in practical use. The basic function of the satellite wasto relay television programs and long-distance two-waymultichannel telephone, phototelephone, and telegraph linksfrom Moscow to the various standard ground receiving stationsin the 'Orbita' system. The satellite was in the form of ahermetically sealed cylinder with conical ends -- one endcontained the orbtial 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 at 1000 MHz. Television service was provided in afrequency range of 3.4 to 4.1 GHz at 40 w. Molniya 1/90,whose cylindrical body was 3.4 m long and 1.6 m in diameter,was much heavier than corresponding U.S. COMSATs, and ithad about 10 times the power output of the Early BirdCOMSAT. In addition, it did not employ a synchronousequatorial orbit as do most U.S. COMSATs because such anorbit would not provide coverage for areas north of 70 deg nlatitude. Instead, the satellite was boosted from a low-altitudeparking orbit into a highly elliptical orbit with two high apogeesdaily over the northern hemisphere -- one over Russia and oneover North America -- and relatively low perigees over thesouthern hemipshere. During its apogee, Molniya 1/90remained relatively stationary with respect to the earth belowfor nearly 8 of every 12 hr. By placing three or more Molniya 1satellites in this type of orbit, spacing them suitably, andshifting their orbital planes relative to each other by 120 deg, a24-hr/day communication system could be obtained.

Molniya 1-90

NSSDC ID: 1997-054A

Alternate Names

24960

Facts in Brief


Funding Agency

Unknown (Russia)

Discipline

Communications


Launch/Orbitalinformation for Molniya 1-90

Experiments on Molniya 1-90

Data collections fromMolniya 1-90



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Molniya 1-90

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Molniya 1-90

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Molniya 1-90

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Molniya 1-90

mailto:[email protected]?Subject=NMC Comment/Question: Molniya 1-90 (1997-054A)











http://www.usa.gov/








Description

Nahuel 1A was an Argentinian communications satellitelaunched from the Kourou Space Center in French Guianaaboard an Ariane rocket. It was placed in a geosynchronousorbit at 71.8 deg W. It was designed to improve the telephone,data transmission, and television broadcasting services inthree coverage zones in Argentina and its neighboringcountries. It was manufactured at Aerospatiale's Satellitefacilities in Cannes and was based on a Spacebus 2000,three-axis stabilized platform. The payload had 19 Ku-bandtransponders (12-14 GHz).

Nahuel 1A

NSSDC ID: 1997-002B

Alternate Names

24714

Facts in Brief


Funding Agency

Unknown (Argentina)

Discipline

Communications


Launch/Orbitalinformation for Nahuel 1A

Experiments on Nahuel 1A

Data collections fromNahuel 1A



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Nahuel 1A (1997-002B)











http://www.usa.gov/








Description

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

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

Navstar 38

NSSDC ID: 1997-067A

Alternate Names

GPS 38

USA 135

25030

Facts in Brief


Funding Agency


Discipline

Navigation & GlobalPositioning


Launch/Orbitalinformation for Navstar 38

Telecommunicationsinformation for Navstar 38

Experiments on Navstar 38

Data collections fromNavstar 38



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Navstar 38

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Navstar 38


mailto:[email protected]?Subject=NMC Comment/Question: Navstar 38 (1997-067A)














Description

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

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

Navstar 43

NSSDC ID: 1997-035A

Alternate Names

GPS 43

USA 132

24876

Facts in Brief


Funding Agency


Discipline

Navigation & GlobalPositioning


Launch/Orbitalinformation for Navstar 43

Telecommunicationsinformation for Navstar 43

Experiments on Navstar 43

Data collections fromNavstar 43



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Navstar 43

















Description

ORBCOMM FM-5 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-05

NSSDC ID: 1997-084F

Alternate Names

Orbcomm FM-5

25117

Facts in Brief

Launch Date: 1997-12-23LaunchVehicle: PegasusLaunch Site: WallopsIsland, United StatesMass: 24.0 kg

Funding Agency

ORBCOMM (UnitedStates)

Discipline

Communications


Launch/Orbitalinformation for OrbcommFM-05

Experiments on OrbcommFM-05

Data collections fromOrbcomm FM-05



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







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


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


mailto:[email protected]?Subject=NMC Comment/Question: Orbcomm FM-05 (1997-084F)











http://www.usa.gov/








Description




Orbcomm FM-06

NSSDC ID: 1997-084G

Alternate Names

Orbcomm FM-6

25118

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-06 (1997-084G)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1997-084H[15/06/2011 0:40:01]


Description




Orbcomm FM-07

NSSDC ID: 1997-084H

Alternate Names

Orbcomm FM-7

25119

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=1997-084H







mailto:[email protected]?Subject=NMC Comment/Question: Orbcomm FM-07 (1997-084H)











http://www.usa.gov/








Description




Orbcomm FM-08

NSSDC ID: 1997-084A

Alternate Names

Orbcomm FM-8

25112

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-08 (1997-084A)











http://www.usa.gov/








Description




Orbcomm FM-09

NSSDC ID: 1997-084E

Alternate Names

Orbcomm FM-9

25116

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-09 (1997-084E)











http://www.usa.gov/








Description

ORBCOMM FM-10 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-10

NSSDC ID: 1997-084B

Alternate Names

25113

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-10 (1997-084B)











http://www.usa.gov/








Description




Orbcomm FM-11

NSSDC ID: 1997-084C

Alternate Names

25114

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-11 (1997-084C)











http://www.usa.gov/








Description




Orbcomm FM-12

NSSDC ID: 1997-084D

Alternate Names

25115

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-12 (1997-084D)











http://www.usa.gov/








Description

PANAMSAT 5 (PAS 5) was launched on a Russian Protonrocket from the Baikonur cosmodrome in Kazakhstan. Itprovided satellite communications services in the Americas,with access to Europe, including direct-to-home television inMexico. The satellite was a 3-axis, body-stabilized launched tomeet anticipated requirements for high-power, multiple-payload satellites for such applications as private businessnetworks and mobile communications. The spacecraft bodywas composed of 2 modules; the primary bus structure thatcarried all launch vehicle loads and contained the propulsionsubsystem, bus electronics, and battery packs; and ahoneycomb structure that housed communications equipment,electronics, and isothermal heat pipes. Reflectors, antennafeeds, and solar arrays were mounted directly to the payloadmodule, and antenna configurations could be placed on 3faces of the bus. Such a modular approach allowed work toproceed in parallel on the 2 structures, thereby shortening themanufacturing schedule and test time.

PanAmSat 5 was placed in a geostationary orbit at 58 degreesW, and had an expected lifetime of 15 years.

PANAMSAT 5

NSSDC ID: 1997-046A

Alternate Names

PAS 5

IS-5

Intelsat 5

24916

Facts in Brief


Funding Agencies



Discipline

Communications


Launch/Orbitalinformation forPANAMSAT 5

Experiments onPANAMSAT 5

Data collections fromPANAMSAT 5



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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


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












be directed to: CoordinatedRequest and User SupportOffice.


mailto:[email protected]?Subject=NMC Comment/Question: PANAMSAT 5 (1997-046A)



http://www.usa.gov/








Description

PAS 6 (PANAMSAT 6) is an American geosynchronousspacecraft that was launched from Kourou in French Guiana byan Ariane 44-LP rocket at 06:46 UT. The 3,420 kg spacecraftcarries 36 Ku-band 100 W transponders to provide direct voiceand video communications throughout South America,especially to Brazil.

PANAMSAT 6

NSSDC ID: 1997-040A

Alternate Names

PAS 6

24891

Facts in Brief

Launch Date: 1997-08-07Launch Vehicle: Ariane44LPLaunch Site: Kourou,French GuianaMass: 3420.0 kg

Funding Agency


Discipline

Communications


Launch/Orbitalinformation forPANAMSAT 6

Experiments onPANAMSAT 6

Data collections fromPANAMSAT 6



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

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

Progress M-34 was launched from Baykonur by a Soyuz-Vrocket at 16:04 UT. It carried 2,430 kg of cargo including 400kg of food, 200 kg of linen and personal wares, 250 kg ofscientific instruments, and many kilograms of urgently neededoxygen cartridges and three fire extinguishers; all weredelivered to Mir station after automatically docking with it at17:30 UT on 8 April, 1997.

Progress M-34

NSSDC ID: 1997-014A

Alternate Names

24757

Facts in Brief

Launch Date: 1997-04-06LaunchVehicle: Soyuz-ULaunch Site: Tyuratam(Baikonur Cosmodrome),KazakhstanMass: 2430.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Resupply/Refurbishment/Repair


Launch/Orbitalinformation for ProgressM-34

Experiments on ProgressM-34

Data collections fromProgress M-34



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Progress M-34


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Progress M-34


mailto:[email protected]?Subject=NMC Comment/Question: Progress M-34 (1997-014A)











http://www.usa.gov/








Description


Progress M-35 was launched from Baykonur cosmodrome by aSoyuz-U rocket at 04:12 UT. It carried 2,500 kg of provisionsand parts to repair Mir, which suffered major damages during acollision with Progress M-34 that was testing an automaticredocking effort on June 25. Progress M-35 dockedautomatically with Mir on 7 July at 05:59 UT and delivered thecargo.

Progress M-35

NSSDC ID: 1997-033A

Alternate Names

24851

Facts in Brief


Funding Agency

Unknown (Russia)

Discipline

Human Crew







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Progress M36 was launched by a Soyuz-U rocket from theBaikonur cosmodrome at 15:08 UT to dock with and deliver3,000 kg of fuel, water, and equipment (including a newreplacement computer) to the MIR space station. It orbitedaround for three days waiting the (eventual) undocking of theearlier Progress M35 and then successfully made anautomatic docking at the vacated port on October 8. It alsocarried a German mini-satellite, Inspector, to be used ininspecting the outer surface of the damaged MIR and a replicaof the first Soviet satellite, Sputnik 1.

Progress M-36

NSSDC ID: 1997-058A

Alternate Names

25002

Facts in Brief


Funding Agency

Unknown (Russia)

Disciplines

Human Crew








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Progress M-37 was launched from the Baikonur cosmodromeaboard a Soyuz-U rocket. It carried 2500 kg of food,equipment, fuel, and research materials to the Mir spacestation.

Progress M-37

NSSDC ID: 1997-081A

Alternate Names

25102

Facts in Brief

Launch Date: 1997-12-20LaunchVehicle: Soyuz-ULaunch Site: Tyuratam(Baikonur Cosmodrome),KazakhstanMass: 7250.0 kg

Funding Agency


Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

RESURS F-1M is a Russian Earth resources spacecraft thatwas launched by a Soyuz (-U ?) rocket from Plesetsk at 11:15UT. The 6,300 kg spacecraft was expected to orbit only for 25days and to release the photo module for safe landing beforethe spacecraft burns up.

Resurs F-1M

NSSDC ID: 1997-072A

Alternate Names

25059

Facts in Brief

Launch Date: 1997-11-18Launch Vehicle: SoyuzLaunch Site: Plesetsk,RussiaMass: 6300.0 kg

Discipline

Earth Science


Launch/Orbitalinformation for Resurs F-1M

Experiments on Resurs F-1M

Data collections fromResurs F-1M



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







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

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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Resurs F-1M (1997-072A)











http://www.usa.gov/








Description

SeaStar was a spacecraft, developed by Orbital SciencesCorporation, to deliver daily, worldwide, high precision,moderate resolution, multispectral visible observations ofocean radiance for research in biogeochemical processes,climate change, and oceanography. A near noon sun-synchronous orbit was flown for optimum illumination of thelighted hemisphere. Data were taken from a single ocean colorscanner on-board the satellite (SeaWiFS - Sea-viewing WideField-of-View Sensor). The SeaStar spacecraft was launchedinto low Earth orbit via a Pegasus launch vehicle which wasflown under the wing of a modified Lockheed L-1011 aircraft.The spacecraft had an on-board hydrazine propulsion systemwhich was used to raise the satellite to its final 705 km circular,noon, sun-synchronous orbit. Final orbit was achieved 20 daysafter launch. The spacecraft was three-axis stabilized by anAttitude Control System (ACS) which consisted of orthogonalmagnetic torque rods for roll and yaw control and twomomentum wheels for pitch stabilization. ACS sensorsincluded redundant sun sensors, horizon sensors, andmagnetometers. The propulsion system consisted of a reactioncontrol subsystem for third stage stabilization and a hydrazinepropulsion subsystem for raising the spacecraft to itsoperational orbit and for orbit stabilization. Local highresolution (1 km) data (LAC) were delivered by directbroadcast at L-Band to regional scientific centers nationwide.Reduced resolution (4 km) data (GAC and selected LAC) weredirectly broadcast at S-band to smaller research centers andships at sea. All reduced resolution data and selected fullresolution data were recorded on board and transmitted toGSFC via daily dump at S-Band or via the Tracking and DataRelay Satellite System (TDRSS). A minimum three yearmission life was expected.

Seastar

NSSDC ID: 1997-037A

Alternate Names

Orbview

Seawifs

24883

Facts in Brief

Launch Date: 1997-08-01LaunchVehicle: PegasusLaunchSite: Vandenberg AFB,United StatesMass: 75.0 kgNominalPower: 170.27 W

Funding Agencies

Orbital Sciences Corp(United States)


Discipline

Earth Science


Launch/Orbitalinformation for Seastar

PDMP information forSeastar

Telecommunicationsinformation for Seastar

Experiments on Seastar

Data collections fromSeastar


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data









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

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

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












Personnel


Mr. Robert G.Kirk

ProgramManager

NASA Goddard Space FlightCenter

[email protected]

Dr. Wayne E.Esaias

ProjectScientist

NASA Goddard Space FlightCenter

Selected References

System concept for wide-field-of-view observations of ocean phenomena from space, Report ofthe Joint EOSAT/NASA SeaWIFS Working Group, edited by E. S. Putnam, Aug. 1987.


mailto:[email protected]?Subject=NMC Comment/Question: Seastar (1997-037A)



http://www.usa.gov/








Description

Sirius 2 was a Swedish communications satellite launched fromthe Kourou Space Complex in French Guiana aboard anAriane 44L rocket. It was placed in a geosynchronus orbit at4.9 deg E. It carried 32 Ku-band transponders powered by 44-watt traveling-wave tube amplifiers (TWTAs). The spacecraftused gallium arsenide solar cells to generate a minimum of1400 watts of power at end of life and relied on nickel-hydrogen batteries for power through eclipses. Its antenna hadshaped surface octagonal reflectors of approximately 2 m indiameter, with single offset feeds. This antenna had threesurfaces: one for horizonatally polarized signals, one forvertically polarized signals, and one for on-station tracking andcommand.

Sirius 2 was used primarily for direct-to-home and cabletelevision services as well as data distribution in Scandinaviaand neighboring countries, but it was also capable of providingtelevision distribution and high-speed internet data toGreenland. The Ku-band effective isotropic radiated power(EIRP) was minimum 54 dBW in the primary zone.

The spacecraft was moved to 31.5 deg E longitude in April2008 in order to expand services to Central and EasternEurope. It suffered an apparent sudden technical anomaly inJanuary 2009 that ended its in-service lifetime. It was to bemoved into a graveyard orbit.

Sirius 2

NSSDC ID: 1997-071A

Alternate Names

Astra 5A

25050

Facts in Brief


Funding Agency

SES (Sweden)

Discipline

Communications


Launch/Orbitalinformation for Sirius 2

Experiments on Sirius 2

Data collections from Sirius2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Sirius 2 (1997-071A)











http://www.usa.gov/








Description

Soyuz TM-25 is a Russian passenger module that waslaunched to carry astronauts and supplies to Mir station. It waslaunched by a Soyuz-U rocket from Baykonur cosmodrome at14:09 UT to ferry three cosmonauts for a 162-day stay at thestation; it docked with the station at 15:51 UT on 12 February97. Within meters of automatic approach to the station, a slightmisalignment was noted, and the commander of the modulehad to dock it by manual steering.

Soyuz-TM 25

NSSDC ID: 1997-003A

Alternate Names

24717

Facts in Brief


Funding Agency

Unknown (Russia)

Discipline

Human Crew


Launch/Orbitalinformation for Soyuz-TM25

Experiments on Soyuz-TM25

Data collections fromSoyuz-TM 25



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Soyuz-TM 25


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Soyuz-TM 25


mailto:[email protected]?Subject=NMC Comment/Question: Soyuz-TM 25 (1997-003A)











http://www.usa.gov/





Soyuz TM-25

Launch, orbit and landing data

Launch date: 10.02.1997 Launch time: 14:09 UT Launch site: Baikonur Launch pad: 1 Altitude: 191,98 - 249,59 km Inclination: 51,64° Landing date: 14.08.1997 Landing time: 12:17 UT Landing site: 46° 46' N, 69° 42' E

Crew No. Surnam

e Given name Job Flight No. Duration Orbits

1 Tsibliyev Vasili Vasiliyevich Commander 2 184d 22h

07m 2926

2 Lazutkin

Aleksandr Ivanovich Flight Engineer 1 184d 22h

07m 2926

3 Ewald Reinhold Research

Cosmonaut 1 19d 16h 34m 311

Crew seating arrangement

Launch 1 Tsibliyev 2 Lazutkin 3 Ewald

Landing 1 Tsibliyev 2 Lazutkin 3

Double Crew

No. Surname Given name Job

1 Musabayev Talgat Amangeldyyevich Commander

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

http://www.spacefacts.de/maps/english/e_soyuz-tm-25.htm�

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



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



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






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

http://www.spacefacts.de/mission/large/english/soyuz-tm-25.htm�

2 Budarin Nikolai Mikhailovich Flight Engineer

3 Schlegel Hans Wilhelm Research Cosmonaut

Flight

Launch from Baikonur; landing 168 km southeast of Dzheskasgan. Docking on MIR spacestation; Tsibliyev and Lazutkin became together with Linenger the 23rd MIR resident crew; scientific experiments together with Ewald during mission EUROMIR 97; on 14th day fire onboard of MIR (cosmonauts quenched it); EVA by Tsibliyev and Linenger on 29.04.1997 (4h 48m) an oxygen cleaning-aparature failed; crew was visited by STS 84-crew. Collision with a Progress-freighter with a heavy damage of the Spektr module; spares with Progress M-35 cargo spacecraft; several more failures (energy, oxygen-generators; heart problems of Commander Tsibliyev); the Soyuz landing rockets failed to fire on touchdown, so the crew performed one of the roughest landings in space history.

Note Ewald returned to Earth with Soyuz TM-24-spacecraft on 02.03.1997 at 06:44 UT.

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

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



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

http://www.spacefacts.de/mir/english/mir-23.htm�




http://www.spacefacts.de/mission/english/sts-84.htm�



http://www.spacefacts.de/mission/english/soyuz-tm24.htm�

http://www.spacefacts.de/mission/large/english/soyuz-tm-25_2.htm�




Description

Soyuz TM-26 is a Russian spacecraft that ferried cosmonautsand supplies to the MIR space station. It was launched by aSoyuz-U rocket from Baykonur cosmodrome at 15:36 UT. Themain mission was to transport two specially trainedcosmonauts to repair or salvage the troubled space station.TM-26 docked with MIR at 17:03 UT on 7 August by manualcontrol. The crew repaired the power cable andharness/connectors in the severely damaged SPEKTR moduleand restored much of the lost power; they also repaired andreplaced the oxygen generators in MIR. The hole(s) in thatmodule that caused total depressurization of the module couldnot be located during their "space walk" inside that module.Repairing or replacing the segments of the solar panels on thatmodule and sealing the hole(s) may be delayed until the nextSoyuz mission.

National Space Science Data Center Header

Soyuz-TM 26

NSSDC ID: 1997-038A

Alternate Names

24886

Facts in Brief


Funding Agency

Unknown (Russia)

Discipline

Human Crew


Launch/Orbitalinformation for Soyuz-TM26

Experiments on Soyuz-TM26

Data collections fromSoyuz-TM 26



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/





Soyuz TM-26


Launch date: 05.08.1997 Launch time: 15:35 UT Launch site: Baikonur Launch pad: 1 Altitude: 192,9 - 248,8 km Inclination: 51,64° Landing date: 19.02.1998 Landing time: 09:10 UT Landing site: 50° 11' N, 67° 31' E

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

s

1 Soloviyov Anatoli

Yakovlevich Commander 5 197d 17h 34m 3128

2 Vinogradov

Pavel Vladimirovich

Flight Engineer 1 197d 17h 34m 3128

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

http://www.spacefacts.de/maps/english/e_soyuz-tm-26.htm�

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

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



http://www.spacefacts.de/mission/p_large/english/soyuz-tm-26.htm�

http://www.spacefacts.de/mission/large/english/soyuz-tm-26.htm�


Launch 1 Soloviyov 2 Vinogradov 3

Landing 1 Soloviyov 2 Vinogradov 3 Eyharts

Double Crew

No. Surnam

e Given name Job

1 Padalka

Gennadi Ivanovich

Commander

2 Avdeyev

Sergei Vasiliyevich

Flight Engineer

hi res version (665 KB)

Flight Launch from Baikonur; landing 30 km southeast of Arkalyk. Docking on MIR spacestation; both cosmonaut and Mike Foale became the 24th resident crew; EVA by Soloviyov and Vinogradov on 22.08.1997 (3h 16m) into the module Spektr to connect new cables and mount a hatch. EVA by Soloviyov and Foale on 06.09.1997 (7h 0m) for more repairing work; main computer was exchanged during docking of STS-86; both cosmonauts performed EVA's on 20.10.1997 (6h 38m), 03.11.1997 (6h 04m) and 06.11.1997 (6h 12m) into the module Spektr; hatch was repaired during an EVA on 08.01.1998 (3h 06m) by both cosmonauts; Soloviyov and new reasearch cosmonaut Dave Wolf (replaced Foale) performed another EVA on 14.01.1998 (3h 52m) to inspect the station interior.





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

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Photos / Drawings

http://www.spacefacts.de/graph/drawing/large/english/mir_1996.htm�

http://www.spacefacts.de/graph/drawing/large/english/soyuz-tm-26_spektr.htm�




Description

Spartan 201-4 is a reusable American solar observatorymodule that was released from STS 87. A computer glitchmade it unable to obtain attitude control; an effort to recaptureit robotically introduced a hazardous spin motion, also.Ultimately, it had to be recaptured by a space walk by twoastronauts. During the three days of free-flying, its orbitalparameters remained close to that of STS 87.

Spartan 201-4

NSSDC ID: 1997-073B

Alternate Names

25062

Facts in Brief


Funding Agency


Discipline

Astronomy


Launch/Orbitalinformation for Spartan201-4

Experiments on Spartan201-4

Data collections fromSpartan 201-4



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Spartan 201-4

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Spartan 201-4

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Spartan 201-4

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Spartan 201-4

mailto:[email protected]?Subject=NMC Comment/Question: Spartan 201-4 (1997-073B)











http://www.usa.gov/








Description

Sputnik Jr is a scaled-down but operational replica of the firstRussian Sputnik; it was released from the Progress M36 cargocraft at 01:30 UT on the 50th anniversary of the first Sputniklaunch. (Progress M36 had been launched on 05 October1997.)

Sputnik Jr

NSSDC ID: 1997-058C

Alternate Names

Sputnik 40

24958

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Disciplines

Earth Science

Space Physics


Launch/Orbitalinformation for Sputnik Jr

Experiments on Sputnik Jr

Data collections fromSputnik Jr



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Sputnik Jr (1997-058C)











http://www.usa.gov/








Description

The Lewis satellite was part of NASA's Small SpacecraftTechnology Initiative. It was also part of NASA's Mission toPlanet Earth, a long-term research program designed to studythe Earth's land, oceans, air, and life as a total system. Built byTRW Space & Electronics Group, Redondo Beach, CA, the890-pound satellite was launched August 23, 1997 fromVandenburg Air Force Base, CA, aboard a Lockheed MartinLaunch Vehicle (LMLV-1). Initial operations and check-outwere proceeding satisfactorily until telemetry received earlyAugust 26 indicated that the spacecraft was spinning atapproximately two revolutions per minute. The spinningresulted in the spacecraft shutting down after its solar panelscould not capture enough sunlight to properly rechargeonboard batteries. On September 28, the Lewis satellite endedin a ball of fire as it plunged into the atmosphere. EDC DAACwas to distribute the data from the Lewis satellite. The Lewishomepage URL address is:

http://crsphome.ssc.nasa.gov/ssti/LEWIS/LEWIS.HTM

SSTI-LEWIS

NSSDC ID: 1997-044A

Alternate Names

Lewis

24909

Facts in Brief

Launch Date: 1997-08-23LaunchVehicle: Athena 1LaunchSite: Vandenberg AFB,United StatesMass: 445.0 kg

Funding Agency

National Aeronautics andSpace Administration(United States)

Discipline

Earth Science


Launch/Orbitalinformation for SSTI-LEWIS

Experiments on SSTI-LEWIS

Data collections from SSTI-LEWIS



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, II


http://crsphome.ssc.nasa.gov/ssti/LEWIS/LEWIS.HTM




http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=SSTI-LEWIS

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=SSTI-LEWIS

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=SSTI-LEWIS

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=SSTI-LEWIS

mailto:[email protected]?Subject=NMC Comment/Question: SSTI-LEWIS (1997-044A)











http://www.usa.gov/







Description

STEP 4 (Space Test Experimental Program 4) was a USmilitary satellite launched from Wallops Island aboard aPegasus XL rocket released from a plane. The solar panelsfailed to deploy properly, and there has been little or no uplinkor downlink contact with the spacecraft. The failure is similar tothose of the previously launched STEP 1, 2, and 3.

STEP 4

NSSDC ID: 1997-063A

Alternate Names

Space Test ExperimentalProgram 4

25013

Facts in Brief

Launch Date: 1997-10-22LaunchVehicle: Pegasus XLLaunch Site: WallopsIsland, United States

Funding Agency


Discipline



Launch/Orbitalinformation for STEP 4

Experiments on STEP 4

Data collections fromSTEP 4



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: STEP 4 (1997-063A)











http://www.usa.gov/








Description

The STS 81 flight was the fifth in a series of joint missionsbetween the US Space Shuttle and the Russian Space StationMir and the second one involving an exchange of USastronauts. Shorthly after docking, STS 81 crew member JerryLinenger transferred over to the station, becoming a memberof the Mir 22 crew. Linenger replaced astronaut John Blaha,who had been aboard the orbiting facility since mid-September. He spent a total of 128 days in space, 118 of themas a Mir crew member.

The payloads consisted of the following:Spacehab - The Spacehab double module in the payload baycontained many of the logistical items that were transferred toMir. It also provided extra space for experiments such asBiorack.

KidSat - The electronic still cameras aboard the shuttlesupported the second flight of KidSat, as part of NASA's three-year pilot education program designed to bring the frontiers ofspace exploration to 15 US middle school classrooms via theInternet.

DTOs/DSOs - Development Test Objectives and DetailedSupplementary Objectives.

The crew consisted of the following:Commander - Michael A Baker Pilot - Brent W. Jett MissionSpecialist - John M. Grunsfeld Mission Specialist - Marsha S.Ivins Mission Specialist - Peter J.K. Wisoff Mission Specialist -Jerry M. Linenger Mission Specialist - John E. Blaha

STS 81

NSSDC ID: 1997-001A

Alternate Names

24711

Facts in Brief

Launch Date: 1997-01-12LaunchVehicle: ShuttleLaunch Site: CapeCanaveral, United StatesMass: 2250.0 kg

Funding Agency

NASA-Office of SpaceFlight (United States)

Discipline

Human Crew


Launch/Orbitalinformation for STS 81

Experiments on STS 81

Data collections from STS81



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=STS 81

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=STS 81


mailto:[email protected]?Subject=NMC Comment/Question: STS 81 (1997-001A)











http://www.usa.gov/





STS-81 Atlantis (18)

USA


Launch date: 12.01.1997 Launch time: 09:27 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-B Altitude: 296 km Inclination: 51,60° Landing date: 22.01.1997 Landing time: 14:23 UT Landing site: Cape Canaveral (KSC)

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s

1 Baker Michael Allen CD

R 4 10d 04h 56m 160

2 Jett Brent Ward, Jr. PLT 2 10d 04h 56m 160

3 Wisoff Peter Jeffrey Kelsay

"Jeff" MSP 3 10d 04h 56m 160

4 Grunsfeld John Mace MS

P 2 10d 04h 56m 160

5 Ivins Marsha Sue MS

P 4 10d 04h 56m 160

6 Linenger Jerry Michael MS

P 2 132d 04h 01m 2091


Launch 1 Baker 2 Jett 3 Wisoff 4 Grunsfeld 5 Ivins 6 Linenger

Landing 1 Baker 2 Jett 3 Ivins 4 Grunsfeld 5 Wisoff 6 Blaha

Backup Crew


6 Foale Colin Michael MSP

Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC).

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

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

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Fifth MIR-mission; successfully docking on the third flight day; five days of common flight (15. - 20.01.1997); Linenger replaced John Blaha as member of the 22. MIR resident crew; payload includes supplies for MIR space station; biological experiments; preparing mission for planned International Space Station.

Note Linenger landed on 24.05.1997 at 13:28 UT with STS-84.

Photos / Drawings


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




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


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Description

STS 82 was the 22nd flight of the Discovery orbiter, the 82ndshuttle mission, and the 16th night launch of the shuttle. Itsobjective was to repair, replace, and/or update the instrumentson the Hubble Space Telescope. During several days of EVA,the crew replaced a failed Fine Guidance Sensor (FGS),swapped one of the reel-to-reel tape recorders with a solid-state recorder, and exchanged two of the original instruments,the Goddard High-Resolution Spectrograph (GHRS) and theFaint Object Spectrograph (FOS), with two new instruments,the Space Telescope Imaging Spectrograph (STIS) and theNear Infrared Camera and Multi-Object Spectrometer(NICMOS). In addition to this planned work, astronautsdiscovered that some of the insulation around the light shieldportion of the telescope had degraded and attached severalthermal insulation blankets to correct the problem. The durationof the mission was 9 days, 23 hours, 38 minutes, and 9seconds and lasted for 149 orbits.

STS 82

NSSDC ID: 1997-004A

Alternate Names

OV 103

24719

Facts in Brief

Launch Date: 1997-02-11LaunchVehicle: ShuttleLaunch Site: CapeCanaveral, United StatesMass: 83122.0 kg

Funding Agency


Disciplines

Astronomy

Human Crew



PDMP information forSTS 82

Telecommunicationsinformation for STS 82





Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


STS 82






















http://nssdc.gsfc.nasa.gov/image/spacecraft/sts-82.jpg

STS-82 Discovery (22)

USA


Launch date: 11.02.1997 Launch time: 08:55 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-A Altitude: 579 km Inclination: 28,45° Landing date: 21.02.1997 Landing time: 08:32 UT Landing site: Cape Canaveral (KSC)

Crew

No. Surname Given name Job Flight No. Duration Orbits

1 Bowersox Kenneth Dwane "Sox" CDR 4 9d 23h 37m 149

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2 Horowitz Scott Jay "Doc" PLT 2 9d 23h 37m 149

3 Tanner Joseph Richard MSP 2 9d 23h 37m 149

4 Hawley Steven Alan MSP 4 9d 23h 37m 149

5 Harbaugh Gregory Jordan MSP 4 9d 23h 37m 149

6 Lee Mark Charles MSP 4 9d 23h 37m 149

7 Smith Steven Lee MSP 2 9d 23h 37m 149


Launch 1 Bowersox 2 Horowitz 3 Tanner 4 Hawley 5 Harbaugh 6 Lee 7 Smith

Landing 1 Bowersox 2 Horowitz 3 Harbaugh 4 Hawley 5 Tanner 6 Lee 7 Smith

Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC). Second Hubble-Servicing-Mission; satellite was captured with the RMS; several EVA`s to upgrade the scientific capabilities of the Hubble Space Telescope (HST). First EVA by Smith and Lee on 14.02.1997 (6h 42m), replaced the Goddard High Resolution Spectograph (GHRS) by the Space Telescope Imaging Spectograph (STIS) and the Faint Object Spectrograph (FOS) by the Near Infrared Camera and Multi-Object Spectrometer (NICMOS). Second EVA by Tanner and Harbaugh on 15.02.1997 (7h 27m) in which the Fine Guidance Sensor (FGS) and one Engineering / Science Tape Recorder (ESTR) were exchanged and the Optical Control Eletronics Enhancement Kit was installed. In a third EVA on 16.02.1997 (7h 11m) astronauts Smith and Lee exchanged one Data Interface Unit (DIU) and replaced a second ESTR by a Solid State Recorder (SSR); at last they removed an older Reaction Wheel Assembly (RWA) and installed a new one. Fourth and final planned EVA by Tanner and Harbaugh on 17.02.1997 (6h 34m); they exchanged one of the Solar Array Drive Electronics (SADE) and installed some covers on the magnometers; after that they started to repair the thermal isolation on the HST - this was not planned, but the isolation was rather damaged. In a final not planned EVA on 18.02.1997 (5h 17m) astronauts Smith and Lee completed repairing work on the isolation; after the successful work the Hubble Space Telescope was again deployed and worked fine.

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

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

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Photos / Drawings


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Description

The primary payload on STS 83 was the Microgravity ScienceLaboratory (MSL), a collection of microgravity experimentshoused inside a European Spacelab. First flight of the MSLwas cut short due to concerns about one of three fuel cells,marking only the third time in Shuttle program history a missionended early. (STS-2, 1981 and STS-44, 1991 were the othertwo times). Fuel cell No. 2 had shown some erratic readingsduring prelaunch startup, but was cleared to fly after additionalcheckout and test. Shortly after on-orbit operations began, thefuel cell no. 2 substack no. 3 differential voltage began trendingupward. There are three fuel cells on each orbiter, eachcontaining three substacks made up of two banks of 16 cells.In one substack of fuel cell no. 2, the difference in outputvoltage between the two banks of cells was increasing. Thefuel cells use a reaction of liquid hydrogen and liquid oxygento generate electricity and produce drinking water. Althoughone fuel cell produces enough electricity to conduct on-orbitand landing operations, Shuttle flight rules require all three tobe functioning well to ensure crew safety and provide sufficientbackup capability during reentry and landing.

When a purge failed to halt the upward trend, the fuel cell wasshut down. Additional purges and other measures failed tocorrect the anomaly, and around 10 a.m., April 6, the MissionManagement Team ordered the mission to end early. Fuel cellno. 2 was shut down for good later that afternoon and safed.

The crew was able to conduct some science in the MSL-1Spacelab module despite the early return. Work was performedin the German electromagnetic levitation furnace facility(TEMPUS) on an experiment called Thermophysical Propertiesof Undercooled Metallic Melts. This experiment studies theamount of undercooling that can be achieved beforesolidification occurs. Another experiment performed was theLiquid-Phase Sintering II experiment in the Large IsothermalFurnace. This investigation uses heat and pressure to testtheories about how the liquefied component bonds with thesolid particles of a mixture without reaching the melting point ofthe new alloy combination.

Also conducted were two fire-related experiments. TheLaminar Soot Processes experiment allowed scientists toobserve for the first time the concentration and structure ofsoot from a fire burning in microgravity. The Structure of FlameBalls at Low Lewis-number experiment completed two runs.This experiment is designed to determine under whatconditions a stable flame ball can exist, and if heat loss isresponsible in some way for the stablilization of the flame ballduring burning.

STS 83

NSSDC ID: 1997-013A

Alternate Names

24755

Facts in Brief


Funding Agency


Disciplines

Human Crew

Life Science







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





















A decision to refly the mission in its entirety was made by theMission Management Team in the days following Columbia'sreturn. The reflight was first designated STS-83R and thenrenamed STS-94.


http://www.usa.gov/





STS-83 Columbia (22)

USA



Crew


1 Halsell James Donald, Jr. CDR 3 3d 23h 13m 63



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2 Still Susan Leigh PLT 1 3d 23h 13m 63

3 Voss Janice Elaine MSP 3 3d 23h 13m 63

4 Gernhardt Michael Landon MSP 2 3d 23h 13m 63

5 Thomas Donald Alan MSP 3 3d 23h 13m 63

6 Crouch Roger Keith PSP 1 3d 23h 13m 63

7 Linteris Gregory Thomas PSP 1 3d 23h 13m 63


Launch 1 Halsell 2 Still 3 Voss 4 Gernhardt 5 Thomas 6 Crouch 7 Linteris

Landing 1 Halsell 2 Still 3 Thomas 4 Gernhardt 5 Voss 6 Crouch 7 Linteris

Backup Crew


5 Coleman Catherine Grace "Cady" MSP

Ronney Paul David PSP

Johnston Alan Eugene PSP

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Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC). Mission "Microgravity Science Lab 1 (MSL)"; mission was aborted due of a fuel-cell failure (third Minimum Duration Mission in the Shuttle history); originally the mission was scheduled to last 15 - 16 days; experiments were only performed on a small level.

Photos / Drawings


http://www.spacefacts.de/graph/drawing/large/english/sts-83_msl-1.htm�






Description

The STS 84 mission was the 6th Shuttle/Mir docking missionand was part of the NASA/Mir program which consisted of ninedockings and seven long duration flights of US astronautsaboard the Russian space station. The previous Shuttle/Mirmissions were STS 71, 74, 76, 79 and 81. This series ofmissions expanded US research on Mir by providing resupplymaterials for experiments to be performed aboard the stationas well as returning experiment samples and data to Earth.

STS 84 involved the transfer of 7,314 pounds of water andlogistics to and from the Mir. During the docked phase, 1,025pounds of water, 844.9 pounds of US science equipment,2,576.4 pounds of Russian logistics along with 392.7 poundsof miscellaneous material was transferred to Mir. Returned toEarth aboard Atlantis was 897.4 pounds of US sciencematerial, 1,171.2 pounds of Russian logistics, 30 pounds ofESA material and 376.4 pounds of miscellaneous material.

The crew consisted of the following members:Charles J. Percourt - Mission Commander Eileen M. Collins -Pilot C. Michael Foale - Mission Specialist Carlos I. Noreiga -Mission Specialist Edward T. Lu - Mission Specialist Jean-Francois Clervoy - ESA Mission Specialist Elena V. Kondakova- RSA Mission Specialist

Downloaded from Mir - Jerry M. Linenger C. Michael Foalestayed aboard Mir, replacing Linenger.

STS 84

NSSDC ID: 1997-023A

Alternate Names

24804

Facts in Brief


Funding Agency


Discipline

Human Crew



PDMP information forSTS 84






Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data
























http://www.usa.gov/








Crew


1 Precourt Charles Joseph CDR 3 9d 05h 20m 145

2 Collins Eileen Marie "MOM" PLT 2 9d 05h 20m 145

3 Clervoy Jean-François MSP 2 9d 05h 20m 145



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

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http://www.spacefacts.de/mission/p_large/english/sts-84_mir-23.htm�

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4 Noriega Carlos Ismael MSP 1 9d 05h 20m 145

5 Lu Edward Tsang MSP 1 9d 05h 20m 145

6 Kondakova Yelena Vladimirovna MSP 2 9d 05h 20m 145

7 Foale Colin Michael MSP 4 144d 13h 48m 2291


Launch 1 Precourt 2 Collins 3 Clervoy 4 Noriega 5 Lu 6 Kondakova 7 Foale

Landing 1 Precourt 2 Collins 3 Lu 4 Noriega 5 Clervoy 6 Kondakova 7 Linenger

Backup Crew


7 Voss James Shelton MSP

Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC). Sixth Shuttle-Mir-Mission; Spacehab-DM onboard; docking on Mir and common flight with the 23. MIR resident crew (17. - 22.05.1997); testing of a new developed docking-maneuver; 3 tons of supplies were transferred (including a new oxygen-aparature); Foale replaced Linenger onboard the MIR.

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

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Note Foale landed on 06.10.1997 at 21:56 UT with STS-86.

Photos / Drawings










Description

STS 85 was the 23rd flight of the orbiter Discovery. Its primarymission was the deployment and retrieval of CRISTA-SPAS 2,a satellite designed to study Earths middle atmosphere alongwith a test of potential International Space Station hardware.

The prime payload for the flight, the Cryogenic InfraredSpectrometers and Telescopes for the Atmosphere-ShuttlePallet Satellite 2 (CRISTA-SPAS 2) made its second flight onthe space shuttle and was the fourth mission in a cooperativeventure between the German Space Agency (DARA) andNASA. CRISTA-SPAS 2 was deployed using the RemoteManipulator System (RMS) on day 1 of the mission andrecaptured with the RMS on day 16.

The STS-85 crew also supported tests of the ManipulatorFlight Demonstration (MFD) investigation sponsored byNASDA, the Japanese Space Agency. MFD consisted of threeseparate experiments located on a support truss in the payloadbay and was designed to demonstrate applications of amechanical arm for possible use on the Japanese ExperimentModule of the future International Space Station.

The STS-85 crew was commanded by Curt Brown, on hisfourth shuttle flight. The pilot was Kent Rominger on his thirdflight. The three mission specialists assigned to this flight wereJan Davis, Robert Curbeam, and Steve Robinson. BjarniTryggvason from the Canadian Space Agency served aspayload specialist.

Two other payloads in Discoverys cargo bay were theTechnology Applications and Science-01 (TAS-01) and theInternational Extreme Ultraviolet Hitchhiker-02 (IEH-02). TASheld seven separate experiments that provided data on theEarths topography and atmosphere, studied the Sun's energy,and tested new thermal control devices. The four experimentscomprising the IEH payload will study ultraviolet radiation fromthe stars, the Sun, and other sources in the solar system.

Payload and experiments flying in the crew cabin areaincluded the Southwest Ultraviolet Imaging System (SWUIS), a7-inch imaging telescope that was pointed out of the orbiterswindows by the crew primarily to observe Comet Hale-Bopp.

Also in the crew cabin was the Bioreactor DemonstrationSystem (BDS), a part of NASA's Medical Sciences DivisionBioreactor program at Johnson Space Center and theBiotechnology Specimen Temperature Controller (BSTC). TheBSTC is a cell culture incubator that is intended to ultimatelylead to the use of microgravity to engineer tissues from

STS 85

NSSDC ID: 1997-039A

Alternate Names

24889

Facts in Brief


Funding Agency


Disciplines

Astronomy

Engineering

Earth Science

Human Crew

Life Science

Microgravity








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


STS 85




















http://nssdc.gsfc.nasa.gov/image/spacecraft/sts-85.jpg



individual cells. This investigation was planned to confirm theprocedures necessary to conduct cell biology experiments onorbit and investigate the assembly of cardiac and smoothmuscle cells in microgravity.

STS 85 returned to Earth after 189 orbits and a missionduration of 11 days, 20 hours, 28 minutes, 7 seconds. Landingoccurred at Kennedy Space Center 19 August 1997 at11:07:59 UTC.


CRISTA-SPAS 2

Other Sources of STS 85 Information/Data

STS 85 information (NASA Shuttle Web)STS 85 information (NASA KSC)


http://spaceflight.nasa.gov/shuttle/archives/sts-85/

http://www.ksc.nasa.gov/shuttle/missions/sts-85/mission-sts-85.html

http://www.usa.gov/





STS-85 Discovery (23)

USA




s

1 Brown Curtis Lee, Jr. "Curt" CD

R 4 11d 20h 28m 189



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




2 Rominger Kent Vernon PLT 3 11d 20h 28m 189

3 Davis Nancy Jan MS

P 3 11d 20h 28m 189

4 Curbeam Robert Lee, Jr.

"Beamer" MSP 1 11d 20h 28m 189

5 Robinson Stephen Kern MS

P 1 11d 20h 28m 189

6 Tryggvason Bjarni Valdimar PSP 1 11d 20h 28m 189


Launch 1 Brown 2 Rominger 3 Davis 4 Curbeam 5 Robinson 6 Tryggvason

Landing 1 Brown 2 Rominger 3 Robinson 4 Curbeam 5 Davis 6 Tryggvason

Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC). Deploying and retrieval of German-built satellite CRISTA-SPAS-02; several scientific experiments; tests with Utraviolet Spectrograph Telescope and Camera; testing tools for ISS (e.g. Japanese-built robot-arm).

Photos / Drawings

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

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

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

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

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
















http://www.spacefacts.de/graph/drawing/large/english/sts-85_crista-spas.htm�




Description

STS 86, the 7th Mir Docking mission, carried a Spacelabdouble module for a docking with Mir, cargo transfer and anastronaut exchange. The previous Mir docking missions wereSTS 71, 74, 76, 79, 81 and 84.

Highlights of the 10-day mission included five days of dockedoperations between Atlantis and Mir and the exchange of crewmembers Foale and Wolf to continue a permanent Americanpresence on the Russian complex. A spacewalk wasscheduled to retrieve the four Mir Environmental EffectsPayloads which were attached to the Mir's docking module byLinda Godwin and Rich Clifford during STS 76 to characterizethe environment surrounding the space station. Atlantis carriedthe Spacelab double module to support the transfer of logisticsand supplies for Mir and the return of experiment hardwareand specimens to Earth.

The crew consisted of the following:James D. Wetherbee - Commander Michael J. Bloomfield -Pilot Vladimar G. Titov - Mission Specialist Scott E. Parazynski- Mission Specialist Jean-Loup Chretien - Mission SpecialistWendy B. Lawrence - Mission Specialist David A. Wolf -Mission Specialist

STS 86

NSSDC ID: 1997-055A

Alternate Names

24964

Facts in Brief


Funding Agency


Disciplines

Human Crew

Microgravity







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/






U SA




s

1 Wetherbee James Donald "Wexbee" CD

R 4 10d 19h 22m 169

2 Bloomfield Michael John "Bloomer" PLT 1 10d 19h 22m 169



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



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


http://www.spacefacts.de/mission/p_large/english/sts-86_nick.htm�




3 Titov Vladimir Georgiyevich MS

P 4 10d 19h 22m 169

4 Parazynski Scott Edward MS

P 2 10d 19h 22m 169

5 Chrétien Jean-Loup Jacques

Marie MSP 3 10d 19h 22m 169

6 Lawrence Wendy Barrien MS

P 2 10d 19h 22m 169

7 Wolf David Alexander "Bluto" MS

P 2 127d 20h 02m 2022


Launch 1 Wetherbee 2 Bloomfield 3 Titov 4 Parazynski 5 Chrétien 6 Lawrence 7 Wolf

Landing 1 Wetherbee 2 Bloomfield 3 Chrétien 4 Parazynski 5 Titov 6 Lawrence 7 Foale

Backup Crew


7 Wolf David Alexander

"Bluto" MSP

Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC). Payload Spacehab DM; 7th Shuttle-MIR-Mission; common flight with the 24. MIR resident crew (27.09. - 03.10.1997); several supplies and equipment were brought to MIR (e.g. a new main computer); EVA by Titov and Parazynski on 02.10.1997 (5h 01m), testing tools and technologies needed for the ISS and to recover MIR Environmental Effects Payload (MEEP),

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

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



http://www.spacefacts.de/bios/international/english/chretien_jean-loup.htm�

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






















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

which were attached during Mission STS-76; Wolf replaced Foale as a member of the MIR resident crew; after separation the Shuttle-crew found two leaks in the module Spektr; mission extended one day, due of high winds over the KSC's Shuttle Landing Facility.

Note Wolf landed on 31.01.1998 at 22:36 UT with STS-89.

Photos / Drawings













Description

STS-87 Flew the United States Microgravity Payload (USMP-4), the Spartan-201, the Orbital Acceleration ResearchExperiment (OARE), the EVA Demonstration Flight Test 5(EDFT-05), the Shuttle Ozone Limb Sending Experiment(SOLSE), the Loop Heat Pipe (LHP), the Sodium Sulfur BatteryExperiment (NaSBE), the Turbulent GAS Jet Diffusion (G-744)experiment and the Autonomous EVA Robotic Camera/Sprint(AERCam/Sprint) experiment. Two middeck experiments werethe Middeck Glovbox Payload (MGBX) and the CollaborativeUkrainian Experiment (CUE).

The United States Microgravity Payload (USMP-4) was aSpacelab project managed by Marshall Space Flight Center,Huntsville, Alabama. The complement of microgravity researchexperiments was divided between two Mission-PeculiarExperiment Support Structures (MPESS) in the payload bay.The extended mission capability offered by the ExtendedDuration Orbiter (EDO) kit provided an opportunity foradditional science gathering time.

The crew consisted of the following:Kevin E. Kregel - Commander Steven W. Lindsey - PilotWinston E. Scott - Mission Specialist Kalpana Chawla -Mission Specialist Takao Doi (NASDA) - Mission SpecialistLeonid K. Kadenyuk - Payload Specialist

STS 87

NSSDC ID: 1997-073A

Alternate Names

25061

Facts in Brief


Funding Agency


Disciplines

Human Crew

Microgravity







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/





STS-87 Columbia (24)

USA


Launch date: 19.11.1997 Launch time: 19:46 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-B Altitude: 277 km Inclination: 28,45° Landing date: 05.12.1997 Landing time: 12:20 UT Landing site: Cape Canaveral (KSC)

Crew


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





1 Kregel Kevin Richard CDR 3 15d 16h 34m 252

2 Lindsey Steven Wayne PLT 1 15d 16h 34m 252

3 Chawla Kalpana MSP 1 15d 16h 34m 252

4 Scott Winston Elliott MSP 2 15d 16h 34m 252

5 Doi Takao MSP 1 15d 16h 34m 252

6 Kadenyuk Leonid Konstantinovich PSP 1 15d 16h 34m 252


Launch 1 Kregel 2 Lindsey 3 Chawla 4 Scott 5 Doi 6 Kadenyuk

Landing 1 Kregel 2 Lindsey 3 Doi 4 Scott 5 Chawla 6 Kadenyuk

Backup Crew


6 Pustovyi Yaroslav Igorevich PSP

hi res version (514 KB)

Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC).

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

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

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

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

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

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













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

http://www.spacefacts.de/bios/portraits_hi/international/pustovyi_yaroslav.jpg�

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

Mission USMP-4 (United States Microgravity Payload); satellite SPARTAN-201-04 was deployed but get then out of control; Scott and Doi captured the satellite with their hands during of a not planned EVA on 24.11.1997 (7h 43m); during this EVA the astronauts tested a new small crane; experiments in the field of materials science, biology (i.e. flame and fluid experiments, experiments with soybeans and moss); second (planned) EVA by Scott and Doi on 02.12.1997 (4h 59m);during this EVA the small crane again was tested; first time testing of the Autonomous EVA Robotic Camera Sprint (AERCam Sprint); this camera is in a "ball" and steered with a joystick in the Flight deck and can check every part of a shuttle (and later the ISS).

Photos / Drawings







http://www.spacefacts.de/graph/drawing/large/english/spartan_sts-87.htm�

http://www.spacefacts.de/graph/drawing/large/english/sts-87_scott.htm�




Description

STS 94 was a reflight of the STS 83 (97-013A) MSL mission,which was cut short due to a problem with Fuel Cell #2. Itlanded after just 3 day 23 hours.

The primary payload on STS 94 was the Microgravity ScienceLaboratory (MSL), a collection of microgravity experimentsloused inside a European Spacelab. It built on the cooperativeand scientific foundation of the International MicrogravityLaboratory missions IML-1 and IML-2, the US MicrogravityLaboratory missions USML-1 and USML-2, the JapaneseSpacelab mission, Spacelab-J, the Spacelab Life andMicrogravity Science Mission, LMS, and the German Spacelabmissions, D-1 and D-2.

MSL featured 19 materials science investigations in 4 majorfacilities. These facilities were the Large Isothermal Furnace,the EXpedite the PRocessing of Experiments to the SpaceStation (EXPRESS) Rack, the Electromagnetic ContainerlessProcessing Facility (TEMPUS) and the Coarsening in Solid-Liquid Mixtures (CSLM) facility. Additional technologyexperiments were also performed in the Middeck Glovebox(MGBX) developed by MSFC and the High-Packed DigitalTelevision (HI-PAC DTV) system used to provide multi-channel real-time analog science video.

The Large Isothermal Furnace was developed by theJapanese Space Agency and housed the Measurement ofDiffusion Coefficient by Shear Cell Method Experiment, theDiffusion of Liquid Metals and Alloys Experiment, the Diffusionin Liquid Led-Tin-Telluride Experiment, the Impurity in IonicMelts Experiment, and the Diffusion Processes in MoltenSemiconductors Experiment.

The Combustion Module-1 (CM-1) facility from the NASA LewisResearch Center housed experiments on Laminar SootProcesses Experiment and the Structure of Flame Balls at LowLewis-number Experiment.

The Droplet Combusion Experiment (DCE) was designed toinvestigate the fundamental combustion aspects of single,isolated droplets under different pressures and ambient oxygenconcentrations for a range of droplet sizes varying between 2and 5mm. The DCE apparatus was integrated into a singlewidth MSL Spacelab rack in the cargo bay.

The EXPRESS rack replaced a Spacelab Double rack andspecial hardware provided the same structural and resourceconnections the rack will have on the Space Station. It willhouse the Physics of Hard Spheres and the Astro/PGBA

STS 94

NSSDC ID: 1997-032A

Alternate Names

24849

Facts in Brief


Funding Agency


Discipline

Human Crew








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data























experiments.

The Electromagnetic Containerless Processing Facility wasused for the Experiments on Nucleation in Different FlowRegimes, Thermophysical Properties of Advanced Materials inthe Undercooled Liquid State Experiment, Measurements ofthe Surface Tension of Liquid and Undercooled Metallic Alloysby Oscillating Drop Technique Experiment, Alloy UndercoolingExperiments, the Study of the Morphological Stability ofGrowing Dendrites by Comparative Velocity Measurements onPure Ni and Dilute Ni-C Alloy in the Earth and SpaceLaboratory Experiment, the Undercooled Melts of Alloys withPolytetrahedral Short-Range Order Experiment, the thermalExpansion of Glass Forming Metallic Alloys on theUndercooled State Experiment, the AC Calorimetry andThermophysical Properties of Bulk Glass-Forming MetallicLiquids experiments and the Measurement of Surface Tensionand Viscosity of Undercooled Liquid Metals experiment.

The crew was the same as the STS 83 crew and consisted ofthe following:

James D. Halsell - Mission Commander Susan L. Still - PilotJanice E. Voss - Payload Commander Donald A. Thomas -Mission Specialist Michael L. Gernhardt - Mission SpecialistRoger Crouch - Payload Specialist Greg Linteris - PayloadSpecialist


http://www.usa.gov/








Description

Superbird-C is a communications satellite launched for SpaceCommunications Corp. (SCC) of Japan. It provides televisionsignals and business communications services throughoutJapan, southern and eastern Asia, and Hawaii using Ku-bandfrequencies. It joined the existing constellation of Superbird-A(158 degrees east longitude) and Superbird-B (162 degreeseast), taking position at 144 degrees east longitude.

The three-axis body-stabilized satellite has both fixed andmovable antennas and is designed to provide a 13-yearmission life. The nearly cube-shaped satellite measures 2.3 x2.3 x 2.4 m. Fully deployed, it measures 26.2 m across thesolar wing span and 7.5 m across the antennas.

Power is provided by a pair of four-panel solar arrays thatgenerate 4500 W of electrical power. During eclipse, electricalpower is supplied by a 29 cell nickel-hydrogen battery, with acapacity of 200 Amp-hours.

Final orbital insertion, as well as stationkeeping operations, isprovided by the satellite's integrated bipropellant propulsionsystem. The required impulse was generated by twelve 22 Nthrusters and one 490 N liquid apogee motor.

The communication payload is a high-power system thatsimultaneously achieves high effective isotropic radiated power(EIRP) while making available a large number of channels overa vast geographic area. The payload includes the ability forchannel bandwidth to be selected from the ground. Thesatellite carries 24 active transponders powered by 90 Wlinearized traveling wave tube amplifiers. Two 54 MHztransponders at 90 W each can be combined to provide asingle 114 MHz transponder at 180 W.

The two 2.16-m-diameter, highly directional and accuratelypointing dual-gridded reflectors were built using shaped beamtechnology. The east antenna covers Japan and Hawaii, andthe west antenna covers northeast and southeast Asia. TheKu-band steerable spot-beam antennas are capable ofproviding coverage to any location visible from the spacecraft'sgeosynchronous orbit location.

Superbird-C

NSSDC ID: 1997-036A

Alternate Names

24880

Facts in Brief

Launch Date: 1997-07-27Launch Vehicle: Atlas-2 ASLaunch Site: CapeCanaveral, United StatesMass: 3100.0 kgNominalPower: 4500.0 W

Funding Agency

Space CommunicationCorporation (SCC)(Japan)

Discipline

Communications


Launch/Orbitalinformation for Superbird-C

Telecommunicationsinformation for Superbird-C

Experiments on Superbird-C

Data collections fromSuperbird-C



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data









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

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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Superbird-C (1997-036A)














Description

TELSTAR 5 is an American geosynchronous spacecraft thatwas launched by a Proton-K rocket from Baykonurcosmodrome at 17:00 UT. The 3,600 kg spacecraft carries 24C-band and 28 Ku-band transponders to provide voice andvideo communications after parking at 97-W longitude.

Telstar 5

NSSDC ID: 1997-026A

Alternate Names

G-25

Galaxy 25

24812

Facts in Brief


Funding Agencies



Discipline

Communications


Launch/Orbitalinformation for Telstar 5

Experiments on Telstar 5

Data collections fromTelstar 5



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Telstar 5 (1997-026A)














Description

Tempo was a commercial communications satellite launchedfrom Cape Canaveral aboard an Atlas 2A rocket. It was built byLoral Space Systems for Telecommunications, Inc ofEnglewood, CA. It was stationed in a geosynchronous orbit at118.7 deg W, at a perigee of 35,765 and an apogee of 35,805km.

Tempo 2

NSSDC ID: 1997-011A

Alternate Names

24748

Facts in Brief

Launch Date: 1997-03-08Launch Vehicle: Atlas2ALaunch Site: CapeCanaveral, United States

Funding Agency


Discipline

Communications


Launch/Orbitalinformation for Tempo 2

Experiments on Tempo 2

Data collections fromTempo 2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Tempo 2 (1997-011A)











http://www.usa.gov/








Description

THAICOM 3 was a three-axis stabilized spacecraft with apayload capacity of 25 C-Band and 14 Ku-Band transponders.Global Beam coverage on THAICOM 3 spanned over fourcontinents and serviced users in Asia, Europe, Australia, andAfrica. The high-powered Ku-Band transponders, with bothspot and steerable beams, were ideally suitable for DigitalDTH services for Thailand and countries in the region. It is in ageosynchronous orbit at 78.5 d E and has a life expectancy of14 years.

THAICOM 3

NSSDC ID: 1997-016A

Alternate Names

24768

Facts in Brief


Funding Agency

Unknown (Thailand)

Discipline

Communications


Launch/Orbitalinformation for THAICOM3

Experiments on THAICOM3

Data collections fromTHAICOM 3



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







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

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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: THAICOM 3 (1997-016A)











http://www.usa.gov/








Description

THOR 2A is a Norwegian geosynchronous communicationsspacecraft that was launched by a Delta 2 rocket from CapeCanaveral to provide voice and video communications toEurope.

THOR 2A

NSSDC ID: 1997-025A

Alternate Names

24808

Facts in Brief

Launch Date: 1997-05-20Launch Vehicle: DeltaII 7925Launch Site: CapeCanaveral, United States

Discipline

Communications


Launch/Orbitalinformation for THOR 2A

Telecommunicationsinformation for THOR 2A

Experiments on THOR 2A

Data collections fromTHOR 2A



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data








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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: THOR 2A (1997-025A)











http://www.usa.gov/








Description

The Tropical Rainfall Measuring Mission (TRMM), one of thespacecraft in the NASA Earth Probe series of researchsatellites, is a highly-focused, limited-objective program aimedat measuring monthly and seasonal rainfall over the globaltropics and subtropics. TRMM is a joint project between theUSA and Japan to measure rainfall between 35 degrees N and35 degrees S at 350 km altitude.

The TRMM Precipitaing Radar data will provide the firstopportunity to estimate the vertical profile of latent heatrelease. Instruments on-board the satellite are: (1) a singlefrequency (13.8 GHz) Precipitation Radar (PR) provided byJapan; (2) a visible-infrared scanning radiometer (VIRS) similarto AVHRR; (3) a passive microwave radiometer called theTRMM Microwave Imager (TMI), similar to the SSM/Imicrowave radiometer on the DMSP-series; (4) a LightningImaging Sensor (LIS) for the detection and distribution ofglobal lightning; and (5) the Clouds and Earth's RadiantEnergy System (CERES) instrument for the measurement ofthe Earth's radiation budget. With the exception of the PR, allof the instruments are provided by NASA.

The launch vehicle was provided by Japan and the satellite byNASA. The TRMM spacecraft is planned to be a free-flyerlaunched on an expendable Japanese HII rocket with a low-altitude, non-sun-synchronous orbit. The primary C&DH linkfor the TRMM payload is the S-band Single Access (SSA)channel through the Tracking and Data Relay Satellite System(TDRSS). Spacecraft housekeeping command and telemetryand back-up for the science data are via the TDRSS S-bandMultiple Access (SMA) channel. The orbital position of thespacecraft is determined by the TDRSS ranging system. Theminimum mission life for TRMM was to be three years.

TRMM

NSSDC ID: 1997-074A

Alternate Names

Tropical RainfallMeasuring Mission

25063

Facts in Brief


Funding Agencies



Discipline

Earth Science


Launch/Orbitalinformation for TRMM

PDMP information forTRMM

Telecommunicationsinformation for TRMM

Experiments on TRMM

Data collections fromTRMM



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data









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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: TRMM (1997-074A)












Personnel


Dr. John S. Theon Program Scientist NASA Headquarters

Other sources of TRMM information

TRMM project (NASA GSFC)




http://trmm.gsfc.nasa.gov/

http://www.usa.gov/








Description

USA 130 is an American military spacecraft that was launchedby a Titan 4B rocket from Cape Canaveral Air Station.

USA 130

NSSDC ID: 1997-008A

Alternate Names

DSP F18

24737

Facts in Brief

Launch Date: 1997-02-24Launch Vehicle: Titan4BLaunch Site: CapeCanaveral, United States

Funding Agency


Discipline



Launch/Orbitalinformation for USA 130

Experiments on USA 130

Data collections from USA130


Image courtesy of the USAF Defense Support Program.


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


USA 130





http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=USA 130

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=USA 130


mailto:[email protected]?Subject=NMC Comment/Question: USA 130 (1997-008A)











http://nssdc.gsfc.nasa.gov/image/spacecraft/dsp_f18.jpg

http://www.usa.gov/








Description

USA 133 was an American military spacecraft that waslaunched by a Titan 4 rocket from Vandenberg AFB at 02:32UT. According to unofficial reports, USA 133 may be the 16-ton Lacrosse 3 spacecraft with a Synthetic Aperture Radar(SAR). For such reports, see

http://newproducts.jpl.nasa.gov/calander/.

USA 133

NSSDC ID: 1997-064A

Alternate Names

Lacrosse 3

25017

Facts in Brief

Launch Date: 1997-10-23Launch Vehicle: TitanIVLaunchSite: Vandenberg AFB,United States

Funding Agency

National ReconnaissanceOffice (United States)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://newproducts.jpl.nasa.gov/calander/.

















http://www.usa.gov/








Description

USA 136 is an American military spacecraft that was launchedby a Titan-4A rocket from Cape Canaveral Air Station at 02:05UT. Also named TRUMPET, it is believed to carry an antennaof the size of "two football fields".

USA 136

NSSDC ID: 1997-068A

Alternate Names

Trumpet 3

25034

Facts in Brief

Launch Date: 1997-11-06Launch Vehicle: Titan4ALaunch Site: CapeCanaveral, United States

Funding Agency


Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description

Launched with MAQSAT-H from the Kourou Space Center inFrench Guiana, YES (Young Engineers Satellite) was atethered subsatellite designed to be deployed on a 35 kmtether. It contained experiments to measure radiation, the solarangle and acceleration in autonomous mode after separationfrom MAQSAT-H. A GPS receiver was also installed toevaluate the use of GPS for navigation, especially above theGPS satellite constellation.

YES

NSSDC ID: 1997-066C

Alternate Names

Young Engineers Satellite

25025

Facts in Brief


Funding Agency


Discipline

Engineering


Launch/Orbitalinformation for YES

Experiments on YES

Data collections from YES



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

mailto:[email protected]?Subject=NMC Comment/Question: YES (1997-066C)











http://www.usa.gov/








Description

Zeya was the first Russian spacecraft successfully launched bythe Start 1 rocket (a converted SS-25 ICBM) from theSvobodnyi cosmodrome and the first launch from thecosmodrome in the Yakutia Republic in the Amur region. It wasa military cartographic spacecraft.

Zeya

NSSDC ID: 1997-010A

Alternate Names

24744

Facts in Brief

Launch Date: 1997-03-03Launch Vehicle: ICBMRS-12M Topol or SS-25Sickle, 3-stage SRMLaunch Site: Svobodniy,RussiaMass: 87.0 kg

Funding Agency

Unknown (Russia)

Discipline



Launch/Orbitalinformation for Zeya

Telecommunicationsinformation for Zeya

Experiments on Zeya

Data collections from Zeya



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


Zeya







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

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

mailto:[email protected]?Subject=NMC Comment/Question: Zeya (1997-010A)











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

http://www.usa.gov/





NASA - NSSDC - Master Catalog - Spacecraft Query · Navstar 43 1997-035A 1997-07-22 ... Historia...

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