nasa - nssdc - master catalog - spacecraft querycosmos 723 1975-024a 1975-04-02 cosmos 724 1975-025a...

Cronología de Lanzamientos Espaciales

Año 1975 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=BF42196878E66700973FCBB7D762704F[27/08/2010 22:55:36]

Friday, 27 August 2010

Spacecraft Query Results

There were 166 spacecraft returned.

Spacecraft Name NSSDC ID Launch Date

AE-D 1975-096A 1975-10-06

AE-E 1975-107A 1975-11-20

Anik A3 1975-038A 1975-05-07

Aryabhata 1975-033A 1975-04-19

ASTP-Apollo 1975-066A 1975-07-15

ASTP-Soyuz 1975-065A 1975-07-15

Bion 3 1975-110A 1975-11-25

Canyon 6 1975-055A 1975-06-18

COS-B 1975-072A 1975-08-09

Cosmos 702 1975-002A 1975-01-17

Cosmos 703 1975-003A 1975-01-21

Cosmos 704 1975-005A 1975-01-23

Cosmos 705 1975-006A 1975-01-28

Cosmos 706 1975-007A 1975-01-30

Cosmos 707 1975-008A 1975-02-05

Cosmos 708 1975-012A 1975-02-12

Cosmos 709 1975-013A 1975-02-12

Cosmos 710 1975-015A 1975-02-26

Cosmos 711 1975-016A 1975-02-28

Cosmos 712 1975-016B 1975-02-28

Cosmos 713 1975-016C 1975-02-28

Cosmos 714 1975-016D 1975-02-28

Cosmos 715 1975-016E 1975-02-28

Cosmos 716 1975-016F 1975-02-28

Cosmos 717 1975-016G 1975-02-28

Cosmos 718 1975-016H 1975-02-28

Cosmos 719 1975-018A 1975-03-12

Cosmos 720 1975-019A 1975-03-21

Cosmos 721 1975-020A 1975-03-26

Cosmos 722 1975-021A 1975-03-27

Cosmos 723 1975-024A 1975-04-02

Cosmos 724 1975-025A 1975-04-07

Cosmos 725 1975-026A 1975-04-08

Cosmos 726 1975-028A 1975-04-11

Cosmos 727 1975-030A 1975-04-16

Cosmos 728 1975-031A 1975-04-18

NSSDC MasterCatalog Search

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Cosmos 729 1975-034A 1975-04-22

Cosmos 730 1975-035A 1975-04-24

Cosmos 731 1975-041A 1975-05-21

Cosmos 732 1975-045A 1975-05-28

Cosmos 733 1975-045B 1975-05-28

Cosmos 734 1975-045C 1975-05-28

Cosmos 735 1975-045D 1975-05-28

Cosmos 736 1975-045E 1975-05-28

Cosmos 737 1975-045F 1975-05-28

Cosmos 738 1975-045G 1975-05-28

Cosmos 739 1975-045H 1975-05-28

Cosmos 740 1975-046A 1975-05-28

Cosmos 741 1975-047A 1975-05-30

Cosmos 742 1975-048A 1975-06-03

Cosmos 743 1975-053A 1975-06-12

Cosmos 744 1975-056A 1975-06-20

Cosmos 745 1975-058A 1975-06-24

Cosmos 746 1975-059A 1975-06-25

Cosmos 747 1975-060A 1975-06-27

Cosmos 748 1975-061A 1975-07-03

Cosmos 749 1975-062A 1975-07-04

Cosmos 750 1975-067A 1975-07-17

Cosmos 751 1975-068A 1975-07-23

Cosmos 752 1975-069A 1975-07-24

Cosmos 753 1975-071A 1975-07-31

Cosmos 754 1975-073A 1975-08-13

Cosmos 755 1975-074A 1975-08-14

Cosmos 756 1975-076A 1975-08-22

Cosmos 757 1975-078A 1975-08-27

Cosmos 758 1975-080A 1975-09-05

Cosmos 759 1975-084A 1975-09-12

Cosmos 760 1975-085A 1975-09-16

Cosmos 761 1975-086A 1975-09-17

Cosmos 762 1975-086B 1975-09-17

Cosmos 763 1975-086C 1975-09-17

Cosmos 764 1975-086D 1975-09-17

Cosmos 765 1975-086E 1975-09-17

Cosmos 766 1975-086F 1975-09-17

Cosmos 767 1975-086G 1975-09-17

Cosmos 768 1975-086H 1975-09-17

Cosmos 769 1975-088A 1975-09-23

Cosmos 770 1975-089A 1975-09-24

Cosmos 771 1975-090A 1975-09-25

Cosmos 772 1975-093A 1975-09-29

Cosmos 773 1975-094A 1975-09-30

Cosmos 774 1975-095A 1975-10-01

Cosmos 775 1975-097A 1975-10-08

Cosmos 776 1975-101A 1975-10-17

Cosmos 777 1975-102A 1975-10-29



Cosmos 778 1975-103A 1975-11-04

Cosmos 779 1975-104A 1975-11-04

Cosmos 780 1975-108A 1975-11-21

Cosmos 781 1975-109A 1975-11-21

Cosmos 783 1975-112A 1975-11-28

Cosmos 784 1975-113A 1975-12-03

Cosmos 785 1975-116A 1975-12-12

Cosmos 786 1975-120A 1975-12-16

D2B 1975-092A 1975-09-27

D5-A 1975-039A 1975-05-17

D5-B 1975-039B 1975-05-17

DADE-A DADE-A 1975-12-05

DADE-B DADE-B 1975-12-05

DIAPO DIAPO 1975-12-01

DMSP 5C/F2 1975-043A 1975-05-24

DSCS II-05 1975-040A 1975-05-20

DSCS II-06 1975-040B 1975-05-20

DUAL-A DUAL-A 1975-08-01

DUAL-A1 DUAL-A1 1975-08-01

ETS 1975-082A 1975-09-09

GEOS 3 1975-027A 1975-04-09

GOES 1 1975-100A 1975-10-16

HOMS HOMS 1975-08-01

IMEWS 5 1975-118A 1975-12-14

INTELSAT 4 F-1 1975-042A 1975-05-22

INTELSAT 4A F-1 1975-091A 1975-09-26

Intercosmos 13 1975-022A 1975-03-27

Intercosmos 14 1975-115A 1975-12-11

ISIS-C ISIS-C 1975-08-01

Jumpseat 3 1975-017A 1975-03-10

KH 8-44 1975-032A 1975-04-18

KH 8-45 1975-098A 1975-10-09

KH 9-10 1975-051A 1975-06-08

KH 9-11 1975-114A 1975-12-04

Landsat 2 1975-004A 1975-01-22

Meteor 1-21 1975-023A 1975-04-01

Meteor 1-22 1975-087A 1975-09-18

Meteor 1-23 1975-124A 1975-12-25

Meteor 2-1 1975-064A 1975-07-11

Molniya 1-29 1975-036A 1975-04-29

Molniya 1-30 1975-049A 1975-06-05

Molniya 1-31 1975-079A 1975-09-02

Molniya 2-12 1975-009A 1975-02-06

Molniya 2-13 1975-063A 1975-07-08

Molniya 2-14 1975-081A 1975-09-09

Molniya 2-15 1975-121A 1975-12-17

Molniya 3- 2 1975-029A 1975-04-14

Molniya 3- 3 1975-105A 1975-11-14

Molniya 3- 4 1975-125A 1975-12-27



NEMS NEMS 1975-08-01

Nimbus 6 1975-052A 1975-06-12

OSO 8 1975-057A 1975-06-21

PRC 3 1975-070A 1975-07-26

PRC 4 1975-111A 1975-11-26

PRC 5 1975-119A 1975-12-16

Prognoz 4 1975-122A 1975-12-22

Raduga 1 1975-123A 1975-12-22

RCA-SATCOM 1 1975-117A 1975-12-13

RM 20 RM20 1975-04-12

S3-2 1975-114B 1975-12-03

S75-1 SS75-1A 1975-11-01

SAS-C 1975-037A 1975-05-07

Sirio-B SIRIO-B 1975-01-01

SMS 2 1975-011A 1975-02-06

Soyuz 17 1975-001A 1975-01-11

Soyuz 18 1975-044A 1975-05-24

Soyuz 20 1975-106A 1975-11-17

SRET 2 1975-049B 1975-06-05

SSU 1/1 1975-051C 1975-06-08

Starlette 1975-010A 1975-02-06

Symphonie 2 1975-077A 1975-08-27

Taiyo 1975-014A 1975-02-24

TIP 2 1975-099A 1975-10-12

Venera 9 1975-050A 1975-06-08

Venera 9 Descent Craft 1975-050D 1975-06-08

Venera 10 1975-054A 1975-06-14

Venera 10 Descent Craft 1975-054D 1975-06-14

Viking 1 Lander 1975-075C 1975-08-20

Viking 1 Orbiter 1975-075A 1975-08-20

Viking 2 Lander 1975-083C 1975-09-09

Viking 2 Orbiter 1975-083A 1975-09-09

+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.12, 23 July 2010

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NASA - NSSDC - Spacecraft - Details

http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1975-096A[27/08/2010 23:06:38]


Description

The purpose of the AE-D mission was to continue theinvestigation begun by AE-C of the chemical processes andenergy transfer mechanisms that control the structure andbehavior of the earth's atmosphere and ionosphere in theregion of high absorption of solar energy. This mission wasplanned to sample the high latitude regions at the same timethat the AE-E mission was sampling the equatorial and lowlatitude regions. The same type of spacecraft as AE-C wasused, and the payload consisted of the same types ofinstruments except for deletion of the extreme solar UVmonitor and the Bennett ion mass spectrometer, which werepart of the AE-E payload. The polar orbit provided thesampling of all latitudes and the perigee moved through alllatitudes in 3 months and all local times in 4 months.Unfortunately, a failure in the solar power panels resulted in thetermination of operations on January 29, 1976, after slightlyless than 4 months of useful life. However, all the regions atthe perigee altitudes were sampled during this time. Thespacecraft re-entered the atmosphere about 1 month aftercessation of telemetry. To continue the correlated observationswith the AE-E mission, AE-C was reactivated on February 28,1976, to replace AE-D. More details can be found in A.Dalgarno et al., Radio Sci., v. 8, n. 4, p. 263, 1973.

AE-D

NSSDC ID: 1975-096A

Alternate Names

Explorer 54

Atmosphere Explorer-D

08353

Facts in Brief

Launch Date: 1975-10-06Launch Vehicle: DeltaLaunchSite: Vandenberg AFB,United StatesMass: 681.0 kg

Funding Agency

NASA-Office of SpaceScience Applications(United States)

Disciplines

Engineering

Earth Science

Solar Physics

Space Physics

AdditionalInformation

Launch/Orbitalinformation for AE-D

Experiments on AE-D

Data collections from AE-D

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


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data



http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1975-096A


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

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mailto:[email protected]?Subject=NMC Comment/Question: AE-D (1975-096A)

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Personnel

Name Role Original Affiliation E-mail

Mr. Frank W. Gaetano Program Manager NASA Headquarters

Mr. David W. Grimes Project Manager NASA Goddard Space Flight Center

Dr. Nelson W. Spencer Project Scientist NASA Goddard Space Flight Center

Dr. Erwin R.Schmerling

Program Scientist NASA Headquarters

Other AE Data/Information at NSSDC

AE-AAE-BAE-CAE-DAE-E


http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1963-009A



http://www.usa.gov/








Description

The purpose of the AE-E mission was to investigate thechemical processes and energy transfer mechanisms thatcontrol the structure and behavior of the earth's atmosphereand ionosphere in the region of high absorption of solar energyat low and equatorial latitudes. The simultaneous sampling athigher latitudes was carried out by the AE-D spacecraft until itsfailure on January 29, 1976, and then by AE-C, until itreentered on December 12, 1978. The same type of spacecraftas AE-C was used, and the payload consisted of the sametypes of instruments except that the low-energy electron andUV nitric oxide experiments were deleted and a backscatterUV spectrometer was added to monitor the ozone content ofthe atmosphere. The two experiments that were deleted weremore appropriate for the high-latitude regions. The perigeeswept through more than six full latitude cycles and two localtime cycles during the first year after launch when the orbit waselliptical and the perigee height was varied between 130 and400 km. The circularization of the orbit around 390 km wasmade on November 20, 1976 and the spacecraft was raised tothis height whenever it would decay to about 250 km. AE-Ereentered on June 10, 1981. More details can be found in A.Dalgarno et al., Radio Sci., v. 8, n. 4, p. 263, 1973.

AE-E

NSSDC ID: 1975-107A

Alternate Names

Explorer 55

AE 5

Atmosphere Explorer-E

08440

Facts in Brief

Launch Date: 1975-11-20Launch Vehicle: DeltaLaunch Site: CapeCanaveral, United StatesMass: 735.0 kg

Funding Agency


Disciplines

Earth Science

Solar Physics

Space Physics


Launch/Orbitalinformation for AE-E

Experiments on AE-E

Data collections from AE-E


Personnel


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=AE-E

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=AE-E

mailto:[email protected]?Subject=NMC Comment/Question: AE-E (1975-107A)

mailto:[email protected]?Subject=NMC Comment/Question: AE-E (1975-107A)












Mr. Herbert B. Chisholm ProgramManager

NASA Headquarters

Mr. J. Patrick Corrigan,III

Project Manager NASA Goddard Space FlightCenter

Dr. Nelson W. Spencer Project Scientist NASA Goddard Space FlightCenter

Dr. Erwin R. Schmerling ProgramScientist

NASA Headquarters

Other AE Data/Information at NSSDC

AE-AAE-BAE-CAE-DAE-E





http://www.usa.gov/








Description

Telesat 3 (Anik A3) was the third domestic communicationssatellite launched by NASA from Cape Canaveral for theCanadian company Telesat. It weighed approximately 281 kgin a geostationary orbit with an anticipated life of seven years.It was about 1.83 m in diameter and 3.35 m high. The satellitecommunications system provided for 12 RF channels, two ofwhich were protection channels for the 10 traffic carryingchannels. Up-link transmission was the 5.925- to 6.425-gHzband, and the down-link operated in the 3.7- to 4.2-gHz band.Telemetry, tracking, and command functions required forsatellite station keeping and positioning were also provided inthose frequency bands.

Anik A3

NSSDC ID: 1975-038A

Alternate Names

Telesat-C

Anik-C

Telesat 3

Anik 3

07790

Facts in Brief


Funding Agencies

Telesat Canada Ltd.,Ottawa (Canada)

NASA-Office ofApplications (UnitedStates)

Discipline

Communications


Launch/Orbitalinformation for Anik A3

Experiments on Anik A3

Data collections from AnikA3

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=Anik A3

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Anik A3

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Anik A3

mailto:[email protected]?Subject=NMC Comment/Question: Anik A3 (1975-038A)














Description

This spacecraft, named after the famous Indian astronomer,was India's first satellite and was completely designed andfabricated in India. It was launched by a Soviet rocket from aSoviet cosmodrome. The spacecraft was quasispherical inshape containing 26 sides and contained three experiments forthe measurement of cosmic X rays, solar neutrons, andGamma rays, and an ionospheric electron trap along with a UVsensor. The spacecraft weighed 360 kg, used solar panels on24 sides to provide 46 watts of power, used a passive thermalcontrol system, contained batteries, and a spin-up gas jetsystem to provide a spin rate of not more than 90 rpm. Therewas a set of altitude sensors comprised of a triaxialmagnetometer, a digital elevation solar sensor, and fourazimuth solar sensors. The data system included a taperecorder at 256 b/s with playback at 10 times that rate. ThePCM-FM-PM telemetry system operated at 137.44 MHz. Thenecessary ground telemetry and telecommand stations wereestablished at Shar Centre in Sriharikota, Andhra Pradesh.

Aryabhata

NSSDC ID: 1975-033A

Alternate Names

Indian Scientific Sat

Ariabat

07752

Facts in Brief

Launch Date: 1975-04-19LaunchVehicle: Intercosmos II,RussiaLaunch Site: KapustinYar, IndiaMass: 360.0 kg

Funding Agencies

Unknown (U.S.S.R)

Indian Space ResearchOrganization (India)

Disciplines

Earth Science

Space Physics


Launch/Orbitalinformation for Aryabhata

Experiments on Aryabhata

Data collections fromAryabhata



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Aryabhata (1975-033A)













Personnel


Prof. Udipi RamachandraRao

ProjectDirector

ISRO Satellite Center [email protected]


http://www.usa.gov/








Description

The United States and the U.S.S.R. launched an Apollospacecraft and a Soyuz spacecraft, respectively, as a jointeffort called the Apollo-Soyuz Test Project (ASTP). The Soyuzspacecraft was launched first, with a two-man crew whomaneuvered their spacecraft into a docking orbit. The Apollospacecraft was launched 7-1/2 h later, with a three-man crewwho placed their spacecraft into a proper configuration fordocking with the Soyuz spacecraft. The docking of the twospacecraft occurred on the third day. After docking, crewtransfers took place, with the Apollo crew first visiting theSoyuz. The combined Apollo-Soyuz crews performed jointexperiments and presented radio and TV reports. After jointexperiments were completed, the spacecraft disengaged andeach continued its separate mission.

ASTP-Apollo

NSSDC ID: 1975-066A

Alternate Names

Soyuz Apollo

Apollo-Soyuz Test Proj.

08032

Facts in Brief

Launch Date: 1975-07-15Launch Vehicle: Saturn1BLaunch Site: CapeCanaveral, United StatesMass: 14856.0 kg

Funding Agency

NASA-Office of MannedSpace Flight (UnitedStates)

Disciplines

Astronomy

Engineering

Earth Science

Human Crew

Life Science

Microgravity

Space Physics


Launch/Orbitalinformation for ASTP-Apollo

Experiments on ASTP-Apollo

Data collections fromASTP-Apollo


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


ASTP-Apollo





http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=ASTP-Apollo

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=ASTP-Apollo

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=ASTP-Apollo

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=ASTP-Apollo









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




Personnel


Mr. Chester M. Lee Project Manager NASA Headquarters

Mr. R. Thomas Giuli Program Scientist NASA Johnson Space Center

ASTP Soyuz PageThe Partnership: A History of the Apollo-Soyuz Test Project - Online BookApollo Home PageMoon Home Page


mailto:[email protected]?Subject=NMC Comment/Question: ASTP-Apollo (1975-066A)



http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1975-065A

http://www.hq.nasa.gov/office/pao/History/SP-4209/cover.htm

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

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

http://www.usa.gov/








Description

The United States and the U.S.S.R. launched an Apollospacecraft and a Soyuz spacecraft, respectively, as a jointeffort called the Apollo-Soyuz Test Project (ASTP). The Soyuzspacecraft was launched first, with a two-man crew whomaneuvered their spacecraft into a docking orbit. The Apollospacecraft was launched 7-1/2 h later, with a three-man crewwho placed their spacecraft into a proper configuration fordocking with the Soyuz spacecraft. The docking of the twospacecraft occurred on the third day. After docking, crewtransfers took place, with the Apollo crew first visiting theSoyuz. The combined Apollo-Soyuz crews performed jointexperiments and presented radio and TV reports. After jointexperiments were completed, the spacecraft disengaged andeach continued its separate mission.

ASTP-Soyuz

NSSDC ID: 1975-065A

Alternate Names

Apollo-Soyuz Test Proj.

Soyuz 19

Soyuz Apollo

08030

Facts in Brief

Launch Date: 1975-07-15LaunchVehicle: Modified SS-6(Sapwood) with 2ndGeneration (Longer) UpperStageLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 6800.0 kg

Funding Agency

Soviet Academy ofSciences (U.S.S.R)

Disciplines

Human Crew

Life Science


Launch/Orbitalinformation for ASTP-Soyuz

Experiments on ASTP-Soyuz

Data collections fromASTP-Soyuz

Questions or commentsabout this spacecraft can


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


ASTP-Soyuz





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

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

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

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









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



be directed to: CoordinatedRequest and User SupportOffice.

Personnel


Dr. Y. K. Khodarev Program Scientist Soviet Academy of Sciences

ASTP Apollo PageThe Partnership: A History of the Apollo-Soyuz Test Project - Online BookApollo Home PageMoon Home Page


mailto:[email protected]?Subject=NMC Comment/Question: ASTP-Soyuz (1975-065A)




http://www.hq.nasa.gov/office/pao/History/SP-4209/cover.htm

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

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

http://www.usa.gov/








Description

Bion 3 (Cosmos 782) was the first joint U.S.-Soviet biomedicalresearch flight. It carried fourteen experiments prepared byseven countries in all. It included a centrifuge with revolvingand fixed sections in which identical groups of animals, plants,and cells could be compared. The subject animals includedwhite rats and tortoises. The effects of aging on fruit fly liversand plant tissues with grafted cancerous growths were alsostudied. The mission ended after 19.5 days.

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

Bion 3

NSSDC ID: 1975-110A

Alternate Names

Cosmos 782

Biocosmos 3

08450

Facts in Brief

Launch Date: 1975-11-25Launch Vehicle: SoyuzLaunch Site: Plesetsk,U.S.S.RMass: 4000.0 kg

Funding Agencies

Institute of BiomedicalProblems, Moscow(U.S.S.R)

National Aeronautics andSpace Administration(United States)

Discipline

Life Science


Launch/Orbitalinformation for Bion 3

Experiments on Bion 3

Data collections from Bion3



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=Bion 3

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Bion 3 (1975-110A)
















Description

This US Air Force electronics intelligence satellite waslaunched from Vandenberg AFB aboard a Atlas Agena Drocket.

Canyon 6

NSSDC ID: 1975-055A

Alternate Names

1975-055A

07963

Facts in Brief

Launch Date: 1975-06-18Launch Vehicle: Atlas-AgenaLaunch Site: CapeCanaveral, United StatesMass: 350.0 kg

Funding Agency

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

Discipline

Surveillance and OtherMilitary


Launch/Orbitalinformation for Canyon 6

Experiments on Canyon 6

Data collections fromCanyon 6



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Canyon 6 (1975-055A)











http://www.usa.gov/








Description

The COS-B scientific satellite was developed by the EuropeanSpace Agency (ESA) to study extraterrestrial gamma radiationin the 25-MeV to 1-GeV energy range from a highly ellipticalorbit of roughly 100,000-km apogee, 350-km perigee, andnear-polar inclination. NASA provided, on a fully reimbursablebasis, the Delta launch vehicle and the associated launchservices. The COS-B spacecraft was cylindrical with adiameter of 140 cm and a height of 121 cm. Four monopoleantennas, protruding 51.2 cm below the bottom of thecylindrical body, gave the spacecraft a total effective height of172.2 cm. The spacecraft obtained orientation of its angularmomentum vector with respect to inertial space using datafrom an earth albedo sensor and a solar sensor. Spacecraftattitude was adjusted by a nitrogen cold-gas attitude controlsystem (ACS). The ACS included two spin-rate-adjust nozzlesto maintain the spin rate at 10 rpm and two precession nozzlesto adjust the momentum vector. The spacecraft had apcm/psk/pm telemetry system with 6.5-W real-time-onlytransmitter providing a switchable bit rate of 160 and 320 bpsand a pcm/psk/pm, up-link/down-link, range-tone commandsystem. Power was supplied by 9480 solar cells mounted on12 subpanels on the cylindrical body of the spacecraft.Communications, command, and control of the COS-B satellitein orbit were provided by the ESA Estrack network. Thespacecraft enclosed a gamma-ray astronomy experimentdescribed under "COS-B Caravane Collaboration" below.Members of the university and research groups whoimplemented this satellite are listed, with their affiliations, inAppendix B.

COS-B

NSSDC ID: 1975-072A

Alternate Names

Cosmic Ray Satellite-B

08062

Facts in Brief


Funding Agency

European Space Agency(International)

Discipline

Astronomy


Launch/Orbitalinformation for COS-B

Experiments on COS-B

Data collections from COS-B


Personnel


Dr. Brian General ESA-European Space Research


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: COS-B (1975-072A)













G. Taylor Contact and Technology Centre

Dr. KevinBennett

ProjectScientist

ESA-European Space Researchand Technology Centre

[email protected]

Mr. G.Altmann

ProjectManager

ESA-European Space Researchand Technology Centre

US Active Archive for COS-B Information/Data

The COS-B Archive at HEASARC

Other Sources of COS-B Information/Data

COS-B (ESA)


http://heasarc.gsfc.nasa.gov/docs/cosb/archive/cosb_archive.html

http://astro.estec.esa.nl/SA-general/Projects/Cosb/cosb.html

http://www.usa.gov/








Description

Cosmos 702 was a Soviet photo surveillance satellite launchedfrom the Baikonur cosmodrome aboard a Soyuz rocket.

Cosmos 702

NSSDC ID: 1975-002A

Alternate Names

07606

Facts in Brief

Launch Date: 1975-01-17Launch Vehicle: SoyuzLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 4000.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline



Launch/Orbitalinformation for Cosmos702

Experiments on Cosmos702

Data collections fromCosmos 702



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Cosmos 702


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Cosmos 702


mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 702 (1975-002A)











http://www.usa.gov/








Description

Cosmos 703 was a Soviet DS type military satellite launchedfrom the Plesetsk cosmodrome.

DS (Dnepropetrovsk Sputnik) were small satellites built byYangel's OKB-586 / KB Yuzhnoye in the Ukraine for launch bythe same KB's Kosmos launch vehicles. They were used for awide range of military and scientific research and componentproving tests.

Cosmos 703

NSSDC ID: 1975-003A

Alternate Names

07611

Facts in Brief

Launch Date: 1975-01-21LaunchVehicle: Kosmos-2ILaunch Site: Plesetsk,U.S.S.RMass: 400.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 704 was a Soviet photo surveillance satellite launchedfrom the Plesetsk cosmodrome aboard a Soyuz rocket. Thespacecraft was maneuverable.

Cosmos 704

NSSDC ID: 1975-005A

Alternate Names

07617

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/







Saturday, 28 August 2010

Description



Cosmos 705

NSSDC ID: 1975-006A

Alternate Names

07623

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 706 was a Soviet missile early warning satellitelaunched from the Plesetsk cosmodrome aboard a Soyuzrocket. It covered the Oko constellation planes 7/8 - 182degree longitude of ascending node.

Cosmos 706

NSSDC ID: 1975-007A

Alternate Names

07625

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 707 was a Soviet ELINT (Electronic and SignalsIntelligence) satellite launched from the Plesetsk cosmodrome.

From 1965 to 1967 two dedicated ELINT systems were tested:the Tselina and the Navy's US. Both reached service, since theMinistry of Defence could not force a single system on themilitary services.

Tselina was developed by Yuzhnoye and consisted of twosatellites: Tselina-O for general observations and Tselina-D fordetailed observations. ELINT systems for Tselina were firsttested under the Cosmos designation in 1962 to 1965. The firstTselina-O was launched in 1970. The Tselina-D took a longtime to enter service due to delays in payload developmentand weight growth. The whole Tselina system was notoperational until 1976. Constant improvement resulted inTselina-O being abandoned in 1984 and all systems being puton Tselina-D.

Cosmos 707

NSSDC ID: 1975-008A

Alternate Names

07637

Facts in Brief

Launch Date: 1975-02-05LaunchVehicle: Kosmos-3Launch Site: Plesetsk,U.S.S.RMass: 900.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 708 was a Soviet geodetic satellite launched from thePlesetsk cosmodrome aboard a Kosmos 3 rocket.

The Sfera geodetic system covered a broad development forsolving problems in geodetics, continental drift, and preciselocation of cartographic points. The spacecraft was equippedwith measurement and signalling apparatus, providingassistance in measuring astronomical-geodetic points ofmilitary topographical research for the Red Army General Staff.The satellite allowed improved accuracy for long rangeweapons. Reshetnev was the Chief Designer. Flight tests werefrom 1968 to 1972. Series flights were from 1973 to 1980. TheKosmos 3M launcher was used. Colonel Ye S Shchapov wasin charge of Sfera development. Sfera used the basic KAUR-1bus, consisting of a 2.035 m diameter cylindrical spacecraftbody, with solar cells and radiators of the thermostatictemperature regulating system mounted on the exterior.Orientation was by a single-axis magneto-gravitational (gravitygradient boom) passive system. The hermetically sealedcompartment had the equipment mounted in cruciform bays,with the chemical batteries protecting the radio and guidanceequipment mounted at the centre.

Cosmos 708

NSSDC ID: 1975-012A

Alternate Names

07663

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Earth Science







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 709

NSSDC ID: 1975-013A

Alternate Names

07664

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 710 was a Soviet photo surveillance satellite launchedfrom the Baikonur cosmodrome aboard a Soyuz rocket. Thespacecraft was maneuverable.

Cosmos 710

NSSDC ID: 1975-015A

Alternate Names

07675

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

The lowest level of the three-tier communications satelliteconstellation was populated with two distinct systems devotedto military and government communications. Both systemswere assessed to be simple store-dump repeaters which wereparticularly useful in relaying traffic between the RussianFederation and overseas stations or forces. These Strela(which means "Arrow" in Russian) satellites recorded radiomessages transmitted by Russian intelligence agentsworldwide and relayed them when flying over Moscow.Debuting in 1970 was a system of small (61 kg, 0.80 m by0.75 m) relay satellites launched from Plesetsk by the Kosmosbooster in groups of eight. Although the mean altitude of thisconstellation was near 1500 km, each set of eight Strela 1satellites was normally dispersed into slightly elliptical orbitswith mean altitudes between 1430 and 1490 km. Theintentional orbital period differences of about 0.15 min ensuredthat the satellites would become randomly spaced about theorbital plane shortly after launch. Unlike the lower altitudeconstellation, this network relied on a single orbital plane withan inclination of 74 deg which was replenished on the averageof once each year. The last mission in this network was inJune 1992, and the network has now been superseded by themore modern and capable Strela 3 system.

Cosmos 711

NSSDC ID: 1975-016A

Alternate Names

07678

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

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=1975-016B[28/08/2010 22:49:23]


Description


Cosmos 712

NSSDC ID: 1975-016B

Alternate Names

07679

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1975-016B







mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 712 (1975-016B)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1975-016C[28/08/2010 22:50:07]


Description


Cosmos 713

NSSDC ID: 1975-016C

Alternate Names

07680

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1975-016C







mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 713 (1975-016C)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1975-016D[28/08/2010 22:50:42]


Description


Cosmos 714

NSSDC ID: 1975-016D

Alternate Names

07681

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1975-016D







mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 714 (1975-016D)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1975-016E[28/08/2010 22:51:09]


Description


Cosmos 715

NSSDC ID: 1975-016E

Alternate Names

07682

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1975-016E







mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 715 (1975-016E)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1975-016F[28/08/2010 22:51:31]


Description


Cosmos 716

NSSDC ID: 1975-016F

Alternate Names

07683

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1975-016F







mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 716 (1975-016F)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1975-016G[28/08/2010 22:52:05]


Description


Cosmos 717

NSSDC ID: 1975-016G

Alternate Names

07684

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1975-016G







mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 717 (1975-016G)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1975-016H[28/08/2010 22:52:31]


Description


Cosmos 718

NSSDC ID: 1975-016H

Alternate Names

07685

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1975-016H







mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 718 (1975-016H)











http://www.usa.gov/








Description


Cosmos 719

NSSDC ID: 1975-018A

Alternate Names

07691

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 720 was a Soviet military topography satellitelaunched from the Plesetsk cosmodrome aboard a Soyuzrocket.

A special version of Zenit was developed for topographicalphotography. This was developed by OKB-1 Filial 1 based onthe Zenit-4M. It utilized the SA-106 topographic camera fromthe Krasnogorsk Mechanical Factory, and a laser altimeter anddoppler apparatus developed by NPO Radiopribor.

Cosmos 720

NSSDC ID: 1975-019A

Alternate Names

07696

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 721 was a Soviet photo surveillance satellite launchedfrom the Plesetsk cosmodrome aboard a Soyuz rocket.Separated science capsule.

Cosmos 721

NSSDC ID: 1975-020A

Alternate Names

07705

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 722

NSSDC ID: 1975-021A

Alternate Names

07709

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 723 was a Soviet nuclear powered Radar OceanReconnaissance Satellite (RORSAT) launched from theBaikonur cosmodrome aboard a Tsyklon 2 rocket. TheRORSATs were designed to search the oceans for US Navytask forces and other shipping.

Cosmos 723

NSSDC ID: 1975-024A

Alternate Names

07718

Facts in Brief

Launch Date: 1975-04-02LaunchVehicle: Tsiklon-2Launch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 3800.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 724 was a Soviet nuclear powered Radar OceanReconnaissance Satellite (RORSAT) launched from theBaikonur cosmodrome aboard a Tsyklon 2 rocket. TheRORSATs were designed to search the oceans for US Navytask forces and other shipping.

Cosmos 724

NSSDC ID: 1975-025A

Alternate Names

07727

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description



Cosmos 725

NSSDC ID: 1975-026A

Alternate Names

07730

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 726 was part of a 6-satellite Soviet military navigationsystem distributed in orbital planes spaced 30 degrees apart,and launched from the Plesetsk cosmodrome aboard aCosmos rocket. Navigation information was derived fromDoppler-shifted VHF transmissions (approximately 150 and400 MHz) of the satellite position and orbital data. By acquiringfixes 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 726

NSSDC ID: 1975-028A

Alternate Names

07736

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Navigation & GlobalPositioning







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 727

NSSDC ID: 1975-030A

Alternate Names

07742

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 728

NSSDC ID: 1975-031A

Alternate Names

07745

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/







Sunday, 29 August 2010

Description


Cosmos 729

NSSDC ID: 1975-034A

Alternate Names

07768

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 730

NSSDC ID: 1975-035A

Alternate Names

07770

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 731 was a Soviet photo surveillance satellite launchedfrom the Baikonur cosmodrome aboard a Soyuz rocket. It alsocarried an x-ray and/or gamma-ray experiment capsule.

Cosmos 731

NSSDC ID: 1975-041A

Alternate Names

07810

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Disciplines

Astronomy








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 732

NSSDC ID: 1975-045A

Alternate Names

07820

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 733

NSSDC ID: 1975-045B

Alternate Names

07822

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 734

NSSDC ID: 1975-045C

Alternate Names

07823

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 735

NSSDC ID: 1975-045D

Alternate Names

07824

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 736

NSSDC ID: 1975-045E

Alternate Names

07825

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 737

NSSDC ID: 1975-045F

Alternate Names

07826

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 738

NSSDC ID: 1975-045G

Alternate Names

07827

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 739

NSSDC ID: 1975-045H

Alternate Names

07828

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 740

NSSDC ID: 1975-046A

Alternate Names

07821

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 741 was a Soviet photo surveillance satellite launchedfrom the Plesetsk Cosmodrome via a Soyuz rocket. The Zenit-2M type satellite was used for earth resources studies as partof the Gektor-Priroda project. It conducted investigations of thenatural resources of the Earth in the interests of variousbranches of the national economy of the USSR andinternational cooperation.

Cosmos 741

NSSDC ID: 1975-047A

Alternate Names

07877

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Disciplines

Earth Science








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 742

NSSDC ID: 1975-048A

Alternate Names

07900

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 743

NSSDC ID: 1975-053A

Alternate Names

07925

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description




Cosmos 744

NSSDC ID: 1975-056A

Alternate Names

07968

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description



Cosmos 745

NSSDC ID: 1975-058A

Alternate Names

07982

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 746

NSSDC ID: 1975-059A

Alternate Names

07985

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


National Space Science Data Center Header

Cosmos 747

NSSDC ID: 1975-060A

Alternate Names

07990

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 748

NSSDC ID: 1975-061A

Alternate Names

08006

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description




Cosmos 749

NSSDC ID: 1975-062A

Alternate Names

08009

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description



Cosmos 750

NSSDC ID: 1975-067A

Alternate Names

08036

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 751 was a Soviet photo surveillance satellite launchedfrom the Plesetsk cosmodrome aboard a Soyuz rocket.

Cosmos 751

NSSDC ID: 1975-068A

Alternate Names

08040

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 752 was a Soviet atmospheric research satellitelaunched from the Plesetsk cosmodrome aboard a Kosmos 3rocket. It was the third in a series of Vektor spacecraft.

Cosmos 752

NSSDC ID: 1975-069A

Alternate Names

08043

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Earth Science







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 753

NSSDC ID: 1975-071A

Alternate Names

08059

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 754

NSSDC ID: 1975-073A

Alternate Names

08069

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 755 was part of a 6-satellite Soviet military navigationsystem distributed in orbital planes spaced 30 degrees apart,and launched from the Plesetsk cosmodrome aboard aKosmos 3 rocket. Navigation information was derived fromDoppler-shifted VHF transmissions (approximately 150 and400 MHz) of the satellite position and orbital data. By acquiringfixes 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 755

NSSDC ID: 1975-074A

Alternate Names

08072

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/







Tuesday, 31 August 2010

Description




Cosmos 756

NSSDC ID: 1975-076A

Alternate Names

08127

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.13, 30 August 2010




















http://www.usa.gov/








Description


Cosmos 757

NSSDC ID: 1975-078A

Alternate Names

08147

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 758 was a Soviet photo surveillance satellite launchedfrom the Plesetsk cosmodrome aboard a Soyuz rocket. ThirdYantar-2K flight, the first with the new Kondor attitude controlsystem. This system experienced problems and failed on thesecond day of flight. The spacecraft's destruct package wasactivated by ground command and the spacecraft wasdestroyed on 6 September 1975 in its second day of flight.

Cosmos 758

NSSDC ID: 1975-080A

Alternate Names

08191

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 759

NSSDC ID: 1975-084A

Alternate Names

08275

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 760

NSSDC ID: 1975-085A

Alternate Names

08281

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 761

NSSDC ID: 1975-086A

Alternate Names

08285

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 762

NSSDC ID: 1975-086B

Alternate Names

08286

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 763

NSSDC ID: 1975-086C

Alternate Names

08287

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 764

NSSDC ID: 1975-086D

Alternate Names

08288

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 765

NSSDC ID: 1975-086E

Alternate Names

08289

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 766

NSSDC ID: 1975-086F

Alternate Names

08290

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 767

NSSDC ID: 1975-086G

Alternate Names

08291

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 768

NSSDC ID: 1975-086H

Alternate Names

08292

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 769 was a Soviet photo surveillance satellite launchedfrom the Plesetsk cosmodrome aboard a Soyuz rocket. Thirdsuccessful test of SpK small film return capsule planned forYantar. SpK capsule FEU-170-13 No. 5L successfullyrecovered.

Cosmos 769

NSSDC ID: 1975-088A

Alternate Names

08322

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 770 was a Soviet geodetic satellite launched from thePlesetsk cosmodrome aboard a Kosmos 3 rocket.

The Sfera geodetic system covered a broad development forsolving problems in geodetics, continental drift, and preciselocation of cartographic points. The spacecraft was equippedwith measurement and signalling apparatus, providingassistance in measuring astronomical-geodetic points ofmilitary topographical research for the Red Army General Staff.The satellite allowed improved accuracy for long rangeweapons. Reshetnev was the Chief Designer. Flight tests werefrom 1968 to 1972. Series flights were from 1973 to 1980. TheKosmos 3M launcher was used. Colonel Ye S Shchapov wasin charge of Sfera development. Sfera used the basic KAUR-1bus, consisting of a 2.035 m diameter cylindrical spacecraftbody, with solar cells and radiators of the thermostatictemperature regulating system mounted on the exterior.Orientation was by a single-axis magneto-gravitational (gravitygradient boom) passive system. The hermetically sealedcompartment had the equipment mounted in cruciform bays,with the chemical batteries protecting the radio and guidanceequipment mounted at the centre.

Cosmos 770

NSSDC ID: 1975-089A

Alternate Names

08325

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Earth Science







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 771 was a Soviet photo surveillance satellite launchedfrom the Plesetsk cosmodrome aboard a Soyuz rocket. Thespacecraft was maneuverable and also performed earthresources tasks.

Cosmos 771

NSSDC ID: 1975-090A

Alternate Names

08327

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 772 was an unmanned Soviet military Soyuz 7K-Stest flight launched from the Baikonur cosmodrome. It wasrecovered October 3, 1975 at 4:10 GMT after an unsuccessfulflight.

Cosmos 772

NSSDC ID: 1975-093A

Alternate Names

08338

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Engineering







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

The lowest level of the three-tier communications satelliteconstellation is now populated with two distinct systemsdevoted to military and government communications. Bothsystems are assessed to be simple store-dump repeaterswhich were particularly useful in relaying non-essential trafficbetween the Russian Federation and overseas stations offorces. The first Strela (which means "Arrow" in Russian)system debuted in 1970 and consisted of 750 - 1000 kgsatellites deployed at mean altitudes of 800 km in three orbitalplanes inclined 74 degrees to the equator and spaced 120degrees apart. These Strela 2 spacecraft were launchedseparately by the Kosmos launch vehicle from the Plesetskcosmodrome into each orbital plane at intervals of 24-36months. The activity of these satellites could be monitored viaa characteristic CW beacon emitted on a frequency of 153.660MHz.

Cosmos 773

NSSDC ID: 1975-094A

Alternate Names

08343

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 774

NSSDC ID: 1975-095A

Alternate Names

08345

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 775 was the first launch of the new Sovietgeosynchronous ballistic missile early warning systemsatellites, launched from the Baikonur cosmodrome aboard aProton 8K82K rocket. It exploded in orbit.

Cosmos 775

NSSDC ID: 1975-097A

Alternate Names

08357

Facts in Brief

Launch Date: 1975-10-08Launch Vehicle: ProtonLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 2000.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 776

NSSDC ID: 1975-101A

Alternate Names

08369

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 777 was a Soviet military naval reconnaisance, oceanmonitoring satellite launched from the Baikonur cosmodromeaboard a Tsyklon 2 rocket. This naval forces monitoringspacecraft was used to determine the position of enemy navalforces through detection and triangulation of theirelectromagnetic emissions (radio, radar, etc). It exploded inJanuary 1976.

Cosmos 777

NSSDC ID: 1975-102A

Alternate Names

08416

Facts in Brief

Launch Date: 1975-10-29LaunchVehicle: TsiklonLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 3000.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 778

NSSDC ID: 1975-103A

Alternate Names

08419

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 779

NSSDC ID: 1975-104A

Alternate Names

08420

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 780 was a Soviet photo surveillance satellite launchedfrom Plesetsk cosmodrome aboard a Soyuz rocket. Separatedscience capsule.

Cosmos 780

NSSDC ID: 1975-108A

Alternate Names

08442

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description




Cosmos 781

NSSDC ID: 1975-109A

Alternate Names

08444

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

The lowest level of the three-tier communications satelliteconstellation is now populated with two distinct systemsdevoted to military and government communications. Bothsystems are assessed to be simple store-dump repeaterswhich were particularly useful in relaying non-essential trafficbetween the Russian Federation and overseas stations offorces. The first Strela (which means "Arrow" in Russian)system debuted in 1970 and consisted of 750 - 1000 kgsatellites deployed at mean altitudes of 800 km in three orbitalplanes inclined 74 degrees to the equator and spaced 120degrees apart. These Strela 2 spacecraft were launchedseparately by the Kosmos launch vehicle from the Plesetskcosmodrome into each orbital plane at intervals of 24-36months. The activity of these satellites could be monitored viaa characteristic CW beacon emitted on a frequency of 153.660MHz.

Cosmos 783

NSSDC ID: 1975-112A

Alternate Names

08458

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 784

NSSDC ID: 1975-113A

Alternate Names

08463

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 785 was a Soviet military naval radar surveillance(RORSAT) satellite launched from the Baikonur cosmodromeaboard a Tsyklon 2 rocket. It failed immediately after reachingorbit.

Cosmos 785

NSSDC ID: 1975-116A

Alternate Names

08473

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 786

NSSDC ID: 1975-120A

Alternate Names

08489

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

This spacecraft carried an EUV experiment for solar andatmospheric investigations and a set of UV experiments formaking stellar, zodiacal light, and integrated sky backgroundand stellar observations. The spacecraft was spinning at about0.25 rpm about an axis that was directed toward the sun. Thedata transmission rate was 256 b/s for real-time data and 11kb/s for stored data at a telemetry frequency of 136.740 MHz.The memory capacity was 1.6 Mb. The cylindrically shapedsatellite had a diameter of 0.8 m and a height of 0.7 m andweighed 106.6 kg. Four solar panels situated perpendicular tothe cylindrical axis provided power for the mission. Thestabilization system failed on December 28, 1976, therebyterminating operation of the spacecraft.

D2B

NSSDC ID: 1975-092A

Alternate Names

Astronomy Satellite D2B

Facts in Brief

Launch Date: 1975-09-27LaunchVehicle: DiamantLaunch Site: Kourou,French GuianaMass: 115.0 kg

Funding Agency

Centre National de laRecherche Scientifique(France)

Discipline

Solar Physics


Launch/Orbitalinformation for D2B

Experiments on D2B

Data collections from D2B


Personnel


Dr. D. Sacotte Project Manager Centre National d'Etudes Spatiales


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=D2B

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=D2B

mailto:[email protected]?Subject=NMC Comment/Question: D2B (1975-092A)














Description

The French D5-A satellite was launched as a piggyback of theD5-B. The external structure of the D5-A was an octahedronmade up of two truncated tetrahedrons, eight facets of whichwere covered with solar cells. The D5-A carried a hydrazinepropeller that was tested in space.

D5-A

NSSDC ID: 1975-039A

Alternate Names

Pollux

07801

Facts in Brief


Funding Agency

Centre National d'EtudesSpatiales (France)

Discipline

Engineering


Launch/Orbitalinformation for D5-A

Experiments on D5-A

Data collections from D5-A


Personnel


Mr. A. Olivero Project Manager Centre National d'Etudes Spatiales

Mr. J. P. Chassaing Project Coordinator Centre National d'Etudes Spatiales


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=D5-A

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=D5-A

mailto:[email protected]?Subject=NMC Comment/Question: D5-A (1975-039A)














Description

This French spacecraft had a 26-face polyhedron shape with adiameter of 80 cm. The primary mission objective was to studythe upper atmosphere density variations. Secondary objectivesincluded a study of gravity field perturbations and a study ofmicrometeorite impacts. A three-axis magnetometer was usedto provide attitude information. Each one of the spacecraftfaces contained a laser reflector. Data were measured eitherevery 0.1 s or every 2.8 s. The data transmission rate was1024 bits/s from the tape recorder and either 256 or 512 bits/sdirectly from telemetry. Operations were conducted by theoperations center in Toulouse using the CNES network oftelemetry and telecommand stations.

D5-B

NSSDC ID: 1975-039B

Alternate Names

Castor

07802

Facts in Brief


Funding Agency


Disciplines

Earth Science

Planetary Science


Launch/Orbitalinformation for D5-B

Experiments on D5-B

Data collections from D5-B


Personnel


Mr. A. Olivero Project Centre National d'Etudes Spatiales


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=D5-B

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=D5-B

mailto:[email protected]?Subject=NMC Comment/Question: D5-B (1975-039B)













Manager

Dr. FrancoisE. Barlier

ProjectScientist

Centre d'Etudes et de RechercheGeodynamiques er Astronomiques

[email protected]

Mr. J. P.Chassaing

GeneralContact

Centre National d'Etudes Spatiales


http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=DADE-A[31/08/2010 1:05:55]


Description

The Dual Air Density Explorer-A (DADE-A) satellite was a 0.76m rigid sphere designed to determine, in conjunction with DualAir Density Explorer-B (DADE-B), the vertical structure of theupper thermosphere and the lower exosphere as a function oflatitude, season, and local solar time. Both satellites wouldhave been launched by a single Scout launch vehicle intocoplanar polar orbits. Measurements of atmospheric densityfrom DADE-A would have been obtained from satellite draganalyses near perigee (apporximately 350 km) and fromcomposition measurements taken by an onboard massspectrometer. DADE-A was equipped with a radio beacon tofacilitate tracking.

DADE-A

NSSDC ID: DADE-A

Alternate Names

AD-1

DAD

Dual Air Density Expl-A

Facts in Brief

Launch Date: 1975-12-05Launch Vehicle: ScoutLaunchSite: Vandenberg AFB,United StatesMass: 40.0 kg

Funding Agency

NASA-Office of SpaceScience (United States)

Discipline

Earth Science


Launch/Orbitalinformation for DADE-A

Experiments on DADE-A

Data collections fromDADE-A


Personnel



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data



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

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

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

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

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

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












http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=DADE-A[31/08/2010 1:05:55]


ProgramScientist

NASA Headquarters

Mr. John E.Canady, Jr.

ProjectManager

NASA Langley ResearchCenter

Mr. Edwin J. Prior ProjectScientist


[email protected]

Mr. John R. Holtz ProgramManager

NASA Headquarters


http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=DADE-B[31/08/2010 1:06:17]


Description

The Dual Air Density Explorer-B (DADE-B) satellite was a3.66-m inflatable sphere designed to determine, in conjunctionwith Dual Air Density Explorer-A (DADE-A), the verticalstructure of the upper thermosphere and lower exosphere as afunction of latitude, season, and local solar time. Bothsatellites would have been launched by a single Scout launchvehicle into coplanar polar orbits. Measurements ofatmospheric density from DADE-B would have been obtainedfrom satellite drag analysis near perigee (approximately 700km) and from composition measurements taken by an onboardspectrometer. DADE-B was equipped with a radio beacon tofacilitate tracking.

DADE-B

NSSDC ID: DADE-B

Alternate Names

DAD

AD-2

Dual Air Density Expl-B

Facts in Brief


Funding Agency


Discipline

Earth Science


Launch/Orbitalinformation for DADE-B

Experiments on DADE-B

Data collections fromDADE-B


Personnel



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data



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

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

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

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

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

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












http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=DADE-B[31/08/2010 1:06:17]


ProgramScientist

NASA Headquarters

Mr. John E.Canady, Jr.

ProjectManager


Mr. Edwin J. Prior ProjectScientist


[email protected]

Mr. John R. Holtz ProgramManager

NASA Headquarters


http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=DIAPO[31/08/2010 1:06:39]


Description

This satellite is part of France's contribution to the InternationalMagnetospheric Study. Its objective is to study the origin andacceleration mechanisms of magnetospheric ions (1) bymeasuring the relative abundances and the angular andenergy distribution of singly ionized hydrogen and helium,doubly ionized helium, and oxygen (6 plus) ions and, (2) bycomparing the results with the ionospheric and solar windcomposition. Additionally, a study of magnetosphericsubstorms is planned with measurements of the angular andenergy distribution of electrons from 50 eV to 1 MeV,complemented with VLF and magnetic field measurements.

DIAPO

NSSDC ID: DIAPO

Facts in Brief

Launch Date: 1975-12-01LaunchVehicle: DiamantLaunch Site: Kourou,French Guiana

Funding Agency

Unknown (France)

Discipline

Space Physics


Launch/Orbitalinformation for DIAPO

Experiments on DIAPO

Data collections fromDIAPO

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


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




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

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

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

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

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

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

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









http://www.usa.gov/








Description

DMSP (75-043A), also known as DMSP 10533, was one of aseries of meteorological satellites developed and operated bythe Air Force under the Defense Meteorological SatelliteProgram. This program, previously known as Data Acquisitionand Processing Program (DAPP), was classified until March1973. The objective of this program was to provide globalvisual and infrared (IR) cloudcover data and specializedenvironmental data to support Department of Defenserequirements. Operationally, the program consisted of twosatellites in 830 km sun-synchronous polar orbits, with theascending node of one satellite near the sunrise terminatorand the other near local noon. The satellite, shaped like thefrustum of a polyhedron, consisted of four subassemblies -- (1)a solar array hat, (2) a base-plate assembly, (3) a sensor AVE(Aerospace Vehicle Electronics) package (SAP), and (4) a dataprocessing system. The primary sensor (SAP) was a fourchannel scanning radiometer. Secondard sensors included avertical temperature profile radiometer (supplementary sensorE - SSE) and an electron spectrograph (supplementary sensorJ/2 - SSJ/2), which were mounted, along with the primarysensor, on the base-plate assembly. Spacecraft stabilizationwas controlled by a combination flywheel and magnetic controlcoil system so that the sensors were maintained in the desiredearth-looking mode. The data processing system includedthree tape recorders capable of storing a total of 440 min ofdata, which allowed full global coverage twice daily. Eitherrecorded or real-time data were transmitted to groundreceiving sites via an s-band transmitter. Recorded data wereread out to tracking sites located at Fairchild AFB, WA, andLoring AFB, ME, and relayed to Air Force Global WeatherCentral, Offutt AFB, NE. Real-time data were read out atmobile tactical sites located around the world.

DMSP 5C/F2

NSSDC ID: 1975-043A

Alternate Names

DMSP 10533

07816

Facts in Brief

Launch Date: 1975-05-24Launch Vehicle: ThorLaunchSite: Vandenberg AFB,United StatesMass: 195.0 kg

Funding Agency


Disciplines

Earth Science

Space Physics


Launch/Orbitalinformation for DMSP5C/F2

Experiments on DMSP5C/F2

Data collections fromDMSP 5C/F2


Personnel


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=DMSP 5C/F2

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=DMSP 5C/F2

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=DMSP 5C/F2

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=DMSP 5C/F2

mailto:[email protected]?Subject=NMC Comment/Question: DMSP 5C/F2 (1975-043A)

mailto:[email protected]?Subject=NMC Comment/Question: DMSP 5C/F2 (1975-043A)












Project Manager US Air Force Space Division


http://www.usa.gov/








Description

This Defense Satellite Communications System (DSCS)satellite was launched from Cape Canaveral aboard a Titan 3Crocket. It was one of a series of satellites that provided securevoice and data communications for the US military. It was spinstabilized with a despun antenna platform. Body mounted solarcells produced 535 watts. Three NiCd batteries provided 36AHr total. The payload consisted of two 20 watt X-Bandtransponders with 500 MHz bandwidths, and steerable narrowbeam antennas and drive mechanism for commincationsprivacy. Its capacity was 1300 voice channels or 100 Mbps ofdata.

DSCS II-05

NSSDC ID: 1975-040A

Alternate Names

1975-040A

Defense SatelliteCommunications SystemII-05

07807

Facts in Brief

Launch Date: 1975-05-20Launch Vehicle: TitanIII-CLaunch Site: CapeCanaveral, United StatesMass: 566.0 kg

Funding Agency


Disciplines

Communications



Launch/Orbitalinformation for DSCS II-05

Experiments on DSCS II-05

Data collections fromDSCS II-05

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


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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


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


mailto:[email protected]?Subject=NMC Comment/Question: DSCS II-05 (1975-040A)

mailto:[email protected]?Subject=NMC Comment/Question: DSCS II-05 (1975-040A)












Description

This Defense Satellite Communications System (DSCS)satellite was launched from Cape Canaveral aboard a Titan 3Crocket. It was one of a series of satellites that provided securevoice and data communications for the US military. It was spinstabilized with a despun antenna platform. Body mounted solarcells produced 535 watts. Three NiCd batteries provided 36AHr total. The payload consisted of two 20 watt X-Bandtransponders with 500 MHz bandwidths, and steerable narrowbeam antennas and drive mechanism for commincationsprivacy. Its capacity was 1300 voice channels or 100 Mbps ofdata.

DSCS II-06

NSSDC ID: 1975-040B

Alternate Names

Defense SatelliteCommunications SystemII-06

07808

Facts in Brief


Funding Agency


Disciplines

Communications



Launch/Orbitalinformation for DSCS II-06

Experiments on DSCS II-06

Data collections fromDSCS II-06



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data










mailto:[email protected]?Subject=NMC Comment/Question: DSCS II-06 (1975-040B)












http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=DUAL-A[31/08/2010 1:08:03]


Description

Two satellites, DUAL-A and DUAL-A1, were to be launchedsimultaneously by the U.S.S.R and placed in elongated orbitswith the direction of the line of apsides toward the neutralpoints of the magnetosphere. The satellites were part of theU.S.S.R. contribution to the International MagnetosphericStudy. They were to perform observations simultaneously incritical regions of the earth's plasma environment. Theinstrumentation was to include magnetometers and plasmaand energetic particle detectors. The missions were cancelled.

DUAL-A

NSSDC ID: DUAL-A

Facts in Brief

Launch Date: 1975-08-01LaunchVehicle: UnknownLaunch Site: U.S.S.R

Funding Agency

Unknown (U.S.S.R)

Discipline

Space Physics


Launch/Orbitalinformation for DUAL-A

Experiments on DUAL-A

Data collections fromDUAL-A



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




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

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

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

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

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

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

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









http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=DUAL-A1[31/08/2010 1:08:25]


Description

Two satellites, DUAL-A and DUAL-A1, were to be launchedsimultaneously by the U.S.S.R and placed in elongated orbitswith the direction of the line of apsides toward the neutralpoints of the magnetosphere. The satellites were part of theU.S.S.R. contribution to the International MagnetosphericStudy. They were to perform observations simultaneously incritial regions of the earth's plasma environment. Theinstrumentation was to include magnetometers and plasmaand energetic particle detectors. The missions were cancelled.

DUAL-A1

NSSDC ID: DUAL-A1

Facts in Brief

Launch Date: 1975-08-01LaunchVehicle: UnknownLaunch Site: U.S.S.R

Funding Agency

Unknown (U.S.S.R)

Discipline

Space Physics


Launch/Orbitalinformation for DUAL-A1

Experiments on DUAL-A1

Data collections fromDUAL-A1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=DUAL-A1

http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=DUAL-A1

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=DUAL-A1

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=DUAL-A1

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=DUAL-A1

mailto:[email protected]?Subject=NMC Comment/Question: DUAL-A1 (DUAL-A1)

mailto:[email protected]?Subject=NMC Comment/Question: DUAL-A1 (DUAL-A1)









http://www.usa.gov/








Description

Japanese Engineering Test Satellite (JETS) was a shortoctagonal right prism with two octagonal pyramids terminatingeither end of the prism. Both pyramids were truncated with asmall end plate. The satellite was approximately 90 cm inheight and diameter. All faces other than the end plates werecovered with solar cells. Several antennas and sensorsextended from the spacecraft. The objectives of this satellitelaunch were to confirm launching technology, to developsatellite tracking and controlling technology, and to carry outother technological experiments and procedures. Initial satelliteoperation, including attitude control and extension of four verylong antennas, was nominal.

ETS

NSSDC ID: 1975-082A

Alternate Names

ETS 1

Engineering Test Sat-1

KIKU

08197

Facts in Brief

Launch Date: 1975-09-09Launch Vehicle: NuLaunchSite: Tanegashima, JapanMass: 85.0 kg

Funding Agency

National SpaceDevelopment Agency(NASDA) (Japan)

Disciplines

Communications

Engineering


Launch/Orbitalinformation for ETS

Experiments on ETS

Data collections from ETS



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

mailto:[email protected]?Subject=NMC Comment/Question: ETS (1975-082A)

mailto:[email protected]?Subject=NMC Comment/Question: ETS (1975-082A)









http://www.usa.gov/








Description

The GEOS 3 (Geodynamics Experimental Ocean Satellite)spacecraft was an octahedron, topped by a truncated pyramid,with a parabolic reflector for a radar altimeter on the flat bottomside. A metal ribbon boom with end mass extended upwardapproximately 6.1 m from the top of the pyramid. Passive laserretroreflector cubes were mounted in a ring around theparabolic reflector with the normal vector from each cubefacing 45 deg outward from the direction of the earth. Aturnstile antenna for VHF and UHF frequencies and separateantennae for earth-viewing 324-MHz Doppler, C-band, and S-band transponders were mounted separately on flat surfacesnext to the parabolic reflector. The dimension across the flatsof the octahedron was 1.22 m, and the spacecraft was 1.11 mhigh. The mission provided the stepping stone between theNational Geodetic Satellite Program (NGSP) and the Earth andOcean Physics Application Program. It provided data to refinethe geodetic and geophysical results of the NGSP and servedas a test for new systems. Mission objectives were to performa satellite altimetry experiment in orbit, to support further thecalibration and position determination of NASA and otheragency C-band radar systems, and to perform a satellite-to-satellite tracking experiment with the ATS 6 spacecraft usingan S-band transponder system. This system was also used forperiodic GEOS 3 telemetry data relay through ATS 6, tosupport further the intercomparison of tracking systems, toinvestigate the solid-earth dynamic phenomena throughprecision laser tracking, to refine further orbit determinationtechniques and determine interdatum ties and gravity models,and to support the calibration and position determination ofNASA Spaceflight Tracking and Data Network (STDN) S-bandtracking stations. For more details, see special reports on theGEOS 3 in J. Geophys. Res., v. 84, n. B8, 1979.

GEOS 3

NSSDC ID: 1975-027A

Alternate Names

Geodetic Explorer Sat.

GEOS-C

07734

Facts in Brief


Funding Agency


Disciplines

Engineering

Earth Science


Launch/Orbitalinformation for GEOS 3

Experiments on GEOS 3

Data collections fromGEOS 3


Personnel


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: GEOS 3 (1975-027A)














Mr. Hubert R.Stanley

ProjectScientist

NASA Wallops FlightFacility

[email protected]

Mr. Charles J.Finley

ProgramManager

NASA Headquarters


http://www.usa.gov/








Description

GOES 1 (SMS-C) was a NASA-developed, NOAA-operated,geosynchronous, and operational spacecraft. The spin-stabilized spacecraft carried (1) a visible infrared spin-scanradiometer (VISSR) to provide high-quality day and nightcloudcover data and to take radiance-derived temperatures ofthe earth/atmosphere system, (2) a meteorological datacollection and transmission system to relay processed datafrom central weather facilities to APT-equipped regionalstations and to collect and retransmit data from remotelylocated earth-based platforms, and (3) a space environmentmonitor (SEM) system to measure proton, electron, and solarX-ray fluxes and magnetic fields. The cylindrically shapedspacecraft measured 190.5 cm in diameter and 230 cm inlength, exclusive of a magnetometer that extended anadditional 83 cm beyond the cylinder shell. The primarystructural members were a honeycombed equipment shelf andthrust tube. The VISSR telescope was mounted on theequipment shelf and viewed the earth through a specialaperture in the side of the spacecraft. A support structureextended radially from the thrust tube and was affixed to thesolar panels, which formed the outer walls of the spacecraftand provided the primary source of electrical power. Locatedin the annulus-shaped space between the thrust tube and thesolar panels were stationkeeping and dynamics controlequipment, batteries, and most of the SEM equipment. Properspacecraft attitude and spin rate (approximately 100 rpm) weremaintained by two separate sets of jet thrusters mountedaround the spacecraft equator and activated by groundcommand. The spacecraft used both UHF-band and S-bandfrequencies in its telemetry and command subsystem. A low-power VHF transponder provided telemetry and commandduring launch and then served as a backup for the primarysubsystem once the spacecraft had attained synchronousorbit. For more detailed information, see "The GOES/SMSUser's Guide" (TRF B28599), available from NSSDC. OnDecember 1, 1978, responsibility for GOES 1 was turned overto ESA to be used as part of GARP. It was stationed over theIndian Ocean and controlled by ESOC in Darmstadt, F.R.G. InDecember 1979, it was returned to the control of NOAA andpositioned at 135 deg W. When GOES 5 VAS experienced afailure on July 30, 1984, GOES 6 was moved east and GOES1 was reactivated by NOAA to provide visible imagingcapability over the western United States. GOES 1 failed onFebruary 3, 1985.

GOES 1

NSSDC ID: 1975-100A

Alternate Names

GOES-A

SMS-C

08366

Facts in Brief


Funding Agencies


NOAA NationalEnvironmental SatelliteService (United States)

Disciplines

Earth Science

Solar Physics

Space Physics


Launch/Orbitalinformation for GOES 1

Experiments on GOES 1

Data collections fromGOES 1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: GOES 1 (1975-100A)













Personnel


Mr. James R.Greaves

ProgramManager

NASA Headquarters [email protected]

Mr. William E.Shenk

ProjectScientist

NASA Goddard SpaceFlight Center


http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=HOMS[31/08/2010 1:09:50]


Description

This satellite will be of the HEOS type, and will be launched tooperate in conjunction with the ESRO spacecraft GEOS. It willprovide correlated data for studying the space-time structureand variations of the magnetosphere. The experiments willinclude magnetometers, plasma and particle detectors, andmagnetic-electric wave instrumentation.

HOMS

NSSDC ID: HOMS

Facts in Brief


Funding Agency


Discipline

Space Physics


Launch/Orbitalinformation for HOMS

Experiments on HOMS

Data collections fromHOMS



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




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

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

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

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

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

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











http://www.usa.gov/








Description

IMEWS 5 was the last in a series of 5 first generation DSPprogram of Integrated Missile Early Warning Satellitesmanufactured by TRW for the US Air Force. The spacecraftspun slowly (6 rpm) about the nadir axis to permit scanning ofthe Earth by the detector system. The body mounted anddeployable panels provided 400W.

IMEWS 5

NSSDC ID: 1975-118A

Alternate Names

Early Warning 5

DSP F5

08482

Facts in Brief


Funding Agency


Discipline



Launch/Orbitalinformation for IMEWS 5

Experiments on IMEWS 5

Data collections fromIMEWS 5


Image courtesy of the USAF Defense Support Program.


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


IMEWS 5




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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: IMEWS 5 (1975-118A)











http://nssdc.gsfc.nasa.gov/image/spacecraft/dsp_f05.jpg




Description

Intelsat 4 F-1 was a communication satellite with a cylindricaldiameter of 213 cm, 281 cm solar drum height, and 528 cmoverall height. Electric power was supplied by solar cellsmounted on the solar drum face. The satellite had multipleaccess and simultaneous transmissions capabilities with acapacity of 3000 circuits with transponder in the earth modeand 9000 circuits with transponder in the spot-beam coveragemode, or 12 TV channels or certain combinations. There were12 transponders, each with a 36-MHz bandwidth, two globaltransmit antennas, two global receive antennas, and twosteerable spot-beam transmit antennas.

INTELSAT 4 F-1

NSSDC ID: 1975-042A

Alternate Names

07815

Facts in Brief

Launch Date: 1975-05-22Launch Vehicle: Atlas-CentaurLaunch Site: CapeCanaveral, United StatesMass: 727.0 kg

Funding Agencies

Unknown (United States)

InternationalTelecommunicationsSatellite Corporation(International)

Discipline

Communications


Launch/Orbitalinformation for INTELSAT4 F-1

Experiments on INTELSAT4 F-1

Data collections fromINTELSAT 4 F-1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


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





http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=INTELSAT 4 F-1

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=INTELSAT 4 F-1

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=INTELSAT 4 F-1

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=INTELSAT 4 F-1

mailto:[email protected]?Subject=NMC Comment/Question: INTELSAT 4 F-1 (1975-042A)











http://www.usa.gov/







Description

Intelsat 4A F-1 was an improved satellite with double thecapacity of previous Intelsats for COMSAT's global commercialcommunications network.

INTELSAT 4A F-1

NSSDC ID: 1975-091A

Alternate Names

08330

Facts in Brief

Launch Date: 1975-09-26Launch Vehicle: AtlasLaunch Site: CapeCanaveral, United StatesMass: 1500.0 kg

Funding Agencies


InternationalTelecommunicationsSatellite Corporation(International)

Discipline

Communications


Launch/Orbitalinformation for INTELSAT4A F-1

Experiments on INTELSAT4A F-1

Data collections fromINTELSAT 4A F-1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=INTELSAT 4A F-1

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=INTELSAT 4A F-1

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=INTELSAT 4A F-1

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=INTELSAT 4A F-1

mailto:[email protected]?Subject=NMC Comment/Question: INTELSAT 4A F-1 (1975-091A)











http://www.usa.gov/








Description

Intercosmos 13 was a Soviet ionospheric research satellitelaunched from the Plesetsk Cosmodrome aboard a Kosmosrocket. It contatined upper magnetosphere experiments andperformed a study of dynamic processes in the earth'smagnetosphere and polar ionosphere. It also conducted aninvestigation of low-frequency electromagnetic waves.

Intercosmos 13

NSSDC ID: 1975-022A

Alternate Names

07710

Facts in Brief

Launch Date: 1975-03-27LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 400.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Space Physics


Launch/Orbitalinformation forIntercosmos 13

Experiments onIntercosmos 13

Data collections fromIntercosmos 13



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Intercosmos 13


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Intercosmos 13


mailto:[email protected]?Subject=NMC Comment/Question: Intercosmos 13 (1975-022A)











http://www.usa.gov/








Description

The spacecraft was a contribution to the InternationalMagnetospheric Study (IMS) program involving the scientificcommunity of socialist countries. The spacecraft contained fiveexperiments which provided measurements of extremely low-frequency (ELF) and very low-frequency (VLF) emissions in themagnetosphere, of the variation of ionospheric plasma densityand electron temperature along the orbit, of variations of totalelectron content in the ionosphere, and of energy andpenetration characteristics of meteor showers. The spacecraftwas magnetically oriented and contained both a standardtelemetry system and a wideband system which transmittedreal-time data from a four-component ELF/VLF receiver and anelectron temperature instrument. The data system included awideband tape recorder (0,05-15 KHz). A large number ofground-based observatories in the socialist countries wereinvolved in measuring ionospheric conditions, geomagneticfield variations, and VLF emissions in conjunction with thesatellite. Operations terminated on June 28, 1976

National Space Science Data Center Header

Intercosmos 14

NSSDC ID: 1975-115A

Alternate Names

IK-14

08471

Facts in Brief

Launch Date: 1975-12-11LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 700.0 kg

Funding Agency

Intercosmos (U.S.S.R)

Disciplines

Planetary Science

Space Physics


Launch/Orbitalinformation forIntercosmos 14

Experiments onIntercosmos 14

Data collections fromIntercosmos 14



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data























Personnel


Dr. J. I. Likhter Project Scientist IZMIRAN


http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=ISIS-C[02/09/2010 0:18:30]

Thursday, 02 September 2010

Description

ISIS-C

NSSDC ID: ISIS-C

Facts in Brief

Launch Date: 1975-08-01Launch Vehicle: DeltaLaunchSite: Vandenberg AFB,United States

Funding Agency


Discipline

Space Physics


Launch/Orbitalinformation for ISIS-C

Experiments on ISIS-C

Data collections from ISIS-C


Personnel


Mr. John E. Jackson Project Scientist NASA Goddard Space Flight Center

Mr. E. D. Nelsen Project Manager NASA Goddard Space Flight Center


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




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

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

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

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

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

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











http://www.usa.gov/








Description

This US Air Force electronics intelligence satellite waslaunched from Vandenberg AFB aboard a Titan 34B rocket.

Jumpseat 3

NSSDC ID: 1975-017A

Alternate Names

07687

Facts in Brief

Launch Date: 1975-03-10Launch Vehicle: TitanIII-BLaunchSite: Vandenberg AFB,United StatesMass: 700.0 kg

Funding Agency


Discipline



Launch/Orbitalinformation for Jumpseat3

Experiments on Jumpseat3

Data collections fromJumpseat 3



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







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

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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Jumpseat 3 (1975-017A)











http://www.usa.gov/







Description

This US Air Force photo surveillance satellite was launchedfrom Vandenberg AFB aboard a Titan 3B rocket. It was a KH-8(Key Hole-8) type spacecraft.

KH 8-44

NSSDC ID: 1975-032A

Alternate Names

1975-032A

07747

Facts in Brief


Funding Agency


Discipline



Launch/Orbitalinformation for KH 8-44

Experiments on KH 8-44

Data collections from KH 8-44



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=KH 8-44

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=KH 8-44


mailto:[email protected]?Subject=NMC Comment/Question: KH 8-44 (1975-032A)











http://www.usa.gov/








Description

This US Air Force photo surveillance satellite was launchedfrom Vandenberg AFB aboard a Titan 3B rocket. It was a KH-8(Key Hole-8) type spacecraft.

KH 8-45

NSSDC ID: 1975-098A

Alternate Names

1975-098A

08360

Facts in Brief


Funding Agency


Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description

This US Air Force photo surveillance satellite was launchedfrom Vandenberg AFB aboard a Titan 3D rocket. It was a KH-9(Key Hole-9) type spacecraft.

KH 9-10

NSSDC ID: 1975-051A

Alternate Names

1975-051A

07918

Facts in Brief

Launch Date: 1975-06-08Launch Vehicle: TitanIII-DLaunchSite: Vandenberg AFB,United StatesMass: 13300.0 kg

Funding Agency


Discipline








Spacecraft

Experiments

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Personnel

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Maps

New/Updated Data




















http://www.usa.gov/








Description

This US Air Force photo surveillance satellite was launchedfrom Vandenberg AFB aboard a Titan 3D rocket. It was a KH-9(Key Hole-9) type spacecraft.

KH 9-11

NSSDC ID: 1975-114A

Alternate Names

1975-114A

08467

Facts in Brief


Funding Agency


Discipline








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Experiments

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New/Updated Data




















http://www.usa.gov/








Description

LANDSAT 2 was the second of a series of modified Nimbussatellites. The near-polar orbiting spacecraft served as astabilized, earth-oriented platform for obtaining information onagricultural and forestry resources, geology and mineralresources, hydrology and water resources, geography,cartography, environmental pollution, oceanography andmarine resources, and meteorological phenomena. Toaccomplish these objectives, the spacecraft was equipped witha three-camera return beam vidicon (RBV) and a four-channelmultispectral scanner (MSS) to obtain visible and near IRphotographic and radiometric images of the earth. A datacollection system (DCS) was also used to collect informationfrom remote individually equipped ground stations and to relaythe data to central acquisition stations. LANDSAT 2 carried twowide-band video tape recorders (WBVTR), capable of storingup to 30 min of scanner or camera data. An advanced attitudecontrol system, consisting of horizon scanners, sun sensors,and a command antenna combined with a freon gas propulsionsystem, permitted the spacecraft's orientation to be controlledto within plus or minus 0.7 deg in all three axes. Spacecraftcommunications included a command subsystem operating at154.2 and 2106.4 MHz and a PCM narrow-band telemetrysubsystem, operating at 2287.5 and 137.86 MHz, forspacecraft housekeeping, attitude, and sensor performancedata. Video data from the three-camera RBV system weretransmitted in both real time and from WBVTR at 2276.5 MHz,while information from the MSS was constrained to a 20-MHzrf bandwidth at 2229.5 MHz.

Landsat 2

NSSDC ID: 1975-004A

Alternate Names

ERTS-B

07615

Facts in Brief


Funding Agency


Disciplines

Engineering

Earth Science


Launch/Orbitalinformation for Landsat 2

Experiments on Landsat 2

Data collections fromLandsat 2


Personnel


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Landsat 2 (1975-004A)














Dr. Stanley C. Freden Project Scientist NASA Goddard Space FlightCenter

Mr. Charles M.MacKenzie

Project Manager NASA Goddard Space FlightCenter

Dr. James C. Welch ProgramManager

NASA Headquarters


http://www.usa.gov/








Description

This was the 21st fully operational meteorological satellite inthe Soviet Meteor 1 program. The satellite was placed in anear-circular, near-polar orbit to provide global observations ofthe earth's weather systems, cloud cover, ice and snow fields,vertical profiles of temperature and moisture, and relected andemitted radiation from the dayside and nightside of the earth-atmosphere system for operational use by the SovietHydrometeorological Service. Its 900-km orbit seemed to verifya continued effort by the USSR to place new Meteor satellitesin high orbit -- about 240 km higher than the orbits of earlyspacecraft in the series. Meteor 1 was equipped with twovidicon cameras with APT capability for taking daysidepictures, a scanning high-resolution IR radiometer, also withAPT capability, for taking dayside and nightside pictures, a setof actinometric instruments for making measurements of theearth's radiation field in the visual and infrared regions, and amedium-resolution scanning diffraction spectrometer fordetermining indirectly the vertical profiles of atmospherictemperature and humidity. The satellite was in the form of acylinder 5 m long and 1.5 m in diameter with two large solarpanels attached to tht sides. The solar panels wereautomatically oriented toward the sun so as to provide thespacecraft with the maximum amount of solar power. Meteor 1was oriented toward the earth by gravity-gradient control of the3 axes. The X and Y axes were mechanically stabilized by asystem of flywheels whose kinetic energy was dampened bythe use of controlled electromagnets on board that interactedwith the magnetic field of the earth. The instruments werehoused in the base of the satellite, which pointed toward theearth, while the solar sensors were mounted in the top section.The operational 'Meteor' weather satellite system usuallyconsists of two satellites spaced at 90-deg intervals. Thisallowed for nearly continuous monitoring of the formation,development, and movement of major weather systems. Whenwithin communication range, the data acquired weretransmitted directly to the ground receiving centers in Moscow,Novosibirsk, or Vladivostok or to APT-equipped stations withinthe USSR. During its passes over regions beyondcommunication range, Meteor 1 recorded the TV and IRpictures, spectrometer data, and actinometric data and storedthem on board until the satellite passed over one of thereceiving centers. The Meteorological data received at thesecenters were processed, reduced, and sent to theHydrometeorological Center in Moscow, where they wereanalyzed and used for preparing various forecast and analysisproducts. Some of the TV and IR pictures were thendistributed in real time to various meteorological centersaround the world.

Meteor 1-21

NSSDC ID: 1975-023A

Alternate Names

Meteor 1-21

07714

Facts in Brief

Launch Date: 1975-04-01LaunchVehicle: Modified SS-6(Sapwood) with 1stGeneration Upper StageLaunch Site: Plesetsk,U.S.S.RMass: 2200.0 kg

Funding Agency

SovietHydrometeorologicalService (U.S.S.R)

Discipline

Earth Science


Launch/Orbitalinformation for Meteor 1-21

Experiments on Meteor 1-21

Data collections fromMeteor 1-21



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Meteor 1-21


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Meteor 1-21


mailto:[email protected]?Subject=NMC Comment/Question: Meteor 1-21 (1975-023A)













Personnel


Project Manager Soviet Hydrometeorological Service


http://www.usa.gov/








Description

This was the 22nd fully operational meteorological satellite inthe Soviet Meteor 1 program. The satellite was placed in anear-circular, near-polar orbit to provide global observations ofthe earth's weather systems, cloud cover, ice and snow fields,vertical profiles of temperature and moisture, and relected andemitted radiation from the dayside and nightside of the earth-atmosphere system for operational use by the SovietHydrometeorological Service. Its 900-km orbit seemed to verifya continued effort by the USSR to place new Meteor satellitesin high orbit -- about 240 km higher than the orbits of earlyspacecraft in the series. Meteor 1 was equipped with twovidicon cameras with APT capability for taking daysidepictures, a scanning high-resolution IR radiometer, also withAPT capability, for taking dayside and nightside pictures, a setof actinometric instruments for making measurements of theearth's radiation field in the visual and infrared regions, and amedium-resolution scanning diffraction spectrometer fordetermining indirectly the vertical profiles of atmospherictemperature and humidity. The satellite was in the form of acylinder 5 m long and 1.5 m in diameter with two large solarpanels attached to tht sides. The solar panels wereautomatically oriented toward the sun so as to provide thespacecraft with the maximum amount of solar power. Meteor 1was oriented toward the earth by gravity-gradient control of the3 axes. The X and Y axes were mechanically stabilized by asystem of flywheels whose kinetic energy was dampened bythe use of controlled electromagnets on board that interactedwith the magnetic field of the earth. The instruments werehoused in the base of the satellite, which pointed toward theearth, while the solar sensors were mounted in the top section.The operational 'Meteor' weather satellite system usuallyconsists of two satellites spaced at 90-deg intervals. Thisallowed for nearly continuous monitoring of the formation,development, and movement of major weather systems. Whenwithin communication range, the data acquired weretransmitted directly to the ground receiving centers in Moscow,Novosibirsk, or Vladivostok or to APT-equipped stations withinthe USSR. During its passes over regions beyondcommunication range, Meteor 1 recorded the TV and IRpictures, spectrometer data, and actinometric data and storedthem on board until the satellite passed over one of thereceiving centers. The Meteorological data received at thesecenters were processed, reduced, and sent to theHydrometeorological Center in Moscow, where they wereanalyzed and used for preparing various forecast and analysisproducts. Some of the TV and IR pictures were thendistributed in real time to various meteorological centersaround the world.

Meteor 1-22

NSSDC ID: 1975-087A

Alternate Names

Meteor 1-22

08293

Facts in Brief


Funding Agency


Discipline

Earth Science







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data























Personnel




http://www.usa.gov/








Description

This was the 23rd fully operational meteorological satellite inthe Soviet Meteor 1 program. The satellite was placed in anear-circular, near-polar orbit to provide global observations ofthe earth's weather systems, cloud cover, ice and snow fields,vertical profiles of temperature and moisture, and relected andemitted radiation from the dayside and nightside of the earth-atmosphere system for operational use by the SovietHydrometeorological Service. Its 900-km orbit seemed to verifya continued effort by the USSR to place new Meteor satellitesin high orbit -- about 240 km higher than the orbits of earlyspacecraft in the series. Meteor 1 was equipped with twovidicon cameras with APT capability for taking daysidepictures, a scanning high-resolution IR radiometer, also withAPT capability, for taking dayside and nightside pictures, a setof actinometric instruments for making measurements of theearth's radiation field in the visual and infrared regions, and amedium-resolution scanning diffraction spectrometer fordetermining indirectly the vertical profiles of atmospherictemperature and humidity. The satellite was in the form of acylinder 5 m long and 1.5 m in diameter with two large solarpanels attached to tht sides. The solar panels wereautomatically oriented toward the sun so as to provide thespacecraft with the maximum amount of solar power. Meteor 1was oriented toward the earth by gravity-gradient control of the3 axes. The X and Y axes were mechanically stabilized by asystem of flywheels whose kinetic energy was dampened bythe use of controlled electromagnets on board that interactedwith the magnetic field of the earth. The instruments werehoused in the base of the satellite, which pointed toward theearth, while the solar sensors were mounted in the top section.The operational 'Meteor' weather satellite system usuallyconsists of two satellites spaced at 90-deg intervals. Thisallowed for nearly continuous monitoring of the formation,development, and movement of major weather systems. Whenwithin communication range, the data acquired weretransmitted directly to the ground receiving centers in Moscow,Novosibirsk, or Vladivostok or to APT-equipped stations withinthe USSR. During its passes over regions beyondcommunication range, Meteor 1 recorded the TV and IRpictures, spectrometer data, and actinometric data and storedthem on board until the satellite passed over one of thereceiving centers. The Meteorological data received at thesecenters were processed, reduced, and sent to theHydrometeorological Center in Moscow, where they wereanalyzed and used for preparing various forecast and analysisproducts. Some of the TV and IR pictures were thendistributed in real time to various meteorological centersaround the world.

Meteor 1-23

NSSDC ID: 1975-124A

Alternate Names

Meteor 1-23

08519

Facts in Brief


Funding Agency


Discipline

Earth Science







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data























Personnel


Project Scientist Soviet Hydrometeorological Service


http://www.usa.gov/








Description

Meteor 2-1

NSSDC ID: 1975-064A

Alternate Names

Meteor 2-1

08026

Facts in Brief


Funding Agency


Discipline

Earth Science






Personnel


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data
























http://www.usa.gov/








Description

Molniya 1/29 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 1/29,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 1/29remained 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 1-29

NSSDC ID: 1975-036A

Alternate Names

Molniya 1ZE

07780

Facts in Brief

Launch Date: 1975-04-29LaunchVehicle: Modified SS-6(Sapwood) with 2ndGeneration Upper Stage +Escape StageLaunch Site: Plesetsk,U.S.S.RMass: 1000.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Communications


Launch/Orbitalinformation for Molniya 1-29

Experiments on Molniya 1-29

Data collections fromMolniya 1-29



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Molniya 1-29


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Molniya 1-29


mailto:[email protected]?Subject=NMC Comment/Question: Molniya 1-29 (1975-036A)











http://www.usa.gov/







Description

Molniya 1/30 was a first-generation Russian communicationssatellite (COMSAT) orbited to test and perfect a system ofradio communications and television broadcasting using earthsatellites as active transponders and to experiment with thesystem in practical use. The basic function of the satellite wasto relay television programs and long-distance two-waymultichannel telephone, phototelephone, and telegraph linksfrom Moscow to the various standard ground receiving stationsin the 'Orbita' system. The satellite was in the form of ahermetically sealed cylinder with conical ends -- one endcontained the orbital correcting engine and a system ofmicrojets, and the other end contained externally mountedsolar and earth sensors. Inside the cylinder were (1) a high-sensitivity receiver and three 800-MHz 40-w transmitters (oneoperational and two in reserve), (2) telemetering devices thatmonitored equipment operation, (3) chemical batteries thatwere constantly recharged by solar cells, and (4) an electroniccomputer that controlled all equipment on board. Mountedaround the central cylinder were six large solar battery panelsand two directional, high-gain parabolic aerials, 180 deg apart.One of the aerials was directed continually toward the earth bythe highly sensitive earth sensors. The second aerial was heldin reserve. Signals were transmitted in a fairly narrow beamensuring a strong reception at the earth's surface. The satellitereceived telemetry at 1000 MHz. Television service wasprovided in a frequency range of 3.4 to 4.1 GHz at 40 w.Molniya 1/30, whose cylindrical body was 3.4 m long and 1.6 min diameter, was much heavier than corresponding U.S.COMSATs, and it had about 10 times the power output of theEarly Bird COMSAT. In addition, it did not employ ageosynchronous equatorial orbit as have most U.S. COMSATsbecause such an orbit would not provide coverage for areasnorth of 70 deg n latitude. Instead, the satellite was boostedfrom a low-altitude parking orbit into a highly elliptical orbit withtwo high apogees daily over the northern hemisphere -- oneover Russia and one over North America -- and relatively lowperigees over the southern hemisphere. During its apogee,Molniya 1/30 remained relatively stationary with respect to theearth below for nearly 8 of every 12 hr. By placing three ofmore Molniya 1 satellites in this type of orbit, spacing themsuitably, and shifting their orbital planes relative to each otherby 120 deg, a 24-hr/day communication system could beobtained.

Molniya 1-30

NSSDC ID: 1975-049A

Alternate Names

Molniya 1ZF

07903

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/







Description

Molniya 1/31 was a first-generation Russian communicationssatellite (COMSAT) orbited to test and perfect a system ofradio communications and television broadcasting using earthsatellites as active transponders and to experiment with thesystem in practical use. The basic function of the satellite wasto relay television programs and long-distance two-waymultichannel telephone, phototelephone, and telegraph linksfrom Moscow to the various standard ground receiving stationsin the 'Orbita' system. The satellite was in the form of ahermetically sealed cylinder with conical ends -- one endcontained the orbital correcting engine and a system ofmicrojets, and the other end contained externally mountedsolar and earth sensors. Inside the cylinder were (1) a high-sensitivity receiver and three 800-MHz 40-w transmitters (oneoperational and two in reserve), (2) telemetering devices thatmonitored equipment operation, (3) chemical batteries thatwere constantly recharged by solar cells, and (4) an electroniccomputer that contorlled all equipment on board. Mountedaround the central cylinder were six large solar battery panelsand two directional, high-gain parabolic aerials, 180 deg apart.One of the aerials was directed continually toward the earth bythe highly sensitive earth sensors. The second aerial was heldin reserve. Signals were transmitted in a fairly narrow beamensuring a strong reception at the earth's surface. The satellitereceived telemetry at 1000 MHz. Television service wasprovided in a frequency range of 3.4 to 4.1 GHz at 40 w.Molniya 1/31, whose cylindrical body was 3.4 m long and 1.6 min diameter, was much heavier than corresponding U.S.COMSATS, and it had about 10 times the power output of theEarly Bird COMSAT. In addition, it did not employ ageosynchronous equatorial orbit as have most U.S. COMSATsbecause such an orbit would not provide coverage for areasnorth of 70 deg n latitude. Instead, the satellite was boostedfrom a low-altitude parking orbit into a highly elliptical orbit withtwo high apogees daily over the northern hemisphere -- oneover Russia and one over North America -- and relatively lowperigees over the southern hemisphere. During its apogee,Molniya 1/31 remained relatively staionary with respect to theearth below for nearly 8 of every 12 hr. By placing three ormore Molniya 1 satellites in this type of orbit, spacing themsuitably, and shifting their orbital planes relative to each otherby 120 deg, a 24-hr/day communication system could beobtained.

Molniya 1-31

NSSDC ID: 1975-079A

Alternate Names

Molniya 1ZG

08187

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/







Description


Molniya 2-12

NSSDC ID: 1975-009A

Alternate Names

Molniya 2M

07641

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/







Description


Molniya 2-13

NSSDC ID: 1975-063A

Alternate Names

Molniya 2N

08015

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/







Description


Molniya 2-14

NSSDC ID: 1975-081A

Alternate Names

Molniya 2P

08195

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/







Description

Molniya 2-15 was a Soviet communications satellite launchedfrom the Plesetsk Cosmodrome aboard a Molniya 8K78Mrocket. Its purpose was to continue operation of the long-rangetelephone and telegraph radio- communication system withinthe Soviet Union and the transmission of USSR centraltelevision programms to stations in the Orbita and participatinginternational networks.

Molniya 2-15

NSSDC ID: 1975-121A

Alternate Names

Molniya 2Q

08492

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/







Description

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

Molniya 3- 2

NSSDC ID: 1975-029A

Alternate Names

Molniya 3B

07738

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications




Data collections fromMolniya 3- 2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







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


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


mailto:[email protected]?Subject=NMC Comment/Question: Molniya 3- 2 (1975-029A)











http://www.usa.gov/







Description


Molniya 3- 3

NSSDC ID: 1975-105A

Alternate Names

Molniya 3C

08425

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/







Description


Molniya 3- 4

NSSDC ID: 1975-125A

Alternate Names

Molniya 3D

08521

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

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=NEMS[02/09/2010 0:30:09]


Description

This satellite was part of ESRO's contirbution to theInternational Magnetospheric Study. Its mission was to supportthe scientific observations of the ESRO GEOS program and toenhance studies of the polar ionosphere and its coupling withthe magnetosphere. The satellite was to be magneticallystabilized. The experiments would have included particle andfield experiments, ionospheric composition experiments, andobservations of VLF radio noise.

NEMS

NSSDC ID: NEMS

Facts in Brief


Funding Agency


Discipline

Space Physics


Launch/Orbitalinformation for NEMS

Experiments on NEMS

Data collections fromNEMS



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




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

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

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

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

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

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











http://www.usa.gov/








Description

The Nimbus 6 research-and-development satellite served as astabilized, earth-oriented platform for testing advancedsystems for sensing and collecting meteorological data on aglobal scale. The polar-orbiting spacecraft consisted of threemajor structures: (1) a hollow torus-shaped sensor mount, (2)solar paddles, and (3) a control housing unit connected to thesensor mount by a tripod truss structure. Configured somewhatlike an ocean buoy, Nimbus 6 was nearly 3.7 m tall, 1.5 m indiameter at the base, and about 3 m wide with solar paddlesextended. The sensor mount that formed the satellite basehoused the electronics equipment and battery modules. Thelower surface of the torus provided mounting space forsensors and antennas. A box-beam structure mounted withinthe center of the torus supported the larger sensorexperiments. Mounted on the control housing unit, which waslocated on top of the spacecraft, were sun sensors, horizonscanners, and a command antenna. The spacecraft spin axiswas pointed at the earth. An advanced attitude-control systempermitted the spacecraft's orientation to be controlled to withinplus or minus 1 deg in all three axes (pitch, roll, and yaw). Thenine experiments selected for Nimbus 6 were (1) earthradiation budget (ERB), (2) electrically scanning microwaveradiometer (ESMR), (3) high-resolution infrared radiationsounder (HIRS), (4) limb radiance inversion radiometer (LRIR),(5) pressure modulated radiometer (PMR), (6) scanningmicrowave spectrometer (SCAMS), (7) temperature-humidityinfrared radiometer (THIR), (8) tracking and data relayexperiment (T+DRE), and (9) tropical wind energy conversionand reference level experiment (TWERLE). This complementof advanced sensors was capable of (1) mapping tropospherictemperature, water vapor abundance, and cloud water content;(2) providing vertical profiles of temperature, ozone, and watervapor; (3) transmitting real-time data to a geostationaryspacecraft (ATS 6); and (4) yielding data on the earth'sradiation budget. A more detailed description can be found in"The Nimbus 6 User's Guide" (TRF B23261), available fromNSSDC.

Nimbus 6

NSSDC ID: 1975-052A

Alternate Names

Nimbus-F

07924

Facts in Brief


Funding Agency


Discipline

Earth Science


Launch/Orbitalinformation for Nimbus 6

Experiments on Nimbus 6

Data collections fromNimbus 6


Personnel



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Nimbus 6 (1975-052A)













Mr. Charles M.MacKenzie

ProjectManager


Dr. Albert J. Fleig,Jr.

ProjectScientist


[email protected]

Dr. George F.Esenwein, Jr.

ProgramManager

NASA Headquarters

Mr. Paul Shapiro GeneralContact



http://www.usa.gov/








Description

The objectives of the OSO satellite series were to performsolar physics experiments above the atmosphere during acomplete solar cycle and to map the entire celestial sphere fordirection and intensity of UV light, X-ray radiation, andgamma-ray radiation. The OSO 8 platform consisted of a sailsection, which pointed two experiments continually toward thesun, and a wheel section, which spun about an axisperpendicular to the pointing direction of the sail and carriedfive experiments. Gas jets and a magnetic torquing coilperformed attitude adjustment. Pointing control permitted thepointed experiments to scan the region of the solar disk in a40- by 40-arc-min to 60- by 60-arc-min raster pattern. Inaddition, the pointed section was capable of beingcommanded to select and scan a 1- by 1-arc-min or 5- by 5-arc-min region anywhere on the solar disk. Data weresimultaneously recorded on tape and transmitted by PCM/PMtelemetry. A command system provided for at least 512ground-based commands. For more information, see S. P.Maran and R. J. Thomas, Sky & Teles., v. 49, p. 355, 1975.

OSO 8

NSSDC ID: 1975-057A

Alternate Names

OSO-I

07970

Facts in Brief


Funding Agency


Disciplines

Astronomy

Solar Physics


Launch/Orbitalinformation for OSO 8

Experiments on OSO 8

Data collections from OSO8


Personnel


Mr. Michael E. Program NASA Headquarters


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: OSO 8 (1975-057A)













McDonald Manager

Dr. Roger J.Thomas

ProjectScientist


[email protected]

Dr. J. DavidBohlin

ProgramScientist

NASA Headquarters

Mr. J. PatrickCorrigan, III

ProjectManager


US Active Archive for OSO-8 Information/Data

The OSO-8 Archive at HEASARC


http://heasarc.gsfc.nasa.gov/docs/oso8/archive/oso8_archive.html

http://www.usa.gov/








Description

China used the FB-1 booster to launched the 1,100 kilogramJSSW (Ji Shu Shiyan Weixing or "Technical Test Satellite")series, the precise mission of which remains somewhatobscure. Three failures resulted from the total of six launchattempts between September 1973 and November 1976, withtwo successful missions probably placing radio-downlinkimagery intelligence spacecraft into orbit. The final successfullaunch in this puzzling series, the JSSW-3 flight of August 30,1976, placed its payload into an eliptical orbit with a perigee ofsome 190 km, but with an apogee of over 2,100 km (versusthe average 400 km apogee of the other two successfulmissions). This much higher apogee in one piece in the puzzlethat propted speculation that the JSSW-3 mission carried anelectronic intelligence payload.

Because of the association of the JSSW series with the FB-1booster, it is reasonable to believe that the JSSW spacecraftwere the product of the same Shanghai Bureau that producedthis launch vehicle, and that the JSSW satellite program mayhave shared both the technical and political woes of the FB-1and the Shanghia Bureau.

PRC 3

NSSDC ID: 1975-070A

Alternate Names

1975-070A

China 3

Mao 3

JSSW-1

08053

Facts in Brief

Launch Date: 1975-07-26Launch Vehicle: FB-1Launch Site: Jiuquan,Peoples Republic of ChinaMass: 1107.0 kg

Funding Agency

Unknown (PeoplesRepublic of China)

Discipline



Launch/Orbitalinformation for PRC 3

Experiments on PRC 3

Data collections from PRC3



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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


mailto:[email protected]?Subject=NMC Comment/Question: PRC 3 (1975-070A)











http://www.usa.gov/







Description

PRC 4 was a Chinese military photo surveillance satellitelaunched from the Jiuquan site aboard a CZ-2C rocket. It wasChina's first retrievable satellite. Ten days after launch theXian ground station commanded the satellite to reenter in therecovery zone at Liuzhi Guizhou Province in southwest China.Although the outer part of the reentry vehicle was damaged onreentry due to defective materials, the imagery intelligencehardware and film were not damaged and the mission wasjudged a success.

PRC 4

NSSDC ID: 1975-111A

Alternate Names

China 4

Mao 4

FSW-0 1

08452

Facts in Brief

Launch Date: 1975-11-26Launch Vehicle: ChangZheng 2Launch Site: ShuangCheng-Tzu, PeoplesRepublic of ChinaMass: 2500.0 kg

Funding Agency


Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


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























Description

China used the FB-1 booster to launched the 1,100 kilogramJSSW (Ji Shu Shiyan Weixing or "Technical Test Satellite")series, the precise mission of which remains somewhatobscure. Three failures resulted from the total of six launchattempts between September 1973 and November 1976, withtwo successful missions probably placing radio-downlinkimagery intelligence spacecraft into orbit. The final successfullaunch in this puzzling series, the JSSW-3 flight of August 30,1976, placed its payload into an eliptical orbit with a perigee ofsome 190 km, but with an apogee of over 2,100 km (versusthe average 400 km apogee of the other two successfulmissions). This much higher apogee in one piece in the puzzlethat propted speculation that the JSSW-3 mission carried anelectronic intelligence payload.

Because of the association of the JSSW series with the FB-1booster, it is reasonable to believe that the JSSW spacecraftwere the product of the same Shanghai Bureau that producedthis launch vehicle, and that the JSSW satellite program mayhave shared both the technical and political woes of the FB-1and the Shanghia Bureau.

PRC 5

NSSDC ID: 1975-119A

Alternate Names

China 5

Mao 5

JSSW-2

08488

Facts in Brief

Launch Date: 1975-12-16Launch Vehicle: FB-1Launch Site: ShuangCheng-Tzu, PeoplesRepublic of ChinaMass: 1110.0 kg

Funding Agency


Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/







Description

The spacecraft was a contribution to the InternationalMagnetospheric Study (IMS) program, which carriedexperiments to investigate solar corpuscular, x-ray, and radioemissions, as well as to measure energetic particles, plasma,and magnetic fields in the magnetosphere and theinterplanetary medium. In a cooperative program withscientists of the socialist countries, sounding rockets werelaunched to altitudes greater than 500 km to study theinteraction of shortwave solar radiation with the atmosphereand ionosphere and to make in situ measurements of variousparameters in these regions of space.

Prognoz 4

NSSDC ID: 1975-122A

Alternate Names

08510

Facts in Brief

Launch Date: 1975-12-22LaunchVehicle: Modified SS-6(Sapwood) with 2ndGeneration Upper Stage +Escape StageLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 905.0 kg

Funding Agency


Disciplines

Astronomy

Solar Physics

Space Physics


Launch/Orbitalinformation for Prognoz 4

Experiments on Prognoz 4

Data collections fromPrognoz 4



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Prognoz 4 (1975-122A)













Personnel


Dr. Albert A.Galeev

ProjectScientist

Institut Kosmicheskich Issledovaniya(Institute of Space Research)

[email protected]


http://www.usa.gov/








Description

Raduga 1 was a Soviet communications satellite launched fromthe Baikonur cosmodrome aboard a Proton rocket. It provideduninterupted round-the-clock telephone and telegraph radio-communications in the USSR, and transmitted centraltelevision programs to stations in the Orbita network andinternational cooperation.

Raduga 1

NSSDC ID: 1975-123A

Alternate Names

08513

Facts in Brief

Launch Date: 1975-12-22Launch Vehicle: ProtonBooster Plus Upper Stageand Escape StagesLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 5000.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Communications


Launch/Orbitalinformation for Raduga 1

Experiments on Raduga 1

Data collections fromRaduga 1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Raduga 1 (1975-123A)











http://www.usa.gov/








Description

The RCA-A commercial communications spacecraft wasdesigned to transmit voice, data, facsimile, and telexmessages to and from Alaska, Hawaii, and the continentalUnited States. The three-axis stabilized spacecraft measuredapproximately 1.2m x 1.6 m for the baseplate and 1.2 m n mainbody height. The communications system used 6-GHz uplinkand 4-GHz downlink signals. Frequency and polarizationinterleaving of the separate channels was employed to achieve24 channels, each having a 36-MHz usable bandwidth withinthe 500-MHz allocation. A broad beam was used to providecommunications on all 24 channels with Alaska and the lower48 states. A spot beam provided communications on 12 of thechannels with Hawaii. The spacecraft was successfullylaunched and placed in a geosynchronous orbit with allsystems working satisfactorily. It was positioned atapproximately 119 deg west longitude above the equator.

RCA-SATCOM 1

NSSDC ID: 1975-117A

Alternate Names

RCA-A

RCA-SATCOM-A

08476

Facts in Brief

Launch Date: 1975-12-13Launch Vehicle: LongTank Thrust AugmentedThor-DeltaLaunch Site: CapeCanaveral, United StatesMass: 869.5 kg

Funding Agencies

Unknown (International)

Radio Corporation ofAmerica (United States)

Discipline

Communications


Launch/Orbitalinformation for RCA-SATCOM 1

Experiments on RCA-SATCOM 1

Data collections from RCA-SATCOM 1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: RCA-SATCOM 1 (1975-117A)












http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=RM20[02/09/2010 0:35:30]


Description

This satellite was a low-altitude satellite in circular orbitcarrying four experiments. Two of the experiments were tostudy radiation from the earth horizon. A third experiment wasto observe solar extinction through the stratosphere, and thefourth was to study ionospheric radio propagation. Thespacecraft experiment support equipment included a three-axisstabilization system and a tape recorder.

RM 20

NSSDC ID: RM20

Alternate Names

ST 72-2A

SESP P72-2A

Facts in Brief

Launch Date: 1975-04-12Launch Vehicle: AtlasFLaunchSite: Vandenberg AFB,United StatesMass: 204.0 kg

Funding Agency


Discipline

Earth Science


Launch/Orbitalinformation for RM 20

Experiments on RM 20

Data collections from RM20


Personnel



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data



http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=RM20

http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=RM20

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=RM 20

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=RM 20

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=RM 20

mailto:[email protected]?Subject=NMC Comment/Question: RM 20 (RM20)












http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=RM20[02/09/2010 0:35:30]

Mr. R. A. Kuiper Program Scientist Aerospace Corporation


http://www.usa.gov/








Description

This US Air Force electronics intelligence satellite waslaunched from Vandenberg AFB aboard a Titan 3D rocket. Notidentified as a subsatellite ferret by McDowell.

S3-2

NSSDC ID: 1975-114B

Alternate Names

SESP S73-6

08468

Facts in Brief


Funding Agency


Disciplines

Earth Science

Space Physics


Launch/Orbitalinformation for S3-2

Experiments on S3-2

Data collections from S3-2


Personnel


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=S3-2

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=S3-2

mailto:[email protected]?Subject=NMC Comment/Question: S3-2 (1975-114B)














Dr. John R.Stevens

ProjectScientist

Aerospace Corporation

ProjectManager

US Air Force Los Angeles Space and MissileSystems


http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=SS75-1A[02/09/2010 0:36:13]


Description

S75-1

NSSDC ID: SS75-1A

Facts in Brief

Launch Date: 1975-11-01Launch Vehicle: nullLaunchSite: Vandenberg AFB,United States

Discipline

Earth Science


Launch/Orbitalinformation for S75-1

Experiments on S75-1

Data collections from S75-1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=SS75-1A

http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=SS75-1A

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=S75-1



mailto:[email protected]?Subject=NMC Comment/Question: S75-1 (SS75-1A)











http://www.usa.gov/








Description

SAS-C was the third in the series of small spacecraft whoseobjectives were to survey the celestial sphere for sourcesradiating in the X-ray, gamma-ray, UV, and other spectralregions. The primary missions of SAS-C were to measure theX-ray emission of discrete extragalactic sources, to monitorthe intensity and spectra of galactic X-ray sources from 0.2 to60 keV, and to monitor the X-ray intensity of Scorpio X-1.

The spacecraft was launched from the San Marco platform offthe coast of Kenya, Africa, into a near-circular, equatorial orbit.This spacecraft contained four instruments: the ExtragalacticExperiment, the Galactic Monitor Experiment, the ScorpioMonitor Experiment, and the Galactic Absorption Experiment.In the orbital configuration, the spacecraft was 145.2 cm highand the tip-to-tip dimension was 470.3 cm. Four solar paddleswere used in conjunction with a 12-cell nickel-cadmium batteryto provide power over the entire orbit. The spacecraft wasstabilized along the Z axis and rotated at about 0.1 deg/s.Changes to the spin-axis orientation were by groundcommand, either delayed or in real time. The spacecraft couldbe made to move back and forth plus or minus 2.5 deg acrossa selected source along the X axis at 0.01 deg/s. Theexperiments looked along the Z axis of the spacecraft,perpendicular to it, and at an angle.

SAS-C

NSSDC ID: 1975-037A

Alternate Names

SAS 3

Explorer 53

Small Astonomical.Satellite 3

07788

Facts in Brief

Launch Date: 1975-05-07Launch Vehicle: ScoutLaunch Site: San MarcoPlatform, KenyaMass: 196.7 kgNominal Power: 65.0 W

Funding Agency


Discipline

Astronomy


Launch/Orbitalinformation for SAS-C

Experiments on SAS-C

Data collections from SAS-C


Personnel


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


SAS-C




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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: SAS-C (1975-037A)











http://nssdc.gsfc.nasa.gov/image/spacecraft/sas3.gif




Dr. Carl E.Fichtel

ProjectScientist


[email protected]

Dr. Nancy G.Roman

ProgramScientist


Dr. James E.Kupperian, Jr.

ProjectManager


Mr. John R.Holtz

ProgramManager

NASA Headquarters

Related Information/Data at NSSDC

Uhuru (SAS-A)SAS-B

US Active Archive for SAS-C Information/Data

The SAS-3 Archive at HEASARC




http://heasarc.gsfc.nasa.gov/docs/sas3/archive/sas3_archive.html

http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=SIRIO-B[02/09/2010 0:37:02]


Description

This satellite will be Italy's contribution to the InternationalMagnetoshperic Study. This satellite will be geostationary andwill contain experiments relevant to the magnetosphere.

Sirio-B

NSSDC ID: SIRIO-B

Facts in Brief

Launch Date: 1975-01-01Launch Vehicle: DeltaLaunch Site: CapeCanaveral, United States

Funding Agency

Unknown (Italy)

Discipline

Space Physics


Launch/Orbitalinformation for Sirio-B

Experiments on Sirio-B

Data collections from Sirio-B



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




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

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

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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Sirio-B (SIRIO-B)











http://www.usa.gov/








Description

The SMS 2, a NASA-developed, NOAA-operated spacecraft,carried (1) a visible-infrared spin-scan radiometer (VISSR) toprovide high-quality day/night cloudcover data and to takeradiance temperatures of the earth/atmosphere system, (2) ameteorological data collection and transmission system torelay processed data from central weather facilities to smallAPT-equipped regional stations and to collect and retransmitdata from remote earth-based platforms, and (3) a spaceenvironment monitor (SEM) system to measure proton,electron, and solar X-ray fluxes and magnetic fields. The spin-stabilized, earth-synchronous, and cylindrically shapedspacecraft measured 190.5 cm in diam and 230 cm in length,exclusive of a magnetometer that extended an additional 83cm beyond the cylinder shell. The primary structural memberswere a honeycomb equipment shelf and a thrust tube. TheVISSR telescope was mounted on the equipment shelf andviewed the earth through a special aperture in the side of thespacecraft. A support structure extended radially out from thethrust tube and was affixed to the solar panels, which formedthe outer walls of the spacecraft. Located in the annulus-shaped space between the thrust tube and the solar panelswere stationkeeping and dynamics control equipment,batteries, and most of the SEM equipment. Proper spacecraftattitude and spin rate (approximately 100 rpm) weremaintained by two separate sets of jet thrusters mountedaround the spacecraft equator and activated by groundcommand. Both UHF-band and S-band frequencies were usedin the telemetry and command subsystems. A low-power VHFtransponder provided telemetry and command during launch,and then served as a backup for the primary subsystem afterthe synchronous orbit was attained. For more detailedinformation, see "The GOES/SMS User's Guide."

SMS 2

NSSDC ID: 1975-011A

Alternate Names

Synch. Meteorol. Sat. B

ME02

07648

Facts in Brief


Funding Agencies


NOAA NationalEnvironmental SatelliteService (United States)

Disciplines

Earth Science

Solar Physics

Space Physics


Launch/Orbitalinformation for SMS 2

Experiments on SMS 2

Data collections from SMS2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: SMS 2 (1975-011A)













Personnel


Mr. Thomas J.Karras

ProjectManager

NOAA National Environmental Satellite, Data andInformation Service

Mr. William E.Shenk

ProjectScientist

NASA Goddard Space Flight Center


http://www.usa.gov/








Description

Soyuz 17 was a manned Soviet mission launched from theBaikonur Cosmodrome and docked with the Salyut 4 spacestation. The flight crew consisted of Cosmonauts Grechko andGubarev. It returned to Earth almost 30 days later on February9, 1975 11:03 GMT, and landed 110 km NE of Tselinograd.

Soyuz 17

NSSDC ID: 1975-001A

Alternate Names

07604

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Human Crew


Launch/Orbitalinformation for Soyuz 17

Experiments on Soyuz 17

Data collections fromSoyuz 17



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Soyuz 17

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Soyuz 17


mailto:[email protected]?Subject=NMC Comment/Question: Soyuz 17 (1975-001A)











http://www.usa.gov/








Description

Soyuz 18 was a manned Soviet mission launched from theBaikonur Cosmodrome. The flight crew consisted ofCosmonauts Kilmuk and Sevastyanov. It docked with theSalyut 4 space station and was recovered on July 26, 197514:18 GMT after 63 days. It landed 56 km E of Arkalyk.

Soyuz 18

NSSDC ID: 1975-044A

Alternate Names

07818

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Human Crew







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description

Soyuz 20 was an unmanned spacecraft launched by theUSSR. It was a long duration test of the Soyuz transportvehicle that docked with the Salyut 4 space station. It wasrecovered on February 16, 1976 2:24 GMT. Soyuz 20performed comprehensive checking of improved on-boardsystems of the spacecraft under various flight conditions. Italso carried a biological payload. Living organisms wereexposed to three months in space.

Soyuz 20

NSSDC ID: 1975-106A

Alternate Names

08430

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Engineering







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description

SRET 2 (MAS 2) was a French satellite launched with Molniya1-30 by the USSR on one booster rocket.

SRET 2

NSSDC ID: 1975-049B

Alternate Names

07910

Facts in Brief


Funding Agencies

Unknown (France)

Unknown (U.S.S.R)

Discipline

Engineering


Launch/Orbitalinformation for SRET 2

Experiments on SRET 2

Data collections fromSRET 2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: SRET 2 (1975-049B)











http://www.usa.gov/








Description

This US Air Force electronics intelligence satellite waslaunched from Vandenberg AFB aboard a Titan 3D rocket.

SSU 1/1

NSSDC ID: 1975-051C

Alternate Names

07937

Facts in Brief


Funding Agency


Discipline



Launch/Orbitalinformation for SSU 1/1

Experiments on SSU 1/1

Data collections from SSU1/1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: SSU 1/1 (1975-051C)











http://www.usa.gov/








Description

The two primary goals of this satellite were to minimize theeffects of non-gravitational forces and to obtain the highestpossible accuracy for laser range measurements. The satellitewas spherically shaped with a 12-cm radius. The core was analloy of uranium 238 and 1.5% molybdenum. The skinconsisted of 20 spherical caps made of an alloy of aluminumand 5% magnesium with triangular bases. Each cap containedthree laser corner cubes. The corner cubes were fused silicatrihedrons with circular apertures made of suprasil 1 with silvercoatings covered by inconel. For Groupe de Recherches deGeodesie Spatiale (GRGS), the principal objective was tostudy earth and ocean tides by (1) the determination of thesecond harmonics (amplitude and phase) of the mainsemidiurnal oceanic tides (M and S) and, if possible, of thediurnal K, O, and P tides; and (2) the determination of thedissipation in the solid earth and in the oceans (Q).

Starlette

NSSDC ID: 1975-010A

Alternate Names

07646

Facts in Brief


Funding Agency


Discipline

Earth Science


Launch/Orbitalinformation for Starlette

Experiments on Starlette

Data collections fromStarlette



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Starlette (1975-010A)











http://www.usa.gov/








Description

Symphonie 2 was a French-German, geostationary, equatorialexperimental communications satellite. The satellite body wasa right hexagonal prism, 1.85-m maximum diameter and 0.5-mhigh. Several antennas and other appendages were mountedon the ends, and three sets of symmetrically placed solarpanels extended outward a distance of 2.6 m from alternateedges of the spacecraft. A flywheel operated attitude controlsystem was maintaining attitude along three axes. A positiveorbit control system placed the spacecraft at a desiredlongitude and was being used to maintain that position. Itprovided 1200 telephone circuits and eight voice and two colorTV channels which operate between 4 and 6 GHz.

Symphonie 2

NSSDC ID: 1975-077A

Alternate Names

Symphonie-B

08132

Facts in Brief


Funding Agencies



Gesellschaft fuerWeltraumforschung,Germany (FederalRepublic of Germany)

Discipline

Communications


Launch/Orbitalinformation forSymphonie 2

Experiments onSymphonie 2

Data collections fromSymphonie 2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Symphonie 2 (1975-077A)













Personnel


Mr. P. Viellard Project Manager Centre National d'Etudes Spatiales

Mr. Robert J. Goss General Contact NASA Goddard Space Flight Center

Dr. Burkhard Pfeiffer Project Manager Ges fur Weltraumforschung


http://www.usa.gov/








Description

SRATS/Taiyo (Solar Radiation and Thermospheric Satellite)was an aeronomy research satellite. It had an octagonalcolumn form (75 cm in diameter and 65 cm in height), in whichthe experiment instruments were mounted. The satellite wasspin stabilized in a rolling wheel mode by a geomagneticattitude control system. Four plasma probes were extendedperpendicular to the spin axis by 0.5-m metallic booms. Powerat an average rate of 15 W was provided by 6000 silicon n-psolar cells. The objectives of the satellite were to study theionosphere systematically by simultaneously observing solarionizing radiations (hydrogen Lyman-Alpha and X rays), theultraviolet albedo of the earth, positive ion composition, andplasma parameters such as electron and ion densities andtemperatures in the ionosphere.

Taiyo

NSSDC ID: 1975-014A

Alternate Names

SRATS

Solar Radiation andThermospheric Satellite

07671

Facts in Brief

Launch Date: 1975-02-24Launch Vehicle: MuLaunch Site: UchinouraSpace Center, JapanMass: 86.0 kgNominal Power: 15.0 W

Funding Agency

Institute of Space andAeronautical Science, Uof Tokyo (Japan)

Disciplines

Earth Science

Solar Physics

Space Physics


Launch/Orbitalinformation for Taiyo

Experiments on Taiyo

Data collections from Taiyo


Personnel


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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

mailto:[email protected]?Subject=NMC Comment/Question: Taiyo (1975-014A)

mailto:[email protected]?Subject=NMC Comment/Question: Taiyo (1975-014A)












Prof. Kunio Hirao Project Manager Institute of Space and Aeronautical Science


http://www.usa.gov/








Description

TIP 2 was the second in a series of improved naviagationsatellites for the US Navy.

TIP 2

NSSDC ID: 1975-099A

Alternate Names

TRIAD 2

08361

Facts in Brief


Funding Agency

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

Discipline



Launch/Orbitalinformation for TIP 2

Experiments on TIP 2

Data collections from TIP 2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

mailto:[email protected]?Subject=NMC Comment/Question: TIP 2 (1975-099A)











http://www.usa.gov/








Description

This spacecraft entered Venus orbit and was separated fromthe lander on October 20, 1975, after about 4.5 months offlight. The orbiter mission was to act as a communicationsrelay for the lander and to explore cloud layers andatmospheric parameters with instruments including a French3500 angstrom UV photometer, a 4000-7000 angstrom photo-polarimeter, a 1.5 to 3 micron infrared spectrometer, and a 8 -30 micron infrared radiometer. The orbiter also carried amagnetometer and charged particle traps. Some reportsindicated a camera system was also aboard. The orbiterconsisted of a cylinder with two solar panel wings and a highgain parabolic antenna attached to the curved surface. A bell-shaped unit holding propulsion systems was attached to thebottom of the cylinder, and mounted on top was a 2.4 metersphere which held the landers. At launch the Venera 9spacecraft, including the lander, had a mass of 4936 kg.

Venera 9

NSSDC ID: 1975-050A

Alternate Names

Venera 9 Orbiter

Venus 9

07915

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Planetary Science


Launch/Orbitalinformation for Venera 9

Experiments on Venera 9

Data collections fromVenera 9

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

Personnel



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


Venera 9




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

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


mailto:[email protected]?Subject=NMC Comment/Question: Venera 9 (1975-050A)










http://nssdc.gsfc.nasa.gov/image/spacecraft/venera9.jpg



Mr. Artem Ivankov General Contact Lavochkin Association [email protected]

Selected References

Harvey, B., The new Russian space programme from competition to collaboration, John Wiley &Sons, Chichester, England, 1996.

Johnson, N. L., Handbook of soviet lunar and planetary exploration - volume 47 science andtechnology series, Amer. Astronau. Soc. Publ., 1979.

Venera 9 Lander

Venera Home PageVenus Home PageVenera lander images of the surface of Venus - and other Venus images


http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1975-050D

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

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

http://nssdc.gsfc.nasa.gov/imgcat/html/group_page/VN.html

http://www.usa.gov/








Description

On October 20, 1975, this spacecraft was separated from theOrbiter, and landing was made with the sun near zenith at0513 UT on October 22. A system of circulating fluid was usedto distribute the heat load. This system, plus precooling prior toentry, permitted operation of the spacecraft for 53 min afterlanding. During descent, heat dissipation and decelerationwere accomplished sequentially by protective hemisphericshells, three parachutes, a disk-shaped drag brake, and acompressible, metal, doughnut-shaped, landing cushion. Thelanding was about 2,200 km from the Venera 10 landing site.Preliminary results indicated: (A) clouds 30-40 km thick withbases at 30-35 km altitude, (B) atmospheric constituentsincluding HCl, HF, Br, and I, (C) surface pressure about 90(earth) atmospheres, (D) surface temperature 485 deg C, (E)light levels comparable to those at earth midlatitudes on acloudy summer day, and (F) successful TV photographyshowing shadows, no apparent dust in the air, and a variety of30-40 cm rocks which were not eroded.

Venera 9 Descent Craft

NSSDC ID: 1975-050D

Facts in Brief


Funding Agency


Discipline

Planetary Science


Launch/Orbitalinformation for Venera 9Descent Craft

Experiments on Venera 9Descent Craft

Data collections fromVenera 9 Descent Craft


Personnel



Selected References



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Venera 9 Descent Craft


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Venera 9 Descent Craft


mailto:[email protected]?Subject=NMC Comment/Question: Venera 9 Descent Craft (1975-050D)










http://nssdc.gsfc.nasa.gov/planetary/image/venera_9_lander.jpg




Venera descent module during landing testVenera 9 Orbiter



http://nssdc.gsfc.nasa.gov/image/spacecraft/venera_9_10_desc_test.gif





http://nssdc.gsfc.nasa.gov/imgcat/hires/v09_lander.gif

http://www.usa.gov/








Description

This spacecraft entered Venus orbit and was separated fromthe lander on October 23, 1975 after about 4.5 months of flight.The orbiter mission was to serve as a communications relayfor the lander and to explore cloud layers and atmosphericparameters with instruments including a French 3500 angstromUV photometer, a 4000-7000 angstrom photo-polarimeter, a1.5 to 3 micron infrared spectrometer, and a 8 - 30 microninfrared radiometer. The orbiter also carried a magnetometerand charged particle traps. Some reports indicated a camerasystem was also aboard. The orbiter consisted of a cylinderwith two solar panel wings and a high gain parabolic antennaattached to the curved surface. A bell-shaped unit holdingpropulsion systems was attached to the bottom of the cylinder,and mounted on top was a 2.4 meter sphere which held thelanders. At launch the Venera 10 spacecraft, including lander,had a mass of 5033 kg.

Venera 10

NSSDC ID: 1975-054A

Alternate Names

Venera 10 Orbiter

07947

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Disciplines

Planetary Science

Space Physics


Launch/Orbitalinformation for Venera 10

Experiments on Venera 10

Data collections fromVenera 10


Personnel



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


Venera 10




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













http://nssdc.gsfc.nasa.gov/image/spacecraft/venera10.jpg




Selected References



Venera 10 Lander



http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1975-054D




http://www.usa.gov/








Description

On October 23, 1975, this spacecraft was separated from theOrbiter, and landing was made with the sun near zenith, at0517 UT, on October 25. A system of circulating fluid wasused to distribute the heat load. This system, plus precoolingprior to entry, permitted operation of the spacecraft for 65 minafter landing. During descent, heat dissipation anddeceleration were accomplished sequentially by protectivehemispheric shells, three parachutes, a disk-shaped dragbrake, and a compressible, metal, doughnut-shaped, landingcushion. The landing was about 2,200 km distant from Venera9. Preliminary results provided: (A) profile of altitude(km)/pressure (earth atmospheres)/temperature (deg C) of42/3.3/158, 15/37/363, and 0/92/465, (B) successful TVphotography showing large pancake rocks with lava or otherweathered rocks in between, and (C) surface wind speed of3.5 m/s.


NSSDC ID: 1975-054D

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Planetary Science


Launch/Orbitalinformation for Venera 10Descent Craft

Experiments on Venera 10Descent Craft

Data collections fromVenera 10 Descent Craft


Personnel



Selected References

Surkov, Yu. A., et al., Investigations of the density of the Venusian surface rocks by Venera 10,


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





















http://nssdc.gsfc.nasa.gov/planetary/image/venera_9_lander.jpg



Pres. at 19th COSPAR Plenary Meet., June 8-19, 1975, Philadelphia, PA.



Venera descent module during landing testVenera 10 Orbiter



http://nssdc.gsfc.nasa.gov/image/spacecraft/venera_9_10_desc_test.gif





http://nssdc.gsfc.nasa.gov/imgcat/hires/v10_lander.gif

http://www.usa.gov/








Description

The Viking project consisted of launches of two separatespacecraft to Mars, Viking 1, launched on 20 August 1975, andViking 2, launched on 9 September 1975. Each spacecraftconsisted of an orbiter and a lander. After orbiting Mars andreturning images used for landing site selection, the orbiter andlander detached and the lander entered the martianatmosphere and soft-landed at the selected site. The orbiterscontinued imaging and other scientific operations from orbitwhile the landers deployed instruments on the surface. Thefully fueled orbiter-lander pair had a mass of 3530 kg. Afterseparation and landing, the lander had a mass of about 600 kgand the orbiter 900 kg. The lander was encased in a bioshieldat launch to prevent contamination by terrestrial organisms.

Spacecraft and InstrumentationThe lander consisted of a six-sided aluminum base withalternate 1.09 m and .56 m long sides, supported on threeextended legs attached to the shorter sides. The leg footpadsformed the vertices of an equilateral triangle with 2.21 m sideswhen viewed from above, with the long sides of the baseforming a straight line with the two adjoining footpads.Instrumentation was attached to the top of the base, elevatedabove the surface by the extended legs. Power was providedby two radioisotope thermal generator (RTG) units containingplutonium 238 affixed to opposite sides of the lander base andcovered by wind screens. Each generator was 28 cm tall, 58cm in diameter, had a mass of 13.6 kg and provided 30 Wcontinuous power at 4.4 volts. Four wet-cell sealed nickel-cadmium 8 amp-hour, 28 volt rechargeable batteries were alsoonboard to handle peak power loads.

Propulsion was provided for deorbit by a monopropellanthydrazine (N2H4) rocket with 12 nozzles arranged in fourclusters of three that provided 32 N thrust, giving a delta-V of180 m/s. These nozzles also acted as the control thrusters fortranslation and rotation of the lander. Terminal descent andlanding was achieved by three (one affixed on each long sideof the base, separated by 120 degress) monopropellanthydrazine engines. The engines had 18 nozzles to dispersethe exhaust and minimize effects on the ground and werethrottleable from 276 N to 2667 N. The hydrazine was purifiedto prevent contamination of the martian surface. The landercarried 85 kg of propellant at launch, contained in twospherical titanium tanks mounted on opposite sides of thelander beneath the RTG windscreens, giving a total launchmass of 657 kg. Control was achieved through the use of aninertial reference unit, four gyros, an aerodecelerator, a radaraltimeter, a terminal descent and landing radar, and the controlthrusters.

Viking 1 Lander

NSSDC ID: 1975-075C

Alternate Names

Viking-B Lander

Viking Lander 1

Thomas Mutch MemorialStation

09024

Facts in Brief

Launch Date: 1975-08-20Launch Vehicle: TitanIIIE-CentaurLaunch Site: CapeCanaveral, United StatesMass: 572.0 kgNominal Power: 70.0 W

Funding Agency


Discipline

Planetary Science


Launch/Orbitalinformation for Viking 1Lander

PDMP information forViking 1 Lander

Telecommunicationsinformation for Viking 1Lander

Experiments on Viking 1Lander

Data collections fromViking 1 Lander


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


Viking 1 Lander





http://nssdc.gsfc.nasa.gov/nmc/spacecraftPdmp.do?id=1975-075C


http://nssdc.gsfc.nasa.gov/nmc/spacecraftTelemetry.do?id=1975-075C



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


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










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



Communications were accomplished through a 20 W S-bandtransmitter and two 20 W TWTA's. A 2-axis steerable high-gainparabolic antenna was mounted on a boom near one edge ofthe lander base. An omnidirectional low-gain S-band antennaalso extends from the base. Both these antennae allowed forcommunication directly with the Earth. A UHF (381 MHz)antenna provided a one-way relay to the orbiter using a 30 Wrelay radio. Data storage was on a 40 Mbit tape recorder, andthe lander computer had a 6000 word memory for commandinstructions.

The lander carried instruments to achieve the primary scientificobjectives of the lander mission: to study the biology, chemicalcomposition (organic and inorganic), meteorology, seismology,magnetic properties, appearance, and physical properties ofthe martian surface and atmosphere. Two 360-degreecylindrical scan cameras were mounted near one long side ofthe base. From the center of this side extended the samplerarm, with a collector head, temperature sensor, and magnet onthe end. A meteorology boom, holding temperature, winddirection, and wind velocity sensors extended out and up fromthe top of one of the lander legs. A seismometer, magnet andcamera test targets, and magnifying mirror are mountedopposite the cameras, near the high-gain antenna. An interiorenvironmentally controlled compartment held the biologyexperiment and the gas chromatograph mass spectrometer.The X-ray flourescence spectrometer was also mounted withinthe structure. A pressure sensor was attached under thelander body. The scientific payload had a total mass ofapproximately 91 kg.

Mission ProfileFollowing launch and a 304 day cruise to Mars, the orbiterbegan returning global images of Mars about 5 days beforeorbit insertion. The Viking 1 spacecraft was inserted into Marsorbit on 19 June 1976 and trimmed to a 1513 x 33,000 km,24.66 hr site certification orbit on 21 June. Imaging ofcandidate sites was begun and the landing site was selectedbased on these pictures. The lander and its aeroshellseparated from the orbiter on 20 July 08:51 UT. At the time ofseparation, the lander was orbiting at about 4 km/s. Afterseparation rockets fired to begin lander deorbit. After a fewhours at about 300 km altitude, the lander was reoriented forentry. The aeroshell with its ablatable heat shield slowed thecraft as it plunged through the atmosphere. During this time,entry science experiments were performed. At 6 km altitude atabout 250 m/s the 16 m diameter lander parachutes weredeployed. Seven seconds later the aeroshell was jettisoned,and 8 seconds after that the three lander legs were extended.In 45 seconds the parachute had slowed the lander to 60 m/s.At 1.5 km altitude, retro-rockets were ignited and fired untillanding 40 seconds later at about 2.4 m/s. The landing rocketsused an 18 nozzle design to spread the hydrogen and nitrogenexhaust over a wide area. It was determined that this wouldlimit surface heating to no more than 1 degree C and that nomore than 1 mm of the surface material would be strippedaway. The Viking 1 Lander touched down in western ChrysePlanitia at 22.697 deg N latitude and 48.222 deg W longitudeat a reference altitude of -2.69 km relative to a referenceellipsoid with an equatorial radius of 3397.2 km and a flatnessof 0.0105 (22.533 deg N, 48.264 deg W planetographic) at11:53:06 UT (4:13 p.m. local Mars time). Approximately 22 kgof propellants were left at landing.

Transmission of the first surface image began 25 seconds afterlanding. The seismometer failed to uncage, and a sampler armlocking pin was stuck and took 5 days to shake out.Otherwise, all experiments functioned nominally. The Viking 1


mailto:[email protected]?Subject=NMC Comment/Question: Viking 1 Lander (1975-075C)




Lander was named the Thomas Mutch Memorial Station inJanuary 1982 in honor of the leader of the Viking imagingteam. It operated until 13 November 1982 when contact waslost.

The total cost of the Viking project was roughly one billiondollars. For a detailed description of the Viking mission andexperiments, see "Scientific Results of the Viking Project," J.Geophys. Res., v. 82, n. 28, 1977.

Personnel


Dr. Gerald A.Soffen

ProjectScientist


Dr. Joseph M.Boyce

ProgramScientist


Mr. James S.Martin, Jr.

ProjectManager


Dr. Guenter K.Strobel

ProgramManager

NASA Headquarters

Selected References

Soffen, G. A., and C. W. Snyder, First Viking mission to Mars, Science, 193, 759-766, Aug.1976.

Masursky, H., and N. L. Crabill, Viking landing sites: Selection and certification, Science, 193,809-812, Aug. 1976.

Tyler, G. L., et al., Radar characteristics of Viking 1 landing sites, Science, 193, 812-815, Aug.1976.

Soffen, G. A., Scientific results of the Viking mission, Science, 194, No. 4271, 1274-1276, Dec.1976.

Soffen, G. A., The Viking project, J. Geophys. Res., 82, No. 28, 3959-3970, Sept. 1977.

Other Viking Information/Data at NSSDCGo to the NSSDC Viking pageRead about and/or order the Viking image mosaic CD-ROM setRead about and/or order the Viking raw image CD-ROM set

View some of the images taken of Mars by Viking and other missions

Viking FTP site - Includes an index of latitude and longitude of all Orbiter images

Related Information/Data at NSSDCMars PageMars Fact SheetMars Frequently Asked Questions

Other Sources of Viking Information/DataViking Lander Images (PDS Imaging Node)PDS Geosciences NodeViking Image Atlas of MarsCenter for Mars ExplorationViking Computer Facility: Meteorology and ImagesFTP access to selected Viking CD-ROMs


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

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

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

http://nssdc.gsfc.nasa.gov/imgcat/html/group_page/MR.html

ftp://nssdcftp.gsfc.nasa.gov/miscellaneous/planetary/viking/

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

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

http://nssdc.gsfc.nasa.gov/planetary/planetaryfaq.html#Mars

http://www-pdsimage.jpl.nasa.gov/PDS/public/vikingl/vl_images.html

http://wwwpds.wustl.edu/

http://ic-www.arc.nasa.gov/ic/projects/bayes-group/Atlas/Mars/

http://cmex-www.arc.nasa.gov/

http://www.atmos.washington.edu/~mars/#viking

ftp://explorer.arc.nasa.gov/cdrom/viking

http://www.usa.gov/








Description

The Viking project consisted of launches of two separatespacecraft to Mars, Viking 1, launched on 20 August 1975, andViking 2, launched on 9 September 1975. Each spacecraftconsisted of an orbiter and a lander. After orbiting Mars andreturning images used for landing site selection, the orbiter andlander detached and the lander entered the martianatmosphere and soft-landed at the selected site. The orbiterscontinued imaging and other scientific operations from orbitwhile the landers deployed instruments on the surface. Thefully fueled orbiter-lander pair had a mass of 3527 kg. Afterseparation and landing, the lander had a mass of about 600 kgand the orbiter 900 kg.

Spacecraft and InstrumentationThe primary objectives of the Viking orbiters were to transportthe landers to Mars, perform reconnaissance to locate andcertify landing sites, act as a communications relays for thelanders, and to perform their own scientific investigations. Theorbiter, based on the earlier Mariner 9 spacecraft, was anoctagon approximately 2.5 m across. The total launch masswas 2328 kg, of which 1445 kg were propellant and attitudecontrol gas. The eight faces of the ring-like structure were.4572 m high and were alternately 1.397 and 0.508 m wide.The overall height was 3.29 m from the lander attachmentpoints on the bottom to the launch vehicle attachment pointson top. There were 16 modular compartments, 3 on each ofthe 4 long faces and one on each short face. Four solar panelwings extended from the axis of the orbiter, the distance fromtip to tip of two oppositely extended solar panels was 9.75 m.The power was provided by eight 1.57 x 1.23 m solar panels,two on each wing. The solar panels were made up of a total of34,800 solar cells and produced 620 W of power at Mars.Power was also stored in 2 nickel-cadmium 30-amp-hrbatteries.

The main propulsion unit was mounted above the orbiter bus.Propulsion was furnished by a bipropellant (monomethylhydrazine and nitrogen tetroxide) liquid-fueled rocket enginewhich could be gimballed up to 9 degrees. The engine wascapable of 1323 N thrust, translating to a delta-V of 1480 m/s.Attitude control was achieved by 12 small compressed-nitrogen jets. An acquisition Sun sensor, a cruise Sun sensor,a Canopus star tracker and an inertial reference unit consistingof 6 gyroscopes allowed three-axis stabilization. Twoaccelerometers were also on board. Communications wereaccomplished through a 20-W S-band (2.3 GHz) transmitterand 2 20-W TWTA's. An X-band (8.4 GHz) downlink was alsoadded specifically for radio science and to conductcommunications experiments. Uplink was via S-band (2.1

Viking 1 Orbiter

NSSDC ID: 1975-075A

Alternate Names

Viking-B Orbiter

Viking Orbiter 1

08108

Facts in Brief

Launch Date: 1975-08-20Launch Vehicle: TitanIIIE-CentaurLaunch Site: CapeCanaveral, United StatesMass: 883.0 kgNominalPower: 620.0 W

Funding Agency


Discipline

Planetary Science


Launch/Orbitalinformation for Viking 1Orbiter

PDMP information forViking 1 Orbiter

Telecommunicationsinformation for Viking 1Orbiter

Experiments on Viking 1Orbiter

Data collections fromViking 1 Orbiter


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


Viking 1 Orbiter





http://nssdc.gsfc.nasa.gov/nmc/spacecraftPdmp.do?id=1975-075A


http://nssdc.gsfc.nasa.gov/nmc/spacecraftTelemetry.do?id=1975-075A



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


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










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



GHz). A 2-axis steerable high-gain parabolic dish antenna witha diameter of approximately 1.5 m was attached at one edgeof the orbiter base, and a fixed low-gain antenna extendedfrom the top of the bus. Two tape recorders were each capableof storing 1280 Mbits. A 381 MHz relay radio was alsoavailable. Temperature control was achieved by multilayerinsulation, thermally activated louvers, and electrical heaters.

Scientific instruments for conducting imaging, atmosphericwater vapor, and infrared thermal mapping were enclosed in atemperature controlled, pointable scan platform extending fromthe base of the orbiter. The scientific instrumentation had atotal mass of approximately 72 kg. Radio scienceinvestigations were also done using the spacecraft transmitter.Command processing was done by two identical andindependent data processors, each with a 4096-word memoryfor storing uplink command sequences and acquired data.

Mission ProfileFollowing launch and a 10 month cruise to Mars, the orbiterbegan returning global images of Mars about 5 days beforeorbit insertion. The Viking 1 Orbiter was inserted into Mars orbiton 19 June 1976 and trimmed to a 1513 x 33,000 km, 24.66 hrsite certification orbit on 21 June. Imaging of candidate siteswas begun and the landing site was selected based on thesepictures. The lander separated from the orbiter on 20 July08:51 UT and landed at Chryse Planitia at 11:56:06 UT. Theorbiter primary mission ended at the beginning of solarconjunction on 5 November 1976. The extended missioncommenced on 14 December 1976 after solar conjunction.Operations included close approaches to Phobos in February1977. The periapsis was reduced to 300 km on 11 March1977. Minor orbit adjustments were done occasionally over thecourse of the mission, primarily to change the walk rate - therate at which the planetocentric longitude changed with eachorbit, and the periapsis was raised to 357 km on 20 July 1979.On 7 August 1980 Viking 1 Orbiter was running low on attitudecontrol gas and its orbit was raised from 357 x 33943 km to320 x 56000 km to prevent impact with Mars and possiblecontamination until the year 2019. Operations were terminatedon 17 August 1980 after 1485 orbits.



Personnel


Dr. Gerald A.Soffen

ProjectScientist


Dr. Joseph M.Boyce

ProgramScientist


Mr. James S.Martin, Jr.

ProjectManager


Dr. Guenter K.Strobel

ProgramManager

NASA Headquarters

Selected References

Tolson, R. H., et al., Orbit and position determination for Mars Orbiters and Landers, J. Spacecr.Rockets, 7, No. 9, 1095-1100, Sept. 1970.

mailto:[email protected]?Subject=NMC Comment/Question: Viking 1 Orbiter (1975-075A)







Snyder, C. W., The missions of the Viking Orbiters, J. Geophys. Res., 82, No. 28, 3971-3983,Sept. 1977.





















http://www.usa.gov/








Description

The Viking project consisted of launches of two separatespacecraft to Mars, Viking 1, launched on 20 August 1975, andViking 2, launched on 9 September 1975. Each spacecraftconsisted of an orbiter and a lander. After orbiting Mars andreturning images used for landing site selection, the orbiter andlander detached and the lander entered the martianatmosphere and soft-landed at the selected site. The orbiterscontinued imaging and other scientific operations from orbitwhile the landers deployed instruments on the surface. Thefully fueled orbiter-lander pair had a mass of 3530 kg. Afterseparation and landing, the lander had a mass of about 600 kgand the orbiter 900 kg. The lander was encased in a bioshieldat launch to prevent contamination by terrestrial organisms.

Spacecraft and InstrumentationThe lander consisted of a six-sided aluminum base withalternate 1.09 m and .56 m long sides, supported on threeextended legs attached to the shorter sides. The leg footpadsformed the vertices of an equilateral triangle with 2.21 m sideswhen viewed from above, with the long sides of the baseforming a straight line with the two adjoining footpads.Instrumentation was attached to the top of the base, elevatedabove the surface by the extended legs. Power was providedby two radioisotope thermal generator (RTG) units containingplutonium 238 affixed to opposite sides of the lander base andcovered by wind screens. Each generator was 28 cm tall, 58cm in diameter, had a mass of 13.6 kg and provided 30 Wcontinuous power at 4.4 volts. Four wet-cell sealed nickel-cadmium 8 amp-hour, 28 volt rechargeable batteries were alsoonboard to handle peak power loads.

Propulsion was provided for deorbit by a monopropellanthydrazine (N2H4) rocket with 12 nozzles arranged in fourclusters of three that provided 32 N thrust, giving a delta-V of180 m/s. These nozzles also acted as the control thrusters fortranslation and rotation of the lander. Terminal descent andlanding was achieved by three (one affixed on each long sideof the base, separated by 120 degress) monopropellanthydrazine engines. The engines had 18 nozzles to dispersethe exhaust and minimize effects on the ground and werethrottleable from 276 N to 2667 N. The hydrazine was purifiedto prevent contamination of the martian surface. The landercarried 85 kg of propellant at launch, contained in twospherical titanium tanks mounted on opposite sides of thelander beneath the RTG windscreens, giving a total launchmass of 657 kg. Control was achieved through the use of aninertial reference unit, four gyros, an aerodecelerator, a radaraltimeter, a terminal descent and landing radar, and the controlthrusters.

Viking 2 Lander

NSSDC ID: 1975-083C

Alternate Names

Viking-A Lander

Viking Lander 2

Gerald Soffen MemorialStation

09408

Facts in Brief

Launch Date: 1975-09-09Launch Vehicle: TitanIIIE-CentaurLaunch Site: CapeCanaveral, United StatesMass: 572.0 kgNominal Power: 70.0 W

Funding Agency


Discipline

Planetary Science


Launch/Orbitalinformation for Viking 2Lander

PDMP information forViking 2 Lander

Telecommunicationsinformation for Viking 2Lander

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Viking 2 Lander






















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



Communications were accomplished through a 20 W S-bandtransmitter and two 20 W TWTA's. A 2-axis steerable high-gainparabolic antenna was mounted on a boom near one edge ofthe lander base. An omnidirectional low-gain S-band antennaalso extends from the base. Both these antennae allowed forcommunication directly with the Earth. A UHF (381 MHz)antenna provided a one-way relay to the orbiter using a 30 Wrelay radio. Data storage was on a 40 Mbit tape recorder, andthe lander computer had a 6000 word memory for commandinstructions.

The lander carried instruments to achieve the primary scientificobjectives of the lander mission: to study the biology, chemicalcomposition (organic and inorganic), meteorology, seismology,magnetic properties, appearance, and physical properties ofthe martian surface and atmosphere. Two 360-degreecylindrical scan cameras were mounted near one long side ofthe base. From the center of this side extended the samplerarm, with a collector head, temperature sensor, and magnet onthe end. A meteorology boom, holding temperature, winddirection, and wind velocity sensors extended out and up fromthe top of one of the lander legs. A seismometer, magnet andcamera test targets, and magnifying mirror are mountedopposite the cameras, near the high-gain antenna. An interiorenvironmentally controlled compartment held the biologyexperiment and the gas chromatograph mass spectrometer.The X-ray flourescence spectrometer was also mounted withinthe structure. A pressure sensor was attached under thelander body. The scientific payload had a total mass ofapproximately 91 kg.

Mission ProfileFollowing launch and a 333 day cruise to Mars, the Viking 2Orbiter began returning global images of Mars prior to orbitinsertion. The orbiter was inserted into a 1500 x 33,000 km,24.6 hr Mars orbit on 7 August 1976 and trimmed to a 27.3 hrsite certification orbit with a periapsis of 1499 km and aninclination of 55.2 degrees on 9 August. Imaging of candidatesites was begun and the landing site was selected based onthese pictures and the images returned by the Viking 1 Orbiter.The lander and its aeroshell separated from the orbiter on 3September 19:39:59 UT. At the time of separation, the landerwas orbiting at about 4 km/s. After separation rockets fired tobegin lander deorbit. After a few hours, at about 300 kmaltitude, the lander was reoriented for entry. The aeroshell withits ablatable heat shield slowed the craft as it plunged throughthe atmosphere. During this time, entry science experimentswere performed. At 6 km altitude at about 250 m/s the 16 mdiameter lander parachutes were deployed. Seven secondslater the aeroshell was jettisoned, and 8 seconds after that thethree lander legs were extended. In 45 seconds the parachutehad slowed the lander to 60 m/s. At 1.5 km altitude, retro-rockets were ignited and fired until landing 40 seconds later atabout 2.4 m/s. The landing rockets used an 18 nozzle designto spread the hydrogen and nitrogen exhaust over a wide area.It was determined that this would limit surface heating to nomore than 1 degree C and that no more than 1 mm of thesurface material would be stripped away.

The Viking 2 Lander touched down about 200 km west of thecrater Mie in Utopia Planitia at 48.269 deg N latitude and225.990 deg W longitude at a reference altitude of 4.23 kmrelative to a reference ellipsoid with an equatorial radius of3397.2 km and a flatness of 0.0105 (48.039 deg N, 226.032deg W planetographic) at 22:58:20 UT (9:49:05 a.m. local Marstime. Approximately 22 kg of propellants were left at landing.Due to radar misidentification of a rock or highly reflectivesurface, the thrusters fired an extra time 0.4 seconds before






landing, cracking the surface and raising dust. The landersettled down with one leg on a rock, tilted at 8.2 degrees. Thecameras began taking images immediately after landing. TheViking 2 Lander operated on the surface for 1281 Mars daysand was turned off on April 11, 1980 when its batteries failed.


Personnel


Dr. Gerald A. Soffen Project Scientist NASA Langley Research Center

Dr. Richard S. Young Program Scientist NASA Headquarters

Mr. James S. Martin, Jr. Project Manager NASA Langley Research Center

Mr. Walter Jakobowski Program Manager NASA Headquarters

Selected References


Masursky, H., and N. L. Crabill, Viking landing sites: Selection and certification, Science, 193,809-812, Aug. 1976.























http://www.usa.gov/








Description

The Viking project consisted of launches of two separatespacecraft to Mars, Viking 1, launched on 20 August 1975, andViking 2, launched on 9 September 1975. Each spacecraftconsisted of an orbiter and a lander. After orbiting Mars andreturning images used for landing site selection, the orbiter andlander detached and the lander entered the martianatmosphere and soft-landed at the selected site. The orbiterscontinued imaging and other scientific operations from orbitwhile the landers deployed instruments on the surface. Thefully fueled orbiter-lander pair had a mass of 3527 kg. Afterseparation and landing, the lander had a mass of about 600 kgand the orbiter 900 kg.

Spacecraft and InstrumentationThe primary objectives of the Viking orbiters were to transportthe landers to Mars, perform reconnaissance to locate andcertify landing sites, act as a communications relays for thelanders, and to perform their own scientific investigations. Theorbiter, based on the earlier Mariner 9 spacecraft, was anoctagon approximately 2.5 m across. The total launch masswas 2328 kg, of which 1445 kg were propellant and attitudecontrol gas. The eight faces of the ring-like structure were.4572 m high and were alternately 1.397 and 0.508 m wide.The overall height was 3.29 m from the lander attachmentpoints on the bottom to the launch vehicle attachment pointson top. There were 16 modular compartments, 3 on each ofthe 4 long faces and one on each short face. Four solar panelwings extended from the axis of the orbiter, the distance fromtip to tip of two oppositely extended solar panels was 9.75 m.The power was provided by eight 1.57 x 1.23 m solar panels,two on each wing. The solar panels were made up of a total of34,800 solar cells and produced 620 W of power at Mars.Power was also stored in 2 nickel-cadmium 30-amp-hrbatteries.

The main propulsion unit was mounted above the orbiter bus.Propulsion was furnished by a bipropellant (monomethylhydrazine and nitrogen tetroxide) liquid-fueled rocket enginewhich could be gimballed up to 9 degrees. The engine wascapable of 1323 N thrust, translating to a delta-V of 1480 m/s.Attitude control was achieved by 12 small compressed-nitrogen jets. An acquisition Sun sensor, a cruise Sun sensor,a Canopus star tracker and an inertial reference unit consistingof 6 gyroscopes allowed three-axis stabilization. Twoaccelerometers were also on board. Communications wereaccomplished through a 20-W S-band (2.3 GHz) transmitterand 2 20-W TWTA's. An X-band (8.4 GHz) downlink was alsoadded specifically for radio science and to conductcommunications experiments. Uplink was via S-band (2.1

Viking 2 Orbiter

NSSDC ID: 1975-083A

Alternate Names

Viking-A Orbiter

Viking Orbiter 2

08199

Facts in Brief

Launch Date: 1975-09-09Launch Vehicle: TitanIIIE-CentaurLaunch Site: CapeCanaveral, United StatesMass: 883.0 kgNominalPower: 620.0 W

Funding Agency


Discipline

Planetary Science


Launch/Orbitalinformation for Viking 2Orbiter

PDMP information forViking 2 Orbiter

Telecommunicationsinformation for Viking 2Orbiter

Experiments on Viking 2Orbiter

Data collections fromViking 2 Orbiter


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Viking 2 Orbiter






















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



GHz). A 2-axis steerable high-gain parabolic dish antenna witha diameter of approximately 1.5 m was attached at one edgeof the orbiter base, and a fixed low-gain antenna extendedfrom the top of the bus. Two tape recorders were each capableof storing 1280 Mbits. A 381 MHz relay radio was alsoavailable. Temperature control was achieved by multilayerinsulation, thermally activated louvers, and electrical heaters.

Scientific instruments for conducting imaging, atmosphericwater vapor, and infrared thermal mapping were enclosed in atemperature controlled, pointable scan platform extending fromthe base of the orbiter. The scientific instrumentation had atotal mass of approximately 72 kg. Radio scienceinvestigations were also done using the spacecraft transmitter.Command processing was done by two identical andindependent data processors, each with a 4096-word memoryfor storing uplink command sequences and acquired data.

Mission ProfileFollowing launch and a 333 day cruise to Mars, the Viking 2Orbiter began returning global images of Mars prior to orbitinsertion. The orbiter was inserted into a 1500 x 33,000 km,24.6 hr Mars orbit on 7 August 1976 and trimmed to a 27.3 hrsite certification orbit with a periapsis of 1499 km and aninclination of 55.2 degrees on 9 August. Imaging of candidatesites was begun and the landing site was selected based onthese pictures and the images returned by the Viking 1 Orbiter.The lander separated from the orbiter on 3 September 1976and landed at Utopia Planitia at 22:37:50 UT. Normaloperations called for the structure connecting the orbiter andlander (the bioshield) to be ejected after separation, butbecause of problems with the separation the bioshield was leftattached to the orbiter. The orbit inclination was raised to 75degrees on 30 September 1976. The orbiter primary missionended at the beginning of solar conjunction on 8 November1976. The extended mission commenced on 14 December1976 after solar conjunction. On 20 December 1976 theperiapsis was lowered to 778 km and the inclination raised to80 degrees. Operations included close approaches to Deimosin October 1977 and the periapsis was lowered to 300 km andthe period changed to 24 hours on 23 October 1977. Theorbiter developed a leak in its propulsion system that vented itsattitude control gas. It was placed in a 302 x 33176 km orbitand turned off on 25 July 1978 after returning almost 16,000images in 706 orbits around Mars.



Personnel


Dr. Gerald A. Soffen Project Scientist NASA Langley Research Center

Dr. Richard S. Young Program Scientist NASA Headquarters

Mr. James S. Martin, Jr. Project Manager NASA Langley Research Center

Mr. Walter Jakobowski Program Manager NASA Headquarters

Selected References

Tolson, R. H., et al., Orbit and position determination for Mars Orbiters and Landers, J. Spacecr.Rockets, 7, No. 9, 1095-1100, Sept. 1970.







Snyder, C. W., The missions of the Viking Orbiters, J. Geophys. Res., 82, No. 28, 3971-3983,Sept. 1977.





















http://www.usa.gov/





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