nasa - nssdc - master catalog - spacecraft query · facts in brief launch date: 1984-06-25. launch...

Cronología de Lanzamientos Espaciales

Año 1984 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[20/11/2010 23:53:57]

Sunday, 21 November 2010

Spacecraft Query Results

There were 170 spacecraft returned.

Spacecraft Name NSSDC ID Launch Date

1984-009A 1984-009A 1984-01-31

1984-065A 1984-065A 1984-06-25

1984-065C 1984-065C 1984-06-25

AMPTE/CCE 1984-088A 1984-08-16

AMPTE/IRM 1984-088B 1984-08-16

AMPTE/UKS 1984-088C 1984-08-16

Anik D2 1984-113B 1984-11-09

BS-2A 1984-005A 1984-01-23

Cosmos 1522 1984-001A 1984-01-05

Cosmos 1523 1984-001B 1984-01-05

Cosmos 1524 1984-001C 1984-01-05

Cosmos 1525 1984-001D 1984-01-05

Cosmos 1526 1984-001E 1984-01-05

Cosmos 1527 1984-001F 1984-01-05

Cosmos 1528 1984-001G 1984-01-05

Cosmos 1529 1984-001H 1984-01-05

Cosmos 1530 1984-002A 1984-01-11

Cosmos 1531 1984-003A 1984-01-11

Cosmos 1532 1984-004A 1984-01-13

Cosmos 1533 1984-006A 1984-01-26

Cosmos 1534 1984-007A 1984-01-26

Cosmos 1535 1984-010A 1984-02-02

Cosmos 1536 1984-013A 1984-02-08

Cosmos 1537 1984-017A 1984-02-16

Cosmos 1538 1984-019A 1984-02-21

Cosmos 1539 1984-020A 1984-02-28

Cosmos 1540 1984-022A 1984-03-02

Cosmos 1541 1984-024A 1984-03-06

Cosmos 1542 1984-025A 1984-03-07

Cosmos 1543 1984-026A 1984-03-10

Cosmos 1544 1984-027A 1984-03-15

Cosmos 1545 1984-030A 1984-03-21

Cosmos 1546 1984-031A 1984-03-29

Cosmos 1547 1984-033A 1984-04-05

Cosmos 1548 1984-036A 1984-04-10

Cosmos 1549 1984-040A 1984-04-19

NSSDC MasterCatalog Search

Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data

Lunar/Planetary Events



Cosmos 1550 1984-043A 1984-05-11

Cosmos 1551 1984-044A 1984-05-11

Cosmos 1552 1984-045A 1984-05-14

Cosmos 1553 1984-046A 1984-05-17

Cosmos 1554 1984-047A 1984-05-19

Cosmos 1555 1984-047B 1984-05-19

Cosmos 1556 1984-047C 1984-05-19

Cosmos 1557 1984-048A 1984-05-22

Cosmos 1558 1984-050A 1984-05-25

Cosmos 1559 1984-052A 1984-05-28

Cosmos 1560 1984-052B 1984-05-28

Cosmos 1561 1984-052C 1984-05-28

Cosmos 1562 1984-052D 1984-05-28

Cosmos 1563 1984-052E 1984-05-28

Cosmos 1564 1984-052F 1984-05-28

Cosmos 1565 1984-052G 1984-05-28

Cosmos 1566 1984-052H 1984-05-28

Cosmos 1567 1984-053A 1984-05-30

Cosmos 1568 1984-054A 1984-06-01

Cosmos 1569 1984-055A 1984-06-06

Cosmos 1570 1984-056A 1984-06-08

Cosmos 1571 1984-058A 1984-06-11

Cosmos 1572 1984-060A 1984-06-15

Cosmos 1573 1984-061A 1984-06-19

Cosmos 1574 1984-062A 1984-06-21

Cosmos 1575 1984-064A 1984-06-22

Cosmos 1576 1984-066A 1984-06-26

Cosmos 1577 1984-067A 1984-06-27

Cosmos 1578 1984-068A 1984-06-28

Cosmos 1579 1984-069A 1984-06-29

Cosmos 1580 1984-070A 1984-06-30

Cosmos 1581 1984-071A 1984-07-03

Cosmos 1582 1984-074A 1984-07-19

Cosmos 1583 1984-075A 1984-07-24

Cosmos 1584 1984-076A 1984-07-27

Cosmos 1585 1984-077A 1984-07-31

Cosmos 1586 1984-079A 1984-08-02

Cosmos 1587 1984-082A 1984-08-06

Cosmos 1588 1984-083A 1984-08-07

Cosmos 1589 1984-084A 1984-08-08

Cosmos 1590 1984-087A 1984-08-16

Cosmos 1591 1984-092A 1984-08-30

Cosmos 1592 1984-094A 1984-09-04

Cosmos 1593 1984-095A 1984-09-04

Cosmos 1594 1984-095B 1984-09-04

Cosmos 1595 1984-095C 1984-09-04

Cosmos 1596 1984-096A 1984-09-07

Cosmos 1597 1984-099A 1984-09-13

Cosmos 1598 1984-100A 1984-09-13



Cosmos 1599 1984-102A 1984-09-25

Cosmos 1600 1984-103A 1984-09-27

Cosmos 1601 1984-104A 1984-09-27

Cosmos 1602 1984-105A 1984-09-28

Cosmos 1603 1984-106A 1984-09-28

Cosmos 1604 1984-107A 1984-10-04

Cosmos 1605 1984-109A 1984-10-11

Cosmos 1606 1984-111A 1984-10-11

Cosmos 1607 1984-112A 1984-10-31

Cosmos 1608 1984-116A 1984-11-14

Cosmos 1609 1984-117A 1984-11-14

Cosmos 1610 1984-118A 1984-11-15

Cosmos 1611 1984-119A 1984-11-21

Cosmos 1612 1984-120A 1984-11-27

Cosmos 1613 1984-121A 1984-11-29

Cosmos 1614 1984-126A 1984-12-19

Cosmos 1615 1984-127A 1984-12-20

DSP F11 1984-037A 1984-04-14

Ekran 12 1984-028A 1984-03-16

Ekran 13 1984-090A 1984-08-24

ERBS 1984-108B 1984-10-05

EUTELSAT 2 1984-081A 1984-08-04

Galaxy-C 1984-101A 1984-09-21

GMS 3 1984-080A 1984-08-02

Gorizont 9 1984-041A 1984-04-22

Gorizont 10 1984-078A 1984-08-02

INTELSAT 5 F-8 1984-023A 1984-03-05

INTELSAT 5 F-9 1984-057A 1984-06-09

IRT 1984-011C 1984-02-03

JD1 1984-012C 1984-02-05

JD2 1984-012D 1984-02-05

JD3 1984-012F 1984-02-05

KH 11-6 1984-122A 1984-12-04

KH 8-54 1984-039A 1984-04-17

Landsat 5 1984-021A 1984-03-01

LDEF 1 1984-034B 1984-04-06

Leasat F1 1984-093C 1984-08-31

Leasat F2 1984-113C 1984-11-10

Marecs-B2 1984-114B 1984-11-10

Meteor 2-11 1984-072A 1984-07-05

Molniya 1-60 1984-029A 1984-03-16

Molniya 1-61 1984-085A 1984-08-10

Molniya 1-62 1984-089A 1984-08-24

Molniya 1-63 1984-124A 1984-12-14

NATO 3-D 1984-115A 1984-11-14

Navstar 9 1984-059A 1984-06-13

Navstar 10 1984-097A 1984-09-08

NOAA 9 1984-123A 1984-12-12

NOSS 6 1984-012A 1984-02-05



NOVA III 1984-110A 1984-10-12

Ohzora 1984-015A 1984-02-14

Palapa-B2 1984-011D 1984-02-03

PRC 14 1984-008A 1984-01-29

PRC 15 1984-035A 1984-04-08

PRC 16 1984-098A 1984-09-12

Progress 19 1984-018A 1984-02-21

Progress 20 1984-038A 1984-04-15

Progress 21 1984-042A 1984-05-07

Progress 22 1984-051A 1984-05-28

Progress 23 1984-086A 1984-08-14

Raduga 14 1984-016A 1984-02-15

Raduga 15 1984-063A 1984-06-22

SBS 4 1984-093B 1984-08-30

SDS F-5A 1984-091A 1984-08-28

Soyuz T-10 1984-014A 1984-02-08

Soyuz T-11 1984-032A 1984-04-03

Soyuz T-12 1984-073A 1984-07-17

Spacenet 1 1984-049A 1984-05-23

Spacenet 2 1984-114A 1984-11-10

STS 41B 1984-011A 1984-02-03

STS 41C 1984-034A 1984-04-06

STS 41D 1984-093A 1984-08-30

STS 41G 1984-108A 1984-10-05

STS 51A 1984-113A 1984-11-08

TELECOM 1A 1984-081B 1984-08-04

Telstar 3C 1984-093D 1984-09-01

UOSAT 2 1984-021B 1984-03-01

USA 7 1984-129A 1984-12-22

Vega 1 1984-125A 1984-12-15

Vega 1 Balloon 1984-125F 1984-12-15

Vega 1 Descent Craft 1984-125E 1984-12-15

Vega 2 1984-128A 1984-12-21

Vega 2 Balloon 1984-128F 1984-12-21

Vega 2 Descent Craft 1984-128E 1984-12-21

Westar 6 1984-011B 1984-02-03

+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010

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NASA - NSSDC - Spacecraft - Details

http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1984-009A[24/11/2010 23:02:02]

Thursday, 25 November 2010

Description

1984-009A

NSSDC ID: 1984-009A

Alternate Names

14675

Facts in Brief

Launch Date: 1984-01-31Launch Vehicle: Titan34DLaunch Site: CapeCanaveral, United StatesMass: 1043.0 kg

Funding Agency

Unknown (United States)

Discipline

Surveillance and OtherMilitary

AdditionalInformation

Launch/Orbitalinformation for 1984-009A

Experiments on 1984-009A

Data collections from 1984-009A

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


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data



http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1984-009A



http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=1984-009A

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=1984-009A


mailto:[email protected]?Subject=NMC Comment/Question: 1984-009A (1984-009A)



http://www.usa.gov/







Description

1984-065A

NSSDC ID: 1984-065A

Alternate Names

15063

Facts in Brief

Launch Date: 1984-06-25Launch Vehicle: Titan34DLaunchSite: Vandenberg AFB,United StatesMass: 13300.0 kg

Funding Agency


Discipline



Launch/Orbitalinformation for 1984-065A

Experiments on 1984-065A

Data collections from 1984-065A



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=1984-065A






http://www.usa.gov/





http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1984-065C[24/11/2010 23:04:44]


Description

1984-065C

NSSDC ID: 1984-065C

Alternate Names

15071

Facts in Brief


Funding Agency


Discipline



Launch/Orbitalinformation for 1984-065C

Experiments on 1984-065C

Data collections from 1984-065C



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data



http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1984-065C



http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=1984-065C

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=1984-065C

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=1984-065C

mailto:[email protected]?Subject=NMC Comment/Question: 1984-065C (1984-065C)



http://www.usa.gov/







Description

The AMPTE (Active Magnetospheric Particle Tracer Explorers)mission was designed to study the access of solar-wind ions tothe magnetosphere, the convective-diffusive transport andenergization of magnetospheric particles, and the interactionsof plasmas in space. The mission consisted of threespacecraft: the CCE; the IRM, which provided multiple ionreleases in the solar wind, the magnetosheath, and themagnetotail, with in situ diagnostics of each; and the UKS,which uses thrusters to keep station near the IRM to providetwo-point local measurements. The CCE (Charge CompositionExplorer) spacecraft was instrumented to detect those lithiumand barium tracer ions from the IRM releases that weretransported into the magnetosphere within the CCE orbit. Thespacecraft was spin-stabilized at 10 rpm, with its spin axis inthe equatorial plane, and offset from the earth-sun line byabout 20 deg. It could adjust attitude with both magnetictorquing and cold gas thrusters. The CCE used a 2.E8-bit taperecorder and redundant 2.5-W S-band transponders. Thespacecraft battery was charged by a 140-W solar array. The PIfor the U.S. AMPTE Program and for the CCE was S. M.Krimigis (now Richard McEntire of JHU/APL); each instrumentwas managed by a lead investigator. The CCE encounteredcommand module/power supply problems since the beginningof 1989, and failed as of 12 July 89. For more details, see J.Dassoulas et al., IEEE Transactions on Geoscience andRemote Sensing, Vol. GE-23, p. 182, 1985.

AMPTE/CCE

NSSDC ID: 1984-088A

Alternate Names

AMPTE/ChargeComposition Explorer

CCE

Charge CompositionExplorer

Explorer 65

15199

Facts in Brief

Launch Date: 1984-08-16Launch Vehicle: DeltaLaunch Site: CapeCanaveral, United StatesMass: 242.0 kgNominalPower: 140.0 W

Funding Agency

NASA-Office of SpaceScience Applications(United States)

Discipline

Space Physics


Launch/Orbitalinformation forAMPTE/CCE

PDMP information forAMPTE/CCE

Telecommunicationsinformation forAMPTE/CCE

Experiments onAMPTE/CCE

Data collections from


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





http://nssdc.gsfc.nasa.gov/nmc/spacecraftPdmp.do?id=1984-088A

http://nssdc.gsfc.nasa.gov/nmc/spacecraftPdmp.do?id=1984-088A

http://nssdc.gsfc.nasa.gov/nmc/spacecraftTelemetry.do?id=1984-088A



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

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

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



AMPTE/CCE

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

Personnel

Name Role Original Affiliation E-mail

Dr. Steven A.Curtis

Project Scientist NASA Goddard SpaceFlight Center

[email protected]

Dr. RichardW. McEntire

Mission PrincipalInvestigator

Applied PhysicsLaboratory

[email protected]

Mr. Gilbert W.Ousley, Sr.

Project Manager NASA Goddard SpaceFlight Center

Dr. Charles P.Holmes

ProgramScientist

NASA Headquarters [email protected]

Other AMPTE Data/Information at NSSDC

AMPTE CCEAMPTE IRMAMPTE UKS

Other Sources of AMPTE Data/Information

AMPTE Science Data CenterAMPTE/IRM Data Center


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

mailto:[email protected]?Subject=NMC Comment/Question: AMPTE/CCE (1984-088A)

mailto:[email protected]?Subject=NMC Comment/Question: AMPTE/CCE (1984-088A)

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

http://www-ssg.sr.unh.edu/index.html?tof/Missions/Ampte-irm/amptemain.html

http://www.usa.gov/





http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1984-088B[24/11/2010 23:06:47]


Description

The AMPTE (Active Magnetospheric Particle Tracer Explorers)mission was designed to study the access of solar-wind ions tothe magnetosphere, the convective-diffusive transport andenergization of magnetospheric particles, and the interactionsof plasmas in space.

The program consisted of three spacecraft: the CCE, whichmeasured in the magnetosphere the ions released by the IRM;the IRM; and the UKS, which used thrusters to keep stationnear the IRM to provide two-point local measurements. TheIRM provided multiple ion releases in the solar wind, themagnetosheath, and the magnetotail, with in situ diagnostics ofeach.

The IRM spacecraft was spin-stabilized at 15 rpm. Its spin axiswas initially in the ecliptic plane, but later it was adjusted withmagnetic torqueing to be at right angles to the ecliptic. Thepower system was a 60 W solar array with redundantbatteries. There was a redundant S-band telemetry andtelecommand system. Telemetry rates could be chosenbetween 1 and 8 kbps. For injection into the final orbit, the IRMcarried its own kick stage. In addition to the ion releases, theinstruments on board the spacecraft monitored the ambient,magnetosphere, but with the data acquisition confined to thepasses that could be tracked in real time from Germany.

The spacecraft became inoperational as of 14 August 86. ThePI for the German AMPTE Program was G. Haerendel. Therelease experiment and the diagnostic instruments were eachprovided by a lead investigator (LI). For more details, see B.Hausler et al., IEEE Transactions on Geoscience and RemoteSensing, v. GE-23, p. 192, 1985.

AMPTE/IRM

NSSDC ID: 1984-088B

Alternate Names

IRM

AMPTE/Ion ReleaseModule

Ion Release Module

15200

Facts in Brief

Launch Date: 1984-08-16Launch Vehicle: Delta3924Launch Site: CapeCanaveral, United StatesMass: 705.0 kgNominal Power: 60.0 W

Funding Agency

Bundesministerium fuerForschung undTecnnologie (FederalRepublic of Germany)

Discipline

Space Physics


Launch/Orbitalinformation forAMPTE/IRM

PDMP information forAMPTE/IRM

Telecommunicationsinformation forAMPTE/IRM

Experiments onAMPTE/IRM

Data collections fromAMPTE/IRM


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1984-088B



http://nssdc.gsfc.nasa.gov/nmc/spacecraftPdmp.do?id=1984-088B


http://nssdc.gsfc.nasa.gov/nmc/spacecraftTelemetry.do?id=1984-088B



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

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

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

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




Personnel


Dr. M.Otterbein

ProgramManager

Bundesministerium fuer Forschungund Technologie

Mr. V.Joneleit

ProjectManager

Deutsche Forschungs-undVersuchsenstalt fuer Luft-undRaumfahrt

Dr. GerhardHaerendel

MissionPrincipalInvestigator

Max-Planck-Institut furExtraterrestrische Physik

[email protected]

Dr. BerndHausler

ProjectManager


[email protected]

Dr. GoetzPaschmann

ProjectScientist


[email protected]






mailto:[email protected]?Subject=NMC Comment/Question: AMPTE/IRM (1984-088B)

mailto:[email protected]?Subject=NMC Comment/Question: AMPTE/IRM (1984-088B)



http://www.usa.gov/







Description

The AMPTE (Active Magnetospheric Particle Tracer Explorers)mission was designed to study the access of solar-wind ions tothe magnetosphere, the convective-diffusive transport andenergization of magnetospheric particles, and the interactionsof plasmas in space. The program consisted of threespacecraft: the CCE, which measured in the magnetospherethe ions released by the IRM; the IRM, which provided multipleion releases in the solar wind, the magnetosheath, and themagnetotail, with in situ diagnostics of each; and the UKS. TheUKS was one spacecraft of the AMPTE (ActiveMagnetosphere Particle Tracer Experiment) program (alongwith CCE and IRM) and served as a subsatellite of the IRMspacecraft. Its purpose was to help distinguish between spatialstructure and temporal changes in the plasma phenomenainitiated by ion releases from the IRM and in the naturalmagnetospheric environment. Measured quantitie were similarto those of the IRM and include magnetic fields, positive ions,electrons, plasma waves, and modulations in ions andelectrons. The spacecraft was spin-stabilized at 12 rpm andemployed S-band communications. It carried a cold gaspropulsion system and a VHF radar system for station keepingwith the IRM normally at a distance of a few hundredkilometers. The lead investigator for the UKS spacecraft wasD. A. Bryant. The spacecraft power supply failed on January15, 1985. For more details, see A.K. Ward, et al., IEEETransaction on Geoscience and Remote Sensing, Vol. GE-23,p 202, 1985.

AMPTE/UKS

NSSDC ID: 1984-088C

Alternate Names

UKS

AMPTE/United KingdomSubsatellite

United KingdomSubsatellite

15201

Facts in Brief

Launch Date: 1984-08-16Launch Vehicle: DeltaLaunch Site: CapeCanaveral, United StatesMass: 77.0 kg

Funding Agency

Science and EngineeringResearch Council, UK(United Kingdom)

Discipline

Space Physics


Launch/Orbitalinformation forAMPTE/UKS

Experiments onAMPTE/UKS

Data collections fromAMPTE/UKS



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: AMPTE/UKS (1984-088C)

mailto:[email protected]?Subject=NMC Comment/Question: AMPTE/UKS (1984-088C)



Personnel


Dr. A. K. Ward ProjectManager

Rutherford AppletonLaboratory

Dr. Trefor Edwards ProjectEngineer


[email protected]

Dr. Duncan A.Bryant

ProjectScientist


[email protected]








http://www.usa.gov/







Description

Telesat-H (Anik D2) was a Canadian communications satellitedeployed by the STS 51-A shuttle mission.

Anik D2

NSSDC ID: 1984-113B

Alternate Names

TELESAT-H

15383

Facts in Brief

Launch Date: 1984-11-09LaunchVehicle: ShuttleLaunch Site: CapeCanaveral, United StatesMass: 1100.0 kg

Funding Agencies

National Aeronautics andSpace Administration(United States)

Telesat Canada Ltd.,Ottawa (Canada)

Discipline

Communications


Launch/Orbitalinformation for Anik D2

Experiments on Anik D2

Data collections from AnikD2



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=Anik D2

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Anik D2

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Anik D2

mailto:[email protected]?Subject=NMC Comment/Question: Anik D2 (1984-113B)



http://www.usa.gov/







Description

BS-2A (Broadcasting Satellite-2A) was launched by theNational Space Development Agency of Japan (NASDA) fromthe Tanegashima Space Center. It was designed to eliminatepoor television reception areas and develop the technologyconcerning broadcasting satellites. Transmitting frequenciesand output powers were 11.91928 GHz at 100 W, 11.99600GHz at 100 W, 11.70299 GHz and 0.1 W, and 2276.99 MHz at1.3 W.

BS-2A

NSSDC ID: 1984-005A

Alternate Names

Broadcasting Sat-2A

Yuri 2A

14659

Facts in Brief

Launch Date: 1984-01-23Launch Vehicle: N-2LaunchSite: Tanegashima, JapanMass: 670.0 kg

Funding Agency

National SpaceDevelopment Agency(NASDA) (Japan)

Discipline

Communications


Launch/Orbitalinformation for BS-2A

Experiments on BS-2A

Data collections from BS-2A



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: BS-2A (1984-005A)



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 1522

NSSDC ID: 1984-001A

Alternate Names

14611

Facts in Brief

Launch Date: 1984-01-05LaunchVehicle: CosmosLaunch Site: Plesetsk,U.S.S.RMass: 40.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Communications


Launch/Orbitalinformation for Cosmos1522

Experiments on Cosmos1522

Data collections fromCosmos 1522



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Cosmos 1522


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Cosmos 1522


mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 1522 (1984-001A)



http://www.usa.gov/







Description


Cosmos 1523

NSSDC ID: 1984-001B

Alternate Names

14612

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data










mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 1523 (1984-001B)



http://www.usa.gov/







Description


Cosmos 1524

NSSDC ID: 1984-001C

Alternate Names

14613

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data










mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 1524 (1984-001C)



http://www.usa.gov/





http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1984-001D[24/11/2010 23:15:35]


Description


Cosmos 1525

NSSDC ID: 1984-001D

Alternate Names

14614

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=1984-001D







mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 1525 (1984-001D)



http://www.usa.gov/





http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1984-001E[24/11/2010 23:16:33]


Description


Cosmos 1526

NSSDC ID: 1984-001E

Alternate Names

14615

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=1984-001E







mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 1526 (1984-001E)



http://www.usa.gov/





http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1984-001F[24/11/2010 23:17:47]


Description


Cosmos 1527

NSSDC ID: 1984-001F

Alternate Names

14616

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=1984-001F







mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 1527 (1984-001F)



http://www.usa.gov/





http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1984-001G[24/11/2010 23:18:57]


Description


Cosmos 1528

NSSDC ID: 1984-001G

Alternate Names

14617

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=1984-001G







mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 1528 (1984-001G)



http://www.usa.gov/





http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1984-001H[24/11/2010 23:19:41]


Description


Cosmos 1529

NSSDC ID: 1984-001H

Alternate Names

14618

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=1984-001H







mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 1529 (1984-001H)



http://www.usa.gov/







Description

Cosmos 1530 was a Soviet military satellite launched from thePlesetsk Cosmodrome aboard a Soyuz rocket. It was a photosurveillance satellite containing a film capsule.

Cosmos 1530

NSSDC ID: 1984-002A

Alternate Names

14622

Facts in Brief

Launch Date: 1984-01-11Launch Vehicle: SoyuzLaunch Site: Plesetsk,U.S.S.RMass: 6300.0 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 1531 was part of a 6-satellite Soviet militarynavigation system distributed in orbital planes spaced 30degrees apart, and launched from the Plesetsk cosmodromeaboard a Cosmos rocket. Navigation information was derivedfrom Doppler-shifted VHF transmissions (approximately 150and 400 MHz) of the satellite position and orbital data. Byacquiring fixes from several satellite, a user's location could becalculated with an accuracy of 100 m. The time needed toascertain a position was dependent upon the user's latitudeand the number of operational spacecraft in orbit. Normally,accurate location determination could be made within 1-2hours.

Cosmos 1531

NSSDC ID: 1984-003A

Alternate Names

14624

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 1532 was a Soviet photo surveillance satellitelaunched from the Baikonur cosmodrome aboard a Soyuzrocket. Two small film capsules were recovered in flight andthe main reentry capsule with remaining film, camera, andcomputer systems at end of flight.

Cosmos 1532

NSSDC ID: 1984-004A

Alternate Names

14634

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 1533 was a Soviet military satellite launched from theBaikonur Cosmodrome aboard a Soyuz rocket. It was a photosurveillance satellite containing a film capsule.

Cosmos 1533

NSSDC ID: 1984-006A

Alternate Names

14666

Facts in Brief

Launch Date: 1984-01-26Launch Vehicle: SoyuzLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 6300.0 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 1534 was a Soviet atmospheric research satellitelaunched from the Plesetsk cosmodrome aboard a Kosmos 11rocket. It was part of a series of Vektor spacecraft.

Cosmos 1534

NSSDC ID: 1984-007A

Alternate Names

14668

Facts in Brief

Launch Date: 1984-01-26LaunchVehicle: CosmosLaunch Site: Plesetsk,U.S.S.R

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 1535 was part of a 6-satellite Soviet militarynavigation system distributed in orbital planes spaced 30degrees apart, and launched from the Plesetsk cosmodromeaboard a Cosmos rocket. Navigation information was derivedfrom Doppler-shifted VHF transmissions (approximately 150and 400 MHz) of the satellite position and orbital data. Byacquiring fixes from several satellite, a user's location could becalculated with an accuracy of 100 m. The time needed toascertain a position was dependent upon the user's latitudeand the number of operational spacecraft in orbit. Normally,accurate location determination could be made within 1-2hours. It replaced Cosmos 1428.

Cosmos 1535

NSSDC ID: 1984-010A

Alternate Names

14679

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 1536 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 1536

NSSDC ID: 1984-013A

Alternate Names

14699

Facts in Brief

Launch Date: 1984-02-08LaunchVehicle: Tsiklon-3Launch Site: Plesetsk,U.S.S.RMass: 2200.0 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 1537 was a third generation, high resolution Sovietphoto surveillance satellite launched from the Plesetskcosmodrome aboard a Soyuz rocket. The spacecraft wasmaneuverable and also performed earth resources tasks.Investigation of the natural resources of the earth in theinterests of various branches of the national economy of theUSSR and international cooperation.

Cosmos 1537

NSSDC ID: 1984-017A

Alternate Names

14737

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 1538 replace Cosmos 1420.

Cosmos 1538

NSSDC ID: 1984-019A

Alternate Names

14759

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 1539

NSSDC ID: 1984-020A

Alternate Names

14763

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 1540 was a Soviet military second generation globalcommand and control system (GKKRS) satellite launched fromthe Baiknour cosmodrome aboard a Proton K rocket. Thesesatellites were integrated with the Luch geostationary systemand featured retransmission of high rate data retransmission inthe centimetre wavelength range. While Luch handledcommunications between spacecraft and ground stations,Potok handled communications between fixed points anddigital data from the Yantar-4KS1 electroptical reconnaissancesatellite. Potok was the first communications spacecraft built bythe Lavochkin design bureau and used the Splav-2transponder by NPO Elas.

Potok is said by one account to have utilized the KAUR-4spacecraft bus. This had an active 3-axis orientation system,with a single central body from which extended 40 squaremetres of solar panels. Its basic structure was that of theKAUR-3, but it was equipped with completely new systems: adigital computer, plasma station-keeping engines, hydrazinemonopropellant orientation engines, and actively-scannedantennae arrays with 0.5 degrees antenna and 0.1 degreespacecraft pointing accuracy. Cosmos 1540 was stationed at79 deg E.

Cosmos 1540

NSSDC ID: 1984-022A

Alternate Names

14783

Facts in Brief

Launch Date: 1984-03-02LaunchVehicle: Proton-KLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 2000.0 kg

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 1541 was a Soviet missile early warning satellitelaunched from the Plesetsk cosmodrome aboard a Molniyarocket. It replaced Cosmos 1278 as part of the Okoconstellation of satellites and covered the plane 3 - 355 degreelongitude of ascending node.

Cosmos 1541

NSSDC ID: 1984-024A

Alternate Names

14790

Facts in Brief

Launch Date: 1984-03-06LaunchVehicle: Molniya-MLaunch Site: Plesetsk,U.S.S.RMass: 1250.0 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 1542 was a Soviet military satellite launched from theBaikonur Cosmodrome aboard a Soyuz rocket. It was a photosurveillance satellite containing a film capsule.

Cosmos 1542

NSSDC ID: 1984-025A

Alternate Names

14793

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 1543

NSSDC ID: 1984-026A

Alternate Names

14797

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 1544 was a Soviet ELINT (Electronic and SignalsIntelligence) satellite launched from the Plesetsk cosmodrome.



Cosmos 1544

NSSDC ID: 1984-027A

Alternate Names

14819

Facts in Brief

Launch Date: 1984-03-15LaunchVehicle: Tsiklon-3Launch Site: Plesetsk,U.S.S.R

Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data













http://www.usa.gov/







Description


Cosmos 1545

NSSDC ID: 1984-030A

Alternate Names

14849

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 1546 was part of a Soviet constellation of satellitescomprised of the first echelon of the Missile Attack WarningSystem (SPRN), which was operated by the Air DefenseForces of the Ministry of Defense. According to Soviet officials,the early warning satellites could detect missile launches within20 seconds of lift-off.

Each satellite possessed a perigee of about 600 km, anapogee of nearly 40,000 km, and an inclination of 63 degrees.This orbit was superfically similar to that employed by theMolniya communications satellites but was distinguished byinitial argument of perigee 316-319 degrees, including to theMolniya 280-288 degree arguments of perigee. The seeminglyminor difference significantly affected the shape of thesatellite's groundtrack in the Northern Hemisphere.

Russian early warning spacecraft were more affected bygravitational perturbations due to their higher argument ofperigee and, therefore, performed periodic station-keepingmaneuvers to maintain an acceptable groundtrack. In addition,the argument of perigee migrated slightly over time (due toinclination variations), causing an alteration in the shape of thegroundtrack. Instead of expending additional propellant toprevent the argument of perigee shift, Russian spacecraftcontrollers altered the satellite's ascending node. This had theeffect of "stabilizing" the apogee point about which surveillanceoperations were performed.

Cosmos 1546

NSSDC ID: 1984-031A

Alternate Names

14867

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 1547 was a Soviet missile early warning satellitelaunched from the Plesetsk cosmodrome aboard a Molniyarocket. It replaced Cosmos 1382 in the Oko constellation ofsatellites and covered the plane 7 - 154 degree longitude planeof ascending node.

Cosmos 1547

NSSDC ID: 1984-033A

Alternate Names

14884

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 1548

NSSDC ID: 1984-036A

Alternate Names

14902

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 1549

NSSDC ID: 1984-040A

Alternate Names

14938

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 1550

NSSDC ID: 1984-043A

Alternate Names

14965

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 1551

NSSDC ID: 1984-044A

Alternate Names

14967

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 1553 was a Soviet digital photo surveillance satellitelaunched from the Baikonur cosmodrome aboard a Soyuz 11rocket.

Cosmos 1552

NSSDC ID: 1984-045A

Alternate Names

14971

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 1553

NSSDC ID: 1984-046A

Alternate Names

14973

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 1554 was a Soviet navigation satellite launched fromthe Baikonur cosmodrome aboard a Proton rocket. It was atest flight of the Glonass system, to test the components andequipment of the space navigation system established in orderto locate the Soviet Union's civil aircraft and its merchant andfishing vessels. Three satellites were launched by a singlecarrier rocket. Glonass was the equivalent of the US GPS(Global Positioning System).

Cosmos 1554

NSSDC ID: 1984-047A

Alternate Names

14977

Facts in Brief

Launch Date: 1984-05-19Launch Vehicle: ProtonLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 700.0 kgNominalPower: 1600.0 W

Funding Agency

Scientific ProductionAssociation(Russia)(U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


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
















Description

Cosmos 1555 was a Soviet navigation satellite launched fromthe Baikonur cosmodrome aboard a Proton rocket. It was atest flight of the Glonass system, flown to test the componentsand equipment of the space navigation system established inorder to locate the Soviet Union's civil aircraft and its merchantand fishing vessels. Three satellites were launched by a singlecarrier rocket. Glonass was the equivalent of the US GPS(Global Positioning System).

Cosmos 1555

NSSDC ID: 1984-047B

Alternate Names

14978

Facts in Brief


Funding Agency


Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


















Description

Cosmos 1556 was a Soviet navigation satellites launched fromthe Baikonor cosmodrome aboard a Proton rocket. It was atest flight of the Glonass syste, flown to test the componentsand equipment of the space navigation system established inorder to locate the Soviet Union's civil aircraft and its merchantand fishing vessels. Three satellite were launched by a singlecarrier rocket. Glonass was the equivalent of the US GPS(Global Positioning System).

Cosmos 1556

NSSDC ID: 1984-047C

Alternate Names

14979

Facts in Brief


Funding Agency


Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


















Description


Cosmos 1557

NSSDC ID: 1984-048A

Alternate Names

14982

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 1558

NSSDC ID: 1984-050A

Alternate Names

14993

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 1559

NSSDC ID: 1984-052A

Alternate Names

14998

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 1560

NSSDC ID: 1984-052B

Alternate Names

14999

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 1561

NSSDC ID: 1984-052C

Alternate Names

15000

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 1562

NSSDC ID: 1984-052D

Alternate Names

15001

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 1563

NSSDC ID: 1984-052E

Alternate Names

15002

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 1564

NSSDC ID: 1984-052F

Alternate Names

15003

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=1984-052G[25/11/2010 0:08:41]


Description


Cosmos 1565

NSSDC ID: 1984-052G

Alternate Names

15004

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=1984-052H[25/11/2010 0:09:08]


Description


Cosmos 1566

NSSDC ID: 1984-052H

Alternate Names

15005

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 1567 was a Soviet naval reconnaisance satellitelaunched from the Baikonur cosmodrome aboard a Tsyklon 2rocket. This naval forces monitoring spacecraft was used todetermine the position of enemy naval forces through detectionand triangulation of their electromagnetic emissions (radio,radar, etc).

Cosmos 1567

NSSDC ID: 1984-053A

Alternate Names

15009

Facts in Brief

Launch Date: 1984-05-30LaunchVehicle: Tsiklon-2Launch 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 1568

NSSDC ID: 1984-054A

Alternate Names

15011

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 1569

NSSDC ID: 1984-055A

Alternate Names

15027

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 1570 replaced Cosmos 1452.

Cosmos 1570

NSSDC ID: 1984-056A

Alternate Names

15031

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 1571 was a Soviet military cartographic photo-surveillance satellite launched from the Baikonur Cosmodromeaboard a Soyuz 11 rocket. It conducted an investigation of thenatural resources of the earth in the interests of variousbranches of the national economy of the USSR andinternational cooperation. Typical orbital profile: inclination 70degrees with altitude of 350-420 km. Designed duration: 15days. Transmission frequencies observed in West: 19.989FSK; 39.978 FSK; 232.0 PPM-AM.

Cosmos 1571

NSSDC ID: 1984-058A

Alternate Names

15039

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 1572

NSSDC ID: 1984-060A

Alternate Names

15046

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 1573

NSSDC ID: 1984-061A

Alternate Names

15051

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


From 1982 several Tsikada maritime navigation satellites wereequipped with the supplemental COSPAS / SARSATinternational space search and rescue system for locatingvessels and aircraft in distress search and rescue package.These were designated 'Nadezhda'. From 1995 these satelliteswere equipped with the Kurs system for better location of air,sea, and ground craft in distress and for transmittal of digitaldata to the Kurs Centre. These were designated Nadezhda-M.Signals at 150,00 MHz and 400.00 MHz. The spacecraftprovided dual use - location of vessels in the Soviet merchantmarine and fishing fleet; and work within the internationalspace search and rescue system for locating vessels andaircraft in distress (COSPAS-SARSAT).

Cosmos 1574

NSSDC ID: 1984-062A

Alternate Names

15055

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 1575

NSSDC ID: 1984-064A

Alternate Names

15060

Facts in Brief

Launch Date: 1984-06-22LaunchVehicle: Modified SS-6(Sapwood) with 2ndGeneration (Longer) UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 6300.0 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 1576

NSSDC ID: 1984-066A

Alternate Names

15070

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 1577

NSSDC ID: 1984-067A

Alternate Names

15077

Facts in Brief

Launch Date: 1984-06-27LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 810.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data













http://www.usa.gov/







Description

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

Cosmos 1578

NSSDC ID: 1984-068A

Alternate Names

15080

Facts in Brief

Launch Date: 1984-06-28LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: KapustinYar, U.S.S.RMass: 550.0 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 1579 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 1579

NSSDC ID: 1984-069A

Alternate Names

15085

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 1580 was a Soviet military cartographic photo-surveillance satellite launched from the Plesetsk Cosmodromeaboard a Soyuz 11 rocket. It conducted an investigation of thenatural resources of the earth in the interests of variousbranches of the national economy of the USSR andinternational cooperation. Typical orbital profile: inclination 70degrees with altitude of 350-420 km. Designed duration: 15days. Transmission frequencies observed in West: 19.989FSK; 39.978 FSK; 232.0 PPM-AM.

Cosmos 1580

NSSDC ID: 1984-070A

Alternate Names

15090

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 1581 was a Soviet missile early warning satellitelaunched from the Plesetsk cosmodrome aboard a Molniyarocket. It replaced Cosmos 1317 in the Oko constellation ofsatellites and covered the plane 8 - 194 degree longitude ofascending node.

Cosmos 1581

NSSDC ID: 1984-071A

Alternate Names

15095

Facts in Brief

Launch Date: 1984-07-03LaunchVehicle: Modified SS-6(Sapwood) with 2ndGeneration Upper Stage +Escape StageLaunch Site: Plesetsk,U.S.S.RMass: 1250.0 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 1582

NSSDC ID: 1984-074A

Alternate Names

15121

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 1583

NSSDC ID: 1984-075A

Alternate Names

15123

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 1584

NSSDC ID: 1984-076A

Alternate Names

15131

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Disciplines

Earth Science








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


















Description


Cosmos 1585

NSSDC ID: 1984-077A

Alternate Names

15142

Facts in Brief

Launch Date: 1984-07-31LaunchVehicle: Modified SS-6(Sapwood) with 2ndGeneration (Longer) UpperStageLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 6700.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


















Description

Cosmos 1586 was a Soviet missile early warning satellitelaunched from the Plesetsk cosmodrome aboard a Molniyarocket. It replace Cosmos 1456 as part of the Oko constellationof satellites and covered the plane 4 - 35 degree longitude ofascending node.

Cosmos 1586

NSSDC ID: 1984-079A

Alternate Names

15147

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 1587

NSSDC ID: 1984-082A

Alternate Names

15163

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 1588 was a Soviet naval reconnaisance satellitelaunched from the Baikonur cosmodrome aboard a Tsyklon 2rocket. This naval forces monitoring spacecraft was used todetermine the position of enemy naval forces through detectionand triangulation of their electromagnetic emissions (radio,radar, etc).

Cosmos 1588

NSSDC ID: 1984-083A

Alternate Names

15167

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 1589 was a Soviet geodetic satellite launched fromthe Plesetsk cosmodrome aboard a Tsyklon 3 rocket. Itprovided five ways for determining satellite position:

1. Doppler system working at 150 and 400 MHz and providing3 cm accuracy 2. High intensity lights flashing 3 times persecond, allowing precise location by ground observatories 3.Radio transponder working at 5.7/3.4 GHz and providing 5 maccuracy 4. Laser reflector providing 1.5 m accuracy 5. Radarreflector working at 9.4 GHz providing 5 m altitude accuracy.

Cosmos 1589

NSSDC ID: 1984-084A

Alternate Names

15171

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 1590

NSSDC ID: 1984-087A

Alternate Names

15197

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 1591

NSSDC ID: 1984-092A

Alternate Names

15232

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/






Version 4.0.14, 08 October 2010




Description


Cosmos 1592

NSSDC ID: 1984-094A

Alternate Names

15257

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 1593 was a Soviet navigation satellite launched fromthe Baikonur cosmodrome aboard a Proton rocket. It was atest flight of the Glonass system, to test the components andequipment of the space navigation system established in orderto locate the Soviet Union's civil aircraft and its merchant andfishing vessels. Three satellites were launched by a singlecarrier rocket. Glonass was the equivalent of the US GPS(Global Positioning System).

Cosmos 1593

NSSDC ID: 1984-095A

Alternate Names

15259

Facts in Brief

Launch Date: 1984-09-04Launch Vehicle: ProtonBooster Plus Upper Stageand Escape StagesLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 700.0 kgNominalPower: 1600.0 W

Funding Agency


Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data















Description

Cosmos 1594 was a Soviet navigation satellite launched fromthe Baikonur cosmodrome aboard a Proton rocket. It was atest flight of the Glonass system, flown to test the componentsand equipment of the space navigation system established inorder to locate the Soviet Union's civil aircraft and its merchantand fishing vessels. Three satellites were launched by a singlecarrier rocket. Glonass was the equivalent of the US GPS(Global Positioning System).

Cosmos 1594

NSSDC ID: 1984-095B

Alternate Names

15260

Facts in Brief


Funding Agency


Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data















Description

Cosmos 1595 was a Soviet navigation satellites launched fromthe Baikonor cosmodrome aboard a Proton rocket. It was atest flight of the Glonass system, flown to test the componentsand equipment of the space navigation system established inorder to locate the Soviet Union's civil aircraft and its merchantand fishing vessels. Three satellite were launched by a singlecarrier rocket. Glonass was the equivalent of the US GPS(Global Positioning System).

Cosmos 1595

NSSDC ID: 1984-095C

Alternate Names

15261

Facts in Brief


Funding Agency


Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data















http://www.usa.gov/







Description


Cosmos 1596

NSSDC ID: 1984-096A

Alternate Names

15267

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 1597

NSSDC ID: 1984-099A

Alternate Names

15287

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 1598

NSSDC ID: 1984-100A

Alternate Names

15292

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 1599

NSSDC ID: 1984-102A

Alternate Names

15318

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 1600 was a Soviet military cartographic photo-surveillance satellite launched from the Baikonur Cosmodromeaboard a Soyuz 11 rocket. It conducted an investigation of thenatural resources of the earth in the interests of variousbranches of the national economy of the USSR andinternational cooperation. Typical orbital profile: inclination 70degrees with altitude of 350-420 km. Designed duration: 15days. Transmission frequencies observed in West: 19.989FSK; 39.978 FSK; 232.0 PPM-AM.

Cosmos 1600

NSSDC ID: 1984-103A

Alternate Names

15324

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


















Description

From 1969 KB Yuzhnoye built the Lira targets for exercise andtest of PVO air defence and space tracking systems. Thesecond generation consisted of Taifun-1 and Taifun-2satellites, which differed in the type of equipment installed.Taifun-1 would release up to 25 Romb sub-satellites, whileTaifun-2 did not. In 1972 KB-3 under B E Khimrov, with the co-operation of assisting organisations and the Ministry ofDefence, completed the draft project. The first Taifun-1 wascompleted in 1974, and flight trials were conducted in thesecond half of the 1970's using Kosmos-3M launch vehiclesfrom Plesetsk and Kapustin Yar. The heads of the State TrialsCommission were B N Karpov, N N Zhukov, and B G Zudin.Taifun-1 normally released 25 Romb subsatellites into an orbitof 300 to 500 km altitude, at inclinations of 50.7 degrees (fromKapustin Yar) and 65.9 74, or 82.9 degrees (from Plesetsk).Two unique missions in 1989-1990 were put into 180 km x1550 km orbits at 65.8 degrees. With this higher apogee thepayload was reduced to 10 Romb subsatellites. Vektorsatellites were spherical in shape, about 2 m in diameter, thesurface covered with solar cells and equipped with fourantennae.

Cosmos 1601

NSSDC ID: 1984-104A

Alternate Names

15326

Facts in Brief

Launch Date: 1984-09-27LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.R

Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data













http://www.usa.gov/







Description

Cosmos 1602 was a Soviet test satellite launched from thePlesetsk cosmodrome aboard a Tsyklon rocket. It gatheredoperational information and continued trials of new kinds ofinformation and measurement apparatus and methods ofremote investigation of the seas and oceans and the earth'ssurface in the interests of science and of various branches ofthe national economy of the USSR.

Cosmos 1602

NSSDC ID: 1984-105A

Alternate Names

15331

Facts in Brief

Launch Date: 1984-09-28Launch Vehicle: F-2Launch Site: Plesetsk,U.S.S.RMass: 1950.0 kg

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 1603 was a Soviet ELINT (Electronic and SignalsIntelligence) satellite launched from the Baikonur cosmodromeaboard a Proton rocket.

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

Cosmos 1603

NSSDC ID: 1984-106A

Alternate Names

15333

Facts in Brief

Launch Date: 1984-09-28Launch Vehicle: ProtonBooster Plus Upper Stageand Escape StagesLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 6000.0 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 1604

NSSDC ID: 1984-107A

Alternate Names

15350

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 1605

NSSDC ID: 1984-109A

Alternate Names

15359

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 1606 was a Soviet ELINT (Electronic and SignalsIntelligence) satellite launched from the Plesetsk cosmodrome.It replaced Cosmos 1455.



Cosmos 1606

NSSDC ID: 1984-111A

Alternate Names

15369

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 1607 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 1607

NSSDC ID: 1984-112A

Alternate Names

15378

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 1608 was a variation of the Yantar-class spacecraftused to conduct high-precision topographic surveys. Thesespacecraft, now referred to as Kometa, typically remained inorbit for 44-45 days and were distinguished by their relativelycircular orbits between 210 and 280 km. These missions werealways launched from the Baikonur cosmodrome intoinclinations of 65 degrees or 70 degrees at the rate of one ortwo per ye

Cosmos 1608

NSSDC ID: 1984-116A

Alternate Names

15393

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


















Description


Cosmos 1609

NSSDC ID: 1984-117A

Alternate Names

15395

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 1610

NSSDC ID: 1984-118A

Alternate Names

15398

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 1611

NSSDC ID: 1984-119A

Alternate Names

15403

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


















Description

Cosmos 1612 was a Soviet meteorological satelllite launchedfrom the Plesetsk cosmdrome aboard a Tsyklon 3 rocket. Itwas the first launch of new Meteor-3 spacecraft. It was placedin an unusable orbit when the rocket's third stage failed toreignite.

Cosmos 1612

NSSDC ID: 1984-120A

Alternate Names

15406

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 1613

NSSDC ID: 1984-121A

Alternate Names

15414

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 1614 was a Soviet subscale spiral spaceplanelaunched from Kapustin Yar. It was the last flight of thesubscale Spiral spaceplane, recovered December 19, 19845:26 GMT, in the Black sea after one orbit of the Earth.

This spacecraft was used to investigate the hypersonicaerodynamic characteristics and heat shield materials of themanned Spiral OS lifting body, 1:3 and 1:2 scale models of theOS were to be built. Unlike the full-scale model, these werehad fixed wings and were designated BOR (unpiloted orbitalrocketplane). BOR-1, -2, and -3 were increasinglysophisticated models of the configuration, flown on suborbitaltrajectories. After the cancellation of Spiral in favour of theBuran, BOR-4 subscale spaceplanes were used to test heatshield materials developed for Buran. Certain essential tests ofthese heat shield materials could not be done in the lab. Theseincluded interaction with the plasma sheath during re-entry,chemical disassociation effects, etc. The BOR-4 was clad in118 tiles of the type developed for Buran as well as carbon-carbon nose cap and leading edge. These BOR-4 unmannedorbiters were equipped with braking engines. After a circuit ofthe earth, the spacecraft would deorbit, perform a gliding re-entry, followed by parachute deployment, splashdown in theocean, and recovery by Soviet naval forces. BOR-4 flew foursuccessful test flights at speeds of from Mach 3 to 25 andaltitudes of 30 to 100 km. These test flights confirmed thephysical, chemical, and catalytic processes that operated onthe selected heat shield materials in the re-entry plasma. BOR-4 also provided important data on the acoustic environmentduring launch and re-entry. Compared to the Spiral MiG 105-11 EPOS configuration, the BOR-4 had a flattened, wider bodywith a much smaller vertical stabilizer.

Cosmos 1614

NSSDC ID: 1984-126A

Alternate Names

15442

Facts in Brief

Launch Date: 1984-12-19LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: KapustinYar, U.S.S.RMass: 1000.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Engineering







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data













http://www.usa.gov/







Description

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

Cosmos 1615

NSSDC ID: 1984-127A

Alternate Names

15446

Facts in Brief

Launch Date: 1984-12-20LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.R

Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data













http://www.usa.gov/







Description

DSP F11 was part of the oldest segments of North America'searly warning system. These Defense Support Systemsatellites were the space-based segment of a 2-tiered ballisticmissile launch detection and warning system. Orbiting 23,000mile above Earth, these satellites provided the first look atpotentially hostile ballistic missiles launched from land or sea,anywhere in the world, in near-real time. For tactical missilewarning, satellite data could be transmitted directly to thetheater commander via the Tactical Event System. DSPsensors also detected nuclear detonations. The speed andaccuracy have greatly reduced the potential for surprise attackand is vital to effective deterrance to war. The DSP sytem hasone satellite watching the eastern hemisphere and twospacecraft watching the western hemisphere for missilelaunches. Since there was less time associated with asubmarine launch from a Soviet boat at the US mainland,these was a great concern that this type of missile must bedetected.

The satellite's infrared sensors detected and tracked exhaustheat generated by balistic missiles. The data were thenrelayed almost instantaneously to USSPACECOM MissileWarning Center in the Cheyenne Mountain Complex. DSPsatellites were used during the Persian Gulf War to detect IragiScud missile launches.

DSP F11

NSSDC ID: 1984-037A

Alternate Names

14930

Facts in Brief


Funding Agency

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

Disciplines


Space Physics


Launch/Orbitalinformation for DSP F11

Experiments on DSP F11

Data collections from DSPF11

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

Personnel



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


DSP F11



http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=DSP F11

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=DSP F11

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=DSP F11

mailto:[email protected]?Subject=NMC Comment/Question: DSP F11 (1984-037A)

mailto:[email protected]?Subject=NMC Comment/Question: DSP F11 (1984-037A)

http://nssdc.gsfc.nasa.gov/image/spacecraft/dsp_f11.jpg



Dr. W. Doyle Evans Project Scientist Los Alamos National Laboratory

Project Manager US Air Force Space Division

Image courtesy of the USAF Defense Support Program.


http://www.usa.gov/







Description

Ekran 12 was a Soviet communications satellite launched fromthe Baikonur Cosmodrome aboard a Proton 8K82K/Block DMrocket. It transmitted color and black-and-white USSR centraltelevision programs to the network of public receiving unitslocated in population centers in Siberia and the Far North. Thesingle-unit body was equipped with solar panels, and activeliquid-gas phase-change thermoregulation system, and acorrective engine unit for making orbital adjustments. Twenty-five square metres of solar panels provided 1280 W of power.

Ekran 12

NSSDC ID: 1984-028A

Alternate Names

14821

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications


Launch/Orbitalinformation for Ekran 12

Experiments on Ekran 12

Data collections fromEkran 12



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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


mailto:[email protected]?Subject=NMC Comment/Question: Ekran 12 (1984-028A)



http://www.usa.gov/







Description

Ekran 13 was a Soviet communications satellite launched fromthe Baikonur Cosmodrome aboard a Proton 8K82K/Block DMrocket. It transmitted color and black-and-white USSR centraltelevision programs to the network of public receiving unitslocated in population centers in Siberia and the Far North. Thesingle-unit body was equipped with solar panels, and activeliquid-gas phase-change thermoregulation system, and acorrective engine unit for making orbital adjustments. Twenty-five square metres of solar panels provided 1280 W of power.

Ekran 13

NSSDC ID: 1984-090A

Alternate Names

15219

Facts in Brief

Launch Date: 1984-08-24Launch Vehicle: ProtonBooster Plus Upper Stageand Escape StagesLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 1970.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Communications


Launch/Orbitalinformation for Ekran 13

Experiments on Ekran 13

Data collections fromEkran 13



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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






http://www.usa.gov/







Description

The Earth Radiation Budget Satellite (ERBS) was designed tobe a 2-year mission to gather required radiation budget data,aerosol data, and ozone data to assess climate change andozone depletion. The two experiments conducted were theEarth Radiation Budget Experiment (ERBE) and theStratospheric Aerosol and Gas Experiment II (SAGE II). TheERBS spacecraft structure was composed of three basicmodules: the keel module, the base module, and theinstrument module. The keel module was a torque-boxstructure providing structural support for the propulsion system,the solar array panels, and the antennas. The base modulewas a torque-box structure that provided a direct interface tothe Shuttle. The ERBE-nonscanning instrument andelectronics was attached to the base module. The instrumentmodule was mounted directly to the base module and housedthe ERBE-scanner and the SAGE II instrument. Other ERBSsubsystems included the Thermal Control Subsystem (TCS) forregulating heat dissipitation; the Electrical Power Subsystem(EPS) which consisted of two 50-amp-hour, 22-cell nickelcadmium batteries; the Power Unit (PCU) for regulatingelectrical power; the Command and Data Handling Subsystem(C&DH) for collection of instrument and spacecraft data forreal-time transmission; the Communications Subsystem (CS),which included NASA TDRSS transponders and antennas; theAttitude Control and Determination Subsystem (AC&DS), athree-axis, momentum system for attitude pointing,maneuvers, and thruster control; and the Orbit AdjustPropulsion System (OAPS), a nonpropellent hydrazinepropulsion system used for raising the ERBS to its operatingorbit after launch from the Shuttle. The ERBS was heldprimarily in the Earth-pointing mode for most of the mission.

ERBS

NSSDC ID: 1984-108B

Alternate Names

Earth Rad Budget Sat

15354

Facts in Brief

Launch Date: 1984-10-05LaunchVehicle: ShuttleLaunch Site: CapeCanaveral, United StatesMass: 2449.0 kgNominalPower: 470.0 W

Funding Agency


Disciplines

Earth Science

Solar Physics


Launch/Orbitalinformation for ERBS

PDMP information forERBS

Telecommunicationsinformation for ERBS

Experiments on ERBS

Data collections fromERBS

Questions or commentsabout this spacecraft canbe directed to: Coordinated


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data








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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: ERBS (1984-108B)



Request and User SupportOffice.

Personnel


Dr. Michael D.King

ProjectScientist

NASA Goddard SpaceFlight Center

[email protected]

Mr. Dick S.Diller

ProgramManager

NASA Headquarters

Mr. Carl L.Wagner, Jr.

ProjectManager


Dr. Robert A.Schiffer

ProgramScientist

NASA Headquarters

Selected References

Earth radiation budget experiment program, NASA-GSFC, NSSDC, Greenbelt, MD, 1984.




http://www.usa.gov/







Description

The EUTELSAT I series of satellites was developed by theEuropean Space Agency (ESA) as part of the EuropeanCommunications Satellite (ECS) program. Once launched andchecked out in a geostationary orbit over Europe, each satellitewas handed to EUTELSAT for commercial operations. FourEUTELSAT I satellites were successfully launched between1983-1988. They served both public and private traffic,including telephone services, fax, data, land mobile service,and television and radio programming. Each had a design lifeof 7 years and a bandwidth of 72 MHz.

EUTELSAT 2

NSSDC ID: 1984-081A

Alternate Names

ECS 2

15158

Facts in Brief

Launch Date: 1984-08-04Launch Vehicle: Ariane3Launch Site: Kourou,French GuianaMass: 700.0 kg

Funding Agency

EuropeanTelecommunicationsSatellite Consortium(International)

Discipline

Communications


Launch/Orbitalinformation forEUTELSAT 2

Experiments onEUTELSAT 2

Data collections fromEUTELSAT 2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: EUTELSAT 2 (1984-081A)



http://www.usa.gov/







Description

Galaxy-C was a Hughes Corporation communications satellitelaunched by NASA with a Delta rocket.

Galaxy-C

NSSDC ID: 1984-101A

Alternate Names

15308

Facts in Brief


Funding Agency

Pan American Satellite(United States)

Discipline

Communications


Launch/Orbitalinformation for Galaxy-C

Experiments on Galaxy-C

Data collections fromGalaxy-C



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Galaxy-C (1984-101A)



http://www.usa.gov/







Description

The Geostationary Meteorological Satellites (GMS) wereJapan's contribution to the international Global AtmosphericResearch Program (GARP). The spacecraft was roughlycylindrical with a height of 345 cm and a diameter of 216 cm.The cylindrical surface was covered with solar cells whichprovide 263 W. The satellite was spin-stabilized with a despunearth-pointing antenna. The satellite was positioned near 140deg E and was designed to operate for 5 years. This was afollow-on GMS type spacecraft launched and controlled byNASDA of Japan.

GMS 3

NSSDC ID: 1984-080A

Alternate Names

Himawari 3

15152

Facts in Brief

Launch Date: 1984-08-02Launch Vehicle: N-2LaunchSite: Tanegashima, JapanMass: 681.0 kg

Funding Agency

National SpaceDevelopment Agency(NASDA) (Japan)

Disciplines

Earth Science

Space Physics


Launch/Orbitalinformation for GMS 3

Experiments on GMS 3

Data collections from GMS3


Personnel



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: GMS 3 (1984-080A)





Project Scientist Japanese Meteorological Agency

Dr. Y.Ichikawa

Project Manager National Space Development Agency of Japan


http://www.usa.gov/







Description

Gorizont 9 was a Soviet geosynchronous communicationssatellite. It was launched to provide telephone, telegraph andfax communications services, in addition to relaying TV andradio broadcasts. It was stationed at 53 deg E.

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

A typical Gorizont communications payload included sixgeneral purpose (TV, audio, facsimile) 6/4 GHz transponders(five 12.5 W and one 60 W), one Luch 14/11 GHz transponder(15 W), and one Volna 1.6/1.5 GHz transponder (20 W). TheVolna transponders were INMARSAT-compatible and wereextensively used by the Russian merchant marine fleet via theprimary GEO television rebroadcasting system, supporting allfive Federation time zones: Zone 1 from 140 deg E, Zone 2from 90 deg E, Zone 3 from 80 deg E, Zone 4 from 53 deg E,and Zone 5 from 14 deg W. These transmissions were handledby Orbita (12-m receiving antenna) and Moskva (2.5-mreceiving antenna) ground stations in the 6/4 GHz band. TheMoskva Globalnaya system was inaugurated in 1989 using 4-m receiving antennas and serviced by Gorizonts at 96.5 deg Eand 11 deg W.

Gorizont 9

NSSDC ID: 1984-041A

Alternate Names

14940

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications


Launch/Orbitalinformation for Gorizont 9

Experiments on Gorizont 9

Data collections fromGorizont 9



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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


mailto:[email protected]?Subject=NMC Comment/Question: Gorizont 9 (1984-041A)



http://www.usa.gov/







Description

Gorizont 10 was a Soviet geosynchronous communicationssatellite. It was launched to provide telephone, telegraph andfax communications services, in addition to relaying TV andradio broadcasts. It was stationed at 80 deg E.

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

A typical Gorizont communications payload included sixgeneral purpose (TV, audio, facsimile) 6/4 GHz transponders(five 12.5 W and one 60 W), one Luch 14/11 GHz transponder(15 W), and one Volna 1.6/1.5 GHz transponder (20 W). TheVolna transponders were INMARSAT-compatible and wereextensively used by the Russian merchant marine fleet via theprimary GEO television rebroadcasting system, supporting allfive Federation time zones: Zone 1 from 140 deg E, Zone 2from 90 deg E, Zone 3 from 80 deg E, Zone 4 from 53 deg E,and Zone 5 from 14 deg W. These transmissions were handledby Orbita (12-m receiving antenna) and Moskva (2.5-mreceiving antenna) ground stations in the 6/4 GHz band. TheMoskva Globalnaya system was inaugurated in 1989 using 4-m receiving antennas and serviced by Gorizonts at 96.5 deg Eand 11 deg W.

Gorizont 10

NSSDC ID: 1984-078A

Alternate Names

15144

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications


Launch/Orbitalinformation for Gorizont10

Experiments on Gorizont10

Data collections fromGorizont 10



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data













http://www.usa.gov/







Description

INTELSAT 5 F-8

NSSDC ID: 1984-023A

Alternate Names

14786

Facts in Brief

Launch Date: 1984-03-05Launch Vehicle: ArianeLaunch Site: Kourou,French GuianaMass: 1928.0 kg

Funding Agency

InternationalTelecommunicationsSatellite Corporation(International)

Discipline

Communications


Launch/Orbitalinformation for INTELSAT5 F-8

Experiments on INTELSAT5 F-8

Data collections fromINTELSAT 5 F-8



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=INTELSAT 5 F-8


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=INTELSAT 5 F-8


mailto:[email protected]?Subject=NMC Comment/Question: INTELSAT 5 F-8 (1984-023A)



http://www.usa.gov/







Description

Intelsat 5G F-9 was a COMSAT Corporation commercialcommunications satellite. It was part of an advanced series ofspacecraft used to provide increased telecommunicationscapacity for Intelsat's global network. It carried a MaritimeCommunications Services (MCS) package for INMARSAT,however, the launch vehicle failed to place the satellite into auseful orbit.

INTELSAT 5 F-9

NSSDC ID: 1984-057A

Alternate Names

15034

Facts in Brief

Launch Date: 1984-06-09Launch Vehicle: AtlasLaunch Site: CapeCanaveral, United StatesMass: 1091.0 kg

Funding Agency

InternationalTelecommunicationsSatellite Corporation(United States)

Discipline

Communications


Launch/Orbitalinformation for INTELSAT5 F-9

Experiments on INTELSAT5 F-9

Data collections fromINTELSAT 5 F-9



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data













http://www.usa.gov/







Description

This was designed as an inflatable rendezvous target, to beejected in a canister from STS 41B, then inflated with nitrogen.However, the mechanism to open the canister was notactivated, because the lanyards pulled loose from the orbiterinstead of pulling out of the canister. The nitrogen inflationcartridge did fire as scheduled, and the balloon burst as itbegan to inflate inside its canister. The remaining pieces of theballoon provided enough of a target for three rendezvousinstruments to provide data important in verifying theircapabilities.

IRT

NSSDC ID: 1984-011C

Alternate Names

14689

Facts in Brief


Funding Agency


Discipline

Engineering


Launch/Orbitalinformation for IRT

Experiments on IRT

Data collections from IRT



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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

mailto:[email protected]?Subject=NMC Comment/Question: IRT (1984-011C)



http://www.usa.gov/







Description

This US Navy Ocean Surveillance Satellite (NOSS) waslaunched from Vandenberg AFB aboard an Atlas E/F rocket. Itplaced a cluster of one primary satellite and three smaller sub-satellites (that trailed along at distances of several hundredkilometers) into low polar orbit. This satellite array determinedthe location of radio and radars transmitters, usingtriangulation, and the identity of naval units, by analysis of theoperating frequencies and transmission patterns.

In external appearance, the sub-satellites were reminiscent ofthe Navy's Transit navigational satellites. The had gravitygradient orientation booms 10-15 meters long. These ensuredthat the side of the satellite body where the signal antennaswere mounted was constantly oriented toward the Earth. Thesatellites maintained an assigned position in a group atdistances of 30 to 240 km one from the other by using on-board low-thrust engines. As a result of ground processing ofdirection-finding data on the signals from target emittersprovided by a group of satellites, and also sequentially byseveral groups of satellites, the coordinates, direction andspeed of travel were obtained.

JD1

NSSDC ID: 1984-012C

Alternate Names

14728

Facts in Brief

Launch Date: 1984-02-05Launch Vehicle: AtlasLaunchSite: Vandenberg AFB,United States

Funding Agency

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

Discipline



Launch/Orbitalinformation for JD1

Experiments on JD1

Data collections from JD1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=JD1

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=JD1

mailto:[email protected]?Subject=NMC Comment/Question: JD1 (1984-012C)



http://www.usa.gov/







Description



JD2

NSSDC ID: 1984-012D

Alternate Names

14729

Facts in Brief


Funding Agency


Discipline




Experiments on JD2




Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







mailto:[email protected]?Subject=NMC Comment/Question: JD2 (1984-012D)



http://www.usa.gov/







Description



JD3

NSSDC ID: 1984-012F

Alternate Names

14795

Facts in Brief


Funding Agency


Discipline




Experiments on JD3




Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







mailto:[email protected]?Subject=NMC Comment/Question: JD3 (1984-012F)



http://www.usa.gov/







Description

KH 11-6

NSSDC ID: 1984-122A

Alternate Names

USA 6

15423

Facts in Brief


Funding Agency


Discipline



Launch/Orbitalinformation for KH 11-6

Experiments on KH 11-6

Data collections from KH11-6



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=KH 11-6

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=KH 11-6


mailto:[email protected]?Subject=NMC Comment/Question: KH 11-6 (1984-122A)



http://www.usa.gov/







Description

This US Air Force photo surveillance satellite was launchedfrom Vandenberg AFB aboard a Titan rocket. It was the last inthe series of KH-8 (KeyHole-8) type spacecraft.

KH 8-54

NSSDC ID: 1984-039A

Alternate Names

14935

Facts in Brief

Launch Date: 1984-04-17Launch Vehicle: TitanIII-BLaunchSite: Vandenberg AFB,United StatesMass: 3000.0 kg

Funding Agency


Discipline



Launch/Orbitalinformation for KH 8-54

Experiments on KH 8-54

Data collections from KH 8-54



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=KH 8-54






http://www.usa.gov/







Description

The Landsat 5 system was an experimental earth resourcesmonitoring system with the new powerful remote-sensingcapabilities of the thematic mapper (TM), and it provides atransition for both foreign and domestic users from themultispectral scanner (MSS) data (which are also part of theinstrument package) to the higher resolution and data rate ofthe TM. It had a complete end-to-end highly automated datasystem, which was designed to be a new generation system,and was a major step forward in global remote-sensingapplications. The Landsat 5 mission consisted of an orbitingsatellite (space segment) with the necessary wideband datalinks and support systems, and a ground segment. TheLandsat 5 was an identical back-up for Landsat 4 (NSSDC ID82-072A). The Landsat 5 space segment consisted of twomajor systems: (1) the instrument module, containing theinstruments together with the mission unique subsystems,such as the solar array and drive, the TDRS antenna, the wide-band module (WBM), and the global positioning system (GPS),and (2) the multimission modular spacecraft (MMS) thatcontained the modularized and standardized power,propulsion, attitude control, and communications and datahandling subsystems. When the Landsat 5 satellite waslaunched, it was deployed at an orbital altitude of 705.3 km,with inclination of 98.2 deg, and with a descending nodeequatorial crossing at 9:30 a.m. local time. This orbit had afrequency of 19-9/16 orbits per day and covers the earth in 16days. The distance between ground tracks was 172 km, which,when used in conjunction with the 185-km TM and MSS swathwidth, provided an overlap of 7.6%. The space segment wasdesigned with 3 years nominal lifetime in orbit and can beextended through in-orbit replacement capability by the SpaceShuttle. The spacecraft and attendant sensors were operatedthrough the Tracking And Data Relay Satellite System(TDRSS).

Landsat 5

NSSDC ID: 1984-021A

Alternate Names

Landsat-D1

14780

Facts in Brief

Launch Date: 1984-03-01Launch Vehicle: DeltaLaunchSite: Vandenberg AFB,United StatesMass: 1407.0 kg

Funding Agencies


NOAA NationalEnvironmental SatelliteService (United States)

Disciplines

Engineering

Earth Science


Launch/Orbitalinformation for Landsat 5

Experiments on Landsat 5

Data collections fromLandsat 5



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Landsat 5 (1984-021A)





Personnel


Mr. E. Moule Project Manager Earth Observation Satellite

Dr. David Fischel Project Scientist Earth Observation Satellite


http://www.usa.gov/







Description

The Long Duration Exposure Facility (LDEF) was developed bythe NASA Office of Aeronautics and Space Technology andthe NASA/Langley Research Center. The purpose of the LDEFwas to accommodate, using the Shuttle, a class of technology,science, and applications experiments that require a free-flyingexposure in space. These experiments benefit from postflightlaboratory studies with the retrieved experiment hardware. TheLDEF was a simple reusable structure approximately 4.3 m indiameter and 9.1 m in length. The experiments were containedin trays mounted to the structure. While the LDEF had nocentral power or data system, it did, however, provide initiationand termination signals at the start and end of the mission.Any required power and/or data systems were included by theexperimenter in his respective tray. Standard ExperimentPower and Data Systems were designed for use in LDEF traysand these could be procured by the experimenters. The LDEFhad a gravity-gradient stabilized orbit orientation. In January1990, during the flight of STS-32, (1990-002A), the LDEF wasretrieved and returned to Earth. It is being examined byinvestigation groups composed of specialists in meteoroidsand space debris, materials, spacecraft systems, andradiation. Following the examinations, it is planned to removethe experiment trays from the LDEF structure and to distributethem to the investigators for data analysis.

LDEF 1

NSSDC ID: 1984-034B

Alternate Names

Long Duration ExposureFacility

LDEF-A

LDEF 1/STS 41C

LDEF

14898

Facts in Brief


Funding Agency


Disciplines

Life Science

Space Physics


Launch/Orbitalinformation for LDEF 1

Experiments on LDEF 1

Data collections from LDEF1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


LDEF 1



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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: LDEF 1 (1984-034B)



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



Personnel


Dr. Leo P. Daspit,Jr.

ProjectManager

NASA Langley ResearchCenter

Dr. William H.Kinard

ProjectScientist

NASA Langley ResearchCenter

[email protected]

Dr. Richard A.Gualdoni

ProgramManager

NASA Headquarters

Related Information/Data at NSSDC

STS 41C (LDEF Deployment Mission)STS 32 (LDEF Retrieval Mission)

Other Sources of LDEF Information/Data

Long Duration Exposure Facility Archive System (NASA LaRC)


http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1990-002A

http://setas-www.larc.nasa.gov/LDEF/

http://www.usa.gov/







Description

Leasat F1 was part of a series of five satellites developed as acommercial venture to provide dedicated communicationsservices to the US military. The program was initiated as aresult of Congressional reviews in 1976 and 1997 whichadvised increased use of leased commercial facilities. Ownedby Hughes Communications, the satellites were designed toprovide global UHF communications to military air, sea, andground forces. The system's primary user was the US Navy,with some support also provided to the Air Force and groundmobile forces. At the end of each satellite's designed 7 yearlife, the Navy had the option of purchasing the satellite for$15M. These satellites, along with the Navy's FLTSATCOMspacecraft, were replaced by the UFO (UHF Follow-On)spacecraft. Launched from the Space Shuttle, Leasat wasplaced in a circular parking orbit at approximately 180 miles(296 km) altitude with 28.6 degrees inclination.

The satellites were spin-stabilized, with the spun portioncontaining the solar array and sun and Earth sensors forattitude determination and Earth pointing reference, batteriesfor eclipse operation, and all propulsion and attitude controlhardware. The despun platform contained Earth-pointingreference, batteries for eclipse operation, and all propulsionand attitude control hardward. The despun platform containedEarth-pointing communcation antennas, communicationsrepeaters, and the majority of the telemetry, tracking, andcommand (TT&C) equipment.

Two large helical UHF antennas provided receive and transmitcapability in the UHF band (240 to 400 MHz). Telemetry,command, and the Fleet Broadcast uplink and beacon were inthe "exclusive" portions of the SHF band (7250 to 7500 MHz,and 7975 and 8025 MHz). Twelve UHF repeaters provided themain communications capability.

The principal Navy Fleet Broadcast function included an SHFuplink, and both SHF and UHF downlinks. The additionalantennas for this channel were the SHF uplink and downlinkearth coverage horns, which supported the uplink andacquisition/timing function, respectively. The UHF downlink forFleet broadcast was multiplexed onto the UHF transmit helix.

National Space Science Data Center Header

Leasat F1

NSSDC ID: 1984-093C

Alternate Names

Leased Satellite F1

Syncom IV-2

15236

Facts in Brief


Funding Agencies



Discipline

Communications


Launch/Orbitalinformation for Leasat F1

Experiments on Leasat F1

Data collections fromLeasat F1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Leasat F1

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Leasat F1


mailto:[email protected]?Subject=NMC Comment/Question: Leasat F1 (1984-093C)






http://www.usa.gov/







Description

Leasat F2 was part of a series of five satellites developed as acommercial venture to provide dedicated communicationsservices to the US military. The program was initiated as aresult of Congressional reviews in 1976 and 1997 whichadvised increased use of leased commercial facilities. Ownedby Hughes Communications, the satellites were designed toprovide global UHF communications to military air, sea, andground forces. The system's primary user was the US Navy,with some support also provided to the Air Force and groundmobile forces. At the end of each satellite's designed 7 yearlife, the Navy had the option of purchasing the satellite for$15M. These satellites, along with the Navy's FLTSATCOMspacecraft, were replaced by the UFO (UHF Follow-On)spacecraft. Launched from the Space Shuttle, Leasat wasplaced in a circular parking orbit at approximately 180 miles(296 km) altitude with 28.6 degrees inclination.

The satellites were spin-stabilized, with the spun portioncontaining the solar array and sun and Earth sensors forattitude determination and Earth pointing reference, batteriesfor eclipse operation, and all propulsion and attitude controlhardware. The despun platform contained Earth-pointingreference, batteries for eclipse operation, and all propulsionand attitude control hardward. The despun platform containedEarth-pointing communcation antennas, communicationsrepeaters, and the majority of the telemetry, tracking, andcommand (TT&C) equipment.

Two large helical UHF antennas provided receive and transmitcapability in the UHF band (240 to 400 MHz). Telemetry,command, and the Fleet Broadcast uplink and beacon were inthe "exclusive" portions of the SHF band (7250 to 7500 MHz,and 7975 and 8025 MHz). Twelve UHF repeaters provided themain communications capability.

The principal Navy Fleet Broadcast function included an SHFuplink, and both SHF and UHF downlinks. The additionalantennas for this channel were the SHF uplink and downlinkearth coverage horns, which supported the uplink andacquisition/timing function, respectively. The UHF downlink forFleet broadcast was multiplexed onto the UHF transmit helix.

Leasat F2

NSSDC ID: 1984-113C

Alternate Names

Leased Satellite F2

Syncom IV-1

15384

Facts in Brief


Funding Agency


Discipline

Communications


Launch/Orbitalinformation for Leasat F2

Experiments on Leasat F2

Data collections fromLeasat F2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Leasat F2






http://www.usa.gov/







Description

MARECS B2 was a geostationary maritime communicationssatellite launched from the Kourou Space Center in FrenchGuiana aboard an Ariane rocket. It was placed ingeosynchronous orbit at 345 deg E. It was part of theINMARSAT world-wide maritime communications satellitenetwork.

Marecs-B2

NSSDC ID: 1984-114B

Alternate Names

Marecs PAC 1

15386

Facts in Brief


Funding Agency

European Space Agency(International)

Discipline

Communications


Launch/Orbitalinformation for Marecs-B2

Experiments on Marecs-B2

Data collections fromMarecs-B2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Marecs-B2

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Marecs-B2

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Marecs-B2

mailto:[email protected]?Subject=NMC Comment/Question: Marecs-B2 (1984-114B)



http://www.usa.gov/







Description

Meteor 2 was launched by the USSR. It carried scientific andmeteorological instruments, and service systems.

Meteor 2-11

NSSDC ID: 1984-072A

Alternate Names

15099

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Earth Science


Launch/Orbitalinformation for Meteor 2-11

Experiments on Meteor 2-11

Data collections fromMeteor 2-11



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Meteor 2-11

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Meteor 2-11

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Meteor 2-11

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Meteor 2-11

mailto:[email protected]?Subject=NMC Comment/Question: Meteor 2-11 (1984-072A)



http://www.usa.gov/







Description

Molniya 1/60 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 1/60, 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 1/60 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 1-60

NSSDC ID: 1984-029A

Alternate Names

14825

Facts in Brief

Launch Date: 1984-03-16LaunchVehicle: MolniyaLaunch Site: Plesetsk,U.S.S.RMass: 1800.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Communications


Launch/Orbitalinformation for Molniya 1-60

Experiments on Molniya 1-60

Data collections fromMolniya 1-60



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Molniya 1-60


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Molniya 1-60


mailto:[email protected]?Subject=NMC Comment/Question: Molniya 1-60 (1984-029A)



http://www.usa.gov/







Description

Molniya 1/61 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 1/61, 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 1/61 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 1-61

NSSDC ID: 1984-085A

Alternate Names

15182

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 1/62 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 1/62, 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 1/62 remained relatively stationary with respect to theearth below for nearly 8 of every 12 hr. By placing three ormore Molniya 1 satellites in this type of orbit, spacing themsuitably, and shifting their orbital planes relative to each otherby 120 deg, a 24-hr/day communication system could beobtained.

Molniya 1-62

NSSDC ID: 1984-089A

Alternate Names

15215

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 1/63 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 1/63, 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 1/63 remained relatively stationary with respect to theearth below for nearly 8 of every 12 hr. By placing three ormore Molniya 1 satellites in this type of orbit, spacing themsuitably, and shifting their orbital planes relative to each otherby 120 deg, a 24-hr/day communication system could beobtained.

Molniya 1-63

NSSDC ID: 1984-124A

Alternate Names

15429

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

NATO 3-D was the fourth in a series of communicationssatellites launched by NASA for NATO. The NATO SatelliteCommunications System provided immediate communicationslinks between officials of the various NATO nations. As of1998, one NATO 3 and two NATO 4 satellites were still inearth orbit at an altitude of more than 23,000 miles. Thesatellites were ultra-high, super- high and extremely-highfrequency systems capable of providing secure voice and faxservices to hundreds of NATO users simultaneously. Membersof an Air Force Space Command unit provided command andcontrol for the NATO system.

NATO 3-D

NSSDC ID: 1984-115A

Alternate Names

15391

Facts in Brief


Funding Agencies

Department of Defense(United States)

North Atlantic TreatyOrganization(International)

Discipline

Communications


Launch/Orbitalinformation for NATO 3-D

Experiments on NATO 3-D

Data collections fromNATO 3-D



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: NATO 3-D (1984-115A)



http://www.usa.gov/







Description

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

The first eleven spacecraft (GPS Block 1) were used todemonstrate the feasibility of the GPS system. They were 3-axis stabilized, nadir pointing using reaction wheels. Dual solararrays supplied over 400 W. They had S-band (SGLS)communications for control and telemetry and UHF cross-linkbetween spacecraft. They were manufactured by RockwellSpace Systems, were 5.3 m across with solar panelsdeployed, and had a design life expectancy of 5 years. Unlikethe later operational satellites, GPS Block 1 spacecraft wereinclined at 63 degrees.

Navstar 9

NSSDC ID: 1984-059A

Alternate Names

GPS 1-9

15039

Facts in Brief

Launch Date: 1984-06-13Launch Vehicle: AtlasELaunchSite: Vandenberg AFB,United StatesMass: 433.0 kgNominalPower: 400.0 W

Funding Agency


Discipline



Launch/Orbitalinformation for Navstar 9

Experiments on Navstar 9

Data collections fromNavstar 9



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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


mailto:[email protected]?Subject=NMC Comment/Question: Navstar 9 (1984-059A)







Curator: E. Bell, IIVersion 4.0.14, 08 October 2010

http://www.usa.gov/





Description

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

The first eleven spacecraft (GPS Block 1) were used todemonstrate the feasibility of the GPS system. They were 3-axis stabilized, nadir pointing using reaction wheels. Dual solararrays supplied over 400 W. They had S-band (SGLS)communications for control and telemetry and UHF cross-linkbetween spacecraft. They were manufactured by RockwellSpace Systems, were 5.3 m across with solar panelsdeployed, and had a design life expectancy of 5 years. Unlikethe later operational satellites, GPS Block 1 spacecraft wereinclined at 63 degrees.

Navstar 10

NSSDC ID: 1984-097A

Alternate Names

GPS 1-10

15271

Facts in Brief

Launch Date: 1984-09-08Launch Vehicle: AtlasFLaunchSite: Vandenberg AFB,United StatesMass: 770.0 kgNominalPower: 400.0 W

Funding Agency


Discipline



Launch/Orbitalinformation for Navstar 10

Experiments on Navstar 10

Data collections fromNavstar 10



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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











Description

NOAA 9 was a third-generation operational meteorologicalsatellite. The satellite design provided an economical andstable sun-synchronous platform for advanced operationalinstruments to measure the earth's atmosphere, its surface andcloud cover, and the near-space environment. Primary sensorsincluded (1) an advanced very high resolution radiometer(AVHRR), (2) a TIROS operational vertical sounder (TOVS),(3) an earth radiation budget experiment (ERBE), and (4) asolar backscattered ultraviolet radiometer (SBUV/2). Thesecondary experiment was a data collection and platformlocation system (DCPLS). A search and rescue satellite aidedtracking (SARSAT) system was also carried on NOAA 9. Thesatellite was based upon the Block 5D spacecraft busdeveloped for the U.S. Air Force, and was capable ofmaintaining an earth-pointing accuracy of better than plus orminus 0.1 deg with a motion rate of less than 0.035 deg/s.

NOAA 9

NSSDC ID: 1984-123A

Alternate Names

NOAA-F

15427

Facts in Brief

Launch Date: 1984-12-12Launch Vehicle: AtlasELaunchSite: Vandenberg AFB,United StatesMass: 1030.0 kg

Funding Agencies

NOAA NationalEnvironmental SatelliteService (United States)


Disciplines

Communications

Earth Science


Launch/Orbitalinformation for NOAA 9

Experiments on NOAA 9

Data collections fromNOAA 9



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: NOAA 9 (1984-123A)





Personnel


Dr. Joel Susskind ProjectScientist


[email protected]

Mr. Gerald W.Longanecker

ProjectManager


Mr. James R.Greaves

ProgramManager

NASA Headquarters [email protected]


http://www.usa.gov/







Description



NOSS 6

NSSDC ID: 1984-012A

Alternate Names

Naval Ocean SurveillanceSatellite 6

14690

Facts in Brief


Funding Agency


Discipline



Launch/Orbitalinformation for NOSS 6

Experiments on NOSS 6

Data collections fromNOSS 6



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: NOSS 6 (1984-012A)



http://www.usa.gov/







Description

NOVA III was an improved Transit Navigation Satellitedeployed by NASA for the US Navy.

NOVA III

NSSDC ID: 1984-110A

Alternate Names

NNSS 30500

15362

Facts in Brief

Launch Date: 1984-10-12Launch Vehicle: ScoutLaunchSite: Vandenberg AFB,United StatesMass: 165.0 kg

Funding Agency


Discipline



Launch/Orbitalinformation for NOVA III

Experiments on NOVA III

Data collections fromNOVA III



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


NOVA III




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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: NOVA III (1984-110A)



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

http://www.usa.gov/







Description

The purpose of this mission was to perform remote sensing ofthe minor constituents of the middle atmosphere and to studythe wave-particle interactions in the ionospheric plasma in theSouth American anomaly and the auroral zones. This missionis part of the Middle Atmosphere Program (MAP).

Ohzora

NSSDC ID: 1984-015A

Alternate Names

Exospheric Sat. C

EXOS-C

14722

Facts in Brief

Launch Date: 1984-02-14Launch Vehicle: M-3SLaunch Site: UchinouraSpace Center, JapanMass: 210.0 kg

Funding Agency

Institute of Space andAeronautical Science, Uof Tokyo (Japan)

Disciplines

Earth Science

Space Physics


Launch/Orbitalinformation for Ohzora

Experiments on Ohzora

Data collections fromOhzora


Personnel



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Ohzora (1984-015A)

mailto:[email protected]?Subject=NMC Comment/Question: Ohzora (1984-015A)



Prof. HiroshiOya

ProjectScientist

University of Tohoku [email protected]

Dr. ToshihiroOgawa

ProjectScientist

Institute of Space and AeronauticalScience

Prof. TomizoItoh

ProjectManager

Institute of Space and AeronauticalScience


http://www.usa.gov/







Description

Palapa-B2, a communications satellite launched from STS-41Bfor the government of Indonesia, was deployed from theShuttle on orbit 19. It did not achieve the desired orbit.

Palapa-B2

NSSDC ID: 1984-011D

Alternate Names

14692

Facts in Brief


Funding Agencies

Unknown (Indonesia)


Discipline

Communications


Launch/Orbitalinformation for Palapa-B2

Experiments on Palapa-B2

Data collections fromPalapa-B2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Palapa-B2

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Palapa-B2

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Palapa-B2

mailto:[email protected]?Subject=NMC Comment/Question: Palapa-B2 (1984-011D)



http://www.usa.gov/







Description

PRC 14 was a technology satellite launched from the Xichangspace center aboard a CZ-3 rocket. It was an experimentalGEO telecommunications satellite that was left in a lower thanplanned orbit after a 3rd stage failure.

PRC 14

NSSDC ID: 1984-008A

Alternate Names

STTW-T1

14670

Facts in Brief

Launch Date: 1984-01-29Launch Vehicle: LongMarch 3Launch Site: Xichang,Peoples Republic of ChinaMass: 900.0 kg

Funding Agency

Unknown (PeoplesRepublic of China)

Discipline

Communications


Launch/Orbitalinformation for PRC 14

Experiments on PRC 14

Data collections from PRC14



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=PRC 14

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=PRC 14


mailto:[email protected]?Subject=NMC Comment/Question: PRC 14 (1984-008A)



http://www.usa.gov/







Description

PRC 15 was a Chinese experimental communications satellitelaunched from the Xichang space center aboard a CZ-3 rocket.It was placed in a geosynchronous orbit at 125 deg E.

PRC 15

NSSDC ID: 1984-035A

Alternate Names

STTW-T2

14899

Facts in Brief

Launch Date: 1984-04-08Launch Vehicle: LongMarch 3Launch Site: Xichang,Peoples Republic of ChinaMass: 900.0 kg

Funding Agency


Disciplines

Communications

Engineering







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data











http://www.usa.gov/







Description

PRC 16 was a military photo surveillance satellite launched bythe People's Republic of China from the Shaung Cheng Tzulaunch site aboard a CZ-2C rocket.

PRC 16

NSSDC ID: 1984-098A

Alternate Names

FSW-0 6

15279

Facts in Brief

Launch Date: 1984-09-12Launch Vehicle: LongMarch 2CLaunch Site: Jiuquan,Peoples Republic of ChinaMass: 2500.0 kg

Funding Agency


Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data











http://www.usa.gov/






Tuesday, 30 November 2010

Description

Automatic cargo ship Progress 20 was launched from theBaikonur cosmodrome aboard a Soyuz rocket. It carriedvarious cargos to the Salyut 7 space station. It deorbited onMay 7, 1984.

Progress 20

NSSDC ID: 1984-038A

Alternate Names

14932

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Resupply/Refurbishment/Repair


Launch/Orbitalinformation for Progress20

Experiments on Progress20

Data collections fromProgress 20



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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


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


mailto:[email protected]?Subject=NMC Comment/Question: Progress 20 (1984-038A)



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NASA - NSSDC - Master Catalog - Spacecraft Query

http://nssdc.gsfc.nasa.gov/nmc/SpacecraftQuery.jsp[03/12/2010 23:18:59]

Saturday, 04 December 2010

Spacecraft Query

Spacecraft Name

Discipline

AllAstronomyEarth SciencePlanetary ScienceSolar PhysicsSpace PhysicsHuman Crew

Launch Date

(YYYY-MM-DD; MM, DD optional)


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data



http://www.usa.gov/




NASA - NSSDC - Master Catalog - Experiment Query

http://nssdc.gsfc.nasa.gov/nmc/ExperimentQuery.jsp[03/12/2010 23:19:53]


Experiment Query

Experiment Name

Spacecraft Name

Principal Investigator

(last name only)


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data



http://www.usa.gov/




NASA - NSSDC - Master Catalog - Data Collection Query

http://nssdc.gsfc.nasa.gov/nmc/DatasetQuery.jsp[03/12/2010 23:20:43]


Data Collection Query

Data Collection Name

Start Date (YYYY-MM-DD)

Stop Date (YYYY-MM-DD)

Spacecraft Name

Experiment Name

Experiment Principal Investigator

(last name only)


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data



http://www.usa.gov/




NASA - NSSDC - Master Catalog - Person Query

http://nssdc.gsfc.nasa.gov/nmc/PersonQuery.jsp[03/12/2010 23:21:26]


Person Query

Last Name

First Name


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data



http://www.usa.gov/




NASA - NSSDC - Master Catalog - Publication Query

http://nssdc.gsfc.nasa.gov/nmc/PublicationQuery.jsp[03/12/2010 23:22:35]


Publication Query

NSSDC Reference ID

Title

Author (Last, F. M.)

Spacecraft Name

Experiment Name


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data



http://www.usa.gov/




NASA - NSSDC - Master Catalog - Maps Query

http://nssdc.gsfc.nasa.gov/nmc/MapQuery.jsp[03/12/2010 23:23:27]


Lunar and Planetary Maps Query

Use the form below to query NSSDC for maps that are in stock. When specifying latitudevalues, enter sourthern latitudes as a negative number.

Planet Moon

Latitude (degrees)

Longitude (degrees)


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data



http://www.usa.gov/




NASA - NSSDC - Master Catalog - New/Updated Data Query

http://nssdc.gsfc.nasa.gov/nmc/NewDataQuery.jsp[03/12/2010 23:24:38]


New and Updated Data Collection Query

Note: Only the start date needs to be specified. If a stop date is not specified, the querydefaults to using today's date.

Start Date

(YYYY-MM-DD)

Stop Date

(YYYY-MM-DD)

New data sets only?


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data



http://www.usa.gov/




NASA - NSSDC - Master Catalog - Event Query

http://nssdc.gsfc.nasa.gov/nmc/EventQuery.jsp[03/12/2010 23:25:28]


Event Query

This form can be used to query for planetary and lunar exploration events. Please note:Months and days of less than two digits must be entered with a leading zero (i.e., 03 for Marchrather than just 3).

Year- Month- Day - -

Description


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data



http://www.usa.gov/







Description

Automatic cargo ship Progress 19 was launched from theBaikonur cosmodrome aboard a Soyuz rocket. It docked withthe Salyut 7 space station and provided various cargos. Itdeorbited on April 1, 1984 at 18:18 GMT.

Progress 19

NSSDC ID: 1984-018A

Alternate Names

14757

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

Automatic cargo ship Progress 21 was launched from theBaikonur cosmodrome aboard a Soyuz rocket. It carriedvarious cargos to the Salyut 7 space station and deborbited onMay 26, 1984.

Progress 21

NSSDC ID: 1984-042A

Alternate Names

14961

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

Automatic cargo ship Progress 22 was launched from theBaikonur cosmodrome aboard a Soyuz rocket. It docked withthe Salyut 7 space station and deorbited on July 15, 1984.

Progress 22

NSSDC ID: 1984-051A

Alternate Names

14996

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

Automatic cargo ship Progress 23 was launched from theBaikonur cosmodrome aboard a Soyuz rocket. It docked withthe Salyut 7 space station and deorbited on August 28, 1984at 1:28 GMT.

Progress 23

NSSDC ID: 1984-086A

Alternate Names

15193

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

Raduga 14 was a Soviet communications satellite launchedfrom the Baikonur cosmodrome aboard a Proton 8K82K/BlockDM rocket. It provided uninterupted round the clock telephoneand telegraph radio communications in the USSR andsimultaneous transmission of color and black and white USSRcentral television programs to stations in the Orbita network.

Raduga 14

NSSDC ID: 1984-016A

Alternate Names

14725

Facts in Brief

Launch Date: 1984-02-15Launch Vehicle: ProtonLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 2000.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Communications


Launch/Orbitalinformation for Raduga14

Experiments on Raduga 14

Data collections fromRaduga 14



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Raduga 14

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Raduga 14


mailto:[email protected]?Subject=NMC Comment/Question: Raduga 14 (1984-016A)



http://www.usa.gov/







Description

Raduga 15 was a Soviet communications satellite launchedfrom the Baikonur cosmodrome aboard a Proton 8K82K/BlockDM rocket. It provided uninterrupted round the clock telephoneand telegraph radio communications in the USSR andsimultaneous transmission of color and black and white USSRcentral television programs to stations in the Orbita network.

Raduga 15

NSSDC ID: 1984-063A

Alternate Names

15057

Facts in Brief

Launch Date: 1984-06-22Launch Vehicle: ProtonLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.R

Funding Agency

Unknown (U.S.S.R)

Discipline

Communications


Launch/Orbitalinformation for Raduga15

Experiments on Raduga 15

Data collections fromRaduga 15



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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






http://www.usa.gov/







Description

SBS 4 was a Satellite Business Systems communicationssatellite deployed by the shuttle Discovery during the STS-41Dmission.

SBS 4

NSSDC ID: 1984-093B

Alternate Names

Satellite BusinessSystems 4

15235

Facts in Brief


Funding Agency

Pan American Satellite(United States)

Discipline

Communications


Launch/Orbitalinformation for SBS 4

Experiments on SBS 4

Data collections from SBS4



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: SBS 4 (1984-093B)



http://www.usa.gov/







Description

The Satellite Data System (SDS-1) was composed of twooperational satellites that had supported near-real timecommunications between low altitude photographic intelligencesatellites and ground control stations, making it a critical part ofthe US Air Force Satellite Communications (AFSATCOM)System. In particular, SDS-1 served as a communications linkbetween the Air Force Satellite Control Facility at Sunnyvale,CA, and 7 remote tracking stations located at VandenbergAFB, Hawaii, Guam, Nahe Island, Greenland, the UK, andBoston. Furthermore, the SDS-1 enabled almost two-way real-time command, control, and UHF communications in the polarregion for Strategic Air Command (SAC) forces. The Northpolar region was not covered by communications satellites ingeostationary orbit, and therefore the SDS-1 filled the gap. Athird and unacknowledged function was to provide a relay forinformation from the KH-11 photo reconnaisance satellite to aground station, which was probably the Defense SpecialMissile and Astronautics Center at Fort Meade, MD. It flew in63 deg orbits, having high apogees over the North Pole andlow perigees. This gave it a long stay time over the polarregion, enabling it to relay communications to aircraft in thoseareas. Two of the SDS-1 satellites had to be in orbit for thecommunications to be constant. Each had 12 communicationschannels in the UHF band. The main transmitting antenna wasover 10 feet in diameter. The body itself, based on the designof the TACSAT, was cylindrical and about 13 feet long and 10feet in diameter. The outside cylinder, call the solar array, wasmade of a silicon skin and spun for thermal distribution of theheat load. The primary electrical power was provided by solarcharged batteries with a total of 980 watts of power.

SDS F-5A

NSSDC ID: 1984-091A

Alternate Names

USA 4

Satellite Data System F-5A

15226

Facts in Brief

Launch Date: 1984-08-28Launch Vehicle: TitanIII-BLaunchSite: Vandenberg AFB,United StatesMass: 700.0 kg

Funding Agency


Discipline



Launch/Orbitalinformation for SDS F-5A

Experiments on SDS F-5A

Data collections from SDSF-5A



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=SDS F-5A

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=SDS F-5A

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=SDS F-5A

mailto:[email protected]?Subject=NMC Comment/Question: SDS F-5A (1984-091A)






http://www.usa.gov/







Description

Soyuz T-10B was a manned Soviet mission launched from theBaikonur cosmodrome with cosmonauts Leonid Kizim, OlegAtkov, and Vladimir Solovyov on board. It docked with theSalyut 7 space station and returned the crew of Soyuz T-11 toEarth. It was recovered on April 11, 1984 at 10:50 GMT, 100miles E of Dzehezkazgan.

Soyuz T-10

NSSDC ID: 1984-014A

Alternate Names

14701

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Human Crew


Launch/Orbitalinformation for Soyuz T-10

Experiments on Soyuz T-10

Data collections fromSoyuz T-10



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Soyuz T-10


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Soyuz T-10


mailto:[email protected]?Subject=NMC Comment/Question: Soyuz T-10 (1984-014A)



http://www.usa.gov/




Soyuz T-10

Launch, orbit and landing data Launch date: 08.02.1984 Launch time: 12:07 UT Launch site: Baikonur Launch pad: 31 Altitude: 226 - 274 km Inclination: 51,6° Landing date: 02.10.1984 Landing time: 10:56 UT Landing site: 46 km E of Arkalyk

Crew

No. Surname Given name Job

1 Kizim Leonid Denisovich Commander

2 Soloviyov Vladimir Alekseyevich Flight Engineer

3 Atkov Oleg Yuriyevich Research Cosmonaut

3 Polyakov Valeri Vladimirovich Research Cosmonaut

Flight Launch from Baikonur; landing with Soyuz T-11-capsule 46 km east of Arkalyk. Docking on Salyut 7; third resident crew of the station; medical experiments; visiting of spacecrafts Soyuz T-11 on 03.04.1984 and Soyuz T-12 on 17.07.1984; five supply-missions with cargo spaceships Progress 19 - 23; Kizim and Soloviyov conducted six EVA's to repair fuel lines and install a solar array on 23.04.1984 (4h 15m), 26.04.1984 (4h 56m), 29.04.1984 (2h 45m), 03.05.1984 (2h 45m), 18.05.1984 (3h 05m), 08.08.1984 (5h 00m); new spaceflight record.

http://www.spacefacts.de/maps/english/e_bai_ussr_31.htm�

http://www.spacefacts.de/maps/english/e_soyuz-t-10.htm�

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

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

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

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

http://www.spacefacts.de/mission/english/soyuz-t11.htm�

http://www.spacefacts.de/salyut/english/salyut-7_3.htm�



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

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




Description

Soyuz T-11 was a manned Soviet mission launched from theBaikonur cosmodrome and carried an international crewconsisting of Y.V. Malyshev (USSR), G.M. Strekalov (USSR)and researcher R. Sharma (India) to the Salyut 7 spacestation. It returned the crew of Soyuz T-10 to Earth and wasrecovered on October 2, 1984 at 10:57 GMT.

Soyuz T-11

NSSDC ID: 1984-032A

Alternate Names

14872

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Disciplines

Human Crew








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data













http://www.usa.gov/




Soyuz T-11

Launch, orbit and landing data Launch date: 03.04.1984 Launch time: 13:08 UT Launch site: Baikonur Launch pad: 31 Altitude: 202 - 240 km Inclination: 51,6° Landing date: 11.04.1984 Landing time: 10:48 UT Landing site: 145 km SE of Dzheskasgan

Crew


1 Malyshev Yuri Vasiliyevich Commander

2 Strekalov Gennadi Mikhailovich Flight Engineer

3 Sharma Rakesh "Rikki" Research Cosmonaut

Flight Launch from Baikonur; landing with Soyuz T-10-capsule 145 km southeast of Dzheskasgan; docking on Salyut 7; scientific work onboard includes photography of India, silicium-fusing tests and Yoga-practice of Rakesh Sharma.



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

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

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


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




Description

Soyuz T-12 was a manned Soviet mission launched from theBaikonur cosmodrome and carried cosmonauts V.A.Dzhanibekov, S.E. Savitsakaya and I.P. Volk to the Salyut 7space station to conduct scientific and technical studies andexperiments. The spacecraft was recovered on July 29, 1984at 12:55 GMT.

Soyuz T-12

NSSDC ID: 1984-073A

Alternate Names

15119

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/




Soyuz T-12

Launch, orbit and landing data Launch date: 17.07.1984 Launch time: 17:40 UT Launch site: Baikonur Launch pad: 31 Altitude: 282 - 309 km Inclination: 51,6° Landing date: 29.07.1984 Landing time: 12:55 UT Landing site: 140 km SE of Dzheskasgan

Crew


1 Dzhanibekov Vladimir Aleksandrovich Commander

2 Savitskaya Svetlana Yevgeniyevna Flight Engineer

3 Volk Igor Petrovich Research Cosmonaut

Flight Launch from Baikonur; landing 140 km southeast of Dzheskasgan; docking on Salyut 7; EVA by Dzhanibekov and Savitskaya on 25.07.1984 (3h 35m); first EVA of a woman; welding work.



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

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

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

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

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

Photos / Drawings




Description

Spacenet 1

NSSDC ID: 1984-049A

Alternate Names

Spacenet F1

14985

Facts in Brief

Launch Date: 1984-05-23Launch Vehicle: ArianeLaunch Site: Kourou,French GuianaMass: 705.0 kg

Funding Agency

GTE/GTE Spacenet(United States)

Discipline

Communications


Launch/Orbitalinformation for Spacenet1

Experiments on Spacenet1

Data collections fromSpacenet 1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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


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


mailto:[email protected]?Subject=NMC Comment/Question: Spacenet 1 (1984-049A)



http://www.usa.gov/







Description

Spacenet 2 was launched for the European Space Agencyfrom the Kourou Space Center in French Guiana on an Arianelaunch vehicle.

Spacenet 2

NSSDC ID: 1984-114A

Alternate Names

Spacenet F2

15385

Facts in Brief


Funding Agency

GTE/GTE Spacenet(United States)

Discipline

Communications


Launch/Orbitalinformation for Spacenet2

Experiments on Spacenet2

Data collections fromSpacenet 2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data













http://www.usa.gov/







Description

STS 41-B was the fourth Challenger shuttle flight with VanceBrand, Robert Gibson, Bruce McCandless, Ronald McNair,and Robert Stewart on board. Misson Highlights consisted ofthe first untethered space walks by McCandless and Stewart,using manned maneuvering unit. WESTAR-VI and PALAPA-B2 satellites were deployed, but failure of Payload AssistModule-D (PAM-D) rocket motors left them in radical low-Earthorbits. German-built Shuttle Pallet Satellite (SPAS), first flownon STS-7, became the first satellite refurbished and flownagain. SPAS remained in the payload bay due to electricalproblem with Remote Manipulator System (RMS). The RMSmanipulator foot restraint was first used, and practiceprocedures performed for Solar Maximum satellite retrievaland repair planned for next mission. Integrated RendezvousTarget (IRT) failed due to internal failure. Five Get AwaySpecial canisters were flown in the cargo bay and a Cinema-360 camera was used by the crew. Other payloadsconsisted of: Acoustic Containerless Experiment System (ACES);Monodisperse Latex Reactor (MLR); and Radiation MonitoringEquipment (RME), and Isoelectric Focusing (IEF) payload. Themission duration was 191 hours 15 minutes 55 seconds.

STS 41B

NSSDC ID: 1984-011A

Alternate Names

STS 10

14681

Facts in Brief


Funding Agency

NASA-Office of SpaceFlight (United States)

Discipline

Human Crew


Launch/Orbitalinformation for STS 41B

Experiments on STS 41B

Data collections from STS41B


Other Sources of STS 41B Information/Data

STS 41B information (NASA KSC)STS 41B Press Release images (NASA JSC)


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


STS 41B



http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=STS 41B

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=STS 41B

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=STS 41B

mailto:[email protected]?Subject=NMC Comment/Question: STS 41B (1984-011A)



http://www.ksc.nasa.gov/shuttle/missions/41-b/mission-41-b.html

http://images.jsc.nasa.gov/iams/html/pao/STS41B.htm

http://nssdc.gsfc.nasa.gov/image/spacecraft/sts-41b.jpg

STS-41-B

Datos de la misión

Misión STS-41-B Transbordador Challenger Plataforma de lanzamiento 39-A Lanzamiento 3 de febrero de 1984 13:00:00 UTC Aterrizaje 11 de febrero de 1984 12:15:55 UTC Centro Espacial Kennedy Duración 7 días, 23 horas, 15 min y 55 s Altitud orbital 350 kilometros Inclinación orbital 28.5 grados Distancia recorrida 5,329,150 kilometros

Tripulación

Izq-Der: Robert L. Stewart, Vance Brand, Ronald McNair, Robert Gibson y Bruce McCandless.

STS-41-B fue l a novena m isión del programa STS y l a cuarta del t ransbordador Challenger. Despues de la misión STS-9, la numeración de los vuelos fue cambiada, de esta manera el que hubiese sido el STS-11 se convirtió en el STS-41-B (la misión STS-10 había sido cancelada). Entre los objetivos de la misión se encontraba el lanzamiento de un satélite WESTAR y de otro tipo P alapa, la r ealización de un pa seo espacial usando una m ochila pr opulsora y el primer aterrizaje de una misión en el Centro Espacial Kennedy.

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

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

http://es.wikipedia.org/wiki/Complejo_de_lanzamiento_39�

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http://es.wikipedia.org/wiki/1984�

http://es.wikipedia.org/wiki/UTC�

http://es.wikipedia.org/wiki/11_de_febrero�



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


http://es.wikipedia.org/wiki/STS-9�


Tripulación




Description

STS 41-C was the fifth Challenger shuttle flight. On boardwere Robert Crippen, Frances Scobee, Terry Hart, GeorgeNelson, and James Van Hoften.

This was the first direct ascent trajectory for Space Shuttle.Using the manned maneuvering unit, astronauts replaced analtitude control system and coronagraph/polarimeterelectronics box in the Solar Max satellite while it remained inorbit. The Long Duration Exposure Facility (LDEF) wasdeployed, carrying 57 experiments. It was left on orbit with theintention of retrieving during later mission. Other payloadsincluded: IMAX camera; Radiation Monitoring Equipment(RME); Cinema 360; Shuttle Student Involvement Program(SSlP) experiment. The mission duration was 167 hours 40minutes 7 seconds.

STS 41C

NSSDC ID: 1984-034A

Alternate Names

STS 11

14897

Facts in Brief


Funding Agency


Discipline

Human Crew


Launch/Orbitalinformation for STS 41C

Experiments on STS 41C

Data collections from STS41C


Related Information/Data at NSSDC

Solar MaxLDEF


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


STS 41C



http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=STS 41C

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=STS 41C

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=STS 41C

mailto:[email protected]?Subject=NMC Comment/Question: STS 41C (1984-034A)




http://nssdc.gsfc.nasa.gov/image/spacecraft/sts-41c.jpg



Other Sources of STS 41C Information/Data

STS 41C information (NASA KSC)STS 41C Press Release images (NASA JSC)


http://www.ksc.nasa.gov/shuttle/missions/41-c/mission-41-c.html

http://images.jsc.nasa.gov/iams/html/pao/STS41C.htm

http://www.usa.gov/




STS-41-C

Datos de la misión

Misión STS-41-C Transbordador Challenger Plataforma de lanzamiento 39-A Lanzamiento 6 de abril de 1984 13:58:00 UTC Aterrizaje 13 de abril de 1984 13:38:07 UTC Base Aérea Edwards Duración 6 días, 23 horas, 40 min y 7 s Altitud orbital 580 kilometros Inclinación orbital 28.5 grados Distancia recorrida 4,619,000 kilometros

Tripulación

Izq-Der: Francis R. Scobee, George D. Nelson, James D. van Hoften, Terry J. Hart y Robert L.

Crippen.

STS-41-C fue la misión 11 del programa STS y la quinta del transbordador Challenger. El lanzamiento fue el primero con una trayectoria ascendente directa en una misión. El vuelo se extendió por un dia debido a los problemas para atrapar al satélite Solar Max. El aterrizaje se realizó en la base Edwards pese a que estaba programado en el Centro Espacial Kennedy.

Los dos objetivos principales de la misión fueron el recuperar, reparar y relanzar el satélite Solar Max, y el lanzamiento del Servicio de Exposición de Larga Duración (LDEF).




http://es.wikipedia.org/wiki/6_de_abril�



http://es.wikipedia.org/wiki/13_de_abril�



http://es.wikipedia.org/wiki/Base_A%C3%A9rea_Edwards�







http://es.wikipedia.org/wiki/Sat%C3%A9lite_artificial�

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


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

Tripulación

Momento en que los astronautas reparan el satélite Solar Max.




Description

STS-41D was the first Discovery shuttle flight. On board wereHenry Hartsfield, Michael Coats, Richard Mullane, StevenHawley, Judith Resnik, and Charles Walker. This missioncarried out experiments including OAST-1 solar array structuraltesting.

Three satellites were deployed: Satellite Business SystemSBS-D, SYNCOM IV-2 (also known as LEASAT2) andTELSTAR. The 102- foot-tall, 13-loot-wide Office of Applicationand Space Technology (OAST-1) solar wing extended from thepayload bay. The wing carried different types of solar cells andextended to full height several times. It demonstrated largelightweight solar arrays for the future in building large facilitiesin space such as the International Space Station. Otherpayloads included: Continuous Flow Electrophoresis System(CFES) Ill; Radiation Monitoring Equipment (RME); ShuttleStudent Involvement Program (SSIP) experiment; lMAXcamera, being flown for the second time; and an Air Forceexperiment, Cloud Logic to Optimize Use of Defense Systems(CLOUDS). The mission duration was 144 hours 56 minutes 4seconds.

STS 41D

NSSDC ID: 1984-093A

Alternate Names

STS 12

15234

Facts in Brief


Funding Agency


Discipline

Human Crew


Launch/Orbitalinformation for STS 41D

Experiments on STS 41D

Data collections from STS41D



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=STS 41D

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=STS 41D

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=STS 41D

mailto:[email protected]?Subject=NMC Comment/Question: STS 41D (1984-093A)



http://www.usa.gov/




STS-41-D

Datos de la misión

Misión STS-41-D Transbordador Discovery Plataforma de lanzamiento 39-A Lanzamiento 30 de agosto de 1984, 8:41:50 EDT Aterrizaje 5 de septiembre de 1984, 8:37:54 PDT, Edwards AFB Duración 6/00:56:04 Altitud orbital 184 millas náuticas (340 km) Inclinación orbital 28,5 grados Distancia recorrida 2.490.000 millas (4.007.000 km)

Tripulación

Al fondo: I-D: Walker, Resnik

En primer plano I-D: Mullane, Hawley, Hartsfield, Coats

La STS-41-D fue una misión del transbordador espacial de la NASA usando el transbordador espacial Discovery. Fue la duodécima misión del transbordor, y el primer vuelo del Discovery.

Tripulación

•

Henry Hartsfield (2), Jr., Comandante • Michael Coats (1), Piloto

Lo más destacado de la misión [editar

El orbitador Discovery fue lanzado en su vuelo inaugural (el nº 12 en el programa) el

]

30 de agosto de 1984. Fue el tercero construido y fue el más ligero de todos de lejos por el bajo peso de los materiales de su escudo térmico.


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


http://es.wikipedia.org/wiki/30_de_agosto�


http://es.wikipedia.org/wiki/5_de_septiembre�


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



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

http://es.wikipedia.org/wiki/NASA�




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

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

http://es.wikipedia.org/w/index.php?title=STS-41-D&action=edit&section=3�





La misión en un principio estaba planeada para el 25 de junio, pero por diversos problemas técnicos, incluyendo el translado al VAB para reemplazar un motor principal, el lanzamiento se llevó a cabo hasta las 8:41 a.m. EDT, el 30 de agosto, después de un retraso de 6 minutos y 50 segundos por la entrada de un avión privado en el espacio aéreo restringido, cerca de la plataforma de despegue. Fue al cuarto intento de lanzamiento para el Discovery. El intento de lanzamiento de junio significó ser la primera vez que una nave espacial tripulada sufría el apagado de sus motores justo antes del lanzamiento, desde el Gemini 6A.

El lanzamiento del STS-41-D.

Por el retraso de dos meses, se canceló la misión STS 41-F (la STS 41-E ya estaba cancelada) y su carga útil principal se incluyó al vuelo STS 41-D. En total la carga sobrepaso las 47.000 lb (21.000 kg), un récord par el transbordador hasta la fecha.

Los seis tripulantes de la tripulación eran Henry W. Hartsfield Jr., comandante, en su segunda misión en el transbordador; el piloto Michael L. Coats; los tres especialistas de la misión: — Judith A. Resnik, Richard M. Mullane y Steven A. Hawley; y un especialista de la carga, Charles D. Walker, un empleado de la corporación McDonnell Douglas. Walker fue el primer especialista de carga con un patrocinador en volar abordo del transbordador.

La carga primaria consistía en tres satélites de comunicaciones, SBS-D para Satellite Business Systems, Telstar 3-C para Telesat (Canada) y el SYNCOM IV-2, ó Leasat-2, un enorme satélite arrendado a la Marina. El Leasat-2 fue el primer gran satélite de comunicaciones diseñado específicamente para ser desplegado por el transbordador espacial. Los tres satélites se fueron desplegados sin problemas y quedaron operativos.

Otra carga que llevaba fue el panel solar OAST-l, un dispositivo de 13 pies (4 m) de ancho, y 102 pies (31 m) de alto, plegado en un paquete de 7 pulgadas (180 mm) de profundidad. El ala portaba diferentes tipos de células fotovoltaicas experimentales y varias veces fue extendida hasta su mayor amplitud. Con lo que se convirtió en la estructura más grande jamas extendida

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

http://es.wikipedia.org/wiki/VAB�

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http://es.wikipedia.org/wiki/Gemini_6A�

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

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



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http://es.wikipedia.org/wiki/C%C3%A9lula_fotovoltaica�

desde un vehículo tripulado y, demostró la viabilidad los grandes paneles solares ligeros para futuras aplicaciones en instalaciones de gran envergadura como la Estación espacial.

El experimento Continuous Flow Electrophoresis System (CFES) patrocinado por McDonnell Douglas, usando células vivas, fue más elaborado que su antecesor y el especialista de carga Walker lo dirigió más de 100 horas durante el vuelo. Se realizó el experimento de un estudiante para estudiar el crecimiento de los cristales en microgravedad. Con una cámara IMAX se filmaron los mejores momentos de la misión, que luego se pudieron ver en la película The Dream is Alive.

La misión duró 6 días, 56 minutos, con el aterrizaje en la pista 17 de la Edwards AFB, a las 8:37 a.m. PDT, el 5 de septiembre. Viajó 2,21 millones de millas (3,6 milliones de km) e hizo 97 orbitas. El 10 de septiembre fue transportado de regreso al KSC.

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

http://es.wikipedia.org/wiki/IMAX�

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



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






Description

The 13th flight of the Space Shuttle (STS 41-G) carried theOSTA-3 (Office of Space and Terrestrial Applications) payloaddesigned for conducting experiments in earth remote sensing.This experiment payload consisted of 1) a Shuttle ImagingRadar (SIR-B) for studies of the earth's surface, 2) a LargeFormat Camera (LFC) for cartographic mappings of the earth,3) a Measurement of Air Pollution from Satellite (MAPS)experiment to determine the distribution of CO in theatmosphere, and 4) a Feature Identification and LocationExperiment (FILE) for classification of surface materials. TheSIR-B was an upgraded version of the SIR-A flown on theOSTA-1 payload during the STS-2 mission (NSSDC ID 81-111A-01). The MAPS and FILE sensors were the reflies ofthose same instruments on the OSTA-1 payload (NSSDC ID81-111A-04 and 81-111A-03). The mission lasted 8 days and,except for SIR-B, all instruments met their prelaunchrequirements.

STS 41G

NSSDC ID: 1984-108A

Alternate Names

OSTA 3/STS 41G

STS 13

15353

Facts in Brief


Funding Agencies



Disciplines

Communications

Earth Science

Human Crew


Launch/Orbitalinformation for STS 41G

Experiments on STS 41G

Data collections from STS41G



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=STS 41G

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=STS 41G

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=STS 41G

mailto:[email protected]?Subject=NMC Comment/Question: STS 41G (1984-108A)





Personnel


Dr. Mark Settle Program Scientist NASA Headquarters

Mr. Louis J. Demas Program Manager NASA Headquarters


http://www.usa.gov/




STS-41-G

Datos de la misión

Misión STS-41-G Transbordador Challenger Plataforma de lanzamiento 39-A Lanzamiento 5 de octubre de 1984 11:03:00 UTC Aterrizaje 13 de octubre de 1984 16:26:33 UTC Centro Espacial Kennedy Duración 8 días, 5 horas, 23 min y 33 s Altitud orbital 404 kilómetros Inclinación orbital 57 grados Distancia recorrida 5,293,847 kilómetros

Tripulación

Al frente, Izq. a Der.: Jon A. McBride, Sally K. Ride, Kathryn D. Sullivan and David C. Leestma. Al fondo, Izq. a Der.: Paul D. Scully-Power, Robert L. Crippen and Marc Garn




http://es.wikipedia.org/wiki/5_de_octubre�



http://es.wikipedia.org/wiki/13_de_octubre�











Description

STS 51-A was the second Discovery shuttle flight. On boardwere Frederick Hauck, David Walker, Joseph Allen, AnnaFisher, and Dale Gardner. Canadian communications satelliteTELESAT-H (ANIK), attached to Payload Assist Module-D(PAM-D), was deployed into geosynchronous orbit on flight daytwo. On third day, defense communications satellite SYNCOMIV-I (also known as LEASAT-1) was deployed. Allen andGardner, wearing jet-propelled manned maneuvering units,retrieved two malfunctioning satellites: PALAPA-B2 andWESTAR-VI, both deployed on Mission 41-B. Fisher operatedthe remote manipulator system, grappling the satellites anddepositing them in the payload bay. Middeck payloadsconsisted of: Diffusive Mixing of Organic Solutions (DMOS),and Radiation Monitoring Equipment (RME). The missionduration was 191 hours 44 minutes 56 seconds.

STS 51A

NSSDC ID: 1984-113A

Alternate Names

STS 14

15382

Facts in Brief


Funding Agency


Discipline

Human Crew


Launch/Orbitalinformation for STS 51A

Experiments on STS 51A

Data collections from STS51A



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=STS 51A

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=STS 51A

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=STS 51A

mailto:[email protected]?Subject=NMC Comment/Question: STS 51A (1984-113A)



http://www.usa.gov/




STS-51-A

Datos de la misión

Misión STS-51-A Transbordador Discovery Plataforma de lanzamiento 39-A Lanzamiento 8 de noviembre de 1984 12:15:00 UTC Aterrizaje 16 de noviembre de 1984 11:59:56 UTC Centro Espacial Kennedy, Pista 15 Duración 7 días, 23 horas, 44 min y 56 s Altitud orbital 343 kilometros Inclinación orbital 28.5 grados Distancia recorrida 5,293,786 kilometros

Tripulación

Izq-Der: Gardner, Walker, Fisher, Hauck, Allen

STS-51-A fue la misión catorce del programa STS y la número dos del transbordador Discovery. La misión tuvo una misión unica al lanzar dos satélites de comunicación y recuperar a otros dos que se encontraban en una órbita incorrecta.

• Masa: o Orbitador al despegue: 119,441 kg o Orbitador al aterrizaje: 94,120 kg o Carga: 20,550 kg

• Perigeo: 289 km • Apogeo: 297 km




http://es.wikipedia.org/wiki/8_de_noviembre�



http://es.wikipedia.org/wiki/16_de_noviembre�










http://es.wikipedia.org/wiki/Sat%C3%A9lite_artificial�


http://es.wikipedia.org/wiki/Masa�

http://es.wikipedia.org/wiki/Perigeo�

http://es.wikipedia.org/wiki/Apogeo�

• Inclinación: 28.4° • Periodo orbital: 90.4 min

http://es.wikipedia.org/wiki/Inclinaci%C3%B3n�

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




Description

TELECOM 1A

NSSDC ID: 1984-081B

Alternate Names

15159

Facts in Brief


Funding Agency

France Telecom (France)

Discipline

Communications


Launch/Orbitalinformation for TELECOM1A

Experiments on TELECOM1A

Data collections fromTELECOM 1A



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: TELECOM 1A (1984-081B)



http://www.usa.gov/







Description

Telstar 3C was an AT&T communications satellite deployed bythe shuttle Discovery during the STS-41D mission. It wasplaced in a geosynchronous orbit at 86 degrees W and had adesign life of 10 years. The spacecraft was launched with themain communications reflector and the outer cylinder stowed,a configuration the made it possible to launch either withexpendable rocket boosters or from the space shuttle. Thecompact stowed configuration allowed the spacecraft to standupright in the cargo bay, occupying a minimum of linear space.It was 7 feet, 1 inch (2.16 meters) in diameter. Its height withantennas and the telescoping solar panel deployed was 22feet, 5 inches (6.84 meters). Like their predecessor satellites,the Telstar 3 satellites operated at 6/4 GHz (C-band).Simultaneous long distance telephone call capacity was21,600. The satellite furnished voice, video, and high speeddata services to the continental US, Hawaii, Alaska, andPuerto Rico.

Telstar 3C

NSSDC ID: 1984-093D

Alternate Names

15237

Facts in Brief


Funding Agency

American Telephone andTelegraph Company(United States)

Discipline

Communications


Launch/Orbitalinformation for Telstar 3C

Experiments on Telstar 3C

Data collections fromTelstar 3C



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Telstar 3C (1984-093D)



http://www.usa.gov/







Description

The experiments selected to be part of the UOSAT 2 payloadhad several objectives which included the following: to providethe educational community with an operational scientificsatellite which could be utilized with a minimal ground station;to provide the scientific community with a new source of datato aid in the understanding of the electro-magnetic propertiesof the near earth environment; and to provide the amateurradio community with a full complement of instruments for thestudy and monitoring of radio propagation conditions from highfrequency to microwave. In order to meet these objectives thefollowing instruments comprised the UOSAT 2 payload; atriaxial fluxgate magnetometer with a resolution of plus orminus 2 nT and maximum vector sample rate of 6.25 per s;two charged particle counters with threshold energies of 20and 60 keV; four phase-referenced high-frequency beacons at7, 14, 21, and 28 MHz; two microwave beacons at 2.4 and10.47 GHz; and a CCD earth-imaging camera with 2 kmresolution, and spectral response of 0.4 -1.0 micrometers. OneVHF and one UHF telemetry channel provided data instandard FSK ASCII at a variety of baud rates, as well asMorse code and synthesized voice formats. Though thedescriptions are the same, there were some differencesbetween UOSAT 2 and UOSAT experiments.

UOSAT 2

NSSDC ID: 1984-021B

Alternate Names

Oscar 11

14781

Facts in Brief

Launch Date: 1984-03-01Launch Vehicle: DeltaLaunchSite: Vandenberg AFB,United StatesMass: 52.0 kg

Funding Agencies

Radio Amateur SatelliteCorporation (UnitedStates)

University of Surrey(United Kingdom)

Disciplines

Communications

Space Physics


Launch/Orbitalinformation for UOSAT 2

Experiments on UOSAT 2

Data collections fromUOSAT 2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: UOSAT 2 (1984-021B)





Personnel


Dr. M. N. Sweeting ProjectManager

University of Surrey

Mr. Richard L.Daniels

ProgramManager

NASA Headquarters

Dr. Ronald A.Parise

ProjectScientist

AMSAT Corporation [email protected]

Dr. J. A. King ProgramScientist

AMSAT Corporation


http://www.usa.gov/







Description

DSP F12 was part of the oldest segments of North America'searly warning system. These Defense Support Systemsatellites were the space-based segment of a 2-tiered ballisticmissile launch detection and warning system. Orbiting 23,000mile above Earth, these satellites provided the first look atpotentially hostile ballistic missiles launched from land or sea,anywhere in the world, in near-real time. For tactical missilewarning, satellite data could be transmitted directly to thetheater commander via the Tactical Event System. DSPsensors also detected nuclear detonations. The speed andaccuracy have greatly reduced the potential for surprise attackand is vital to effective deterrance to war. The DSP sytem hasone satellite watching the eastern hemisphere and twospacecraft watching the western hemisphere for missilelaunches. Since there was less time associated with asubmarine launch from a Soviet boat at the US mainland,these was a great concern that this type of missile must bedetected.

The satellite's infrared sensors detected and tracked exhaustheat generated by balistic missiles. The data were thenrelayed almost instantaneously to USSPACECOM MissileWarning Center in the Cheyenne Mountain Complex. DSPsatellites were used during the Persian Gulf War to detect IragiScud missile launches.

USA 7

NSSDC ID: 1984-129A

Alternate Names

DSP F12

15453

Facts in Brief


Funding Agency


Discipline



Launch/Orbitalinformation for USA 7

Experiments on USA 7

Data collections from USA7


Image courtesy of the USAF Defense Support Program.


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


USA 7




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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: USA 7 (1984-129A)

mailto:[email protected]?Subject=NMC Comment/Question: USA 7 (1984-129A)

http://nssdc.gsfc.nasa.gov/image/spacecraft/dsp_f12.jpg

http://www.usa.gov/







Description

This spacecraft mission combined a Venus swingby and aComet Halley flyby. Two identical spacecraft, Vega 1 andVega 2, were launched December 15 and 21, 1984,respectively. After carrying Venus entry probes to the vicinity ofVenus (arrival and deployment of probes were scheduled forJune 11-15, 1985), the two spacecraft were retargetted usingVenus gravity field assistance to intercept Comet Halley inMarch 1986. The first spacecraft encountered Comet Halley onMarch 6, 1986, and the second three days later. The flybyvelocity was 77.7 km/s. Although the spacecraft could betargetted with a precision of 100 km, the position of thespacecraft relative to the comet nucleus was estimated to beknown only to within a few thousand kilometers. This, togetherwith the problem of dust protection, led to estimated flybydistances of 10,000 km for the first spacecraft and 3000 km forthe second.

Spacecraft and SubsystemsThe spacecraft was three-axis stabilized. Its main featureswere large solar panels, a high-gain antenna dish, and anautomatic pointing platform carrying those experiments thatrequired pointing at the comet nucleus. The automatic platformcould rotate through + or -110 deg and + or -40 deg in twoperpendicular directions with a pointing accuracy of 5 arc-minand a stability of 1 arc-min/s. It carried the narrow- and thewide-angle camera, the three-channel spectrometer, and theinfrared sounder. All other experiments were body-mounted,with the exception of two magnetometer sensors mounted on a2-m boom and various plasma probes and plasma wavwanalyzers mounted on a 5-m boom. The total scientificpayloadweighed 125 kg and had a data rate of 65 kbs in fast telemetrymode for encounter. There was also a slow telemetry mode forthe cruise mode. The comet-encounter science data-take wasfrom 2.5 h before until 0.5 h after the closest approach, withseveral periods of data-take before and after, each lastingabout 2 h. Continuous coverage for plasma and dustinstruments was provided by an onboard memory (5-megabittape recorder). The spacecraft was shielded from hypervelocitydust impacts by a shield consisting of a 100-micrometermultilayer sheet 20 to 30 cm from the spacecraft, and a 1-mmAl sheet 5 to 10 cm from the spacecraft. Approximately half ofthe VEGA spacecraft was devoted to the Halley module, andhalf to the Venus lander package. The total scientific payloadweight was 144.3 kg.

Venus Descent ModuleThe Venus package consisted of a sphere 240 cm in diameter,which separated two days before arrival at Venus and enteredthe planet's atmosphere on an inclined path, without active

Vega 1

NSSDC ID: 1984-125A

Alternate Names

Venera-Halley 1

15432

Facts in Brief


Funding Agency

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

Disciplines

Planetary Science

Space Physics


Launch/Orbitalinformation for Vega 1

Experiments on Vega 1

Data collections from Vega1

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


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


Vega 1



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

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


mailto:[email protected]?Subject=NMC Comment/Question: Vega 1 (1984-125A)


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



maneuvers, as was done on previous Venera missions. Thelander probe was identical to those of Venera 9 through 14and similarly had two objectives, the study of the atmosphereand the study of the superficial crust. In addition totemperature and pressure measuring instruments, the descentprobe carried a UV spectrometer for measurement of minoratmospheric constituents, an instrument dedicated tomeasurement of the concentration of H2O, and otherinstruments for determination of the chemical composition ofthe condensed phase: a gas-phase chromatograph; an X-rayspectrometer observing the fluorescence of grains or drops;and a mass spectrograph measuring the chemical compositionof the grains or drops. The X-ray spectrometer separated thegrains according to their sizes using a laser imaging device,while the mass spectrograph separated them according to theirsizes using an aerodynamical inertial separator. After landing,a small surface sample near the probe was to be analyzed bygamma spectroscopy and X-ray fluorescence. The UVspectrometer, the mass spectrograph, and the pressure- andtemperature-measuring instruments were developed incooperation between French and Soviet investigators.

Balloon AerostatIn addition to the lander probe, a constant-pressureinstrumented balloon aerostat was deployed after entry into theatmosphere from the upper heat protection hemisphere. Itfloated at approximately 50 km altitude in the middle, mostactive layer of the Venus three-tiered cloud system. Data fromthe balloon instruments were transmitted directly to Earth forthe 47-hr lifetime of the mission. For more on the balloons,see:

http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1984-125F

Personnel


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

Selected References

Reinhard, R., Space missions to Halley's comet and related activities, ESA Bull., No. 29, 68-83,Feb. 1982.

Sagdeev, R. Z., et al., Vega spacecraft encounters with comet Halley, Nature, 321, No. 6067,259-262, May 1986.

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

Additional Information About Vega at NSSDC

Vega 1 Descent CraftVega 1 BalloonVega 2



Vega mission profile and the Vega atmospheric probeVega atmospheric probe model on display at the NPO Lavochkin Museum(Probe image courtesy of Alexander Chernov and the Virtual Space Museum)

Vega 1 Halley data on CD-ROMOrder the International Halley Watch CD-ROMsMore on the International Halley Watch CD-ROMs

Other International Halley Watch Missions

GiottoICESakigakeSuisei

Related Information at NSSDC

Venus pageComet page


http://nssdc.gsfc.nasa.gov/image/spacecraft/vega-mission.jpg

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

http://vsm.host.ru/emain.htm

http://nssdc.gsfc.nasa.gov/planetary/ihw2526.html

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

http://nssdc.gsfc.nasa.gov/nmc/datasetDisplay.do?id=PSSB-00049





http://nssdc.gsfc.nasa.gov/image/spacecraft/vega_1-2.jpg

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

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

http://www.usa.gov/







Description

A constant-pressure instrumented balloon aerostat wasdeployed from the upper heat protection hemisphere of each ifthe two Vega lander craft immediately after entry into theatmosphere. The primary scientific objective of the Vegaballoon probes was to obtain information about the large- andsmall-scale motions, structure, and cloud properties of theVenus atmosphere at the float altitude. The probes floated atan altitude of about 54 km in the middle, most active layer ofthe Venus three-tiered cloud system and measured the localatmospheric dynamics, pressure, temperature, lightning,illumination levels, and cloud properties over a period of about46 hours in both the night- and day-side.

Spacecraft and SubsystemsThe Vega balloon probe comprised a 3.4 meter diameterballoon and a gondola, suspended below the balloon by a 13meter long tether strap. The total mass of the deployed balloonprobe was 21.5 kg: 12.5 kg for the balloon and tether, 6.9 kgfor the gondola, and 2.1 kg of helium in the balloon. Theballoon, gondola, parachute, ballast, tanks of helium, andtiming electronics and pyrotechnic release devices with a totalmass of 120 kg were stored in a toroidal compartmentsurrouding the lander antenna before deployment.

The balloon was made of a teflon cloth matrix coated withteflon film and filled with helium to 30 mbar overpressure. Thediffusion of helium from the balloon was slow enough that theballoon would outlast the probe battery lifetime, losing lessthan 5% of its helium and 500 meters of altitude. The balloonitself was transparent to the downlink radio frequency used.

The gondola was 1.2 meters high and had three parts,connected by straps. The upper section, connected to thetether, was a 37 cm long, 15 degree half-angle conicalantenna 14 cm diameter at its base. The middle section wasconnected by two straps to the upper section with dimensionsapproximately 40.8 x 14.5 x 13.0 cm. The upper part of thesection contained a radio transmitter and modulator, data-handling system, and signal-processing and power-regulatingelectronics. The lower part had pressure and illuminationsensors and a deployable arm which held temperature sensorsand an anemometer. The lower section was 9.0 x 14.5 x 15.0cm, was also connected to the middle section by two straps,and held the batteries and nephelometer. The gondola waspainted with a white coating that resisted corrosion by sulfuricacid and increased the surface albedo.

The radio transmitter had two modes of operation. In telemetry,or TM, mode a 30 second transmission of pure carrier signal

Vega 1 Balloon

NSSDC ID: 1984-125F

Alternate Names

15859

Facts in Brief


Funding Agency


Discipline

Planetary Science


Launch/Orbitalinformation for Vega 1Balloon

Experiments on Vega 1Balloon

Data collections from Vega1 Balloon


Selected References

Sagdeev, R. Z., et al., TheVEGA Venus balloonexperiment, Science, 231, No.4744, 1407, Mar. 1986.


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


Vega 1 Balloon




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


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


mailto:[email protected]?Subject=NMC Comment/Question: Vega 1 Balloon (1984-125F)


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



for use in the VLBI tracking was followed by a 270 secondperiod of transmission of 900 bits (at 4 bits/s for the first 840bits and 1 bit/s for the last 60) of data collected over theprevious 30 minutes, followed by another 30 second carriertransmission. In coordinated transmission (KI) mode two toneswith a suppressed carrier were transmitted for 330 seconds foruse in the VLBI tracking. Three consecutive TM transmissionsand one KI were made every 2 hours during the first 10 hoursand from roughly hours 22 to 34 of the flight, at other timesone TM and one KI transmission were made every two hoursto conserve battery power. The carrier signal frequency was1.6679 GHz and the radiated power was about 4.5 W. Thepower supply consisted of 1 kg of lithium batteries with 250 W-hrs capacity and an expected life of 46 to 52 hours.

Twenty ground stations were used for Very Long BaselineInterferometry (VLBI) tracking of the balloons. Six of thesestations were on Soviet territory and were coordinated by IKI,the Soviet space agency. The other fourteen antennas werecoordinated by CNES (France) and included three NASA DeepSpace Network antennas and eleven radio astronomyobservatories.

Mission ProfileThe Vega 1 Lander/Balloon capsule entered the Venusatmosphere (125 km altitude) at 2:06:10 UT (Earth receivedtime; Moscow time 5:06:10 a.m.) on 11 June 1985 at roughly11 km/sec. At approximately 2:06:25 UT the parachuteattached to the landing craft cap opened at an altitude of 64km. The cap and parachute were released 15 seconds later at63 km altitude. The balloon package was pulled out of itscompartment by parachute 40 seconds later at 61 km altitude,at 8.1 degrees N, 176.9 degrees east. A second parachuteopened at an altitude of 55 km, 200 seconds after entry,extracting the furled balloon. The balloon was inflated 100seconds later at 54 km and the parachute and inflation systemwere jettisoned. The ballast was jettisoned when the balloonreached roughly 50 km and the balloon floated back to a stableheight between 53 and 54 km some 15 to 25 minutes afterentry. The mean stable height was 53.6 km, with a pressure of535 mbar and a temperature of 300-310 K in the middle, mostactive layer of the Venus three-tiered cloud system. Theballoon drifted westward in the zonal wind flow with an averagespeed of about 69 m/s at nearly constant latitude. The probecrossed the terminator from night to day at 12:20 UT on 12June after traversing 8500 km. The probe continued to operatein the daytime until the final transmission was received at00:38 UT on 13 June from 8.1 N, 68.8 E after a total traversedistance of 11,600 km. It is not known how much further theballoon travelled after the final communication.

Kremnev, R. S., et al., VEGABalloon System andInstrumentation, Science,231, No. 4744, 1408, Mar.1986.

Sagdeev, R. Z., and V. I.Moroz, Project Vega firststage: missions to Venus,Sov. Astron. Lett., 12, No. 1,Jan.-Feb. 1986.

Sagdeev, R. Z., et al., TheVEGA balloon experiments,Sov. Astron. Lett., 12, No. 1,3, Jan.-Feb. 1986.

Kremnev, R. S., et al., TheVega balloons - A tool forstudying atmospheredynamics on Venus, Sov.Astron. Lett., 12, No. 1, 7,Jan.-Feb. 1986.

Vega 1 SpacecraftVega 1 LanderVega 2 Balloon - Informationon Vega 1's companionmission

Vega atmospheric probemodel on display at the NPOLavochkin Museum(Probe image courtesy ofAlexander Chernov and theVirtual Space Museum)

Venus home page



http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1984-125A

http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1984-125E

http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1984-128F



http://www.usa.gov/







Description

The Vega 1 lander probe was identical to those of Venera 9through 14 and similarly had two objectives, the study of theatmosphere and the study of the superficial crust. The landerconsisted of a hemispherical insulated pressure vesselmounted with shock absorbers on a deformable landing ring.On top of the pressure vessel was a disc-shaped aerobrakewhich also served as a reflector for the cylindrical fixedcommunications antenna above it. The lander was held duringthe cruise to Venus and atmospheric entry in an insulated heatprotection sphere 240 cm in diameter, consisting of an upperand lower hemisphere joined nonhermetically.

InstrumentationIn addition to temperature and pressure measuringinstruments, the descent probe carried an ISAV UVspectrometer for measurement of minor atmosphericconstituents, a VM-4 hygrometer dedicated to measurement ofthe concentration of H2O, an IPF aerosol analyzer, an ISAV-Aparticle size spectrometer/nephelometer and other instrumentsfor determination of the chemical composition of thecondensed phase: a Sigma 3 gas-phase chromatograph; aBDRP-AM25 X-ray spectrometer observing the fluorescenceof grains or drops; and a Malachite mass spectrographmeasuring the chemical composition of the grains or drops.The X-ray spectrometer separated the grains according to theirsizes using a laser imaging device, while the massspectrograph separated them according to their sizes using anaerodynamical inertial separator. After landing, a small surfacesample near the probe was to be collected by a drilling deviceand analyzed by a GS-15-SCV gamma ray spectrometer andX-ray fluorescence spectrometer. The UV spectrometer, themass spectrograph, and the pressure- and temperature-measuring instruments were developed in cooperationbetween French and Soviet investigators. Data collected by theinstruments were transmitted to the Vega 1 spacecraft andrelayed to Earth.

Mission ProfileThe lander separated from the Vega 1 spacecraft two daysbefore arrival at Venus and entered the planet's atmosphereon an inclined path, without active maneuvers, as was done onprevious Venera missions. (The flyby spacecraft was thenretargetted using Venus gravity assistance to intercept CometHalley in March 1986.) After separation from the Vega 1spacecraft the lander entered the Venus atmosphere on 11June 1985 at 01:59:49 UT at 10.75 km/s with an entry angle of18.23 degrees. The pilot parachute was deployed at 02:00:27UT at an altitude of 65 km and the braking parachute opened11 seconds later at 64.5 km. The upper heat protection

Vega 1 Descent Craft

NSSDC ID: 1984-125E

Alternate Names

Vega 1 Lander

Vega 1 Balloon Aerostat

15858

Facts in Brief


Funding Agency


Discipline

Planetary Science


Launch/Orbitalinformation for Vega 1Descent Craft

Experiments on Vega 1Descent Craft

Data collections from Vega1 Descent Craft



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Vega 1 Descent Craft


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Vega 1 Descent Craft


mailto:[email protected]?Subject=NMC Comment/Question: Vega 1 Descent Craft (1984-125E)


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



hemisphere was released at this time and the lowerhemisphere 4 seconds later at 64.2 km. The upper hemispherecontained the deployment system for the balloon aerostats.The parachute was released at 02:09:37 at 47 km. After thisthe lander was allowed to aerobrake through the thick Venusatmosphere, with drag devices minimizing vibrations and spinand providing stability. At an altitude of 18 km a mechanicalshock of unknown origin (possibly due to a jammed valve in anupper compartment suddenly releasing) triggered a ground-contact accelerometer which caused early deployment of thesoil drill of the X-ray flourescence spectrometer. This drill wasrendered unusable at landing due to the prematuredeployment. A toroidal system similar to that on Veneras 13and 14 was designed to absorb shock on landing. The landertouched down at 03:02:54 UT on 11 June 1985 at 7.5 N, 177.7E, just north of eastern Aphrodite Terra. The altitude of thetouchdown site was 0.6 km below the planetary mean radius.The measured pressure at the landing site was 95 atm and thetemperature was 740 K. The balloon measured downwardgusts of 1 meter/s and showed horizontal wind velocities up to240 km/hr.

Balloon AerostatsIn addition to the lander probe, a constant-pressureinstrumented balloon aerostat was deployed after entry into theatmosphere from the upper heat protection hemisphere. Itfloated at approximately 50 km altitude in the middle, mostactive layer of the Venus three-tiered cloud system. Data fromthe balloon instruments were transmitted directly to Earth forthe 47-hr lifetime of the mission. For more on the balloons,see:


Personnel



Selected References


Surkov, Yu. A., et al., Uranium, thorium, and potassium in the Venusian rocks at the landingsites of Vega 1 and 2, J. Geophys. Res., 92, No. B4, E537-E540, Mar. 1987.

Surkov, Yu. A., et al., The water vapor content profile in the Venusian atmosphere according tothe results of experiments from Vega 1 and 2, J. Geophys. Res., 91, No. B13, E219-E221, Nov.1986.

Sagdeev, R. Z., and V. I. Moroz, Project Vega first stage: missions to Venus, Sov. Astron. Lett.,12, No. 1, Jan.-Feb. 1986.





Vega 1 SpacecraftVega 1 BalloonVega 2 Lander - Information on Vega 1's companion mission

Vega atmospheric probeModel on display at the NPO Lavochkin Museum(Probe image courtesy of Alexander Chernov and the Virtual Space Museum)

Venus home page









http://www.usa.gov/







Description

This spacecraft mission combined a Venus swingby and aComet Halley flyby. Two identical spacecraft, Vega 1 andVega 2, were launched December 15 and 21, 1984,respectively. After carrying Venus entry probes to the vicinity ofVenus (arrival and deployment of probes were scheduled forJune 11-15, 1985), the two spacecraft were retargetted usingVenus gravity field assistance to intercept Comet Halley inMarch 1986. The first spacecraft encountered Comet Halley onMarch 6, 1986, and the second three days later. The flybyvelocity was 77.7 km/s. Although the spacecraft could betargetted with a precision of 100 km, the position of thespacecraft relative to the comet nucleus was estimated to beknown only to within a few thousand kilometers. This, togetherwith the problem of dust protection, led to estimated flybydistances of 10,000 km for the first spacecraft and 3000 km forthe second.

Spacecraft and SubsystemsThe spacecraft was three-axis stabilized. Its main featureswere large solar panels, a high-gain antenna dish, and anautomatic pointing platform carrying those experiments thatrequired pointing at the comet nucleus. The automatic platformcould rotate through + or -110 deg and + or -40 deg in twoperpendicular directions with a pointing accuracy of 5 arc-minand a stability of 1 arc-min/s. It carried the narrow- and thewide-angle camera, the three-channel spectrometer, and theinfrared sounder. All other experiments were body-mounted,with the exception of two magnetometer mounted on a 2-mboom and various plasma probes and plasma wave analyzersmounted on a 5-m boom. The total scientific payload weighed125 kg and had a data rate of 65 kbs in fast telemetry modefor encounter. There was also a slow telemetry mode for thecruise mode. The comet-encounter science data-take was from2.5 h before until 0.5 h after the closest approach, with severalperiods of data-take before and after, each lasting about 2 h.Continuous coverage for plasma and dust instruments wasprovided by an onboard memory (5-megabit tape recorder).The spacecraft was shielded from hypervelocity dust impactsby a shield consisting of a 100-micrometer multilayer sheet 20to 30 cm from the spacecraft, and a 1-mm Al sheet 5 to 10 cmfrom the spacecraft. Approximately half of the Vega spacecraftwas devoted to the Halley module, and half to the Venuslander package. The total scientific payload weight was 144.3kg.

Venus Descent ModuleThe Venus package consisted of a sphere 240 cm in diameter,which separated two days before arrival at Venus and enteredthe planet's atmosphere on an inclined path, without active

Vega 2

NSSDC ID: 1984-128A

Alternate Names

Venera-Halley 2

15449

Facts in Brief


Funding Agency


Disciplines

Planetary Science

Space Physics


Launch/Orbitalinformation for Vega 2

Experiments on Vega 2

Data collections from Vega2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


Vega 2



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





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



maneuvers, as was done on previous Venera missions. Thelander probe was identical to those of Venera 9 through 14and similarly had two objectives, the study of the atmosphereand the study of the superficial crust. In addition totemperature and pressure measuring instruments, the descentprobe carried a UV spectrometer for measurement of minoratmospheric constituents, an instrument dedicated tomeasurement of the concentration of H2O, and otherinstruments for determination of the chemical composition ofthe condensed phase: a gas-phase chromatograph; an X-rayspectrometer observing the fluorescence of grains or drops;and a mass spectrograph measuring the chemical compositionof the grains or drops. The X-ray spectrometer separated thegrains according to their sizes using a laser imaging device,while the mass spectrograph separated them according to theirsizes using an aerodynamical inertial separator. After landing,a small surface sample near the probe was to be analyzed bygamma spectroscopy and X-ray fluorescence. The UVspectrometer, the mass spectrograph, and the pressure- andtemperature-measuring instruments were developed incooperation between French and Soviet investigators.

Balloon AerostatsIn addition to the lander probe, a constant-pressureinstrumented balloon aerostat was deployed after entry into theatmosphere from the upper heat protection hemisphere. Itfloated at approximately 50 km altitude in the middle, mostactive layer of the Venus three-tiered cloud system. Data fromthe balloon instruments were transmitted directly to Earth forthe 47-hr lifetime of the mission. For more on the balloons,see:

http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1984-128F

Personnel



Selected References

Reinhard, R., Space missions to Halley's comet and related activities, ESA Bull., No. 29, 68-83,Feb. 1982.

Sagdeev, R. Z., et al., Vega spacecraft encounters with comet Halley, Nature, 321, No. 6067,259-262, May 1986.


Additional Information About Vega at NSSDC

Vega 2 Descent CraftVega 2 BalloonVega 1



Vega mission profile and the Vega atmospheric probeVega atmospheric probe model on display at the NPO Lavochkin Museum(Probe image courtesy of Alexander Chernov and the Virtual Space Museum)

Vega 2 Halley data on CD-ROMOrder the International Halley Watch CD-ROMsMore on the International Halley Watch CD-ROMs

Other International Halley Watch Missions

GiottoICESakigakeSuisei

Related Information at NSSDC

Venus pageComet page





http://nssdc.gsfc.nasa.gov/planetary/ihw2526.html

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

http://nssdc.gsfc.nasa.gov/nmc/datasetDisplay.do?id=PSSB-00049





http://nssdc.gsfc.nasa.gov/image/spacecraft/vega_1-2.jpg


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

http://www.usa.gov/







Description

A constant-pressure instrumented balloon aerostat wasdeployed from the upper heat protection hemisphere of each ifthe two Vega lander craft immediately after entry into theatmosphere. The primary scientific objective of the Vegaballoon probes was to obtain information about the large- andsmall-scale motions, structure, and cloud properties of theVenus atmosphere at the float altitude. The probes floated atan altitude of about 54 km in the middle, most active layer ofthe Venus three-tiered cloud system and measured the localatmospheric dynamics, pressure, temperature, lightning,illumination levels, and cloud properties over a period of about46 hours in both the night- and day-side.

Spacecraft and SubsystemsThe Vega balloon probe comprised a 3.4 meter diameterballoon and a gondola, suspended below the balloon by a 13meter long tether strap. The total mass of the deployed balloonprobe was 21.5 kg: 12.5 kg for the balloon and tether, 6.9 kgfor the gondola, and 2.1 kg of helium in the balloon. Theballoon, gondola, parachute, ballast, tanks of helium, andtiming electronics and pyrotechnic release devices with a totalmass of 120 kg were stored in a toroidal compartmentsurrouding the lander antenna before deployment.

The balloon was made of a teflon cloth matrix coated withteflon film and filled with helium to 30 mbar overpressure. Thediffusion of helium from the balloon was slow enough that theballoon would outlast the probe battery lifetime, losing lessthan 5% of its helium and 500 meters of altitude. The balloonitself was transparent to the downlink radio frequency used.

The gondola was 1.2 meters high and had three parts,connected by straps. The upper section, connected to thetether, was a 37 cm long, 15 degree half-angle conicalantenna 14 cm diameter at its base. The middle section wasconnected by two straps to the upper section with dimensionsapproximately 40.8 x 14.5 x 13.0 cm. The upper part of thesection contained a radio transmitter and modulator, data-handling system, and signal-processing and power-regulatingelectronics. The lower part had pressure and illuminationsensors and a deployable arm which held temperature sensorsand an anemometer. The lower section was 9.0 x 14.5 x 15.0cm, was also connected to the middle section by two straps,and held the batteries and nephelometer. The gondola waspainted with a white coating that resisted corrosion by sulfuricacid and increased the surface albedo.

The radio transmitter had two modes of operation. In telemetry,or TM, mode a 30 second transmission of pure carrier signal

Vega 2 Balloon

NSSDC ID: 1984-128F

Alternate Names

15857

Facts in Brief


Funding Agency


Discipline

Planetary Science


Launch/Orbitalinformation for Vega 2Balloon

Experiments on Vega 2Balloon

Data collections from Vega2 Balloon


Selected References

Sagdeev, R. Z., et al., TheVEGA Venus balloonexperiment, Science, 231, No.4744, 1407, Mar. 1986.


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


Vega 2 Balloon










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for use in the VLBI tracking was followed by a 270 secondperiod of transmission of 900 bits (at 4 bits/s for the first 840bits and 1 bit/s for the last 60) of data collected over theprevious 30 minutes, followed by another 30 second carriertransmission. In coordinated transmission (KI) mode two toneswith a suppressed carrier were transmitted for 330 seconds foruse in the VLBI tracking. Three consecutive TM transmissionsand one KI were made every 2 hours during the first 10 hoursand from roughly hours 22 to 34 of the flight, at other timesone TM and one KI transmission were made every two hoursto conserve battery power. The carrier signal frequency was1.6679 GHz and the radiated power was about 4.5 W. Thepower supply consisted of 1 kg of lithium batteries with 250 W-hrs capacity and an expected life of 46 to 52 hours.

Twenty ground stations were used for Very Long BaselineInterferometry (VLBI) tracking of the balloons. Six of thesestations were on Soviet territory and were coordinated by IKI,the Soviet space agency. The other fourteen antennas werecoordinated by CNES (France) and included three NASA DeepSpace Network antennas and eleven radio astronomyobservatories.

Mission ProfileThe Vega 2 Lander/Balloon capsule entered the Venusatmosphere (125 km altitude) at 2:06:04 UT (Earth receivedtime; Moscow time 5:06:04 a.m.) on 15 June 1985 at roughly11 km/sec. At approximately 2:06:19 UT the parachuteattached to the landing craft cap opened at an altitude of 64km. The cap and parachute were released 15 seconds later at63 km altitude. The balloon package was pulled out of itscompartment by parachute 40 seconds later at 61 km altitude,at 7.45 degrees S, 179.8 degrees east. A second parachuteopened at an altitude of 55 km, 200 seconds after entry,extracting the furled balloon. The balloon was inflated 100seconds later at 54 km and the parachute and inflation systemwere jettisoned. The ballast was jettisoned when the balloonreached roughly 50 km and the balloon floated back to a stableheight between 53 and 54 km some 15 to 25 minutes afterentry. The mean stable height was 53.6 km, with a pressure of535 mbar and a temperature of 308-316 K in the middle, mostactive layer of the Venus three-tiered cloud system. Theballoon drifted westward in the zonal wind flow with an averagespeed of about 66 m/s at nearly constant latitude. The probecrossed the terminator from night to day at 9:10 UT on 16June after traversing 7400 km. The probe continued to operatein the daytime until the final transmission was received at00:38 UT on 17 June from 7.5 S, 76.3 E after a total traversedistance of 11,100 km. It is not known how much further theballoon travelled after the final communication.

Kremnev, R. S., et al., VEGABalloon System andInstrumentation, Science,231, No. 4744, 1408, Mar.1986.

Sagdeev, R. Z., and V. I.Moroz, Project Vega firststage: missions to Venus,Sov. Astron. Lett., 12, No. 1,Jan.-Feb. 1986.

Sagdeev, R. Z., et al., TheVEGA balloon experiments,Sov. Astron. Lett., 12, No. 1,3, Jan.-Feb. 1986.

Kremnev, R. S., et al., TheVega balloons - A tool forstudying atmospheredynamics on Venus, Sov.Astron. Lett., 12, No. 1, 7,Jan.-Feb. 1986.

Vega 2 SpacecraftVega 2 LanderVega 1 Balloon - Informationon Vega 2's companionmission

Vega atmospheric probemodel on display at the NPOLavochkin Museum(Probe image courtesy ofAlexander Chernov and theVirtual Space Museum)

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Description

The Vega 2 lander probe was identical to those of Venera 9through 14 and similarly had two objectives, the study of theatmosphere and the study of the superficial crust. The landerconsisted of a hemispherical insulated pressure vesselmounted with shock absorbers on a deformable landing ring.On top of the pressure vessel was a disc-shaped aerobrakewhich also served as a reflector for the cylindrical fixedcommunications antenna above it. The lander was held duringthe cruise to Venus and atmospheric entry in an insulated heatprotection sphere 240 cm in diameter, consisting of an upperand lower hemisphere joined nonhermetically.

InstrumentationIn addition to temperature and pressure measuringinstruments, the descent probe carried an ISAV UVspectrometer for measurement of minor atmosphericconstituents, a VM-4 hygrometer dedicated to measurement ofthe concentration of H2O, an IPF aerosol analyzer, an ISAV-Aparticle size spectrometer/nephelometer and other instrumentsfor determination of the chemical composition of thecondensed phase: a Sigma 3 gas-phase chromatograph; aBDRP-AM25 X-ray spectrometer observing the fluorescenceof grains or drops; and a Malachite mass spectrographmeasuring the chemical composition of the grains or drops.The X-ray spectrometer separated the grains according to theirsizes using a laser imaging device, while the massspectrograph separated them according to their sizes using anaerodynamical inertial separator. After landing, a small surfacesample near the probe was to be collected by a drilling deviceand analyzed by a GS-15-SCV gamma ray spectrometer andX-ray fluorescence spectrometer. The UV spectrometer, themass spectrograph, and the pressure- and temperature-measuring instruments were developed in cooperationbetween French and Soviet investigators. Data collected by theinstruments were transmitted to the Vega 2 spacecraft andrelayed to Earth.

Mission ProfileThe lander separated from the Vega 2 spacecraft two daysbefore arrival at Venus and entered the planet's atmosphereon an inclined path, without active maneuvers, as was done onprevious Venera missions. (The flyby spacecraft was thenretargetted using Venus gravity assistance to intercept CometHalley in March 1986.) After separation from the Vega 2spacecraft the lander entered the Venus atmosphere on 15June 1985 at 01:59:30 UT at 10.80 km/s with an entry angle of19.08 degrees. The pilot parachute was deployed at 02:00:05UT at an altitude of 65 km and the braking parachute opened11 seconds later at 64.5 km. The upper heat protection


NSSDC ID: 1984-128E

Alternate Names

Vega 2 Lander

Vega 2 Balloon Aerostat

15856

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Planetary Science


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hemisphere was released at this time and the lowerhemisphere 4 seconds later at 64.2 km. The upper hemispherecontained the deployment system for the balloon aerostats.The parachute was released at 02:09:15 at 47 km. After thisthe lander was allowed to aerobrake through the thick Venusatmosphere, with drag devices minimizing vibrations and spinand providing stability. A toroidal system similar to that onVeneras 13 and 14 was designed to absorb shock on landing.The lander touched down at 03:00:50 UT on 15 June 1985 at8.5 S, 164.5 E, in eastern Aphrodite Terra. The altitude of thetouchdown site was 0.1 km above the planetary mean radius.The measured pressure at the landing site was 91 atm and thetemperature was 736 K. The surface sample was found to bean anorthosite-troctolite. The balloon measured downwardgusts of 1 meter/s and found horizontal winds up to 240 km/hr.

Balloon AerostatsIn addition to the lander probe, a constant-pressureinstrumented balloon aerostat was deployed after entry into theatmosphere from the upper heat protection hemisphere at analtitude of 54 km. The balloon released from the hemisphere,deployed a two-stage parachute, and then unfolded andinflated. The 3.4 meter diameter balloon supported a total massof 25-kg. A 5-kg payload hung suspended 12 meters below theballoon. It floated at approximately 50 km altitude in the middle,most active layer of the Venus three-tiered cloud system. Datafrom the balloon instruments were transmitted directly to Earthfor the 47-hr lifetime of the mission. (The batteries had alifetime of 60 hrs.) Onboard instruments were to measuretemperature, pressure, vertical wind velocity, visibility (densityand size of local aerosols), light level and to detect lightning.Very long baseline interferometry was used to track the motionof the balloon to provide the wind velocity in the clouds. Thetracking was to be done by a 6-station network on Sovietterritory and by a network of 12 stations distributed world-wide(organized by France and the NASA Deep Space Network).After two days the balloon entered the dayside of Venus andexpanded and burst due to solar heating.

Personnel



Selected References


Surkov, Yu. A., et al., Uranium, thorium, and potassium in the Venusian rocks at the landingsites of Vega 1 and 2, J. Geophys. Res., 92, No. B4, E537-E540, Mar. 1987.

Surkov, Yu. A., et al., The water vapor content profile in the Venusian atmosphere according tothe results of experiments from Vega 1 and 2, J. Geophys. Res., 91, No. B13, E219-E221, Nov.1986.

Sagdeev, R. Z., and V. I. Moroz, Project Vega first stage: missions to Venus, Sov. Astron. Lett.,12, No. 1, Jan.-Feb. 1986.



Vega 2 SpacecraftVega 2 BalloonVega 1 Lander - Information on Vega 2's companion mission

Vega atmospheric probeModel on display at the NPO Lavochkin Museum(Probe image courtesy of Alexander Chernov and the Virtual Space Museum)

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Description

Westar 6 was a domestic communications satellite deployed bythe STS 41-B mission for Western Union.

Westar 6

NSSDC ID: 1984-011B

Alternate Names

14688

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Communications


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