lanzamientos.files.wordpress.comNASA - NSSDC - Spacecraft - Query Results 14/08/2010 23:19:08]...

Cronología de Lanzamientos Espaciales

Año 1972 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[14/08/2010 23:19:08]

Saturday, 14 August 2010

Spacecraft Query Results

There were 129 spacecraft returned.

Spacecraft Name NSSDC ID Launch Date

1972-032A 1972-032A 1972-04-19

1972-052C 1972-052C 1972-07-07

Aeros-A 1972-100A 1972-12-16

Anik A1 1972-090A 1972-11-10

Apollo 16 Command and Service Module (CSM) 1972-031A 1972-04-16

Apollo 16 Lunar Module / ALSEP 1972-031C 1972-04-16

Apollo 16 SIVB 1972-031B 1972-04-16

Apollo 16 Subsatellite 1972-031D 1972-04-24

Apollo 17 Command and Service Module (CSM) 1972-096A 1972-12-07

Apollo 17 Lunar Module / ALSEP 1972-096C 1972-12-07

Apollo 17 SIVB 1972-096B 1972-12-07

Canyon 5 1972-101A 1972-12-20

Cosmos 471 1972-001A 1972-01-12

Cosmos 472 1972-004A 1972-01-25

Cosmos 473 1972-006A 1972-02-03

Cosmos 474 1972-008A 1972-02-16

Cosmos 475 1972-009A 1972-02-25

Cosmos 476 1972-011A 1972-03-01

Cosmos 477 1972-013A 1972-03-04

Cosmos 478 1972-015A 1972-03-15

Cosmos 479 1972-017A 1972-03-22

Cosmos 480 1972-019A 1972-03-25

Cosmos 481 1972-020A 1972-03-25

Cosmos 482 1972-023A 1972-03-31

Cosmos 483 1972-024A 1972-04-03

Cosmos 484 1972-026A 1972-04-06

Cosmos 485 1972-028A 1972-04-11

Cosmos 486 1972-030A 1972-04-14

Cosmos 487 1972-033A 1972-04-21

Cosmos 488 1972-034A 1972-05-05

Cosmos 489 1972-035A 1972-05-06

Cosmos 490 1972-036A 1972-05-18

Cosmos 491 1972-038A 1972-05-25

Cosmos 492 1972-040A 1972-06-09

Cosmos 493 1972-042A 1972-06-21

Cosmos 494 1972-043A 1972-06-23

NSSDC MasterCatalog Search

Spacecraft

Experiments

Data Collections

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Publications

Maps

New/Updated Data

Lunar/Planetary Events

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Cosmos 495 1972-044A 1972-06-23

Cosmos 496 1972-045A 1972-06-26

Cosmos 497 1972-048A 1972-06-30

Cosmos 498 1972-050A 1972-07-05

Cosmos 499 1972-051A 1972-07-06

Cosmos 500 1972-053A 1972-07-10

Cosmos 501 1972-054A 1972-07-12

Cosmos 502 1972-055A 1972-07-13

Cosmos 503 1972-056A 1972-07-19

Cosmos 504 1972-057A 1972-07-20

Cosmos 505 1972-057B 1972-07-20

Cosmos 506 1972-057C 1972-07-20

Cosmos 507 1972-057D 1972-07-20

Cosmos 508 1972-057E 1972-07-20

Cosmos 509 1972-057F 1972-07-20

Cosmos 510 1972-057G 1972-07-20

Cosmos 511 1972-057H 1972-07-20

Cosmos 512 1972-059A 1972-07-28

Cosmos 513 1972-060A 1972-08-02

Cosmos 514 1972-062A 1972-08-16

Cosmos 515 1972-063A 1972-08-18

Cosmos 516 1972-066A 1972-08-21

Cosmos 517 1972-067A 1972-08-30

Cosmos 518 1972-070A 1972-09-15

Cosmos 519 1972-071A 1972-09-16

Cosmos 520 1972-072A 1972-09-19

Cosmos 521 1972-074A 1972-09-29

Cosmos 522 1972-077A 1972-10-04

Cosmos 523 1972-078A 1972-10-05

Cosmos 524 1972-080A 1972-10-11

Cosmos 525 1972-083A 1972-10-18

Cosmos 526 1972-084A 1972-10-25

Cosmos 527 1972-086A 1972-10-31

Cosmos 528 1972-087A 1972-11-01

Cosmos 529 1972-087B 1972-11-01

Cosmos 530 1972-087C 1972-11-01

Cosmos 531 1972-087D 1972-11-01

Cosmos 532 1972-087E 1972-11-01

Cosmos 533 1972-087F 1972-11-01

Cosmos 534 1972-087G 1972-11-01

Cosmos 535 1972-087H 1972-11-01

Cosmos 536 1972-088A 1972-11-03

Cosmos 537 1972-093A 1972-11-25

Cosmos 538 1972-099A 1972-12-14

Cosmos 539 1972-102A 1972-12-21

Cosmos 540 1972-104A 1972-12-26

Cosmos 541 1972-105A 1972-12-27

Cosmos 542 1972-106A 1972-12-28

DENPA 1972-064A 1972-08-19



DMSP 5B/F2 1972-018A 1972-03-24

DMSP 5B/F3 1972-089A 1972-11-09

ESRO 4 1972-092A 1972-11-22

HEOS 2 1972-005A 1972-01-31

IMEWS 3 1972-010A 1972-03-01

IMP-H 1972-073A 1972-09-23

INTELSAT 4 F-4 1972-003A 1972-01-23

INTELSAT 4 F-5 1972-041A 1972-06-13

Intercosmos 6 1972-027A 1972-04-07

Intercosmos 7 1972-047A 1972-06-30

Intercosmos 8 1972-094A 1972-11-30

KH 8-34 1972-016A 1972-03-17

KH 8-36 1972-068A 1972-09-01

KH 8-37 1972-103A 1972-12-21

KH 9-02 1972-002A 1972-01-20

KH 9-03 1972-052A 1972-07-07

KH 9-04 1972-079A 1972-10-10

KH-4B 1117 1972-039A 1972-05-25

Landsat 1 1972-058A 1972-07-23

Luna 20 1972-007A 1972-02-14

Meteor 1-11 1972-022A 1972-03-30

Meteor 1-12 1972-049A 1972-06-30

Meteor 1-13 1972-085A 1972-10-27

Meteoroid Technology Satellite 1972-061A 1972-08-13

Molniya 1-20 1972-025A 1972-04-04

Molniya 1-21 1972-081A 1972-10-14

Molniya 1-22 1972-095A 1972-12-02

Molniya 2- 2 1972-037A 1972-05-19

Molniya 2- 3 1972-075A 1972-09-30

Molniya 2- 4 1972-098A 1972-12-12

Nimbus 5 1972-097A 1972-12-11

NOAA 2 1972-082A 1972-10-15

OAO 3 1972-065A 1972-08-21

OSCAR 6 1972-082B 1972-10-15

Pioneer 10 1972-012A 1972-03-03

Prognoz 1 1972-029A 1972-04-14

Prognoz 2 1972-046A 1972-06-29

RADCAT 2 1972-076A 1972-10-02

RADSAT 1972-076B 1972-10-02

SAS-B 1972-091A 1972-11-15

SRET 1 1972-025B 1972-04-04

TD 1A 1972-014A 1972-03-12

TIP 1 1972-069A 1972-09-02

Venera 8 1972-021A 1972-03-27

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

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NASA - NSSDC - Spacecraft - Details

http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1972-032A[14/08/2010 23:31:01]


Description

This spacecraft contained two known experiments, a neutraldensity gauge and nightglow photometers. Little information isavailable on the spacecraft, but orbit adjustments (presumablyby firing an onboard motor) were made to extend the satellitelifetime. Three-axis stabilization was required to keep thedensity gauge aperture perpendicular to the velocity vector.

1972-032A

NSSDC ID: 1972-032A

Alternate Names

SESP 71-3

06003

Facts in Brief

Launch Date: 1972-04-19Launch Vehicle: ThorLaunchSite: Vandenberg AFB,United StatesMass: 2000.0 kg

Funding Agency

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

Discipline

Earth Science

AdditionalInformation

Launch/Orbitalinformation for 1972-032A

Experiments on 1972-032A

Data collections from 1972-032A

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

Personnel

Name Role Original Affiliation E-mail


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data



http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1972-032A



http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=1972-032A

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=1972-032A

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=1972-032A

mailto:[email protected]?Subject=NMC Comment/Question: 1972-032A (1972-032A)














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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1972-052C[14/08/2010 23:31:42]


Description

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

1972-052C

NSSDC ID: 1972-052C

Alternate Names

06096

Facts in Brief

Launch Date: 1972-07-07Launch Vehicle: TitanLaunchSite: Vandenberg AFB,United StatesMass: 60.0 kg

Funding Agency

Unknown (United States)

Discipline

Surveillance and OtherMilitary


Launch/Orbitalinformation for 1972-052C

Experiments on 1972-052C

Data collections from 1972-052C



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1972-052C



http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=1972-052C

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=1972-052C

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=1972-052C

mailto:[email protected]?Subject=NMC Comment/Question: 1972-052C (1972-052C)











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Description

The AEROS satellite had a circular cylindrical shape, 0.914 min diameter and 0.710 m in height. It was launched into anelliptical, polar, nearly sun-synchronous earth orbit. Thespacecraft was spin stabilized at 10 rpm and oriented with thespin axis toward the sun. The purpose of the mission was tostudy the state and behavior of the upper atmosphere andionospheric F region, especially with regard to the influence ofsolar ultraviolet radiation. Five experiments provided data onthe temperature and density of electrons, ions, and neutralparticles, the composition of ions and neutral particles, andsolar ultraviolet flux.

Aeros-A

NSSDC ID: 1972-100A

Alternate Names

Aeros 1

06315

Facts in Brief

Launch Date: 1972-12-16Launch Vehicle: ScoutLaunchSite: Vandenberg AFB,United StatesMass: 125.7 kg

Funding Agencies

Bundesministerium fuerBildung und Wissenschaft(Federal Republic ofGermany)

NASA-Office of SpaceScience Applications(United States)

Disciplines

Earth Science

Solar Physics

Space Physics


Launch/Orbitalinformation for Aeros-A

Experiments on Aeros-A

Data collections fromAeros-A

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


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Aeros-A (1972-100A)

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Personnel


Dr. Siegfried J.Bauer

ProjectScientist

NASA Goddard Space Flight Center

Dr. PeterLaemmerzahl

ProjectScientist

Max-Planck-Institut fur Kernphysik

Ing. HorstSchreiber

ProjectManager

Deutsche Forschungs-und Versuchsenstalt fuerLuft-und Raumfahrt

Mr. Carl L.Wagner, Jr.

ProjectManager



http://www.usa.gov/








Description

This satellite was a Canadian telecommunications satellite ingeostationary orbit with an anticipated life of seven years. Itwas about 1.83 m in diameter and 3.35 m high. The satellitecommunication system provided for 12 C-band channels, twoof which were protection channels for the ten traffic carryingchannels. Uplink transmission was the 5.925-6.425 GHz band,and the down link operated in three 3.7-4.2 GHz band.Telemetry, tracking, and command functions required forsatellite stationkeeping and positioning were also provided inthose frequency bands.

Anik A1

NSSDC ID: 1972-090A

Alternate Names

Anik 1

Anik-A

Telesat-A

Telesat 1

06278

Facts in Brief

Launch Date: 1972-11-10Launch Vehicle: Delta1914Launch Site: CapeCanaveral, United StatesMass: 565.0 kg

Funding Agency

Telesat Canada Ltd.,Ottawa (Canada)

Discipline

Communications


Launch/Orbitalinformation for Anik A1

Telecommunicationsinformation for Anik A1

Experiments on Anik A1

Data collections from AnikA1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





http://nssdc.gsfc.nasa.gov/nmc/spacecraftTelemetry.do?id=1972-090A


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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Anik A1 (1972-090A)














Description

Apollo 16 was the fifth mission in which humans walked on thelunar surface and returned to Earth. On 21 April 1972 twoastronauts (Apollo 16 Commander John W. Young and LMpilot Charles M. Duke, Jr.) landed in the Descartes region ofthe Moon in the Lunar Module (LM) while the Command andService Module (CSM) (with CM pilot Thomas K. Mattingly, II)continued in lunar orbit. During their stay on the Moon, theastronauts set up scientific experiments, took photographs,and collected lunar samples. The LM took off from the Moonon 24 April and the astronauts returned to Earth on 27 April.

Mission ProfileApollo 16 launched on 16 April 1972 at 17:54:00 (12:54:00p.m. EST) on Saturn V SA-511 from Pad 39A at KennedySpace Center. (The launch was postponed from the originallyscheduled date, March 17, because of a docking ring jettisonmalfunction.) The spacecraft entered Earth parking orbit at18:05:56 UT and translunar injection took place at 20:27:37UT. The CSM and S-IVB stage separated at 20:58:59 UT andCSM-LM docking was achieved at 21:15:53 UT. The S-IVBstage was released into a lunar impact trajectory, but due to anearlier problem with the auxiliary propulsion system (APS)helium regulators, which resulted in continuous venting andloss of helium, the second APS burn could not be made.Tracking of the S-IVB was lost on 17 April at 21:03 UT due toa transponder failure. (The S-IVB stage impacted the Moon on19 April at 21:02:04 UT at 1.3 N, 23.8 W with a velocity of 2.5to 2.6 km/s at a 79 degree angle from the horizontal, asestimated from the Apollo 12, 14 and 16 seismic station data.)A mid-course correction was performed at 00:33:01 UT on 18April. During translunar coast a CSM navigation problem wasdiscovered in which a false indication would cause loss ofinertial reference, this was solved by a real-time change in thecomputer program. The SIM door was jettisoned on 19 April at15:57:00 UT and lunar orbit insertion took place at 20:22:28UT. Two revolutions later the orbit was lowered to one with aperilune of 20 km.

At 15:24 UT on 20 April Young and Duke entered the LM. TheLM separated from the CSM at 18:08:00 UT, but the LMdescent was delayed almost 6 hours due to a malfunction inthe yaw gimbal servo loop on the CSM which causedoscillations in the service propulsion system (SPS). Engineersdetermined that the problem would not seriously affect CSMsteering and the miision was allowed to continue with the LMdescent. The LM landed at 02:23:35 UT on 21 April in theDescartes highland region just north of the crater Dolland at9.0 S, 15.5 E. Young and Duke made three moonwalk EVAstotaling 20 hours, 14 minutes. During this time they covered 27

Apollo 16 Command and Service Module (CSM)

NSSDC ID: 1972-031A

Alternate Names

Casper

Apollo 16 CSM

CSM-113

06000

Facts in Brief

Launch Date: 1972-04-16Launch Vehicle: Saturn5Launch Site: CapeCanaveral, United StatesMass: 30354.0 kg

Funding Agency

NASA-Office of MannedSpace Flight (UnitedStates)

Disciplines

Astronomy

Engineering

Human Crew

Life Science

Microgravity

Planetary Science

Solar Physics


Launch/Orbitalinformation for Apollo 16Command and ServiceModule (CSM)

PDMP information forApollo 16 Command andService Module (CSM)

Telecommunicationsinformation for Apollo 16


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


Apollo 16 Command andService Module (CSM)






http://nssdc.gsfc.nasa.gov/nmc/spacecraftPdmp.do?id=1972-031A













http://nssdc.gsfc.nasa.gov/image/spacecraft/apollo_16_cm.jpg



km using the Lunar Roving Vehicle, collected 95.71 kg of rockand soil samples, took photographs, and set up the ALSEPand other scientific experiments. Other experiments were alsoperformed from orbit in the CSM during this time.

The LM lifted off from the Moon at 01:25:48 UT on 24 Aprilafter 71 hours, 2 minutes on the lunar surface. After the LMdocked with the CSM at 03:35:18 UT the lunar samples andother equipment were transferred from the LM and the LM wasjettisoned at 20:54:12 UT on 24 April. The LM began tumbling,apparently due to an open circuit breaker in the guidance andnavigation system. As a result the planned deorbit and lunarimpact could not be attempted. The LM remained in lunar orbitwith an estimated lifetime of one year. The instrument boomwhich carried the orbital mass spectrometer would not retractand was jettisoned. Because of earlier problems with the SPSyaw gimbal servo loop the mission was shortened by one day.The orbital shaping maneuver was cancelled, and thesubsatellite was spring-launched at 21:56:09 UT into anelliptical orbit with a lifetime of one month, rather than theplanned one-year orbit. Transearth injection began at 02:15:33UT on 25 April. On 25 April at 20:43 UT Mattingly began acislunar EVA to retrieve camera film from the SIM bay andinspect instruments, two trips taking a total of 1 hour, 24minutes. The CM separated from the SM on 27 April at19:16:33 UT. Apollo 16 splashed down in the Pacific Ocean on27 April 1972 at 19:45:05 UT (2:45:05 p.m. EST) after amission elapsed timeof 265 hrs, 51 mins, 5 secs. Thesplashdown point was 0 deg 43 min S, 156 deg 13 min W, 215miles southeast of Christmas Island and 5 km (3 mi) from therecovery ship USS Ticonderoga.

Performance of the spacecraft, the second of the Apollo J-series missions, was good for most aspects of the mission.The primary mission goals of inspecting, surveying, andsampling materials in the Descartes region, emplacement andactivation of surface experiments, conducting inflightexperiments and photographic tasks from lunar orbit,engineering evaluation of spacecraft and equipment, andperformance of zero-gravity experiments were achieveddespite the mission being shortened by one day. Young, 41,was a Navy Captain who had flown on three previousspaceflights (Gemini 3, Gemini 10, and Apollo 10; he later flewon STS-1 and STS-9), Mattingly, 36, was a Navy lt.commander on his first spaceflight (he later flew STS-4 andSTS-51C), and Duke, 36, was an Air Force lt. colonel also onhis first spaceflight. The backup crew for this mission was FredHaise, Stuart Roosa, and Edger Mitchell. The Apollo 16Command Module "Casper" is on display at the AlabamaSpace and Rocket Center in Huntsville, Alabama.

Spacecraft and SubsystemsAs the name implies, the Command and Service Module(CSM) was comprised of two distinct units: the CommandModule (CM), which housed the crew, spacecraft operationssystems, and re-entry equipment, and the Service Module(SM) which carried most of the consumables (oxygen, water,helium, fuel cells, and fuel) and the main propulsion system.The total length of the two modules attached was 11.0 meterswith a maximum diameter of 3.9 meters. Block II CSM's wereused for all the crewed Apollo missions. Apollo 16 was thesecond of the Apollo J-series spacecraft. The CSM mass of30,354 kg was the launch mass including propellants andexpendables, of this the Command Module (CM-113) had amass of 5840 kg and the Service Module (SM-113) 24,514 kg.

Telecommunications included voice, television, data, andtracking and ranging subsystems for communications between

Command and ServiceModule (CSM)

Experiments on Apollo 16Command and ServiceModule (CSM)

Data collections fromApollo 16 Command andService Module (CSM)

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



http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Apollo 16 Command and Service Module (CSM)



http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Apollo 16 Command and Service Module (CSM)



mailto:[email protected]?Subject=NMC Comment/Question: Apollo 16 Command and Service Module (CSM) (1972-031A)




astronauts, CM, LM, and Earth. Voice contact was provided byan S-band uplink and downlink system. Tracking was donethrough a unified S-band transponder. A high gain steerable S-band antenna consisting of four 79-cm diameter parabolicdishes was mounted on a folding boom at the aft end of theSM. Two VHF scimitar antennas were also mounted on theSM. There was also a VHF recovery beacon mounted in theCM. The CSM environmental control system regulated cabinatmosphere, pressure, temperature, carbon dioxide, odors,particles, and ventilation and controlled the temperature rangeof the electronic equipment.

Command ModuleThe CM was a conical pressure vessel with a maximumdiameter of 3.9 m at its base and a height of 3.65 m. It wasmade of an aluminum honeycomb sandwhich bonded betweensheet aluminum alloy. The base of the CM consisted of a heatshield made of brazed stainless steel honeycomb filled with aphenolic epoxy resin as an ablative material and varied inthickness from 1.8 to 6.9 cm. At the tip of the cone was a hatchand docking assembly designed to mate with the lunar module.The CM was divided into three compartments. The forwardcompartment in the nose of the cone held the three 25.4 mdiameter main parachutes, two 5 m drogue parachutes, andpilot mortar chutes for Earth landing. The aft compartment wassituated around the base of the CM and contained propellanttanks, reaction control engines, wiring, and plumbing. Thecrew compartment comprised most of the volume of the CM,approximately 6.17 cubic meters of space. Three astronautcouches were lined up facing forward in the center of thecompartment. A large access hatch was situated above thecenter couch. A short access tunnel led to the docking hatch inthe CM nose. The crew compartment held the controls,displays, navigation equipment and other systems used by theastronauts. The CM had five windows: one in the accesshatch, one next to each astronaut in the two outer seats, andtwo forward-facing rendezvous windows. Five silver/zinc-oxidebatteries provided power after the CM and SM detached, threefor re-entry and after landing and two for vehicle separationand parachute deployment. The CM had twelve 420 N nitrogentetroxide/hydrazine reaction control thrusters. The CM providedthe re-entry capability at the end of the mission afterseparation from the Service Module.

Service ModuleThe SM was a cylinder 3.9 meters in diameter and 7.6 m longwhich was attached to the back of the CM. The outer skin ofthe SM was formed of 2.5 cm thick aluminum honeycombpanels. The interior was divided by milled aluminum radialbeams into six sections around a central cylinder. At the backof the SM mounted in the central cylinder was a gimbalmounted re-startable hypergolic liquid propellant 91,000 Nengine and cone shaped engine nozzle. Attitude control wasprovided by four identical banks of four 450 N reaction controlthrusters each spaced 90 degrees apart around the forwardpart of the SM. The six sections of the SM held three 31-cellhydrogen oxygen fuel cells which provided 28 volts, anauxiliary battery, three cryogenic oxygen and three cryogenichydrogen tanks, four tanks for the main propulsion engine, twofor fuel and two for oxidizer, the subsystems the mainpropulsion unit, and a Scientific Instrument Module (SIM) baywhich held a package of science instruments and cameras tobe operated from lunar orbit and a small subsatellite to be putinto lunar orbit. Two helium tanks were mounted in the centralcylinder. Electrical power system radiators were at the top ofthe cylinder and environmental control radiator panels spacedaround the bottom.

Apollo Program



The Apollo program included a large number of uncrewed testmissions and 12 crewed missions: three Earth orbitingmissions (Apollo 7, 9 and Apollo-Soyuz), two lunar orbitingmissions (Apollo 8 and 10), a lunar swingby (Apollo 13), andsix Moon landing missions (Apollo 11, 12, 14, 15, 16, and 17).Two astronauts from each of these six missions walked on theMoon (Neil Armstrong, Edwin Aldrin, Charles Conrad, AlanBean, Alan Shepard, Edgar Mitchell, David Scott, James Irwin,John Young, Charles Duke, Gene Cernan, and HarrisonSchmitt), the only humans to have set foot on another solarsystem body. Total funding for the Apollo program wasapproximately $20,443,600,000.

For information on the Lunar Module and details of activities onthe lunar surface, see:

http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1972-031C

Personnel


Dr. Rocco A. Petrone Project Manager NASA Headquarters

Selected References

Apollo 16 preliminary science report, NASA, SP-315, Wash., D.C., 1972.

Diagram of the Apollo CSM courtesy of NASA History Office.Apollo 16 Lunar Module record - LM/ALSEP and surface operationsApollo 16 Subsatellite recordApollo 16 Home Page - with links to other Apollo 16 sites

Apollo Home PageLunar Science Home PageMoon Home Page




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

http://history.nasa.gov/diagrams/apollo.html


http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1972-031D

http://nssdc.gsfc.nasa.gov/planetary/lunar/apollo16info.html

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

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

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

http://www.usa.gov/








Description

The Apollo 16 lunar module (LM) "Orion" was the fifth crewedvehicle to land on the Moon. It carried two astronauts,Commander John W. Young and LM pilot Charles M. Duke Jr.,the ninth and tenth men to walk on the Moon. The LM alsocarried a Lunar Roving Vehicle (LRV), an Apollo Lunar SurfaceExperiments Package (ALSEP) that contained scientificexperiments to be deployed and left on the lunar surface, andother scientific and sample collection apparatus. Theexperiments performed on the Moon, in addition to the ALSEPsuite, were geologic sample collection, surface photography,soil mechanics investigations to study the physical propertiesof the lunar regolith, the solar wind composition experimentwhich collected samples of solar wind for return to Earth, acosmic-ray detector to measure heavy cosmic rays, a far-ultraviolet camera for lyman-alpha astronomical observations,and a portable surface magnetometer to study local magneticsources.

Mission ProfileThe LM separated from the Command/Service Module (CSM)at 18:08:00 UT on 20 April 1972 and landed at 02:23:35 UT on21 April (9:23:35 p.m. EST, 20 April) in the Descartes highlandregion just north of the crater Dolland at 8.9730 S latitude,15.5002 E longitude (IAU Mean Earth Polar Axis coordinatesystem). Young and Duke made three moonwalk extra-vehicular activities (EVAs) totaling 20 hours, 14 minutes.During this time they covered 27 km and collected 95.71 kg ofrock and soil samples, stopping at 11 sites. The LRV wasused during EVAs to extend the range of manned lunarexploration. The first EVA was on 21 April from 16:47:38 UT to23:58:40 UT, during which the astronauts set up the ALSEP,deployed the LRV, and explored surrounding craters in a 4.2km traverse. During ALSEP set up Young tripped on the cableto the heat flow experiment and broke it, rendering theinstrument inoperable. During the second EVA on 22 April from16:33:35 UT to 23:56:44 UT the astronauts explored a ridgeand mountain slope during a 11.1 km traverse and on the third,of 11.4 km, on 23 April from 15:25:28 UT to 21:05:31 UT theytravelled to North Ray Crater. During all these EVAs theastronauts collected samples and took photographs. The LMlifted off from the Moon on 24 April at 01:25:48 UT after 71hours, 2 minutes on the lunar surface. After docking with theCSM (piloted by Thomas K. Mattingly 2nd) at 03:35:18 UT, theLM was jettisoned into lunar orbit at 20:54:12 UT on 24 April.Loss of attitude control on the LM made the planned impactnear the Apollo 16 site impossible, so it was left in lunar orbitwith an estimated life of 1 year.

Lunar Module Spacecraft and Subsystems

Apollo 16 Lunar Module / ALSEP

NSSDC ID: 1972-031C

Alternate Names

LEM 16

Rover 16

Apollo 16C

Apollo 16 LM/ALSEP

Orion

LM-11

ALSEP 16

06005

Facts in Brief


Funding Agencies

NASA-Office of SpaceScience (United States)


Disciplines

Astronomy

Human Crew

Planetary Science

Space Physics


Launch/Orbitalinformation for Apollo 16Lunar Module / ALSEP

PDMP information forApollo 16 Lunar Module /ALSEP


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Apollo 16 Lunar Module /ALSEP





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The lunar module was a two-stage vehicle designed for spaceoperations near and on the Moon. The spacecraft mass of16,428 kg was the mass of the LM including astronauts,expendables, and approximately 12,000 kg of propellants. Thefully fueled mass of the ascent stage was about 4971 kg andthe descent stage 11,457 kg. The ascent and descent stagesof the LM operated as a unit until staging, when the ascentstage functioned as a single spacecraft for rendezvous anddocking with the command and service module (CSM). Thedescent stage comprised the lower part of the spacecraft andwas an octagonal prism 4.2 meters across and 1.7 m thick.Four landing legs with round footpads were mounted on thesides of the descent stage and held the bottom of the stage1.5 m above the surface. The distance between the ends of thefootpads on opposite landing legs was 9.4 m. One of the legshad a small astronaut egress platform and ladder. A one meterlong conical descent engine skirt protruded from the bottom ofthe stage. The descent stage contained the landing rocket, twotanks of aerozine 50 fuel, two tanks of nitrogen tetroxideoxidizer, water, oxygen and helium tanks and storage spacefor the lunar equipment and experiments, and in the case ofApollo 15, 16, and 17, the lunar rover. The descent stageserved as a platform for launching the ascent stage and wasleft behind on the Moon.

The ascent stage was an irregularly shaped unit approximately2.8 m high and 4.0 by 4.3 meters in width mounted on top ofthe descent stage. The ascent stage housed the astronauts ina pressurized crew compartment with a volume of 6.65 cubicmeters. There was an ingress-egress hatch in one side and adocking hatch for connecting to the CSM on top. Also mountedalong the top were a parabolic rendezvous radar antenna, asteerable parabolic S-band antenna, and 2 in-flight VHFantennas. Two triangular windows were above and to eitherside of the egress hatch and four thrust chamber assemblieswere mounted around the sides. At the base of the assemblywas the ascent engine. The stage also contained an aerozine50 fuel and an oxidizer tank, and helium, liquid oxygen,gaseous oxygen, and reaction control fuel tanks. There wereno seats in the LM. A control console was mounted in the frontof the crew compartment above the ingress-egress hatch andbetween the windows and two more control panels mountedon the side walls. The ascent stage was launched from theMoon at the end of lunar surface operations and returned theastronauts to the CSM.

The descent engine was a deep-throttling ablative rocket witha maximum thrust of about 45,000 N mounted on a gimbal ringin the center of the descent stage. The ascent engine was afixed, constant-thrust rocket with a thrust of about 15,000 N.Maneuvering was achieved via the reaction control system,which consisted of the four thrust modules, each onecomposed of four 450 N thrust chambers and nozzles pointingin different directions. Telemetry, TV, voice, and rangecommunications with Earth were all via the S-band antenna.VHF was used for communications between the astronautsand the LM, and the LM and orbiting CSM. There wereredundant tranceivers and equipment for both S-band andVHF. An environmental control system recycled oxygen andmaintained temperature in the electronics and cabin. Powerwas provided by 6 silver-zinc batteries. Guidance andnavigation control were provided by a radar ranging system,an inertial measurement unit consisting of gyroscopes andaccelerometers, and the Apollo guidance computer.

Apollo Lunar Surface Experiments Package(ALSEP)The Apollo Lunar Surface Experiments Package (ALSEP)consisted of a set of scientific instruments emplaced at the

Telecommunicationsinformation for Apollo 16Lunar Module / ALSEP

Experiments on Apollo 16Lunar Module / ALSEP

Data collections fromApollo 16 Lunar Module /ALSEP


http://nssdc.gsfc.nasa.gov/nmc/spacecraftTelemetry.do?id=1972-031C



http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Apollo 16 Lunar Module / ALSEP


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landing site by the astronauts. The instruments were arrayedaround a central station and connected by cables whichsupplied power to run the instruments and communications sodata collected by the experiments could be relayed to Earth.The central station was a 25 kg box with a stowed volume of34,800 cubic cm. Thermal control was achieved by passiveelements (insulation, reflectors, thermal coatings) as well aspower dissipation resistors and heaters. Communications withEarth were achieved through a 58 cm long, 3.8 cm diametermodified axial-helical antenna mounted on top of the centralstation and pointed towards Earth by the astronauts.Transmitters, receivers, data processors and multiplexers werehoused within the central station. Data collected from theinstruments were converted into a telemetry format andtransmitted to Earth. The ALSEP system and instruments werecontrolled by commands from Earth. The uplink frequency forall Apollo mission ALSEP's was 2119 MHz, the downlinkfrequency for the Apollo 16 ALSEP was 2276.0 MHz.

Radioisotope Thermoelectric Generator (RTG)The SNAP-27 model RTG produced the power to run theALSEP operations. The generator consisted of a 46 cm highcentral cylinder and eight radiating rectangular fins with a totaltip-to-tip diameter of 40 cm. The central cylinder had a thinnerconcentric inner cylinder inside, and the two cylinders wereattached along their surfaces by 442 spring-loaded lead-telluride thermoelectric couples mounted radially along thelength of the cylinders. The generator assembly had a totalmass of 17 kg. The power source was an approximately 4 kgfuel capsule in the shape of a long rod which containedplutonium-238 and was placed in the inner cylinder of the RTGby the astronauts on deployment. Plutonium-238 decays with ahalf-life of 89.6 years and produces heat. This heat wouldconduct from the inner cylinder to the outer via thethermocouples which would convert the heat directly toelectrical power. Excess heat on the outer cylinder would beradiated to space by the fins. The RTG producedapproximately 70 W DC at 16 V. (63.5 W after one year.) Theelectricity was routed through a cable to a power conditioningunit and a power distribution unit in the central station tosupply the correct voltage and power to each instrument.

ALSEP Scientific InstrumentsAll ALSEP instruments were deployed on the surface by theastronauts and attached to the central station by cables. TheApollo 16 ALSEP instruments consisted of: (1) a passiveseismometer, designed to measure seismic activity andphysical properties of the lunar crust and interior; (2) an activeseismometer to study the physical properties of lunar surfaceand subsurface materials and the structure of the local near-surface layers; (3) a lunar surface magnetometer (LSM),designed to measure the magnetic field at the lunar surface;and (4) a heat flow experiment, designed to measure the rateof heat loss from the lunar interior and the thermal propertiesof lunar material. The central station, located at 8.9754 Slatitude, 15.4981 E longitude, was turned on at 19:38 UT on21 April 1972 and shut down along with the other ALSEPstations on 30 September 1977.

Personnel


Mr. Floyd I. Roberson Program Manager NASA Headquarters

Mr. Wilbert F. Eichelman Project Manager NASA Johnson Space Center

Dr. John B. Hanley Program Scientist NASA Headquarters



Selected References


Davies, M. E., and T. R. Colvin, Lunar coordinates in the regions of the Apollo landers,J. Geophys. Res., 105, No. E8, 20277-20280, Aug. 2000.

Diagram of the Apollo LM courtesy of NASA History Office.Apollo 16 Command Module recordApollo 16 Subsatellite recordThe Apollo Lunar Roving VehicleApollo 16 Home PageApollo landing sites and ALSEP and LRRR locations - and information on the modified DMA/603control network



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


http://nssdc.gsfc.nasa.gov/planetary/lunar/lunar_sites.txt




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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1972-031B[14/08/2010 23:35:18]


Description

The Apollo Saturn V SIVB was the third stage of the Saturn Vbooster. The SIVB consisted of a truncated cone with a bottomdiameter of 10.06 m topped by a long cylinder with a diameterof 6.60 m. Total height was 17.80 m. It contained liquidhydrogen and liquid oxygen tanks and a J2 engine. It waslaunched into Earth orbit attached to the Command, Service,and Lunar Modules (CSM and LM). The SIVB provided thethrust to take the CSM and LM from Earth orbit into a lunartransfer orbit. After achieving trajectory towards the Moon, theLM and CSM decoupled from the SIVB at 21:53:15 UT on 16April 1972. The SIVB was left on a course towards the Moonwhere it compacted on 19 April. A malfunction resulted inpremature loss of tracking data for the Apollo 16 SIVB.Estimates from seismic data indicate that impact occurred atabout 21:02:03 UT at 1.3 N, 23.8 W at a velocity of 2.5 to 2.6km/s.

Apollo 16 SIVB

NSSDC ID: 1972-031B

Alternate Names

Apollo Saturn V thirdstage

06001

Facts in Brief


Funding Agency

National Aeronautics andSpace Administration(United States)

Discipline

Planetary Science


Launch/Orbitalinformation for Apollo 16SIVB

PDMP information forApollo 16 SIVB

Experiments on Apollo 16SIVB

Data collections fromApollo 16 SIVB



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http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1972-031B



http://nssdc.gsfc.nasa.gov/nmc/spacecraftPdmp.do?id=1972-031B


http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Apollo 16 SIVB


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Apollo 16 SIVB


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Personnel


Dr. Charles W. Mathews Project Manager NASA Headquarters


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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1972-031D[14/08/2010 23:35:46]


Description

The Apollo 16 subsatellite (PFS-2) was a small satellitereleased into lunar orbit from the Apollo 16 Service Module. Itsmain objectives were to study the plasma, particle, andmagnetic field environment of the Moon and map the lunargravity field. Specifically it measured plasma and energeticparticle intensities and vector magnetic fields, and facilitatedtracking of the satellite velocity to high precision. A basicrequirement was that the satellite acquire fields and particledata everywhere on the orbit around the Moon. Thesubsatellite was virtually identical to the one deployed byApollo 15. The Moon's roughly circular orbit about the Earth at~380000 km (60 Earth radii) carried the subsatellite into bothinterplanetary space and various regions of the Earth'smagnetosphere. The subsatellite orbited the Moon andreturned data from 24 April until 29 May 1972.

Spacecraft and SubsystemsThe Apollo 16 subsatellite was a hexagonal cylinder 78 cm inlength and approximately 36 cm across opposite corners of thehexagon with a mass of 36.3 kg. Three equally-spaced 1.5-meter-long deployable booms were hinged to one of the endplatforms. A fluxgate magnetometer was on the end of oneboom and the other two carried tip masses to provide balance.A short cylinder was attached to the end platform opposite thebooms and was used for the initial deployment and spin-up ofthe satellite, which was achieved using a spring loadedmechanism in the SM bay. A wobble damper inside thesatellite removed precessional and nutational motions. An S-band antenna protruded from the panel opposite the booms.Solar panels covering the six sides provided about 24 W ofenergy in sunlight and an average power of 14 W over oneorbit of the Moon. The power subsystem also included abattery pack of 11 silver cadmium cells. An S-band transmitterwas capable of sending 128 bits/s to the Earth. A magneticcore memory unit provided a storage capacity of 49,152 bitswhen the spacecraft could not transmit directly. Two solid stateparticle telescopes were mounted on an end panel of thespacecraft and four particle analyzer devices were attached tothe sides.

Mission ProfileApollo 16 launched at 17:54:00 UT (12:54:00 p.m. EST) on 16April 1972 and went into orbit around the Moon on 19 April at20:22 UT. The Apollo 16 subsatellite was deployed on 24 Aprilat 21:56:09 UT by launching it from the Service Module at arelative velocity of approximately 1.2 m/s using a spring loadeddevice which also imparted a spin of 140 rpm to the satellite.After release, the booms were deployed, lowering the spin rateto 12 rpm. The spin axis was about 5.5 degrees from normal to

Apollo 16 Subsatellite

NSSDC ID: 1972-031D

Alternate Names

Apollo 16D

PFS-2

06009

Facts in Brief

Launch Date: 1972-04-24Launch Vehicle: nullLaunch Site: UnitedStatesMass: 36.3 kgNominal Power: 24.0 W

Funding Agency


Disciplines

Planetary Science

Space Physics


Launch/Orbitalinformation for Apollo 16Subsatellite

Experiments on Apollo 16Subsatellite

Data collections fromApollo 16 Subsatellite

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

Selected References


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


Apollo 16 Subsatellite


http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1972-031D



http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Apollo 16 Subsatellite

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Apollo 16 Subsatellite

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Apollo 16 Subsatellite

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Apollo 16 Subsatellite

mailto:[email protected]?Subject=NMC Comment/Question: Apollo 16 Subsatellite (1972-031D)

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



the ecliptic plane. A planned CSM orbit shaping maneuver wasnot performed prior to deployment to avoid firing the CSMmain engine due to degraded backup thrust vector control, sothe satellite was not released into a nominal orbit. The initialperiselene was 90 km, initial aposelene was 130 km, and initialorbital inclination was 10 degrees with respect to the Moon'sequator, but the orbit was rapidly altered by gravitationalperturbations. The orbital period was approximately 120minutes, clockwise as viewed from north. The geocentricecliptic longitude of the Moon at the time of launch was 138degrees. Because the initial orbit was not optimal, it decayedrapidly and the subsatellite prematurely impacted the Moon onMay 29, 1972, after 34 days (425 revolutions) in orbit. The finaltelemetry was received at 20:31 UT just before lunar impact.

Anderson, K. J., et al.,Subsatellite measurements ofplasma and energeticparticles, In -- Apollo 16Prelim. Sci. Rept., NASA SP-315, 22, 1-6, Wash., DC,1972.

Apollo 16 - expedition toDescartes (mission report),NASA, MR-11, Wash., D.C.,1972.

Apollo 16 Command Modulerecord

Apollo 16 Lunar Module recordApollo 16 Home PageApollo 15 SubsatelliteApollo Home PageLunar Science Home PageMoon Home Page










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Description

Apollo 17 was the sixth and last Apollo mission in whichhumans walked on the lunar surface. On 11 December 1972two astronauts (Commander Eugene A. Cernan and LM pilotHarrison H. Schmitt, the first scientist on the Moon) landed inthe Taurus-Littrow region of the Moon in the Lunar Module(LM) while the Command and Service Module (CSM) (with CMpilot Ronald E. Evans) continued in lunar orbit. During theirstay on the Moon, the astronauts set up scientific experiments,took photographs, and collected lunar samples. The LM tookoff from the Moon on 14 December and the astronautsreturned to Earth on 19 December.

Mission ProfileApollo 17 lifted off at 05:33:00 UT (12:33:00 a.m. EST) on 7December 1972 after a 2 hour, 40 minute delay due to amalfunction of a launch sequencer. Launch was on Saturn VSA-512 from Pad 39A at Kennedy Space Center and was thefirst nighttime launch of an Apollo. The spacecraft began Earthparking orbit at 05:44:53 UT and translunar injection took placeat 08:45:37 UT. The CSM separated from the S-IVB at09:15:29 UT and CSM-LM docking took place at 09:29:45 UT.The S-IVB was released at 10:18 UT into a lunar impacttrajectory. (It impacted the lunar surface on 10 December at20:32:42.3 UT at 4.21 S, 12.31 W with a velocity of 2.55 km/sat a 55 degree angle from the horizontal.) A single mid-coursecorrection requiring a 1.6 second burn of the ServicePropulsion System (SPS) was made at 17:03:00 UT on 8December. On December 10 at 15:05:40 UT the SIM bay doorwas jettisoned and a 398 second burn of the SPS was initiatedat 19:47:23 UT to insert Apollo 17 into lunar orbit.Approximately 4 hours 20 minutes later another maneuverlowered the orbit to a perilune of 28 km. At 14:35 UT on 11December Cernan and Schmitt entered the LM.

The LM separated from the CSM at 17:20:56 UT on 11December 1972 and reduced its orbit to 11.5 km perilune at18:55:42 UT. The descent burn took place at 19:43 UT and theLM landed at 19:54:57 UT on the southeastern rim of MareSerenitatis in a valley at Taurus-Littrow, at 20.2 N, 30.8 E.Cernan and Schmitt made three moonwalk extra-vehicularactivities (EVAs) totaling 22 hours, 4 minutes. During this timethey covered 30 km using the Lunar Roving Vehicle, collected110.52 kg of lunar samples, took photographs, and set up theALSEP and performed other scientific experiments. Evansperformed experiments from orbit in the CSM during this time.

The LM lifted off from the Moon at 22:54:37 UT on 14December after 75 hours on the lunar surface. After the LMdocked with the CSM at 01:10:15 UT on 15 December the

Apollo 17 Command and Service Module (CSM)

NSSDC ID: 1972-096A

Alternate Names

Apollo 17 CSM

CSM-114

Apollo 17A

America

06300

Facts in Brief


Funding Agency


Disciplines

Astronomy

Human Crew

Life Science

Planetary Science


Launch/Orbitalinformation for Apollo 17Command and ServiceModule (CSM)

PDMP information forApollo 17 Command andService Module (CSM)

Telecommunicationsinformation for Apollo 17Command and ServiceModule (CSM)


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Apollo 17 Command andService Module (CSM)





















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lunar samples and other equipment were transferred from theLM and the LM was jettisoned at 04:51:31 UT. The LMimpacted the Moon at 06:50:20.8 UT at 19.96 N, 30.50 E,approximately 15 km from the Apollo 17 landing site, with anestimated impact velocity of 1.67 km/s at an angle ~4.9degrees from horizontal. After another 1 1/2 days in lunar orbit,transearth injection took place at 23:35:09 UT on 16December. On 17 December at 20:27 UT Evans began acislunar spacewalk EVA consisting of three trips to the SM SIMbay to collect camera and lunar sounder film over a period of67 minutes. The CM and SM separated at 18:56:49 UT on 19December. Apollo 17 splashed down in the Pacific Ocean on19 December 1972 at 19:24:59 UT (2:24:59 p.m. EST) after amission elapsed time of 301 hrs, 51 mins, 59 secs. Thesplashdown point was 17 deg 53 min S, 166 deg 7 min W, 350nautical miles SE of the Samoan Islands and 6.5 km (4 mi)from the recovery ship USS Ticonderoga.

Performance of the spacecraft, the third of the Apollo J-seriesmissions, was excellent for all aspects of the mission. Theprimary mission goals of investigating the lunar surface andenvironment in the Taurus-Littrow region, emplacing andactivating surface experiments, performing experiments inlunar orbit, obtaining and returning lunar surface samples, andenhancing the capability for future astronaut lunar explorationwere achieved. Cernan, 38, was a Navy captain with twoprevious spaceflights (Gemini 9, Apollo 10), Evans, 39, was aNavy commander making his first spaceflight, and Schmitt, 37,was a civilian also making his first spaceflight. The backupcrew for this mission was John Young, Stuart Roosa, andCharles Duke. The Apollo 17 command module capsule"America" is on display at the Johnson Space Center inHouston, Texas.

Spacecraft and SubsystemsAs the name implies, the Command and Service Module(CSM) was comprised of two distinct units: the CommandModule (CM), which housed the crew, spacecraft operationssystems, and re-entry equipment, and the Service Module(SM) which carried most of the consumables (oxygen, water,helium, fuel cells, and fuel) and the main propulsion system.The total length of the two modules attached was 11.0 meterswith a maximum diameter of 3.9 meters. Block II CSM's wereused for all the crewed Apollo missions. Apollo 17 was thethird of the Apollo J-series spacecraft. The CSM mass of30,320 kg was the launch mass including propellants andexpendables, of this the Command Module (CM-114) had amass of 5960 kg and the Service Module (SM-114) 24,360 kg.

Telecommunications included voice, television, data, andtracking and ranging subsystems for communications betweenastronauts, CM, LM, and Earth. Voice contact was provided byan S-band uplink and downlink system. Tracking was donethrough a unified S-band transponder. A high gain steerable S-band antenna consisting of four 79-cm diameter parabolicdishes was mounted on a folding boom at the aft end of theSM. Two VHF scimitar antennas were also mounted on theSM. There was also a VHF recovery beacon mounted in theCM. The CSM environmental control system regulated cabinatmosphere, pressure, temperature, carbon dioxide, odors,particles, and ventilation and controlled the temperature rangeof the electronic equipment.

Command ModuleThe CM was a conical pressure vessel with a maximumdiameter of 3.9 m at its base and a height of 3.65 m. It wasmade of an aluminum honeycomb sandwhich bonded betweensheet aluminum alloy. The base of the CM consisted of a heat

Experiments on Apollo 17Command and ServiceModule (CSM)

Data collections fromApollo 17 Command andService Module (CSM)












shield made of brazed stainless steel honeycomb filled with aphenolic epoxy resin as an ablative material and varied inthickness from 1.8 to 6.9 cm. At the tip of the cone was a hatchand docking assembly designed to mate with the lunar module.The CM was divided into three compartments. The forwardcompartment in the nose of the cone held the three 25.4 mdiameter main parachutes, two 5 m drogue parachutes, andpilot mortar chutes for Earth landing. The aft compartment wassituated around the base of the CM and contained propellanttanks, reaction control engines, wiring, and plumbing. Thecrew compartment comprised most of the volume of the CM,approximately 6.17 cubic meters of space. Three astronautcouches were lined up facing forward in the center of thecompartment. A large access hatch was situated above thecenter couch. A short access tunnel led to the docking hatch inthe CM nose. The crew compartment held the controls,displays, navigation equipment and other systems used by theastronauts. The CM had five windows: one in the accesshatch, one next to each astronaut in the two outer seats, andtwo forward-facing rendezvous windows. Five silver/zinc-oxidebatteries provided power after the CM and SM detached, threefor re-entry and after landing and two for vehicle separationand parachute deployment. The CM had twelve 420 N nitrogentetroxide/hydrazine reaction control thrusters. The CM providedthe re-entry capability at the end of the mission afterseparation from the Service Module.

The SM was a cylinder 3.9 meters in diameter and 7.6 m longwhich was attached to the back of the CM. The outer skin ofthe SM was formed of 2.5 cm thick aluminum honeycombpanels. The interior was divided by milled aluminum radialbeams into six sections around a central cylinder. At the backof the SM mounted in the central cylinder was a gimbalmounted re-startable hypergolic liquid propellant 91,000 Nengine and cone shaped engine nozzle. Attitude control wasprovided by four identical banks of four 450 N reaction controlthrusters each spaced 90 degrees apart around the forwardpart of the SM. The six sections of the SM held three 31-cellhydrogen oxygen fuel cells which provided 28 volts, anauxiliary battery, three cryogenic oxygen and three cryogenichydrogen tanks, four tanks for the main propulsion engine, twofor fuel and two for oxidizer, the subsystems the mainpropulsion unit, and a Scientific Instrument Module (SIM) baywhich held a package of science instruments and cameras tobe operated from lunar orbit. Two helium tanks were mountedin the central cylinder. Electrical power system radiators wereat the top of the cylinder and environmental control radiatorpanels spaced around the bottom.

Apollo ProgramThe Apollo program included a large number of uncrewed testmissions and 12 crewed missions: three Earth orbitingmissions (Apollo 7, 9 and Apollo-Soyuz), two lunar orbitingmissions (Apollo 8 and 10), a lunar swingby (Apollo 13), andsix Moon landing missions (Apollo 11, 12, 14, 15, 16, and 17).Two astronauts from each of these six missions walked on theMoon (Neil Armstrong, Edwin Aldrin, Charles Conrad, AlanBean, Alan Shepard, Edgar Mitchell, David Scott, James Irwin,John Young, Charles Duke, Gene Cernan, and HarrisonSchmitt), the only humans to have set foot on another solarsystem body. Total funding for the Apollo program wasapproximately $20,443,600,000.a

For information on the Lunar Module and details of activities onthe lunar surface, see:






Personnel


Dr. Rocco A. Petrone Project Manager NASA Headquarters

Selected References


Diagram of the Apollo CSM courtesy of NASA History Office.Apollo 17 Lunar Module record - LM/ALSEP and surface operationsApollo 17 Home Page - with links to other Apollo 17 sites



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







http://www.usa.gov/








Description

The Apollo 17 Lunar Module (LM) "Challenger" was the sixthand last lunar lander in the Apollo program. It carried twoastronauts, Commander Eugene A. Cernan and LM pilotHarrison H. Schmitt, the eleventh and twelfth men to walk onthe Moon. Schmitt was the first scientist-astronaut to walk onthe Moon. The LM also carried a Lunar Roving Vehicle (LRV),an Apollo Lunar Surface Experiments Package (ALSEP) thatcontained scientific experiments to be deployed and left on thelunar surface, and other scientific and sample collectionapparatus.

Mission ProfileThe LM separated from the Command/Service Module (CSM)at 17:20:56 UT on 11 December 1972 and landed at 19:54:57UT (2:54:57 p.m. EST) on the southeastern rim of MareSerenitatis (the Sea of Serenity) in a dark deposit betweenmassive units of the southwestern Taurus Mountains south ofLittrow Crater, at 20.1908 N latitude, 30.7717 E longitude (IAUMean Earth Polar Axis coordinate system). Cernan andSchmitt made three moonwalk extra-vehicular activities(EVAs) totaling 22 hours, 4 minutes. During this time theycovered 30 km and collected 110.52 kg of lunar samples. TheLRV was used during EVAs to extend the range of mannedlunar exploration. The first EVA was from 23:54:49 UT on 11December to 07:06:42 UT on 12 December, during which theLRV was deployed and driven and the ALSEP was set up.During the second EVA, which began at 23:28:06 UT on 12December and ended at 07:05:02 UT on 13 December, theastronauts deployed explosive packages for the active seismicexperiment and Schmitt discovered a patch of orange soil. Thethird EVA involved more traverses and sample collection andlasted from 22:25:48 UT on 13 December to 05:40:56 UT on14 December. At the end of the final EVA the astronautsunveiled the plaque on the LM and read it on TV, "Here mancompleted his first exploration of the Moon, December 1972A.D. May the spirit of peace in which he came be reflected inthe lives of all mankind." The EVA ended with Gene Cernantaking the final step off the lunar surface. During these EVAsthe astronauts set up the ALSEP and performed otherscientific experiments. The LM lifted off from the Moon on 14December at 22:54:37 UT after 75 hours on the lunar surface.The LM docked with the CSM (piloted by Ronald E. Evans) at01:10:15 UT on 15 December. At 04:51:31 UT on 15December 1972 the LM was jettisoned from the CM and laterfired into the Moon. It struck at 06:50:21 UT at 19.96 N, 30.50E.

Lunar Module Spacecraft and SubsystemsThe lunar module was a two-stage vehicle designed for space

Apollo 17 Lunar Module / ALSEP

NSSDC ID: 1972-096C

Alternate Names

LEM 17

Rover 17

Apollo 17 LM/ALSEP

Challenger

LM-12

Apollo 17C

06307

Facts in Brief


Funding Agencies



Disciplines

Human Crew

Planetary Science

Space Physics


Launch/Orbitalinformation for Apollo 17Lunar Module / ALSEP

PDMP information forApollo 17 Lunar Module /ALSEP

Telecommunicationsinformation for Apollo 17


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


Apollo 17 Lunar Module /ALSEP


















http://nssdc.gsfc.nasa.gov/image/spacecraft/apollo_17_lm.jpg



operations near and on the Moon. The spacecraft mass of16,448 kg was the mass of the LM including astronauts,expendables, and approximately 12,000 kg of propellants. Thefully fueled mass of the ascent stage was about 4985 kg andthe descent stage 11,463 kg. The ascent and descent stagesof the LM operated as a unit until staging, when the ascentstage functioned as a single spacecraft for rendezvous anddocking with the command and service module (CSM). Thedescent stage comprised the lower part of the spacecraft andwas an octagonal prism 4.2 meters across and 1.7 m thick.Four landing legs with round footpads were mounted on thesides of the descent stage and held the bottom of the stage1.5 m above the surface. The distance between the ends of thefootpads on opposite landing legs was 9.4 m. One of the legshad a small astronaut egress platform and ladder. A one meterlong conical descent engine skirt protruded from the bottom ofthe stage. The descent stage contained the landing rocket, twotanks of aerozine 50 fuel, two tanks of nitrogen tetroxideoxidizer, water, oxygen and helium tanks and storage spacefor the lunar equipment and experiments, and in the case ofApollo 15, 16, and 17, the lunar rover. The descent stageserved as a platform for launching the ascent stage and wasleft behind on the Moon.

The ascent stage was an irregularly shaped unit approximately2.8 m high and 4.0 by 4.3 meters in width mounted on top ofthe descent stage. The ascent stage housed the astronauts ina pressurized crew compartment with a volume of 6.65 cubicmeters. There was an ingress-egress hatch in one side and adocking hatch for connecting to the CSM on top. Also mountedalong the top were a parabolic rendezvous radar antenna, asteerable parabolic S-band antenna, and 2 in-flight VHFantennas. Two triangular windows were above and to eitherside of the egress hatch and four thrust chamber assemblieswere mounted around the sides. At the base of the assemblywas the ascent engine. The stage also contained an aerozine50 fuel and an oxidizer tank, and helium, liquid oxygen,gaseous oxygen, and reaction control fuel tanks. There wereno seats in the LM. A control console was mounted in the frontof the crew compartment above the ingress-egress hatch andbetween the windows and two more control panels mountedon the side walls. The ascent stage was launched from theMoon at the end of lunar surface operations and returned theastronauts to the CSM.

The descent engine was a deep-throttling ablative rocket witha maximum thrust of about 45,000 N mounted on a gimbal ringin the center of the descent stage. The ascent engine was afixed, constant-thrust rocket with a thrust of about 15,000 N.Maneuvering was achieved via the reaction control system,which consisted of the four thrust modules, each onecomposed of four 450 N thrust chambers and nozzles pointingin different directions. Telemetry, TV, voice, and rangecommunications with Earth were all via the S-band antenna.VHF was used for communications between the astronautsand the LM, and the LM and orbiting CSM. There wereredundant tranceivers and equipment for both S-band andVHF. An environmental control system recycled oxygen andmaintained temperature in the electronics and cabin. Powerwas provided by 6 silver-zinc batteries. Guidance andnavigation control were provided by a radar ranging system,an inertial measurement unit consisting of gyroscopes andaccelerometers, and the Apollo guidance computer.

Apollo Lunar Surface Experiments Package(ALSEP)The Apollo Lunar Surface Experiments Package (ALSEP)consisted of a set of scientific instruments emplaced at the

Lunar Module / ALSEP

Experiments on Apollo 17Lunar Module / ALSEP

Data collections fromApollo 17 Lunar Module /ALSEP












landing site by the astronauts. The instruments were arrayedaround a central station which supplied power to run theinstruments and communications so data collected by theexperiments could be relayed to Earth. The central station wasa 25 kg box with a stowed volume of 34,800 cubic cm.Thermal control was achieved by passive elements (insulation,reflectors, thermal coatings) as well as power dissipationresistors and heaters. Communications with Earth wereachieved through a 58 cm long, 3.8 cm diameter modifiedaxial-helical antenna mounted on top of the central station andpointed towards Earth by the astronauts. Transmitters,receivers, data processors and multiplexers were housedwithin the central station. Data collected from the instrumentswere converted into a telemetry format and transmitted toEarth. The ALSEP system and instruments were controlled bycommands from Earth. The uplink frequency for all Apollomission ALSEP's was 2119 MHz, the downlink frequency forthe Apollo 17 ALSEP was 2275.5 MHz.

Radioisotope Thermoelectric Generator (RTG)The SNAP-27 model RTG produced the power to run theALSEP operations. The generator consisted of a 46 cm highcentral cylinder and eight radiating rectangular fins with a totaltip-to-tip diameter of 40 cm. The central cylinder had a thinnerconcentric inner cylinder inside, and the two cylinders wereattached along their surfaces by 442 spring-loaded lead-telluride thermoelectric couples mounted radially along thelength of the cylinders. The generator assembly had a totalmass of 17 kg. The power source was an approximately 4 kgfuel capsule in the shape of a long rod which containedplutonium-238 and was placed in the inner cylinder of the RTGby the astronauts on deployment. Plutonium-238 decays with ahalf-life of 89.6 years and produces heat. This heat wouldconduct from the inner cylinder to the outer via thethermocouples which would convert the heat directly toelectrical power. Excess heat on the outer cylinder would beradiated to space by the fins. The RTG producedapproximately 70 W DC at 16 V. (63.5 W after one year.) Theelectricity was routed through a cable to a power conditioningunit and a power distribution unit in the central station tosupply the correct voltage and power to each instrument.

ALSEP Scientific InstrumentsAll ALSEP instruments were deployed on the surface by theastronauts and attached to the central station by cables. TheApollo 17 ALSEP instruments consisted of: (1) a heat flowexperiment, designed to measure the rate of heat loss from thelunar interior and the thermal properties of lunar material; (2) alunar surface gravimeter, designed to measure the lunarsurface gravity and its temporal variations at a selected pointon the surface; (3) a lunar mass spectrometer, designed tomeasure the composition of the tenuous lunar atmosphere; (4)a lunar seismic profiling experiment, to study the physicalproperties of lunar surface and subsurface materials and thestructure of the local near-surface layers; and (5) a lunar ejectaand meteorites experiment, designed to measure the speed,direction, energy, and momentum of cosmic dust particles andlunar ejecta. The central station, located at 20.1921 N latitude,30.7649 E longitude, was turned on at 02:53 UT on 12December 1972 and shut down along with the other ALSEPstations on 30 September 1977.

Personnel


Mr. Floyd I. Roberson Program Manager NASA Headquarters



Mr. Wilbert F. Eichelman Project Manager NASA Johnson Space Center

Dr. John B. Hanley Program Scientist NASA Headquarters

Selected References


Davies, M. E., and T. R. Colvin, Lunar coordinates in the regions of the Apollo landers,J. Geophys. Res., 105, No. E8, 20277-20280, Aug. 2000.

Diagram of the Apollo LM courtesy of NASA History Office.Apollo 17 Command Module recordThe Apollo Lunar Roving VehicleApollo 17 Home PageApollo landing sites and ALSEP and LRRR locations - and information on the modified DMA/603control network



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



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


http://nssdc.gsfc.nasa.gov/planetary/lunar/lunar_sites.txt




http://www.usa.gov/








Description

The Apollo Saturn V SIVB was the third stage of the Saturn Vbooster. The SIVB consisted of a truncated cone with a bottomdiameter of 10.06 m topped by a long cylinder with a diameterof 6.60 m. Total height was 17.80 m. It contained liquidhydrogen and liquid oxygen tanks and a J2 engine. It waslaunched into Earth orbit attached to the Command, Service,and Lunar Modules (CSM and LM). The SIVB provided thethrust to take the CSM and LM from Earth orbit into a lunartransfer orbit. After achieving trajectory towards the Moon, theLM and CSM decoupled from the SIVB at 10:18:02 UT on 7December 1972. The SIVB was left on a course towards theMoon where it impacted at 20:32:41 UT on 10 December 1972at 4.21 S, 12.31 W at approximately 2.55 km/sec, providing aseismic source for the ALSEP seismic stations.

Apollo 17 SIVB

NSSDC ID: 1972-096B

Alternate Names

Apollo sturn V third stage

06301

Facts in Brief


Funding Agency


Discipline

Planetary Science


Launch/Orbitalinformation for Apollo 17SIVB

PDMP information forApollo 17 SIVB

Experiments on Apollo 17SIVB

Data collections fromApollo 17 SIVB



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data
























Personnel


Dr. Charles W. Mathews Project Manager NASA Headquarters


http://www.usa.gov/








Description

Canyon 5 was part of the first series of US signals intelligencesatellites. It was launched by the US Air Force from CapeCanaveral aboard an Atlas Agena-D rocket.

Canyon 5

NSSDC ID: 1972-101A

Alternate Names

1972-101A

06317

Facts in Brief

Launch Date: 1972-12-20Launch Vehicle: Atlas-Agena DLaunchSite: Vandenberg AFB,United StatesMass: 700.0 kg

Funding Agency


Discipline



Launch/Orbitalinformation for Canyon 5

Experiments on Canyon 5

Data collections fromCanyon 5



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Canyon 5 (1972-101A)











http://www.usa.gov/








Description

Cosmos 471 was a third generation, high resolution Sovietphoto surveillance satellite launched from the Baikonurcosmodrome aboard a Soyuz rocket. It was maneuverable.

Cosmos 471

NSSDC ID: 1972-001A

Alternate Names

05764

Facts in Brief

Launch Date: 1972-01-12Launch Vehicle: SoyuzLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 6300.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline



Launch/Orbitalinformation for Cosmos471

Experiments on Cosmos471

Data collections fromCosmos 471



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Cosmos 471


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Cosmos 471


mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 471 (1972-001A)











http://www.usa.gov/








Description

Cosmos 472 was a Soviet DS type military satellite launchedfrom the Plesetsk cosmodrome.

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

Cosmos 472

NSSDC ID: 1972-004A

Alternate Names

05804

Facts in Brief

Launch Date: 1972-01-25LaunchVehicle: Kosmos-2ILaunch Site: Plesetsk,U.S.S.RMass: 250.0 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 473 was a third generation, low resolution Sovietphoto surveillance satellite launched from the Baikonurcosmodrome aboard a Soyuz rocket.

Cosmos 473

NSSDC ID: 1972-006A

Alternate Names

05821

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

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http://www.usa.gov/








Description

Cosmos 474 was a third generation, high resolution Sovietphoto surveillance satellite launched from the Baikonurcosmodrome aboard a Soyuz rocket.

Cosmos 474

NSSDC ID: 1972-008A

Alternate Names

05839

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 475 was part of a 6-satellite Soviet military navigationsystem distributed in orbital planes spaced 30 degrees apart,and launched from the Plesetsk cosmodrome aboard aCosmos rocket. Navigation information was derived fromDoppler-shifted VHF transmissions (approximately 150 and400 MHz) of the satellite position and orbital data. By acquiringfixes from several satellite, a user's location could becalculated with an accuracy of 100 m. The time needed toascertain a position was dependent upon the user's latitudeand the number of operational spacecraft in orbit. Normally,accurate location determination could be made within 1-2hours.

Cosmos 475

NSSDC ID: 1972-009A

Alternate Names

05846

Facts in Brief

Launch Date: 1972-02-25LaunchVehicle: Kosmos-3Launch Site: Plesetsk,U.S.S.RMass: 680.0 kg

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 476 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 476

NSSDC ID: 1972-011A

Alternate Names

05852

Facts in Brief

Launch Date: 1972-03-01Launch Vehicle: SoyuzLaunch Site: Plesetsk,U.S.S.RMass: 4994.0 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 477 was a third generation, low resolution Sovietphoto surveillance satellite launched from the Plesetskcosmodrome aboard a Soyuz rocket. Separated particle fluxand radiation experiment capsule.

Cosmos 477

NSSDC ID: 1972-013A

Alternate Names

05862

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 468 was a third generation, high resolution Sovietphoto surveillance satellite launched from the Plesetskcosmodrome aboard a Soyuz rocket. It was maneuverable.

Cosmos 478

NSSDC ID: 1972-015A

Alternate Names

05885

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 479

NSSDC ID: 1972-017A

Alternate Names

05894

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

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Maps

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http://www.usa.gov/








Description

Cosmos 480 was a Soviet geodetic satellite launched from thePlesetsk cosmodrome aboard a Cosmos 11 rocket.

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

Cosmos 480

NSSDC ID: 1972-019A

Alternate Names

05905

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Earth Science







Spacecraft

Experiments

Data Collections

Personnel

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Maps

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http://www.usa.gov/








Description

Cosmos 481 was a military weather satellite launched as partof the Cosmos space research program. Its actual mission wasto determine cloudcover conditions over selected areas.Cosmos 481 was one of a long series of spin-stabilizedspacecraft that is believed to have originated concurrently withthe Soviets first tests, in 1962, of recoverable reconnaissancesatellites. To achieve greater spatial resolution, these Cosmosmilitary weather satellites were launched into relatively loworbits. Consequently, the spacecraft had a fairly short lifetime(generally five to six months) and had to be continuallyreplaced. It appeared that launches of this type were mademost frequently in spring and summer, and tapered off in thewinter months. Other than this, little is known about theCosmos military weather satellite.

Cosmos 481

NSSDC ID: 1972-020A

Alternate Names

05906

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

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Maps

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http://www.usa.gov/








Description

This mission has been identified as an attempted Venus probewhich failed to escape low Earth orbit. It was launched by anSL-6/A-2-e launcher 4 days after the Venera 8 atmosphericprobe and may have been similar in design and mission plan.After achieving an Earth parking orbit, the spacecraft made anapparent attempt to launch into a Venus transfer trajectory. Itseparated into four pieces, two of which remained in low Earthorbit and decayed within 48 hours, and two pieces(presumably the payload and detached engine unit) went intoa higher 210 x 9800 km orbit. It is thought that a malfunctionresulted in an engine burn which did not achieve sufficientvelocity for the Venus transfer and left the payload in thiselliptical Earth orbit.

Beginning in 1962, the name Cosmos was given to Sovietspacecraft which remained in Earth orbit, regardless ofwhether that was their intended final destination. Thedesignation of this mission as an intended planetary probe isbased on evidence from Soviet and non-Soviet sources andhistorical documents. Typically Soviet planetary missions wereinitially put into an Earth parking orbit as a launch platform witha rocket engine and attached probe. The probes were thenlaunched toward their targets with an engine burn with aduration of roughly 4 minutes. If the engine misfired or the burnwas not completed, the probes would be left in Earth orbit andgiven a Cosmos designation.

Cosmos 482

NSSDC ID: 1972-023A

Alternate Names

05919

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Planetary Science



PDMP information forCosmos 482

Telecommunicationsinformation for Cosmos482





Spacecraft

Experiments

Data Collections

Personnel

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Maps

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Personnel


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

Selected References

Cosmos 482 identified as failed Venus mission, Aviat. Week Space Technol., 96, No. 15, 15,Apr. 1972.

Shelton, W., Soviet space exploration - the first decade, Arthur Barker Ltd., Unnumbered,London, England, 1969.

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


http://www.usa.gov/








Description


Cosmos 483

NSSDC ID: 1972-024A

Alternate Names

05924

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

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http://www.usa.gov/








Description

Cosmos 484 was a third generation, low resolution Sovietphoto surveillance satellite launched from Plesetskcosmodrome aboard a Soyuz rocket. Separated cosmic rayexperiment capsule.

Cosmos 484

NSSDC ID: 1972-026A

Alternate Names

05933

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 485 was a military weather satellite launched as partof the Cosmos space research program. Its actual mission wasto determine cloudcover conditions over selected areas.Cosmos 485 was one of a long series of spin-stabilizedspacecraft that was believed to have originated concurrentlywith the Soviets first tests, in 1962, of recoverablereconnaissance satellites. To achieve greater spatialresolution, these Cosmos military weather satellites werelaunched into relatively low orbits. Consequently, thespacecraft had a fairly short lifetime (generally five to sixmonths) and were continually replaced. It appeared thatlaunches of this type were made most frequently in spring andsummer, and taper off in the winter months. Other than this,little is known about the Cosmos military weather satellites.

Cosmos 485

NSSDC ID: 1972-028A

Alternate Names

05938

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

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Maps

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http://www.usa.gov/








Description


Cosmos 486

NSSDC ID: 1972-030A

Alternate Names

05945

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 487 was a military weather satellite launched as partof the Cosmos space research program. Its actual mission wasto determine cloudcover conditions over selected areas.Cosmos 487 was one of a long series of spin-stabilizedspacecraft that was believed to have originated concurrentlywith the Soviets first tests, in 1962, of recoverablereconnaissance satellites. To achieve greater spatialresolution, these Cosmos military weather satellites werelaunched into relatively low orbits. Consequently, thespacecraft had a fairly short lifetime (generally five to sixmonths) and had to be continually replaced. It appears thatlaunches of this type were made most frequently in spring andsummer, and taper off in the winter months. Other than this,little is know about the Cosmos military satellite.

Cosmos 487

NSSDC ID: 1972-033A

Alternate Names

06006

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 488

NSSDC ID: 1972-034A

Alternate Names

06016

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 489

NSSDC ID: 1972-035A

Alternate Names

06019

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 490 was a third generation, low resolution Sovietphoto surveillance satellite launched from the Plesetskcosmodrome aboard a Soyuz rocket. Separated electron fluxcosmic ray experiment capsule.

Cosmos 490

NSSDC ID: 1972-036A

Alternate Names

06021

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 491

NSSDC ID: 1972-038A

Alternate Names

06035

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 492

NSSDC ID: 1972-040A

Alternate Names

06049

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 493

NSSDC ID: 1972-042A

Alternate Names

06053

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 494

NSSDC ID: 1972-043A

Alternate Names

06059

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 495 was a third generation, high resolution Sovietphoto surveillance satellite launched from the Plesetskcosmodrome aboard a Soyuz rocket.

Cosmos 495

NSSDC ID: 1972-044A

Alternate Names

06060

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 496 was an unmanned spacecraft launched to test animproved model of the Soyuz spacecraft. In particular thespacecraft was designed to test new equipment and safetyfeatures incorporated into Soyuz since the flight of Soyuz 11,the three-man crew of which was found dead by recoverypersonnel after an apparently normal re-entry and recovery.Cosmos 496 was launched on June 26, 1972 and successfullyre-entered the earth's atmosphere six days later, paving theway for future USSR manned space flight.

Cosmos 496

NSSDC ID: 1972-045A

Alternate Names

06066

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Engineering







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 497 was a military weather satellite launched as partof the Cosmos space research program. Its actual mission wasto determine cloudcover conditions over selected areas.Cosmos 497 was one of a long series of spin-stabilizedspacecraft believed to have originated concurrently with theSoviets first test by the Soviet Union of recoverablereconnaissance satellite in 1962. To achieve greater spatialresolution, these Cosmos military weather satellites werelaunched into relatively low orbits. Consequently, thesespacecraft have a fairly short lifetime (generally five to sizemonths) and must be continually replaced.

Cosmos 497

NSSDC ID: 1972-048A

Alternate Names

06076

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 498 was a military weather satellite launched as partof the Cosmos space research program. Its actual mission wasto determine cloudcover conditions over selected areas.Cosmos 498 was one of a long series of spin-stabilizedspacecraft that is believed to have originated concurrently withthe Soviets first tests, in 1962, of recoverable reconnaissancesatellites. To achieve greater spatial resolution, these Cosmosmilitary weather satellites were launched into relatively loworbits. Consequently, the spacecraft has a fairly short lifetime(generally five to six months) and must be continually replaced.It appears that launches of this type are made most frequentlyin spring and summer, and taper off in the winter months.Other than this, little is known about the Cosmos militaryweather satellite.

Cosmos 498

NSSDC ID: 1972-050A

Alternate Names

06086

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 499

NSSDC ID: 1972-051A

Alternate Names

06090

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 500

NSSDC ID: 1972-053A

Alternate Names

06097

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 501 was a Soviet DS type military satellite launchedfrom Kapustin Yar.

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

Cosmos 501

NSSDC ID: 1972-054A

Alternate Names

06099

Facts in Brief

Launch Date: 1972-07-12LaunchVehicle: Kosmos-2ILaunch Site: KapustinYar, U.S.S.RMass: 250.0 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 502 was a third generation, low resolution Sovietphoto surveillance satellite launched from the Plesetskcosmodrome aboard a Soyuz rocket. The spacecraft carried ascience package.

Cosmos 502

NSSDC ID: 1972-055A

Alternate Names

06105

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 503

NSSDC ID: 1972-056A

Alternate Names

06114

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

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

Cosmos 504

NSSDC ID: 1972-057A

Alternate Names

06117

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 505

NSSDC ID: 1972-057B

Alternate Names

06118

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 505 (1972-057B)











http://www.usa.gov/








Description


Cosmos 506

NSSDC ID: 1972-057C

Alternate Names

06119

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 506 (1972-057C)











http://www.usa.gov/








Description


Cosmos 507

NSSDC ID: 1972-057D

Alternate Names

06120

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 507 (1972-057D)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1972-057E[14/08/2010 23:57:30]


Description


Cosmos 508

NSSDC ID: 1972-057E

Alternate Names

06121

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=1972-057E







mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 508 (1972-057E)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1972-057F[14/08/2010 23:57:52]

Sunday, 15 August 2010

Description


Cosmos 509

NSSDC ID: 1972-057F

Alternate Names

06122

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=1972-057F







mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 509 (1972-057F)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1972-057G[14/08/2010 23:58:13]


Description


Cosmos 510

NSSDC ID: 1972-057G

Alternate Names

06123

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=1972-057G







mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 510 (1972-057G)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1972-057H[14/08/2010 23:58:36]


Description


Cosmos 511

NSSDC ID: 1972-057H

Alternate Names

06124

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=1972-057H







mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 511 (1972-057H)











http://www.usa.gov/








Description

Cosmos 512 was a third generation, low resolution Sovietphoto surveillance satellite launched from the Plesetskcosmodrome aboard a Soyuz rocket.

Cosmos 512

NSSDC ID: 1972-059A

Alternate Names

06130

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 513

NSSDC ID: 1972-060A

Alternate Names

06135

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 514

NSSDC ID: 1972-062A

Alternate Names

06148

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 515 was third generation, high resolution Soviet photosurveillance satellite launched from the Plesetsk cosmodromeaboard a Soyuz rocket. It was maneuverable.

Cosmos 515

NSSDC ID: 1972-063A

Alternate Names

06150

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 516 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 516

NSSDC ID: 1972-066A

Alternate Names

06154

Facts in Brief

Launch Date: 1972-08-21LaunchVehicle: Tsiklon-2Launch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 3800.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 517

NSSDC ID: 1972-067A

Alternate Names

06168

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 518 was a third generation, low resolution Sovietphoto surveillance satellite launched from the Plesetskcosmodrome aboard a Soyuz rocket. Separated sciencecapsule.

Cosmos 518

NSSDC ID: 1972-070A

Alternate Names

06186

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 519

NSSDC ID: 1972-071A

Alternate Names

06188

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 520 was a Soviet missile early warning satellitelaunched from the Plesetsk cosmodrome aboard a Molniyarocket. It was part of the Oko constellation and covered theplane 3 - 355 degree longitude of ascending node.

Cosmos 520

NSSDC ID: 1972-072A

Alternate Names

06192

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 521 was an ASAT target launched to testmodifications to ASAT interceptor. Interceptor launch cancelleddue to technical failure in target telemetry system. Signature ofSALT treaty in May 1972 resulted in military being ordered todiscontinue further ASAT tests.

Cosmos 521

NSSDC ID: 1972-074A

Alternate Names

06206

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 522

NSSDC ID: 1972-077A

Alternate Names

06219

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 523

NSSDC ID: 1972-078A

Alternate Names

06222

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 524 was a military weather satellite launched as partof the Cosmos space research program. Its actual mission wasto determine cloudcover conditions over selected areas.Cosmos 524 was one of a long series of spin-stabilizedspacecraft that is believed to have originated concurrently withthe Soviets first tests, in 1962, of recoverable reconnaissancesatellites. To achieve greater spatial resolution, these Cosmosmilitary weather satellites were launched into relatively loworbits. Consequently, the spacecraft had a fairly short lifetime(generally five to six months) and were continually replaced. Itappears that launches of this type are made most frequently inspring and summer, and taper off in the winter months. Otherthan this, little is known about the Cosmos military weathersatellite.

Cosmos 524

NSSDC ID: 1972-080A

Alternate Names

06229

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 525

NSSDC ID: 1972-083A

Alternate Names

06248

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 526

NSSDC ID: 1972-084A

Alternate Names

06254

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 527

NSSDC ID: 1972-086A

Alternate Names

06260

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 528

NSSDC ID: 1972-087A

Alternate Names

06262

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 529

NSSDC ID: 1972-087B

Alternate Names

06264

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 530

NSSDC ID: 1972-087C

Alternate Names

06265

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 531

NSSDC ID: 1972-087D

Alternate Names

06266

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=1972-087E[15/08/2010 0:09:12]


Description


Cosmos 532

NSSDC ID: 1972-087E

Alternate Names

06267

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=1972-087F[15/08/2010 0:09:39]


Description


Cosmos 533

NSSDC ID: 1972-087F

Alternate Names

06268

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=1972-087G[15/08/2010 0:10:00]


Description


Cosmos 534

NSSDC ID: 1972-087G

Alternate Names

06269

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=1972-087H[15/08/2010 0:10:24]


Description


Cosmos 535

NSSDC ID: 1972-087H

Alternate Names

06270

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 536

NSSDC ID: 1972-088A

Alternate Names

06272

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 537

NSSDC ID: 1972-093A

Alternate Names

06287

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


National Space Science Data Center Header

Cosmos 538

NSSDC ID: 1972-099A

Alternate Names

06311

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 539 was a Soviet geodetic satellite launched from thePlesetsk cosmodrome aboard a Cosmos 11 rocket.

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

Cosmos 539

NSSDC ID: 1972-102A

Alternate Names

06319

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

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 540

NSSDC ID: 1972-104A

Alternate Names

06323

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 541

NSSDC ID: 1972-105A

Alternate Names

06326

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 542

NSSDC ID: 1972-106A

Alternate Names

06328

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

DENPA was a spacecraft with a diameter of 75 cm, anoctagonal column form, and a height of 75 cm. Threeantennas, each 2 m long, were extended from the mainstructure. A fluxgate magnetometer sensor was located on theboom 0.5 m from the base. The satellite was spin stabilized atabout 3 rps. Power was supplied from 5000 silicon N-P solarcells mounted on the octagonal faces to supply minimumaverage power of 13 w. Data from experiments were stored ina tape recorder and transmitted from the 136-mHz PCMtelemeter by ground command. The primary objectives ofDENPA was to measure electromagnetic wave, plasma wave,ambient electron density, energetic electron flux, cyclotronwave instability, and magnetic disturbances in the ionosphereand the lower magnetosphere. The satellite stoppedtransmitting radio signals several days after launch. Thereforeno scientific results were obtained from this mission. The finalreport concluded that the satellite malfunction was due to highvoltage arching that occurred after instrument turn on.

DENPA

NSSDC ID: 1972-064A

Alternate Names

MU-4S-4

06152

Facts in Brief

Launch Date: 1972-08-19Launch Vehicle: MuLaunch Site: UchinouraSpace Center, JapanMass: 75.0 kg

Funding Agency

Institute of Space andAeronautical Science, Uof Tokyo (Japan)

Discipline

Space Physics


Launch/Orbitalinformation for DENPA

Experiments on DENPA

Data collections fromDENPA


Personnel


Prof. Tatsuzo Project Institute of Space and Aeronautical


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: DENPA (1972-064A)

mailto:[email protected]?Subject=NMC Comment/Question: DENPA (1972-064A)











Obayashi Manager Science


http://www.usa.gov/








Description

DMSP (72-018A), also known as DMSP 5528, was one of aseries of meteorological satellites developed and operated bythe Air Force under the Defense Meteorological SatelliteProgram. This program, previously known as Data Acquisitionand Processing Program (DAPP), was classified until March1973. The objective of this program was to provide globalvisual and infrared (IR) cloudcover data and specializedenvironmental data to support Department of Defenserequirements. Operationally, the program consisted of twosatellites in 830 km sun-synchronous polar orbits, with theascending node of one satellite near the sunrise terminatorand the other near local noon. The satellite, shaped like thefrustum of a polyhedron, consisted of four subassemblies -- (1)a solar array hat, (2) a base-plate assembly, (3) a Sensor AVE(Aerospace Vehicle Electronics) Package (SAP), and (4) adata processing system. The primary sensor (SAP) was athree channel scanning radiometer which was mounted on thebase-plate assembly. Spacecraft stabilization was controlledby a combination flywheel and magnetic control coil system sothat the sensors were maintained in the desired earth-lookingmode. The data processing system included three taperecorders capable of storing a total of 440 min of data, whichallowed full global coverage twice daily. Either recorded orreal-time data were transmitted to ground receiving sites viaan s-band transmitter. Recorded data were read out totracking sites located at Fairchild AFB, WA, and Loring AFB,ME, and relayed to Air Force Global Weather Central, OffuttAFB, NE. Real-time data were read out at mobile tactical siteslocated around the world. The spacecraft was reactivated for abrief period beginning Oct 12, 1975 to study spacecraftdeterioration which had occurred during the past 1.5 years.

DMSP 5B/F2

NSSDC ID: 1972-018A

Alternate Names

DMSP 5528

05903

Facts in Brief


Funding Agency


Disciplines

Earth Science

Space Physics


Launch/Orbitalinformation for DMSP5B/F2

Experiments on DMSP5B/F2

Data collections fromDMSP 5B/F2


Personnel


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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


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


mailto:[email protected]?Subject=NMC Comment/Question: DMSP 5B/F2 (1972-018A)













Project Manager US Air Force Space Division


http://www.usa.gov/








Description

DMSP (72-089A), also known as DMSP 6530, was one of aseries of meteorological satellites developed and operated bythe Air Force under the Defense Meteorological SatelliteProgram. The program, previously known as Data Acquisitionand Processing Program (DAPP), was classified until March1973. The objective of this program was to provide globalvisual and infrared (IR) cloudcover data and specializedenvironmental data to support Department of Defenserequirements. Operationally, the program consisted of twosatellites in 830 km sun-synchronous polar orbits, with theascending node of one satellite near the sunrise terminatorand the other near local noon. The satellite, shaped like thefrustum of a polyhedron, consisted of four subassemblies -- (1)a solar array hat, (2) a base-plate assembly, (3) a sensor AVE(Aerospace Vehicle Electronics) package (SAP), and (4) a dataprocessing system. The primary sensor (SAP) was a fourchannel scanning radiometer. Secondary sensors included avertical temperature profile radiometer (supplementary sensorE -SSE) and an electron spectrograph (supplementary sensorJ/2 - SSJ/2), which were mounted, along with the primarysensor, on the base-plate assembly. Spacecraft stabilizationwas controlled by a combination flywheel and magnetic controlcoil system so that the sensors were maintained in the desiredearth-looking mode. The data processing system includedthree tape recorders capable of storing a total of 440 min ofdata, which allowed full global coverage twice daily. Eitherrecorded or real-time data were transmitted to groundreceiving sites via an s-band transmitter. Recorded data wereread out to tracking sites located at Fairchild AFB, Wa, andLoring AFB, ME, and relayed to Air Force Global WeatherCentral, Offutt AFB, NE. Real-time data were read out amobile tactical sites located arounf the world.

DMSP 5B/F3

NSSDC ID: 1972-089A

Alternate Names

DMSP 6530

06275

Facts in Brief

Launch Date: 1972-11-09Launch Vehicle: Thor-Burner IILaunchSite: Vandenberg AFB,United StatesMass: 195.0 kg

Funding Agency


Disciplines

Earth Science

Space Physics


Launch/Orbitalinformation for DMSP5B/F3

Experiments on DMSP5B/F3

Data collections fromDMSP 5B/F3



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















Personnel


Project Manager US Air Force Space Division


http://www.usa.gov/








Description

The ESRO 4 spacecraft was designed to investigate neutralparticle and ion concentrations in the ionosphere and nearmagnetosphere, to detect auroral particles, and to monitorsolar particles in order to discover the mechanism by whichthey penetrate and diffuse in the magnetosphere. Thespacecraft was launched into a polar orbit with a nodalregression rate near zero, thus providing a complete scan oflocal time in 1 year. To provide an altitude scan over the wholeglobe, the perigee precessed at a rate of -3.5 deg/day. Thespacecraft was cylindrical in shape (similar in construction toESRO 2), was spin stabilized, and used a PCM/PM telemetrymode transmitted in three forms: real-time telemetry at 64 bps,tape-recorder playback, and high-speed telemetry at 10,240bps. The spacecraft spin rate was about 1 rps. The spin axisdirection was changed periodically during the mission. Thespacecraft reentered the earth's atmosphere after a successfulmission on April 15, 1974.

ESRO 4

NSSDC ID: 1972-092A

Alternate Names

06285

Facts in Brief


Funding Agency

European Space Agency(International)

Discipline

Space Physics


Launch/Orbitalinformation for ESRO 4

Experiments on ESRO 4

Data collections fromESRO 4



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: ESRO 4 (1972-092A)

mailto:[email protected]?Subject=NMC Comment/Question: ESRO 4 (1972-092A)









http://www.usa.gov/








Description

HEOS 2 was a spin-stabilized spacecraft with a highlyeccentric orbit whose apogee occurred at high latitude. Itsprimary scientific mission was the investigation ofinterplanetary space and the high-latitude magnetosphere andits boundary in the region around the northern neutral point.HEOS 2 provided new data on the sources and accelerationmechanisms of particles found in the trapped radiation beltsand in the polar precipitation regions and auroral zones. It alsomonitored solar activity and cosmic radiation. The satellitecarried a magnetometer and particle detectors which covered abroad range from thermal to cosmic-ray energies. The satellitehad three antennas to study extreme low frequency (ELF)waves and carried a sensitive micrometeorite detector. Thespacecraft functioned normally until it reentered the earth'satmosphere on August 5, 1974.

HEOS 2

NSSDC ID: 1972-005A

Alternate Names

HEOS-A2

05814

Facts in Brief

Launch Date: 1972-01-31Launch Vehicle: DeltaLaunchSite: Vandenberg AFB,United StatesMass: 108.0 kg

Funding Agency


Discipline

Space Physics


Launch/Orbitalinformation for HEOS 2

Experiments on HEOS 2

Data collections fromHEOS 2


Personnel



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: HEOS 2 (1972-005A)













Mr. C. W. Thomas GeneralContact

ESA-European Space Research andTechnology Centre

Mr. R. Collette GeneralContact


Dr. J.Vandenkerckhove

ProjectManager


Dr. Brian G. Taylor ProjectScientist



http://www.usa.gov/








Description

IMEWS 3 was the third in a series of first generation DSPprogram of Integrated Missile Early Warning Satellitesmanufactered by TRW for the US Air Force. The spacecraftspun slowly (6 rpm) about the nadir axis to permit scanning ofthe Earth by the detector system. Body mounted anddeployable panels provided 400W of power.

IMEWS 3

NSSDC ID: 1972-010A

Alternate Names

Code 647

Early Warning 3

DSP F3

05851

Facts in Brief

Launch Date: 1972-03-01Launch Vehicle: TitanIII-CLaunch Site: CapeCanaveral, United StatesMass: 820.0 kg

Funding Agency


Discipline



Launch/Orbitalinformation for IMEWS 3

Experiments on IMEWS 3

Data collections fromIMEWS 3


Image courtesy of the USAF Defense Support Program.


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


IMEWS 3




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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: IMEWS 3 (1972-010A)











http://nssdc.gsfc.nasa.gov/image/spacecraft/dsp_f03.jpg




Description

IMP-H continued the study begun by earlier IMP spacecraft ofthe interplanetary and magnetotail regions from a nearlycircular orbit, near 37 earth radii. This 16-sided drum-shapedspacecraft was 157 cm high and 135 cm in diameter. It wasdesigned to measure energetic particles, plasma, and electricand magnetic fields. The spin axis was normal to the eclipticplane, and the spin period was 1.3 s. The spacecraft waspowered by solar cells and a chemical battery. Scientific datawere telemetered at 1600 bps (with a secondary 400-bps rateavailable). The spacecraft was turned off on October 31, 1978.

IMP-H

NSSDC ID: 1972-073A

Alternate Names

Explorer 47

IMP 7

06197

Facts in Brief

Launch Date: 1972-09-23Launch Vehicle: DeltaLaunch Site: CapeCanaveral, United StatesMass: 390.0 kg

Funding Agency


Disciplines

Solar Physics

Space Physics


Launch/Orbitalinformation for IMP-H

Experiments on IMP-H

Data collections from IMP-H


Personnel


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: IMP-H (1972-073A)














Mr. John R. Holtz ProgramManager

NASA Headquarters

Mr. William R.Limberis

ProjectManager

NASA Goddard Space FlightCenter

Dr. Norman F.Ness

ProjectScientist


[email protected]

Dr. Joseph H.King

ProjectScientist


[email protected]

Dr. Erwin R.Schmerling

ProgramScientist

NASA Headquarters

Dr. James H.Trainor

GeneralContact


Other IMP 7 Data/Information at NSSDCRetrieve/browse OMNI (hourly solar wind field/plasma) data with OMNIWeb

Related Data/Information at NSSDCIMP 8Information on other IMP spacecraftInformation on other Explorer spacecraft

Other Sources of IMP 7 Data/InformationDaily LEPEDEA (IMP 7 and IMP 8) spectrograms at U. Iowa


http://nssdc.gsfc.nasa.gov/omniweb/ow.html

http://nssdc.gsfc.nasa.gov/omniweb/ow.html

http://nssdc.gsfc.nasa.gov/space/imp-8.html

http://nssdc.gsfc.nasa.gov/space/imp.html

http://nssdc.gsfc.nasa.gov/multi/explorer.html

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

http://www.usa.gov/








Description

INTELSAT 4 F-4 was a communication satellite with acylindrical diameter of 238 cm, 281 cm solar drum height, and528 cm overall height. Electric power was supplied by solarcells mounted on the solar drum face. The satellite hadmultiple access and simultaneous transmission capabilitieswith a capacity of 3000 circuits with transponder in the earthmode and 9000 circuits with transponder in the spot-beamcoverage mode, or 12 TV channels or certain combinations.There were 12 transponders, each with a 36-MHz bandwidth,two global transmit antennas, two global receive antennas, andtwo steerable spot-beam transmit antennas. The design life ofthe satellite was 7 years.

INTELSAT 4 F-4

NSSDC ID: 1972-003A

Alternate Names

05775

Facts in Brief

Launch Date: 1972-01-23Launch Vehicle: AtlasLaunch Site: CapeCanaveral, United StatesMass: 1410.0 kg

Funding Agency

InternationalTelecommunicationsSatellite Corporation(International)

Discipline

Communications


Launch/Orbitalinformation for INTELSAT4 F-4

Experiments on INTELSAT4 F-4

Data collections fromINTELSAT 4 F-4



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







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


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


mailto:[email protected]?Subject=NMC Comment/Question: INTELSAT 4 F-4 (1972-003A)











http://www.usa.gov/








Description

INTELSAT 4 F-5 was a communcations satellite with acylindrical diameter of 238 cm, 281 cm solar drum height, and528 cm overall height. Electic power was supplied by solarcells mounted on the solar drum face. The satellite hadmultiple access and simultaneous transmission capabilitieswith a capacity of 3000 circuits with transponder in the earthmode and 9000 circuits with transponder in the spot-beamcoverage mode, or 12 TV channels or certain combination.There were 12 transponders, each with a 36-MHz bandwidth,two global transmit antennas, two global receive antennas, andtwo steerable spot-beam transmit antennas. The design life ofthe satellite was 7 years.

INTELSAT 4 F-5

NSSDC ID: 1972-041A

Alternate Names

06052

Facts in Brief

Launch Date: 1972-06-13Launch Vehicle: AtlasLaunch Site: CapeCanaveral, United StatesMass: 1410.0 kg

Funding Agency

InternationalTelecommunicationsSatellite Corporation(International)

Discipline

Communications


Launch/Orbitalinformation for INTELSAT4 F-5

Experiments on INTELSAT4 F-5

Data collections fromINTELSAT 4 F-5



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Intercosmos 6 was the first of a series of second generationIntercosmos research satellite to be launched. It was largerand heavier than the previous five Intercosmos satellites andweighed nearly 1825 kg. It carried a scientific package,weighing more than 1044 kg, that consisted of experimentsthat were joint ventures of the COMECON East Europe bloc.The main instrument on board was an ionization calorimeterassembled by the Soviets with components supplied byHungary, Poland, Czechoslavakia, and Romania. Also includedwas a multilayered silver bromide photographic emulsiondesigned to track high-energy cosmic radiation, as well aselectronic equipment to detect, identify, and measure thisradiation. Experience gained from the heavy proton satelliteseries was used in the construction and design of Intercosmos6. The satellite measured (1) primary cosmic radiation withenergies from 10 to the 12 power to 10 to the 13 power ev, (2)the chemical composition and energy spectra of high-energyradiation in space, and (3) meteoroid particles. The satellitereturned to earth after only 4 days in orbit and was recoveredintact. The low altitude of the flight and the 4-day durationwere both chosen to collect optimum data, i.e., to stay belowthe Van Allen radiation belt and thus prevent too muchradiation from passing through the emulsion.

Intercosmos 6

NSSDC ID: 1972-027A

Alternate Names

IK- 6

05936

Facts in Brief

Launch Date: 1972-04-07LaunchVehicle: Modified SS-6(Sapwood) with 2ndGeneration (Longer) UpperStageLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 1825.0 kg

Funding Agency

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

Discipline

Space Physics


Launch/Orbitalinformation forIntercosmos 6

Experiments onIntercosmos 6

Data collections fromIntercosmos 6



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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


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


mailto:[email protected]?Subject=NMC Comment/Question: Intercosmos 6 (1972-027A)














Description

This spacecraft was a continuation of research started withIntercosmos 1 and 4. It was designed for solar study. Datafrom it were to be correlated with information received fromPrognoz 2. Earlier solar-study Intercosmos spacecraft werelaunched in the fall of the year, but early summer was selectedfor Intercosmos 7 to improve the chances of matching datawith visual solar observations. Intercosmos 7 carried EastGerman and Czechoslovakian as well as Soviet equipmentand was part of the Comecon East Europe trading bloc jointspace research program.

Intercosmos 7

NSSDC ID: 1972-047A

Alternate Names

IK- 7

06075

Facts in Brief

Launch Date: 1972-06-30LaunchVehicle: Modified SS-4(Sandal IRBM) plus UpperStageLaunch Site: KapustinYar, U.S.S.RMass: 375.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Solar Physics







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

This spacecraft was a follow-on to Intercosmos 2, but wasintended for higher latitudes. It was designed to obtain data on:(1) the concentration of electrons and positive ions in theimmediate vicinity of the spacecraft while in orbit; (2) theelectron temperature and the total electron columnconcentration (between the satellite and the earth's surface) atvarious points in flight; and, (3) particle streams of electronswith energies >40 KeV and protons with energies >1 MeV. Thespacecraft contained a Bulgarian-made ion trap as well assensing and measuring equipment made in East Germany andCzechoslovakia. The majority of on-board equipment wasSoviet.

Intercosmos 8

NSSDC ID: 1972-094A

Alternate Names

IK- 8

06291

Facts in Brief

Launch Date: 1972-11-30LaunchVehicle: Modified SS-4(Sandal IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 340.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Space Physics







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

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

KH 8-34

NSSDC ID: 1972-016A

Alternate Names

1972-016A

05888

Facts in Brief


Funding Agency


Discipline



Launch/Orbitalinformation for KH 8-34

Experiments on KH 8-34

Data collections from KH 8-34



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=KH 8-34

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=KH 8-34


mailto:[email protected]?Subject=NMC Comment/Question: KH 8-34 (1972-016A)











http://www.usa.gov/








Description

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

KH 8-36

NSSDC ID: 1972-068A

Alternate Names

1972-068A

06172

Facts in Brief


Funding Agency


Discipline








Spacecraft

Experiments

Data Collections

Personnel

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Maps

New/Updated Data




















http://www.usa.gov/








Description

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

KH 8-37

NSSDC ID: 1972-103A

Alternate Names

1972-103A

06321

Facts in Brief


Funding Agency


Discipline








Spacecraft

Experiments

Data Collections

Personnel

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Maps

New/Updated Data




















http://www.usa.gov/








Description

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

KH 9-02

NSSDC ID: 1972-002A

Alternate Names

1972-002A

05769

Facts in Brief


Funding Agency


Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


KH 9-03

NSSDC ID: 1972-052A

Alternate Names

1972-052A

06094

Facts in Brief


Funding Agency


Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description


KH 9-04

NSSDC ID: 1972-079A

Alternate Names

1972-079A

06227

Facts in Brief


Funding Agency


Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















http://www.usa.gov/








Description

This US Air Force photo surveillance satellite was launchedfrom Vandenberg AFB aboard a Thor Agena D rocket. It was aKH-4B (Key Hole-4B) type spacecraft. It was a very successfulmission and image quality was good. Final CORONA mission.

KH-4B 1117

NSSDC ID: 1972-039A

Alternate Names

SESP 71-5

1972-039A

06037

Facts in Brief


Funding Agency


Discipline



Launch/Orbitalinformation for KH-4B1117

Experiments on KH-4B1117

Data collections from KH-4B 1117



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=KH-4B 1117

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=KH-4B 1117

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=KH-4B 1117

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=KH-4B 1117

mailto:[email protected]?Subject=NMC Comment/Question: KH-4B 1117 (1972-039A)











http://www.usa.gov/







Description

Landsat 1 (formerly ERTS 1) was a modified version of theNimbus 4 meteorological satellite. The near-polar orbitingspacecraft served as a stabilized, earth-oriented platform forobtaining information on agricultural and forestry resources,geology and mineral resources, hydrology and waterresources, geography, cartography, environmental pollution,oceanography and marine resources, and meteorologicalphenomena. To accomplish these objectives, the spacecraftwas equipped with (1) a three-camera return beam vidicon(RBV) to obtain visible and near IR photographic images of theearth, (2) a four-channel multispectral scanner (MSS) to obtainradiometric images of the earth, and (3) a data collectionsystem (DCS) to collect information from remote, individuallyequipped ground stations and to relay the data to centralacquisition stations. Landsat 1 carried two wide-band videotape recorders (WBVTR) capable of storing up to 30 min ofscanner or camera data to give the spacecraft's sensors anear-global coverage capability. An advanced attitude controlsystem consisting of horizon scanners, sun sensors, and acommand antenna combined with a freon gas propulsionsystem permitted the spacecraft's orientation to be maintainedwithin plus or minus 0.7 deg in all three axes. Spacecraftcommunications included a command subsystem operating at154.2 and 2106.4 MHz and a PCM narrow-band telemetrysubsystem, operating at 2287.5 and 137.86 MHz, forspacecraft housekeeping, attitude, and sensor performancedata. Video data from the three-camera RBV system wastransmitted in both real-time and tape-recorder modes at2265.5 MHz, while information from the MSS was constrainedto a 20-MHz rf bandwidth at 2229.5 MHz. The spacecraft wasturned off on January 6, 1978, when cumulative precession ofthe orbital plane caused the spacecraft to see almost constantsunlight which led to overheating. More information can befound in "Landsat Data Users Handbook," available from U.S.Geological Survey, Arlington, Va.

Landsat 1

NSSDC ID: 1972-058A

Alternate Names

ERTS-A

06126

Facts in Brief


Funding Agency

NASA-Office of Spaceand TerrestrialApplications (UnitedStates)

Disciplines

Engineering

Earth Science


Launch/Orbitalinformation for Landsat 1

Experiments on Landsat 1

Data collections fromLandsat 1


Personnel


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Landsat 1 (1972-058A)














Mr. Charles M.MacKenzie

Project Manager NASA Goddard Space FlightCenter

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

Dr. B. T. Nolan ProgramManager

NASA Headquarters

Ms. Ruth I. Whitman ProgramScientist

NASA Headquarters


http://www.usa.gov/








Description

Luna 20 was placed in an intermediate earth parking orbit andfrom this orbit was sent towards the Moon. It entered lunar orbiton February 18, 1972. On 21 February 1972, Luna 20 softlanded on the Moon in a mountainous area known as theApollonius highlands near Mare Foecunditatis (Sea of Fertility),120 km from where Luna 16 had impacted. While on the lunarsurface, the panoramic television system was operated. Lunarsamples were obtained by means of an extendable drillingapparatus. The ascent stage of Luna 20 was launched from thelunar surface on 22 February 1972 carrying 30 grams ofcollected lunar samples in a sealed capsule. It landed in theSoviet Union on 25 February 1972. The lunar samples wererecovered the following day.

Luna 20

NSSDC ID: 1972-007A

Alternate Names

Lunik 20

05835

Facts in Brief

Launch Date: 1972-02-14Launch Vehicle: ProtonBooster Plus Upper Stageand Escape StagesLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 5600.0 kg

Funding Agency

Unknown (U.S.S.R)

Disciplines

Planetary Science

Space Physics


Launch/Orbitalinformation for Luna 20

Experiments on Luna 20

Data collections from Luna20


Personnel



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


Luna 20




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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Luna 20 (1972-007A)

mailto:[email protected]?Subject=NMC Comment/Question: Luna 20 (1972-007A)









http://nssdc.gsfc.nasa.gov/image/spacecraft/luna-20_ret.jpg




Selected References

Luna 20 sample return system detailed, Aviat. Week Space Technol., 96, No. 12, 20, Mar. 1972.

Vinogradov, A. P., Preliminary data on lunar soil collected by the Luna-20 unmanned spacecraft,Geochim. et Cosmochim. Acta, 37, No. 4, 721-729, Apr. 1973. (Presented at a Meeting of thePresidium of the U.S.S.R. Academy of Sciences, 11 May, 1972). (Trans. from Geokhimiya, 763-774, 1972).


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

Sample return capsules from Luna 16, 20, and 24 on display at the NPOLavochkin Museum Courtesy of Alexander Chernov and the Virtual Space Museum

Other Soviet Lunar MissionsLunar Science Home Page


http://nssdc.gsfc.nasa.gov/image/spacecraft/luna_16_20_24_ret_vsm.jpg

http://vsm.host.ru/

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


http://www.usa.gov/








Description

Meteor 1-11 was the eleventh fully operational Russianmeteorological satellite and the twentieth meteorologicalsatellite launched from the Plesetsk site. The satellite wasplaced in a near-circular, near-polar prograde orbit to providenear-global observations of the earth's weather systems, cloudcover, ice and snow fields, vertical profiles of temperature andmoisture, and reflected and emitted radiation from the daysideand nightside of the earth-atmosphere system for operationaluse by the Soviet Hydrometeorological Service. This was thethird satellite of the Meteor series to be placed in a high orbit --about 240 km higher than that of most other Meteor launches.Other high-orbit flights were made by Meteor 5, 10, and 12.Meteor 1 was equipped with two vidicon cameras and APTcamera(s) for taking dayside pictures, a scanning high-resolution IR radiometer with APT capability, for taking daysideand nightside pictures, an actinometric instrument for makingmeasurements of the earth's radiation field in the visible andinfrared regions, and a medium-resolution scanning diffractionspectrometer for determining indirectly the vertical profiles ofatmospheric temperature and humidity. The satellite was in theform of a cylinder 5 m long and 1.5 m in diameter with twolarge solar panels attached to the sides. The solar panels wereautomatically oriented towards the sun so as to provide thespacecraft with the maximum amount of solar power. Meteor 1was oriented toward the earth by a gravity-gradient triaxialstabilization system consisting of flywheels whose kineticenergy was dampened by the use of controlled electromagnetson board that interacted with the magnetic field of the earth.The instruments were housed in the base of the satellite,which pointed toward the earth, while the solar sensors weremounted in the top section. The operational 'Meteor' weathersatellite system usually consists of at least two satellitesspaced at 90-deg intervals in longitude so as to observe agiven area of the earth every 6 hr. When within communicationrange, the data acquired were transmtted directly to theground receiving centers in Moscow, Novosibirsk, orVladivostok or to APT-equipped stations within the USSR.During passes over regions beyond communication range,Meteor 1 recorded the TV and IR pictures, spectrometer data,and actinometric data and stored them on board until thesatellite passed over one of the receiving centers. Themeteorological data received at these centers were processed,reduced, and sent to the Hydrometeorological Center inMoscow, where they were analyzed and used for preparingvarious forecast and analysis products. Some of the TV and IRpictures and analyzed actinometric data were then distributedto various meteorological centers around the world. It isbelieved that the satellite was deactivated in September 1972,as indicated by the termination of video and IR data being

Meteor 1-11

NSSDC ID: 1972-022A

Alternate Names

Meteor 1-11

05917

Facts in Brief

Launch Date: 1972-03-30LaunchVehicle: Modified SS-6(Sapwood) with 1stGeneration Upper StageLaunch Site: Plesetsk,U.S.S.RMass: 3300.0 kg

Funding Agency

SovietHydrometeorologicalService (U.S.S.R)

Discipline

Earth Science


Launch/Orbitalinformation for Meteor 1-11

Experiments on Meteor 1-11

Data collections fromMeteor 1-11



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Meteor 1-11


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Meteor 1-11


mailto:[email protected]?Subject=NMC Comment/Question: Meteor 1-11 (1972-022A)













transmitted to the United States from Moscow via the 'cold line'facsimile link.

Personnel


Project Scientist Soviet Hydrometeorological Service


http://www.usa.gov/








Description

Meteor 1-12 was the twelfth fully operational Russianmeteorological satellite and the twenty-first meteorologicalsatellite launched from the Plesetsk site. The satellite wasplaced in a near-circular, near-polar prograde orbit to providenear-global observations of the earth's weather systems, cloudcover, ice and snow fields, vertical profiles of temperature andmoisture, and reflected and emitted radiation from the daysideand nightside of the earth-atmosphere system for operationaluse by the Soviet Hydrometeorological Service. This was thefourth satellite of the Meteor series to be placed in a high orbit-- about 240 km higher than most other Meteor launches.Other high-orbit flights were made by Meteor 5, 10, and 11.Meteor 1 was equipped with two vidicon cameras and APTcamera(s) for dayside photography, a scanning high-resolutionIR radiometer for dayside and nightside photography, anactinometric instrument for measuring the earth's radiation fieldin the visible and infrared regions, and a medium-resolutionscanning diffraction spectrometer for determining indirectly thevertical profiles of atmospheric temperature and humidity. Thesatellite was in the form of a cylinder 5 m long and 1.5 m indiameter with two large solar panels attached to the sides. Thesolar panels were automatically oriented toward the sun toprovide the spacecraft with the maximum amount of solarpower. Meteor 1 was oriented toward the earth by a gravity-gradient triaxial stabilization system consisting of flywheelswhose kinetic energy was dampened by the use of controlledelectromagnets on board that interacted with the magnetic fieldof the earth. The instruments were housed in the base of thesatellite, which pointed toward the earth, while the solarsensors were mounted in the top section. The operational'Meteor' weather satellite system consists ideally of at least twosatellites spaced at 90-deg intervals in longitude so as toobserve a given area of the earth every 6 hr. The dataacquired were transmitted directly to ground receiving centersin Moscow, Novosibirsk, Vladisvostok, or APT-equippedstations within the U.S.S.R. when within communication range.During its passes over regions beyond communication range,Meteor 1 recorded the TV and IR pictures, spectrometer data,and actinometric data and stored them on board until thesatellite passed over one of the receiving centers. Themeteorological data received at these center were processed,reduced, and sent to the Hydrometeorological Center inMoscow, where they were analyzed and used for preparingvarious forecast and analysis products. Some of the TV and IRpictures were then distributed to various meteorologicalcenters around the world. The satellite functioned successfullyafter launch.

Meteor 1-12

NSSDC ID: 1972-049A

Alternate Names

Meteor 1-12

06079

Facts in Brief


Funding Agency


Discipline

Earth Science







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data























Personnel


Project Manager Soviet Hydrometeorological Service


http://www.usa.gov/








Description

This was the 13th fully operational meteorological satellite inthe Soviet Meteor 1 program. The satellite was placed in anear-circular, near-polar orbit to provide global observations ofthe earth's weather systems, cloud cover, ice and snow fields,vertical profiles of temperature and moisture, and relected andemitted radiation from the dayside and nightside of the earth-atmosphere system for operational use by the SovietHydrometeorological Service. Its 900-km orbit seemed to verifya continued effort by the USSR to place new Meteor satellitesin high orbit -- about 240 km higher than the orbits of earlyspacecraft in the series. Meteor 1 was equipped with twovidicon cameras with APT capability for taking daysidepictures, a scanning high-resolution IR radiometer, also withAPT capability, for taking dayside and nightside pictures, a setof actinometric instruments for making measurements of theearth's radiation field in the visual and infrared regions, and amedium-resolution scanning diffraction spectrometer fordetermining indirectly the vertical profiles of atmospherictemperature and humidity. The satellite was in the form of acylinder 5 m long and 1.5 m in diameter with two large solarpanels attached to tht sides. The solar panels wereautomatically oriented toward the sun so as to provide thespacecraft with the maximum amount of solar power. Meteor 1was oriented toward the earth by gravity-gradient control of the3 axes. The X and Y axes were mechanically stabilized by asystem of flywheels whose kinetic energy was dampened bythe use of controlled electromagnets on board that interactedwith the magnetic field of the earth. The instruments werehoused in the base of the satellite, which pointed toward theearth, while the solar sensors were mounted in the top section.The operational 'Meteor' weather satellite system usuallyconsists of two satellites spaced at 90-deg intervals. Thisallowed for nearly continuous monitoring of the formation,development, and movement of major weather systems. Whenwithin communication range, the data acquired weretransmitted directly to the ground receiving centers in Moscow,Novosibirsk, or Vladivostok or to APT-equipped stations withinthe USSR. During its passes over regions beyondcommunication range, Meteor 1 recorded the TV and IRpictures, spectrometer data, and actinometric data and storedthem on board until the satellite passed over one of thereceiving centers. The Meteorological data received at thesecenters were processed, reduced, and sent to theHydrometeorological Center in Moscow, where they wereanalyzed and used for preparing various forecast and analysisproducts. Some of the TV and IR pictures were thendistributed in real time to various meteorological centersaround the world.

Meteor 1-13

NSSDC ID: 1972-085A

Alternate Names

Meteor 1-13

06256

Facts in Brief


Funding Agency


Discipline

Earth Science







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data























Personnel


Project Manager Soviet Hydrometeorological Service


http://www.usa.gov/








Description

The objectives of the Meteoroid Technology Satellite were tomeasure the meteoroid penetration rates in the bumper-protected target, and to obtain data on meteoroid velocity andflux distribution. The central hub of the satellite was 320 cmlong and carried the velocity and impact experiments. Bumpertargets extended from the satellite, giving it an overall width of701.5 cm.

Meteoroid Technology Satellite

NSSDC ID: 1972-061A

Alternate Names

METEC

MTS

Explorer 46

06142

Facts in Brief

Launch Date: 1972-08-13Launch Vehicle: ScoutLaunch Site: WallopsIsland, United StatesMass: 90.0 kg

Funding Agency

NASA-Office ofAeronautics and SpaceTechnology (UnitedStates)

Discipline

Planetary Science


Launch/Orbitalinformation for MeteoroidTechnology Satellite

Experiments on MeteoroidTechnology Satellite

Data collections fromMeteoroid TechnologySatellite



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Meteoroid Technology Satellite

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Meteoroid Technology Satellite

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Meteoroid Technology Satellite



mailto:[email protected]?Subject=NMC Comment/Question: Meteoroid Technology Satellite (1972-061A)













Personnel


Mr. R. L. Mitchell GeneralContact


Dr. William H.Kinard

ProjectScientist

NASA Langley ResearchCenter

[email protected]

Mr. Charles V.Woerner

ProjectManager

NASA Langley ResearchCenter


http://www.usa.gov/








Description

Molniya 1/20 was a first-generation Russian communicationssatellite orbited to test and perfect a system of radiocommunications and television broadcasting using earthsatellites as active transponders and to experiment with thesystem in practical use. The basic function of the satellite wasto relay television programs and long-distance two-waymultichannel telephone, phototelephone, and telegraph linksfrom Moscow to the various standard ground receiving stationsin the orbital 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) electroniccomputer that controlled all equipment on board. Mountedaround the central cylinder were six large solar battery panelsand two directional, high-gain parabolic aerials, 180 deg apart.One of the aerials was directed continually toward the earth bythe highly sensitive earth sensors. The second aerial was heldin reserve. Signals were transmitted in a fairly narrow beamensuring a strong reception at the earth's surface. The satellitereceived at 1000 MHz. Television service was provided in afrequency range of 3.4 to 4.1 GHz at 40 w. Molniya 1/20,whose cylindrical body was 3.4 m long and 1.6 m in diameter,was much heavier than corresponding U.S. COMSATs, and ithad about 10 times the power output of the Early BirdCOMSAT. In addition, it did not employ a synchronousequatorial orbit as do most U.S. COMSATs because such anorbit would not provide coverage for areas north of 70 deg nlatitude. Instead, the satellite was boosted from a low-altitudeparking orbit into a highly elliptical orbit with two high apogeesdaily over the northern hemisphere -- one over Russia and oneover North America -- and relatively low perigees over thesouthern hemisphere. During its apogee, Molniya 1/20remained relatively stationary with respect to the earth belowfor nearly 8 of every 12 hr. By placing three or more Molniya 1satellites in this type of orbit, spacing them suitably, andshifting their orbital planes relative to each other by 120 deg, a24-hr/day communication system could be obtained. A small(15.9 kg) French-built satellite called MAS (or SRET 1) waslaunched in tandem with Molniya 1V to provide additional dataon the effect of radiation on experimental solar cells andsemiconductor materials. As of May 1972, Molniya 1/20remained in orbit.

Molniya 1-20

NSSDC ID: 1972-025A

Alternate Names

Molniya 1V

05927

Facts in Brief

Launch Date: 1972-04-04LaunchVehicle: Modified SS-6(Sapwood) with 2ndGeneration Upper Stage +Escape StageLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 998.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Communications


Launch/Orbitalinformation for Molniya 1-20

Experiments on Molniya 1-20

Data collections fromMolniya 1-20



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Molniya 1-20


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Molniya 1-20


mailto:[email protected]?Subject=NMC Comment/Question: Molniya 1-20 (1972-025A)














Description

Molniya 1/21 was a first-generation Russian communicationssatellite orbited to test and perfect a system of radiocommunications and television broadcasting using earthsatellites as active transponders and to experiment with thesystem in practical use. The basic function of the satellite wasto relay television programs and long-distance two-waymultichannel telephone, phototelephone, and telegraph linksfrom Moscow to the various standard ground receiving stationsin the 'Orbita' system. The satellite was in the form of ahermetically sealed cylinder with conical ends -- one endcontained the orbital correcting engine and a system ofmicrojets, and the other end contained externally mountedsolar and earth sensors. Inside the cylinder were (1) a high-sensitivity receiver and three 800-MHz 40-w transmitters (oneoperational and two in reserve), (2) telemetering devices thatmonitored equipment operation, (3) chemical batteries thatwere constantly recharged by solar cells, and (4) an electroniccomputer that controlled all equipment on board. Mountedaround the central cylinder were six large solar battery panelsand two directional, high-gain parabolic aerials, 180 deg apart.One of the aerials was directed continually toward the earth bythe highly sensitive earth sensors. The second aerial was heldin reserve. Signals were transmitted in a fairly narrow beamensuring a strong reception at the earth's surface. The satellitereceived telemetry at 1000 MHz. Television service wasprovided in a frequency range of 3.4 to 4.1 GHz at 40 w.Molniya 1/21, 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 1/21 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 1-21

NSSDC ID: 1972-081A

Alternate Names

Molniya 1W

06231

Facts in Brief

Launch Date: 1972-10-14LaunchVehicle: Modified SS-6(Sapwood) with 2ndGeneration Upper Stage +Escape StageLaunch Site: Plesetsk,U.S.S.RMass: 1750.0 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

Molniya 1/22 was a first-generation Russian communicationssatellite orbited to test and perfect a system of radiocommunications and television broadcasting using earthsatellites as active transponders and to experiment with thesystem in practical use. The basic function of the satellite wasto relay television programs and long-distance two-waymultichannel telephone, phototelephone, and telegraph linksfrom Moscow to the various standard ground receiving stationsin the 'Orbita' system. The satellite was in the form of ahermetically sealed cylinder with conical ends -- one endcontained the orbital correcting engine and a system ofmicrojets, and the other end contained externally mountedsolar and earth sensors. Inside the cylinder were (1) a high-sensitivity receiver and three 800-MHz 40-w transmitters (oneoperational and two in reserve), (2) telemetering devices thatmonitored equipment operation, (3) chemical batteries thatwere constantly recharged by solar cells, and (4) an electroniccomputer that controlled all equipment on board. Mountedaround the central cylinder were six large solar battery panelsand two directional, high-gain parabolic aerials, 180 deg apart.One of the aerials was directed continually toward the earth bythe highly sensitive earth sensors. The second aerial was heldin reserve. Signals were transmitted in a fairly narrow beamensuring a strong reception at the earth's surface. The satellitereceived telemetry at 1000 MHz. Television service wasprovided in a frequency range of 3.4 to 4.1 GHz at 40 w.Molniya 1/22, 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 1/22 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 1-22

NSSDC ID: 1972-095A

Alternate Names

Molniya 1X

06294

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


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

























Description

Molniya 2/2 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 2/2, 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 2/2 remained relatively stationary with respect to theearth below for nearly 8 of every 12 hr. By placing three ofmore Molniya 2 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 2- 2

NSSDC ID: 1972-037A

Alternate Names

Molniya 2B

06031

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications




Data collections fromMolniya 2- 2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







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


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


mailto:[email protected]?Subject=NMC Comment/Question: Molniya 2- 2 (1972-037A)











http://www.usa.gov/







Description


Molniya 2- 3

NSSDC ID: 1972-075A

Alternate Names

Molniya 2C

06208

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/







Description


Molniya 2- 4

NSSDC ID: 1972-098A

Alternate Names

Molniya 2D

06308

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/







Description

The Nimbus 5 research-and-development satellite wasdesigned to serve as a stabilized, earth-oriented platform forthe testing of advanced meteorological sensor systems andcollecting meteorological and geological data on a globalscale. The polar-orbiting spacecraft consisted of three majorstructures: (1) a hollow, ring-shaped sensor mount, (2) solarpaddles, and (3) a control system housing. The solar paddlesand control system housing were connected to the sensormount by a truss structure, giving the satellite the appearanceof an ocean buoy. Nimbus 5 was nearly 3.7 m tall, 1.5 m indiameter at the base, and about 3 m wide with solar paddlesextended. The torus-shaped sensor mount, which formed thesatellite base, housed the electronics equipment and batterymodules. The lower surface of the torus provided mountingspace for sensors and antennas. A box-beam structuremounted within the center of the torus provided support for thelarger sensor experiments. Mounted on the control systemhousing, which was located on top of the spacecraft, were sunsensors, horizon scanners, and a command antenna. Anadvanced attitude-control system permitted the spacecraftorientation to be controlled to within plus or minus 1 deg in allthree axes (pitch, roll, and yaw). Primary experiments included(1) a temperature-humidity infrared radiometer (THIR) formeasuring day and night surface and cloudtop temperatures,as well as the water vapor content of the upper atmosphere,(2) an electrically scanning microwave radiometer (ESMR) formapping the microwave radiation from the earth's surface andatmosphere, (3) an infrared temperature profile radiometer(ITPR) for obtaining vertical profiles of temperature andmoisture, (4) a Nimbus E microwave spectrometer (NEMS) fordetermining tropospheric temperature profiles, atmosphericwater vapor abundances, and cloud liquid water contents, (5) aselective chopper radiometer (SCR) for observing the globaltemperature structure of the atmosphere, and (6) a surfacecomposition mapping radiometer (SCMR) for measuring thedifferences in the thermal emission characteristics of theearth's surface. A more detailed description can be found in"The Nimbus 5 User's Guide" (TRF 14758), available fromNSSDC.

Nimbus 5

NSSDC ID: 1972-097A

Alternate Names

Nimbus-E

06305

Facts in Brief


Funding Agency


Discipline

Earth Science


Launch/Orbitalinformation for Nimbus 5

Experiments on Nimbus 5

Data collections fromNimbus 5


Personnel



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Nimbus 5 (1972-097A)













Mr. Paul Shapiro GeneralContact

NASA Goddard SpaceFlight Center

Mr. Charles M.MacKenzie

ProjectManager


Dr. Albert J. Fleig,Jr.

ProjectScientist


[email protected]

Dr. George F.Esenwein, Jr.

ProgramManager

NASA Headquarters


http://www.usa.gov/








Description

NOAA 2 was the first in a series of reconfigured ITOS-Msatellies launched with new meteorological sensors onboard toexpand the operational capability of the ITOS system. NOAA 2was not equipped with conventional TV cameras. It was thefirst operational weather satellite to rely solely upon radiometricimaging to obtain cloudcover data. The primary objective ofNOAA 2 was to provide global daytime and nighttime directreadout real-time cloudcover data on a daily basis. The sun-synchronous spacecraft was also capable of supplying globalatmospheric temperature soundings and very high resolutioninfrared cloudcover data for selected areas in either a directreadout or a tape-recorder mode. A secondary objective wasto obtain global solar-proton flux data on a real-time dailybasis. The primary sensors consisted of Very High ResolutionRadiometer (VHRR), a Vertical Temperature ProfileRadiometer (VTPR), and a Scanning Radiometer (SR). TheVHRR, VTPR, and SR were mounted on the satellite baseplatewith their optical axes directed vertically earthward. The nearlycubical spacecraft measured 1 by 1 by 1.2 m. The satellite wasequipped with three curved solar panels that were foldedduring launch and deployed after orbit was achieved. Eachpanel measured over 4.2 m in length when unfolded and wascovered with approximately 3500 solar cells measuring 2 by 2cm. The NOAA 2 dynamics and attitude control systemmaintained desired spacecraft orientation through gyroscopicprinciples incorporated into the satellite design. Earthorientation of the satellite body was maintained by takingadvantage of the precession induced from a momentumflywheel so that the satellite body precession rate of onerevolution per orbit provided the desired earth-looking attitude.Minor adjustments in attitude and orientation were made bymeans of magnetic coils and by varying the speed of themomentum flywheel. The spacecraft operated satisfactorilyuntil March 18, 1974, when VTPR failed. NOAA 2 was thenplaced in a marginal standby mode from March 19 to July 1,1974. It was then used as the operational NOAA satellite untilOctober 16, 1974, when it was again placed in a marginalstandby mode. The spacecraft was deactivated on January 30,1975.

NOAA 2

NSSDC ID: 1972-082A

Alternate Names

ITOS-D

06235

Facts in Brief


Funding Agencies

NASA-Office ofApplications (UnitedStates)

NOAA NationalEnvironmental SatelliteService (United States)

Disciplines

Earth Science

Space Physics


Launch/Orbitalinformation for NOAA 2

Experiments on NOAA 2

Data collections fromNOAA 2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: NOAA 2 (1972-082A)













Personnel


Mr. Charles M. Hunter General Contact NASA Goddard Space Flight Center

Mr. Stanley Weiland Project Manager NASA Goddard Space Flight Center

Dr. Morris Tepper Program Scientist NASA Goddard Space Flight Center

Mr. Isidore L. Goldberg Project Scientist NASA Goddard Space Flight Center


http://www.usa.gov/








Description

This mission was the third in the OAO program and its secondsuccessful spacecraft to observe the celestial sphere fromabove the earth's atmosphere. A UV telescope with aspectrometer measured high-resolution spectra of stars,galaxies, and planets with the main emphasis on thedetermination of interstellar absorption lines. Three X-raytelescopes and a collimated proportional counter providedmeasurements of celestial X-ray sources and interstellarabsorption between 1 and 100 A.

The OAO 3 spacecraft was an octagonally shaped aluminumstructure with a 1.21 m hollow central tubular area, whichhoused the experiment container. Solar panels were mountedon each side of the spacecraft at angles of 34 degrees andhad an area of 38.2 square m. A sun baffle protected theexperiments and increased the length of the spacecraft to 4.9m. Two inertial balance booms, one forward and one aft,extended approximately 6.8 m.

The spacecraft was equipped with an inertial reference unit (ahigh-precision three-axis gyro inertial system), sun sensors, amagnetometer, and star trackers, which enabled spacecraftpointing to be determined in many different ways. A boresightstar tracker, sensitive to sixth magnitude, controlled pitch andyaw to within 5 arc-s. In addition, the high-resolution telescopeexperiment had a fine pointing control, which could control thepitch and yaw to within 0.1 arc-s on bright stars. Spacecraftattitude was controlled by inertia wheels and thrusters.

Redundant tracking beacons facilitated ground tracking of thespacecraft. Two UHF (400.55 MHz) transmitters providedwideband telemetry for transmitting digital data to the groundstations. Two redundant VHF (136.26 MHz) transmitters wereused in a narrow-band telemetry link primarily for transmittingspacecraft housekeeping data, although they served asbackups for the wideband telemetry system. Two redundantpairs of VHF command receivers were carried as part ofcommand system capable of storing 1280 commands. Datawere stored on an onboard tape recorder and in core storage.An onboard processor monitored telemetry data, issuedcommands, and was programmed via the command receiveruplink.

The observational life of the mission was August 1972 toFebruary 1981 (9.5 years).

OAO 3

NSSDC ID: 1972-065A

Alternate Names

OAO-C

Copernicus

Orbiting AstronomicalObservatory 3

06153

Facts in Brief

Launch Date: 1972-08-21Launch Vehicle: Atlas-CentaurLaunch Site: CapeCanaveral, United StatesMass: 2150.0 kg

Funding Agency


Discipline

Astronomy


Launch/Orbitalinformation for OAO 3

Experiments on OAO 3

Data collections from OAO3


Personnel


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


OAO 3




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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: OAO 3 (1972-065A)











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



This image shows the Copernicus(OAO 3) spacecraft during assembly.


Mr. Herbert B.Chisholm

ProgramManager

NASA Headquarters

Mr. J. PatrickCorrigan, III

ProjectManager


Dr. James E.Kupperian, Jr.

ProjectScientist


Dr. Edward J.Weiler

ProgramScientist

NASA Headquarters [email protected]

Additional Images of Copernicus

US Active Archive for Copernicus Information/Data

The Copernicus Archive at MAST(STScI)

Other Sources of Copernicus Information/Data

The Copernicus Archive at HEASARC


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

http://archive.stsci.edu/copernicus/

http://heasarc.gsfc.nasa.gov/docs/copernicus/archive/copernicus_archive.html

http://www.usa.gov/








Description

Oscar 6 was a small communications satellite designed for useby amateur radio operators. It was a rectangular, magneticallystabilized spacecraft which measured 16 x 30 x 44 cm, andincluded antenna protruding from the centers of the foursmaller surfaces. With the attitude magnet aligned normal tothe 10-m split dipole antenna and parallel to the two othermonopole antennae, 10-m nulls occurred synchronously withspacecraft spin except over polar regions where nulls occurredfor the 0.7-m and 2-m signals. The 29-MHz beacon used ahalf-wavelength, 5-m dipole extending through the spacecraftwhile the other two quarter-wavelength monopole antennaeextended 50 cm (146-MHz receiver) and 17.5 cm (29.5-MHzbeacon and repeater transmitter) respectively, along the spinaxis. The satellite contained telemetry-tracking beacons and arepeater which could use a storage capability. The powersupply was provided by batteries which were rechargeablefrom solar cells located on all exterior satellite surface. Acommand system was capable of turning off all equipmentexcept the 29.45 beacon. This exception of drastic signaloutput decrease from the 435.1-MHz beacon since January 10,1973. Complete structural details of experiments are containedin 'The sixth amateur satellite,' by King (QST, July/August1973).

OSCAR 6

NSSDC ID: 1972-082B

Alternate Names

AMSAT OSCAR C

A-O-C

06236

Facts in Brief


Funding Agencies

Radio Amateur SatelliteCorporation(International)


Discipline

Communications


Launch/Orbitalinformation for OSCAR 6

Experiments on OSCAR 6

Data collections fromOSCAR 6



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: OSCAR 6 (1972-082B)













Personnel


Dr. Perry I. Klein General Contact AMSAT Corporation [email protected]


http://www.usa.gov/








Description

This mission was the first to be sent to the outer solar systemand the first to investigate the planet Jupiter, after which itfollowed an escape trajectory from the solar system. Thespacecraft achieved its closest approach to Jupiter on 04December 1973, when it reached approximately 2.8 Jovianradii (about 200,000 km). As of 01 January 1997 Pioneer 10was at about 67 AU from the Sun near the ecliptic plane andheading outward from the Sun at 2.6 AU/year and downstreamthrough the heliomagnetosphere towards the tail region andinterstellar space. This solar system escape direction is uniquebecause the Voyager 1 and 2 spacecraft (and the nowterminated Pioneer 11 spacecraft mission) are heading in theopposite direction towards the nose of the heliosphere in theupstream direction relative to the inflowing interstellar gas. Thespacecraft is heading generally towards the red starAldebaran, which forms the eye of Taurus (The Bull). Thejourney over a distance of 68 light years to Aldebaran willrequire about two million years to complete. Routine trackingand project data processing operatations were terminated on31 March 1997 for budget reasons. Occasional trackingcontinued later under support of the Lunar Prospector projectat NASA Ames Research Center with retrieval of energeticparticle and radio science data. The last successful dataacquisitions through NASA's Deep Space Network (DSN)occurred on 03 March 2002, the 30th anniversary of Pioneer10's launch date, and on 27 April 2002. The spacecraft signalwas last detected on 23 January 2003 after an uplink wastransmitted to turn off the last operational experiment, theGeiger Tube Telescope (GTT), but lock-on to the sub-carriersignal for data downlink was not achieved. No signal at all wasdetected during a final attempt on 06-07 February 2003.Pioneer Project staff at NASA Ames then concluded that thespacecraft power level had fallen below that needed to powerthe onboard transmitter, so no further attempts would bemade.

The history of the Pioneer 10 tracking status is available fromthe web site of the former Pioneer Project at the followinglocation:

http://spaceprojects.arc.nasa.gov/Space_Projects/pioneer/PNhome.html

Fifteen experiments were carried to study the interplanetaryand planetary magnetic fields; solar wind parameters; cosmicrays; transition region of the heliosphere; neutral hydrogenabundance; distribution, size, mass, flux, and velocity of dustparticles; Jovian aurorae; Jovian radio waves; atmosphere ofJupiter and some of its satellites, particularly Io; and tophotograph Jupiter and its satellites. Instruments carried for

Pioneer 10

NSSDC ID: 1972-012A

Alternate Names

Pioneer-F

05860

Facts in Brief

Launch Date: 1972-03-03Launch Vehicle: Atlas-CentaurLaunch Site: CapeCanaveral, United StatesMass: 258.0 kgNominalPower: 165.0 W

Funding Agency


Disciplines

Astronomy

Planetary Science

Space Physics


Launch/Orbitalinformation for Pioneer 10

PDMP information forPioneer 10

Telecommunicationsinformation for Pioneer 10

Experiments on Pioneer 10

Data collections fromPioneer 10

Questions or commentsabout this spacecraft can


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


Pioneer 10


http://spaceprojects.arc.nasa.gov/Space_Projects/pioneer/PNhome.html







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

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

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









http://nssdc.gsfc.nasa.gov/image/spacecraft/pioneer10-11.jpg



these experiments were magnetometer, plasma analyzer,charged particle detector, ionizing detector, non-imagingtelescopes with overlapping fields of view to detect sunlightreflected from passing meteoroids, sealed pressurized cells ofargon and nitrogen gas for measuring the penetration ofmeteoroids, UV photometer, IR radiometer, and an imagingphotopolarimeter, which produced photographs and measuredpolarization. Further scientific information was obtained fromthe tracking and occultation data.

The spacecraft body was mounted behind a 2.74-m-diameterparabolic dish antenna that was 46 cm deep. The spacecraftstructure was a 36-cm-deep flat equipment compartment, thetop and bottom being regular hexagons. Its sides were 71 cmlong. One side joined a smaller compartment that carried thescientific experiments. The high-gain antenna feed wassituated on three struts, which projected forward about 1.2 m.This feed was topped with a medium-gain antenna. A low-gainomnidirectional antenna extended about 0.76 m behind theequipment compartment and was mounted below the high-gainantenna. Power for the spacecraft was obtained by four SNAP-19 radioisotope thermonuclear generators (RTG), which wereheld about 3 m from the center of the spacecraft by two three-rod trusses 120 deg apart. A third boom extended 6.6 m fromthe experiment compartment to hold the magnetometer awayfrom the spacecraft. The four RTG's generated about 155 W atlaunch and decayed to approximately 140 W by the time thespacecraft reached Jupiter, 21 months after launch. Therewere three reference sensors: a star sensor for Canopuswhich failed shortly after Jupiter encounter and two sunsensors. Attitude position could be calculated from thereference directions to the earth and the sun, with the knowndirection to Canopus as a backup. Three pairs of rocketthrusters provided spin-rate control and changed the velocityof the spacecraft, the spin period near the end of the missionbeing 14.1 seconds. These thrusters could be pulsed or firedsteadily by command. The spacecraft was temperature-controlled between minus 23 deg C and plus 38 deg C. Aplaque was mounted on the spacecraft body with drawingsdepicting a man, a woman, and the location of the sun and theearth in our galaxy.

Communications were maintained via (1) the omnidirectionaland medium-gain antennas which operated together whileconnected to one receiver and (2) the high-gain antenna whichwas connected to another receiver. These receivers could beinterchanged by command to provide some redundancy. Tworadio transmitters, coupled to two traveling-wave tubeamplifiers, produced 8 W at 2292 MHz each. Uplink wasaccomplished at 2110 MHz, while data transmission downlinkwas at 2292 MHz. The data were received by NASA's DeepSpace Network (DSN) at bit rates up to 2048 bps enroute toJupiter and at 16 bps near end of the mission.

Space experiments mostly continued to operate for planetaryor interplanetary measurements until failure or until insufficientspacecraft power from the RTG's was available for operation ofall instruments, such that some were turned off permanentlyand others were cycled on and off in accordance with a powersharing plan implemented in September 1989. TheAsteroid/Meteroid Detector failed in December 1973, followedby the Helium Vector Magnetometer (HVM) in November 1975and the Infrared Radiometer in January 1974. The MeteroidDetector was turned off in October 1980 due to inactivesensors at low temperatures. The spacecraft sun sensorsbecame inoperative in May 1986, and the ImagingPhotopolarimeter (IPP) instrument was used to obtain rollphase and spin period information until being turned off inOctober 1993 to conserve power. The Trapped Radiation

be directed to: Dr. John F.Cooper.

mailto:[email protected]?Subject=NMC Comment/Question: Pioneer 10 (1972-012A)

mailto:[email protected]?Subject=NMC Comment/Question: Pioneer 10 (1972-012A)



Detector (TRD) and Plasma Analyzer (PA) were respectivelyturned off in November 1993 and September 1995 for thesame reason. As of January 1996 the final power cycling planincluded part-time operations of the Charged ParticleInstrument (CPI), the Cosmic Ray Telescope (CRT), theGeiger Tube Telescope (GTT), and the Ultraviolet Photometer(UV). As of August 2000, only the GTT instrument was stillreturning data.

Various other spacecraft subsystems also either failed or wereturned off for power or other reasons, and an account of thesemay be of interest for engineering design of long duration deepspace missions. The primary antenna feed offset bellows failedsometime in 1976 but a redundant unit was available for usethereafter. The Program Storage and Execution (PSE)subsystem was turned off in September 1989 for powerconservation, after which spacecraft maneuvers wereperformed by ground command sequences. A receiver problemin mid-1992 prevented uplink to the high gain antenna, afterwhich uplink commands could only be sent with 70-meter DSNantennas which also supported the 16 bps downlink. TheBackup Line Heater experienced a sticking thermostatoperation in March 1993 for 30 days but the problem did notreoccur. Undervoltage Protection Logic was turned off inDecember 1993 to prevent loss of critical spacecraft systemsin the event of a transient undervoltage condition. Duration andSteering Logic (DSL) was turned off in February 1995 toconserve power, after which it was turned on again only forspacecraft maneuvers. RTG power levels are low enough thatthe spacecraft occasionally relies in part on battery power(accumulated during inactive periods) to run experiments andother systems.

The total mission cost for Pioneer 10 through the 1997 end ofofficial science operations was about 350 million in FY 2001U.S. dollars. This included about 200 million dollars for pre-launch design and development, and another 150 million forlaunch, telemetry tracking, mission operations and dataanalysis. These estimates were provided by the former PioneerProject at NASA Ames Research Center.

Personnel


Dr. James B.Willett

ProgramManager

NASA Headquarters

Mr. Richard O.Fimmel

ProjectManager

NASA Ames ResearchCenter

Dr. Palmer Dyal ProjectScientist

NASA Ames ResearchCenter

Dr. W. VernonJones

ProgramScientist


Selected References

Hall, C. F., Pioneer 10, Science, 183, No. 4122, 301-302, Jan. 1974.

Fimmel, R. O., et al., Pioneer odyssey encounter with a giant, NASA, SP-349, Washington,D.C., 1974.

Fimmel, R. O., et al., Pioneer first to Jupiter, Saturn, and beyond, NASA, SP-466, Washington,D.C., 1980.

Other Pioneer 10/11 Information/Data at NSSDC



This image shows the plaque that wasmounted on the Pioneer 10 and 11spacecraft.

This is an image of the Pioneer 10/11mission patch.

Interplanetary magnetic field, plasma, and ephemeris data from Pioneer 10 and 11 are availableas COHO data collections. COHOWeb allows the display and retrieval of COHO data. Thesedata are also available via anonymous FTP.

COHOWebPioneer data on NSSDC's anonymous FTP site

Pioneer 10/11 position data (heliographic coordinates)

Pioneer 10's last signal (NASA Press Release, 2003-02-25)Pioneer 11 ends operations (NASA Press Release, 1995-09-29)Status of Pioneer 10 and 11 (1997-12-01)Status of Pioneer 10 and 11 (1996-12-02)Status of Pioneer 10 and 11 (1996-05-24)

Related Information/Data at NSSDC

Jupiter PageSaturn Page

Other Sources of Pioneer 10/11 Information/Data

Pioneer GTT Charged Particle page (U. of Iowa)Pioneer Plasma Group page (NASA ARC)

Online version of Pioneer Odyssey (NASA History Office)


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

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

http://cohoweb.gsfc.nasa.gov/

ftp://nssdcftp.gsfc.nasa.gov/spacecraft_data/pioneer/

http://cohoweb.gsfc.nasa.gov/helios/

http://nssdc.gsfc.nasa.gov/planetary/text/pion10_pr_20030225.txt

http://nssdc.gsfc.nasa.gov/planetary/text/pioneer-11_endops.txt

http://nssdc.gsfc.nasa.gov/planetary/text/pioneer_10-11_status_971201.txt



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

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

http://www-pw.physics.uiowa.edu/pioneer/home.html

http://arwen.arc.nasa.gov/

http://history.nasa.gov/SP-349/sp349.htm

http://history.nasa.gov/SP-349/sp349.htm

http://www.usa.gov/








Description

Prognoz 1 carried scientific apparatus for research of radiationfrom the sun, solar wind, and magnetic fields incircumterrestrial space, radio transmitter on 928.4 MHz. It waslaunched from the Baikonur cosmodrome aboard a Molniyarocket.

Prognoz 1

NSSDC ID: 1972-029A

Alternate Names

05941

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Disciplines

Solar Physics

Space Physics


Launch/Orbitalinformation for Prognoz 1

Experiments on Prognoz 1

Data collections fromPrognoz 1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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


mailto:[email protected]?Subject=NMC Comment/Question: Prognoz 1 (1972-029A)











http://www.usa.gov/








Description

Prognoz 2 was placed in a highly elliplical orbit with apogee200,000 km, perigee 550 km, and inclination 65 degrees. Itcarried the first instrument package, SIGNE 1, resulting fromthe Franco-Soviet SIGNE collaboration. This instrument wasintended to perform solar radiation studies. However, itdetected cosmic gamma-ray bursts as well as solar events. Itreentered the earths atmosphere on 15 December 1982.

The SIGNE 1 detector consisted of a Stilbene scintilator, 38.1mm in diameter and 38.1 mm high. It was shielded by a plasticanticoincidence scintilator. There were 8 energy channels: 0.4-0.7 MeV, 0.7-1.0 MeV, 1-1.6 MeV, 1.6-2.4 MeV, 2.4-2.9 MeV,2.9-3.9 MeV, 3.9-8.1 Mev, and 8.1-11.8 MeV. Counts wereintegrated for every 41 or 160 seconds, depending on theexperiment mode. The effective area was 17.1 sq-cm.

Prognoz 2

NSSDC ID: 1972-046A

Alternate Names

06068

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Disciplines

Solar Physics

Space Physics


Launch/Orbitalinformation for Prognoz 2

Experiments on Prognoz 2

Data collections fromPrognoz 2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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














http://www.usa.gov/








Description

The objectives of this spacecraft were to provide a passiveoptical and radar calibration target of about 5 sq m crosssection.

RADCAT 2

NSSDC ID: 1972-076A

Alternate Names

SESP 72-1

S72-1

06217

Facts in Brief

Launch Date: 1972-10-02Launch Vehicle: AtlasLaunchSite: Vandenberg AFB,United StatesMass: 726.0 kg

Funding Agency


Disciplines

Engineering



Launch/Orbitalinformation for RADCAT2

Experiments on RADCAT 2

Data collections fromRADCAT 2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: RADCAT 2 (1972-076A)














Description

The objectives of this spacecraft were to measure backgroundgamma radiation over the whole earth in the 100 to 300-kVrange and in the >700-kV range. Fluxes and spectra of low-altitude charged particles were to be measured as a function oftime and magnetospheric position. The effects of the spaceenvironment on various thermal control coatings were to bedetermined. Measurements of UV radiation, and H and Heatoms and ions were taken. Observation was made of extremeand far UV originating in interaction of solar wind withinterplanetary medium or from galactic sources. The cylindricalspacecraft, which was 2.13 m long and 1.37 m in diametercarried a gamma-ray spectrometer, a low-altitude particlemeasuring sensor, and an extreme UV radiation experiment.The antenna booms extended 2.74 m from each end,coincident with the spin axis.

RADSAT

NSSDC ID: 1972-076B

Alternate Names

SESP 72-1

S72-1

STP 72-1B

06212

Facts in Brief

Launch Date: 1972-10-02Launch Vehicle: AtlasLaunchSite: Vandenberg AFB,United StatesMass: 208.0 kg

Funding Agencies

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

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


Disciplines

Engineering

Space Physics


Launch/Orbitalinformation for RADSAT

Experiments on RADSAT

Data collections fromRADSAT

Questions or comments


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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

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











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


mailto:[email protected]?Subject=NMC Comment/Question: RADSAT (1972-076B)

mailto:[email protected]?Subject=NMC Comment/Question: RADSAT (1972-076B)

http://www.usa.gov/








Description

SAS-B was the second in the series of small spacecraftdesigned to extend the astronomical studies in the X-ray,gamma-ray, ultraviolet, visible, and infrared regions. Theprimary objective of the SAS-B was to measure the spatial andenergy distribution of primary galactic and extragalacticgamma radiation with energies between 20 and 300 MeV. Theinstrumentation consisted principally of a guard scintillationdetector, an upper and a lower spark chamber, and a chargedparticle telescope.

SAS-B was launched from the San Marco platform off thecoast of Kenya, Africa, into a nearly equatorial orbit. Theorbiting spacecraft was in the shape of a cylinderapproximately 59 cm in diameter and 135 cm in length. Foursolar paddles were used to recharge the 6 amp-h nickel-cadmium battery and provide power to the spacecraft andtelescope experiment. The spacecraft was spin stabilized, anda magnetically torqued commandable control system was usedto point the spin axis of the spacecraft to any position in spacewithin approximately 1 degree. The experiment axis lay alongthis axis allowing the telescope to look at any selected regionof the sky with its plus or minus 30 degree acceptanceaperture. The nominal spin rate was 1/12 rpm. Data weretaken at 1000 bps and could be recorded on an onboard taperecorder and simultaneously transmitted in real time. Therecorded data were transmitted once per orbit. This requiredapproximately 5 minutes.

The telescope experiment was initially turned on November 20,1972, and by November 27, 1972, the spacecraft became fullyoperational. The low-voltage power supply for the experimentfailed on June 8, 1973. No useful scientific data were obtainedafter that date. With the exception of a slightly degraded starsensor, the spacecraft control section performed in anexcellent manner.

SAS-B

NSSDC ID: 1972-091A

Alternate Names

Explorer 48

SAS 2

06282

Facts in Brief

Launch Date: 1972-11-15Launch Vehicle: ScoutLaunch Site: San MarcoPlatform, KenyaMass: 166.0 kg

Funding Agency


Discipline

Astronomy


Launch/Orbitalinformation for SAS-B

Experiments on SAS-B

Data collections from SAS-B


Personnel


Mrs. Marjorie R.Townsend

ProjectManager



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


SAS-B




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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: SAS-B (1972-091A)

mailto:[email protected]?Subject=NMC Comment/Question: SAS-B (1972-091A)









http://nssdc.gsfc.nasa.gov/image/spacecraft/sas2.gif



Dr. Carl E.Fichtel

ProjectScientist


[email protected]

Dr. Nancy G.Roman

ProgramScientist


Selected References

Derdeyn, S. M., et al., SAS-B digitized spark chamber gamma ray telescope, Nuclear Instrum.and Methods, 98, 557-566, 1972.

Fichtel, C. E., et al., High energy gamma ray astronomy, Phys. Today, 28, No. 9, Sept. 1975.

Related Information/Data at NSSDC

Uhuru (SAS-A)SAS-C

US Active Archive for SAS-B Information/Data

The SAS-2 Archive at HEASARC


http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1970-107A

http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1975-037A

http://heasarc.gsfc.nasa.gov/docs/sas2/archive/sas2_archive.html

http://www.usa.gov/








Description

SRET 1 (a French acronym for 'Satellite for Research onEnvironment and Technology') was a French-built satellitelaunched in tandem with the Russian COMSAT Molniya 1V totest thin film cadmium sulfide and cadmium telluride solar cellsas well as a new lightweight battery. The satellite, also calledMAS (a Russian acronym for 'Small Automatic Satellite'), wasin the form of an eight-sided polyhedron with a diameter of55.9 cm and a weight of about 15.9 kg. Four of the eight sideswere faced with conventional silicon cells and provided powerfor the experiment. Two of the remaining sides had cadmiumsulfide cells and the other two had cadmium telluride cells. Thesatellite orbited in the approximate path of Molniya 2A, rangingbetween 46,250 and 545 km. Its elliptical orbit took it throughthe Van Allen radiation belt four times each day, thus providingadditional data on the effect of radiation on the experimentalsolar cells and semiconductor materials. SRET 1 was the firstFrench satellite launched by the Soviets, with two moreplanned in the 1972-74 time period.

SRET 1

NSSDC ID: 1972-025B

Alternate Names

MAS

05928

Facts in Brief


Funding Agency

Unknown (France)

Discipline

Engineering


Launch/Orbitalinformation for SRET 1

Experiments on SRET 1

Data collections fromSRET 1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: SRET 1 (1972-025B)











http://www.usa.gov/








Description

The TD-1 satellite carried seven experiments devoted toastophysical studies. Its scientific mission was to make asystematic sky survey in the ultraviolet and high-energyregions of the spectrum. The experiments were divided intotwo main categories: five experiments--measuring ultraviolet, xand gamma rays, and heavy nuclei--scanned strips of the sky;the other two viewed along the sun-pointing x axis andmeasured solar x and gamma rays. The satellite was atriaxially stabilized platform with the x axis always pointed atthe center of the sun with an accuracy of 1 arc min. Thesatellite rotated around this axis at a constant rate of 1revolution per orbit during normal operations when sunsensors were used for stabilization but it was spun up duringeclipse periods to maintain attitude. The sky-scanninginstruments were able to scan a narrow band of the sky duringeach orbit and the whole celestial sphere in 6 months. Twoand one-half complete scans of the celestial sphere werecompleted before the attitude control was lost in May 1974following exhaustion of the on-board gas supply. Despiteintermittent tape recorder failure, data coverage was achievedover 95 percent of the celestial sphere and many areas wereobserved during two or three separate scans. The spacecraftwas a rectangular structure and comprised a bottomcompartment containing the spacecraft subsystems and a topcompartment containing the outward-viewing scienceinstruments. It had a cross section of 1 by 0.9 m and was 2.2m high; its mass was 473 kg including 120 kg of instruments.For additional information see "ESRO Report Presented to theEighteenth COSPAR Meeting, Varna, Bulgaria, June 1975".

TD 1A

NSSDC ID: 1972-014A

Alternate Names

TD 1

05879

Facts in Brief


Funding Agency


Disciplines

Astronomy

Solar Physics


Launch/Orbitalinformation for TD 1A

Experiments on TD 1A

Data collections from TD1A


Personnel

Name Role Original Affiliation E-


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: TD 1A (1972-014A)













mail

Mr. Robert J.Goss

ProjectManager


Mr. T. I. Curl ProjectManager

ESA-European Space Research and TechnologyCentre

Dr. J. VonVochel

ProjectScientist

ESA-European Space Research and TechnologyCentre


http://www.usa.gov/








Description

This three-body spacecraft was connected by booms whichserved as gravity-gradient stabilizers in the radial direction. Amomentum wheel was used for stabilization in roll and yaw.The primary function of the spacecraft was to test variousconcepts for improving the USN Transit Navigation System.The power was supplied by a radioisotope thermal electricgenerator.

TIP 1

NSSDC ID: 1972-069A

Alternate Names

TRIAD OI 1X

TRIAD A

TRIAD 1

TRIAD

06173

Facts in Brief


Funding Agency

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

Disciplines


Space Physics


Launch/Orbitalinformation for TIP 1

Experiments on TIP 1

Data collections from TIP 1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





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

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

mailto:[email protected]?Subject=NMC Comment/Question: TIP 1 (1972-069A)

mailto:[email protected]?Subject=NMC Comment/Question: TIP 1 (1972-069A)











Personnel


Mr. John Dassoulas Project Manager Applied Physics Laboratory [email protected]

Mr. Robert E. Fischell Project Scientist Applied Physics Laboratory


http://www.usa.gov/








Description

Venera 8 was a Venus atmospheric probe and lander. Itsinstrumentation included temperature, pressure, and lightsensors as well as an altimeter, gamma-ray spectrometer, gasanalyzer, and radio transmitters. The spacecraft took 117 daysto reach Venus with one mid-course correction on 6 April1972, separating from the bus (which contained a cosmic raydetector, solar wind detector, and ultraviolet spectrometer) andentering the atmosphere on 22 July 1972 at 08:37 UT.Descent speed was reduced from 41,696 km/hr to about 900km/hr by aerobraking. The 2.5 meter diameter parachuteopened at an altitude of 60 km, and a refrigeration system wasused to cool the interior components. Venera 8 transmitteddata during the descent. A sharp decrease in illumination wasnoted at 35 to 30 km altitude and wind speeds of less than 1km/s were measured below 10 km. Venera 8 landed at 09:32UT at 10 degrees south, 335 degrees west, in sunlight about500 km from the morning terminator. The lander mass was 495kg. It continued to send back data for 50 minutes, 11 secondsafter landing before failing due to the harsh surface conditions.The probe confirmed the earlier data on the high Venussurface temperature and pressure (470 degrees C, 90atmospheres) returned by Venera 7, and also measured thelight level as being suitable for surface photography, finding itto be similar to the amount of light on Earth on an overcastday with roughly 1 km visibility.

Venera 8

NSSDC ID: 1972-021A

Alternate Names

Venus 8

05912

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Planetary Science


Launch/Orbitalinformation for Venera 8

PDMP information forVenera 8

Telecommunicationsinformation for Venera 8

Experiments on Venera 8

Data collections fromVenera 8



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


Venera 8








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

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

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

mailto:[email protected]?Subject=NMC Comment/Question: Venera 8 (1972-021A)

mailto:[email protected]?Subject=NMC Comment/Question: Venera 8 (1972-021A)









http://nssdc.gsfc.nasa.gov/image/spacecraft/venera8.jpg



Personnel



Selected References

Shelton, W., Soviet space exploration - the first decade, Arthur Barker Ltd., Unnumbered,London, England, 1969.


Model of the Venera 8 descent module at the Lavochkin Museum

Venera pageVenus Page


http://nssdc.gsfc.nasa.gov/planetary/image/venera_8_capsule.jpg

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

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

http://www.usa.gov/





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