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Small Astronomy Satellite 3 information


Small Astronomy Satellite 3
Small Astronomy Satellite 3
Mission typeX-ray astronomy
OperatorNASA
COSPAR ID1975-037A Edit this at Wikidata
SATCAT no.07788
Mission duration4 years
Spacecraft properties
ManufacturerAPL · Johns Hopkins University
Launch mass196.7 kilograms (434 lb)
Power65.0 watts
Start of mission
Launch date7 May 1975, 22:45:01 (1975-05-07UTC22:45:01Z) UTC
RocketScout F-1 S194C
Launch siteSan Marco
End of mission
Decay date9 April 1979 (1979-04-10)
Orbital parameters
Reference systemGeocentric
RegimeLEO
Eccentricity0.0000313
Perigee altitude509.0 kilometers (316.3 mi)
Apogee altitude516.0 kilometers (320.6 mi)
Inclination3.0033°
Period94.90 minutes
RAAN13.5403 degrees
Argument of perigee37.2127 degrees
Mean anomaly322.7960 degrees
Mean motion16.22945651
Epoch8 April 1979
Revolution no.21935
Explorers Program
← Explorer 52
Explorer 54 →
 
SAS 3 spacecraft as it might have appeared deployed on orbit. The nominal spin axis, or +z axis, points to the upper right, with the RMC and one star tracker for attitude determination. The remaining instruments and a second star tracker point out of the image towards the viewer. The four solar panels charged batteries during orbit day.

The Small Astronomy Satellite 3 (SAS 3, also known as SAS-C before launch) was a NASA X-ray astronomy space telescope.[1] It functioned from May 7, 1975 to April 1979. It covered the X-ray range with four experiments on board. The satellite, built by the Johns Hopkins University Applied Physics Laboratory (APL), was proposed and operated by MIT's Center for Space Research (CSR). It was launched on a Scout vehicle from the Italian San Marco launch platform near Mombasa, Kenya, into a low-Earth, nearly equatorial orbit. It was also known as Explorer 53, as part of NASA's Explorer program.[2]

The spacecraft was 3-axis stabilized with a momentum wheel that was used to establish stability about the nominal rotation, or z-axis. The orientation of the z-axis could be altered over a period of hours using magnetic torque coils that interacted with the Earth's magnetic field. Solar panels charged batteries during the daylight portion of each orbit, so that SAS 3 had essentially no expendables to limit its lifetime beyond the life of the tape recorders, batteries, and orbital drag. The spacecraft typically operated in a rotating mode, spinning at one revolution per 95-min orbit, so that the LEDs, tube and slat collimator experiments, which looked out along the y-axis, could view and scan the sky almost continuously. The rotation could also be stopped, allowing extended (up to 30 min) pointed observations of selected sources by the y-axis instruments. Data were recorded on board by magnetic tape recorders, and played back during station passes every orbit.[3]

SAS 3 was commanded from the NASA Goddard Space Flight Center (GSFC) in Greenbelt MD, but data were transmitted by modem to MIT for scientific analysis, where scientific and technical staff were on-duty 24 hours a day. The data from each orbit were subjected to quick-look scientific analysis at MIT before the next orbital station pass, so the science operational plan could be altered by telephoned instruction from MIT to GSFC in order to study targets in near real-time.

  1. ^ Annual Review of Astronomy and Astrophysics "X-ray Astronomy Missions", H. Bradt, T. .Ohashi,. and K. Pound., Vol. 30, p. 391 ff (1992)
  2. ^ HEASARC GSFC, retrieved Oct 17, 2009 Mission Overview
  3. ^ W. Mayer 1975, APL Tech Digest, 14, 14.

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