Orbit Inclination: 105.8
Perigee: 1082 km
Apogee: 1570 km

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Spacecraft Brief Description
The GEOS 2 (Geodetic Earth Orbiting Satellite) was a
gravity-gradient-stabilized, solar-cell-powered spacecraft that
carried electronic and ... geodetic instrumentation. The geodetic
instrumentation systems included (1) four optical beacons, (2) two
C-band radar transponders, (3) a passive radar reflector, (4) a
sequential collation of range radio range transponder, (5) a Goddard
range and range rate transponder, (6) laser reflectors, and (7)
Doppler beacons. Non-geodetic systems included a laser detector and a
Minitrack interferometer beacon. The objectives of the spacecraft
were to optimize optical station visibility periods and to provide
complementary data for inclination-dependent terms established by the
Explorer 29 (GEOS 1) gravimetric studies. The spacecraft was placed
into a retrograde orbit to accomplish these objectives. Operational
problems occurred in the main power system, optical beacon flash
system, and the spacecraft clock, and adjustments in scheduling
resulted in nominal operations.
Auxiliary Information
Launch Date and Time : 1968-01-11 16:19:00
Epoch Date and Time : 1977-02-28
Orbit Type : Geocentric
Apogee(km) : 1570.
Perigee(km) : 1082.
Inclination : 105.8
Date of last update : 1992-03-09

http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1978-071A