3-axis stabilized using bipropellant thrusters (1220 kg propellant - unified with apogee insertion and maneuvering propulsion) and momentum wheels. Solar arrays generate 3.0 kW at end of life.

Total Length: 7.1 m. Maximum Diameter: 1.6 m. Total Mass: 1,318 kg. Total Payload: 250 kg. Primary Engine Thrust: 40 kgf. Main Engine Propellants: N2O4/MMH.

West German communications; solar panel failed to deploy making spacecraft unusable. Because of a malfunction of the solar generator, the satellite is being used only for technical tests. Geostationary position 19 W. Launch by Ariane-2 flight no. 20. Due to a malfunction of the solar generator, TV-SAT 1 was taken out of commission and sen t to a so-called parking orbit beyond the geostationary orbit. Semi-major axis 42485.605 km. Eccentricity 0.00116. Inc 0.716, Arg of perigee 216.66, RA 76.77, Mean anomaly 47.1 Mean drift -4.071 deg/day, E long 350.617, latitude -0.713.

French DBS; 19 deg W. Direct broadcasting satellite. French registration: TDF-1, 1988-5-B.

TV, business communications for Nordic countries; 5 deg E. High power telecommunications satellite with a dual mission; direct TV broadcasting and data communications. Four active transponders with two redundant; power output 200 W per transponder. Coverage area - East Nordic coverage zone as defined by ITU (WARC -77). Mission period estimated to be 6 to 8 years. Position 5 deg E.

TV services to West Germany; 19 deg W. Direct broadcasting satellite. Position 19 deg W. Ariane 4, flight no 33.

French DBS; 19 deg W. Direct broadcasting satellite. Registration 1990-2-B.

• 2 - McDowell, Jonathan, The United Nations Registry of Space Objects, Harvard University, 1997. HTML when accessed: http://hea-www.harvard.edu/QEDT/jcm/space/un/un.html
• 6 - JPL Mission and Spacecraft Library, Jet Propulsion Laboratory, 1997. HTML when accessed: http://msl.jpl.nasa.gov/home.html
• 279 - McDowell, Jonathan, Launch Log, October 1998. HTML when accessed: http://hea-www.harvard.edu/~jcm/space/log/launch.html