ORION: A Supersynchronous Transfer Orbit mission

Details ORION: A Supersynchronous Transfer Orbit mission ORION: A Supersynchronous Transfer Orbit mission

May 1995

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1995fmet.symp..435w&link_type=abstract

In NASA. Goddard Space Flight Center, Flight Mechanics/Estimation Theory Symposium 1995 p 435-447 (SEE N95-27763 09-13)

Other

Aerospace Systems, Attitude (Inclination), Communication Satellites, Geosynchronous Orbits, Mission Planning, Orbit Calculation, Spacecraft Maneuvers, Synchronous Platforms, Systems Analysis, Transfer Orbits, Algorithms, Apogees, Atlas Launch Vehicles, Burning Rate, Least Squares Method, Longitude, Satellite Antennas, Solar Sensors

Scientific paper

ORION F1 was launched on 29th November 1994 on an Atlas IIA launch vehicle. It was designed, built and delivered in-orbit by Matra Marconi Space Systems Plc and was handed over to ORION Satellite Corporation on 20th January 1995 at its on-station longitude of 37.5 deg W. The mission differed significantly from that of any other geostationary communications satellite in that the Transfer Orbit apogee altitude of 123,507 km was over three times geosynchronous (GEO) altitude and one third of the way to the moon. The SuperSynchronous Transfer Orbit (SSTO) mission is significantly different from the standard Geostationary Transfer Orbit (GTO)mission in a number of ways. This paper discusses the essential features of the mission design through its evolution since 1987 and the details of the highly successful mission itself including a detailed account of the attitude determination achieved using the Galileo Earth and Sun Sensor (ESS).

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