Thrust nozzle system and method for the orbit and attitude control of a geostationary satellite
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United States of America Patent
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Jan 30, 2018
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N/A
app pub date -
Nov 25, 2014
filing date -
Nov 29, 2013
priority date (Note) -
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Abstract
A thrust nozzle system is provided for a satellite designed to be stabilized in autorotation over a geostationary orbit, the satellite comprising three reference axes X, Y and Z, the Y axis representing the North/South axis and the Z axis corresponding to an Earth pointing direction. The thrust nozzle system comprises a first set of thrust nozzles configured for maintaining the satellite in station, the first set comprising an even number of thrust nozzles using electrical propulsion, with a pre-adjusted orientation, the even number being equal to at least 4, the thrust nozzles being oriented along three spatial components, and having, taken in pairs, different signs of X and Y components.
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