Thrust nozzle system and method for the orbit and attitude control of a geostationary satellite
AssigneeThales
InventorJoel AMALRIC
Life of this patent
Estimating the term…
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.
Claims22
A thrust nozzle system for a satellite designed to be stabilized in autorotation over a geostationary orbit, the said 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, comprising 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 said even number being equal to at least 4, the said thrust nozzles being oriented along three spatial components, and having, taken in pairs, different signs of X and Y components.
Dependencies are inferred from the claim text.