Power optimized system for electric propulsion...

Aeronautics and astronautics – Spacecraft – Spacecraft formation – orbit – or interplanetary path

Reexamination Certificate

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C244S169000, C244S172700

Reexamination Certificate

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07922124

ABSTRACT:
Systems and methods are disclosed employing electric propulsion stationkeeping in a cyclical manner to better match the cyclical pattern of power generated by the solar array system. For a typical orbit design, e.g. a geostationary orbit, North-South stationkeeping can be intermittently suspended, tolerating some additional drift but yielding in a very significant reduction in the required solar power system. If necessary, stationkeeping can be supplemented with a chemical thrusters during off periods for the electric propulsion. Because of this, the overall electrical power margin for the solar array system design can be reduced without compromising the mission performance.

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Croci et al., “Influence of Ion Propulsion System (IPS) on the Electrical Power System Sizing”, 1997, NASA Astrophysics Data System, Proceedings of the Second European Spacecraft Propulsion Conference, May 27-29, 1997 (ESA SP-398, Aug. 1997) pp. 619-625.

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