Energy efficient satellite maneuvering

Abstract

Energy efficient satellite maneuvering is described herein. One disclosed example method includes maneuvering a satellite that is in an orbit around a space body so that a principle sensitive axis of the satellite is oriented to an orbit frame plane to reduce gravity gradient torques acting upon the satellite. The orbit frame plane is based on an orbit frame vector.

Description

technical field [0001] This patent relates generally to satellites, and more particularly to energy efficient satellite maneuvering. Background technique [0002] Space vehicles (eg, satellites or resident space objects (RSOs)) typically encounter significant gravitational moments (eg, ambient moments, ambient moment disturbances, etc.) during maneuvers to final orbits after launch. Typically, an Earth-orbiting satellite or resident space object (RSO) may be positioned in a parking or initial orbit before performing an initial maneuver to initiate a transfer orbit (geosynchronous transfer orbit, etc.) to a final orbit. The satellite can then perform the final maneuver to maintain the final orbit. For example, a satellite may start in Low Earth Orbit (LEO) and maneuver through a Geosynchronous Transfer Orbit (GTO) to a final Geosynchronous Orbit (GEO). During these maneuvers, the satellite's gravitational moment and / or momentum increase may require significant use of thrust...

AI Technical Summary

Problems solved by technology

However, these reaction wheels require additional payload space and / or weight and may also require energy to operate

Further, some of the more recent satellites employ deployable solar panels to generate power as such satellites move towards the final orbit, thereby increasing the moment of inertia and thus resulting in a greater sensitivity to the gravitational gradient moment, necessitating the use of relative Larger reaction wheels, which in turn require correspondingly more payload space and weight of the launch vehicle

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