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Deorbiting a Spacecraft from a Highly Inclined Elliptical Orbit
Deorbiting a Spacecraft from a Highly Inclined Elliptical Orbit
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机译:从高度倾斜的椭圆轨道上使航天器脱离轨道
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摘要
Deorbiting of an earth-orbiting satellite is accomplished by executing an orbit transfer maneuver, the orbit transfer maneuver resulting in transference of the satellite from an operational orbit to a disposal orbit, where the disposal orbit is substantially circular and has a nominal radius of approximately, 31,000 kilometers. The operational orbit may be substantially geosynchronous and have at least one of (i) an inclination of greater than 10 degrees and (ii) a nominal eccentricity greater than 0.1. Alternatively, the operational orbit may be a medium earth orbit.
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