Deorbiting a Spacecraft from a Highly Inclined Elliptical Orbit
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United States of America Patent
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Issued Date -
May 17, 2012
app pub date -
Jul 1, 2010
filing date -
Jul 2, 2009
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Abandoned
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Abstract
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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