Free return lunar flyby transfer method for geosynchronous satellites havint multiple perilune stages
AssigneeHughes Electronics Corporation
InventorsJeremiah O. Salvatore, Cesar A. Ocampo
Life of this patent
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Abstract
A method is provided for using at least two lunar flyby maneuvers to transfer a satellite from a quasi-geosynchronous transfer orbit having a high inclination to a final geosynchronous orbit having a low inclination. The invention may be used to take the inclination of a final geosynchronous orbit of a satellite to zero, through the use of a first leading-edge lunar flyby and subsequent successive leading or trailing edge lunar flybys resulting in a geostationary orbit.
Claims4
A method for transferring a satellite from an initial orbit about the earth, the initial orbit having a first inclination, to a final geosynchronous orbit about the earth, the final geosynchronous orbit having a second inclination significantly less than the first inclination, by using multiple lunar gravity-assist flyby maneuvers, the method comprising the steps of:
- placing the satellite into the initial orbit about the earth, the initial orbit having an apogee significantly lower than lunar radius;
- placing the satellite into a first translunar orbit, the first translunar orbit having an apogee near lunar radius;
- placing the satellite into a first leading edge lunar flyby maneuver near apogee of the first translunar orbit, whereby the inclination of the orbit of the satellite with respect to the earth is initially significantly reduced;
- placing the satellite into an earth-return orbit, the earth-return orbit having a perigee near geostationary radius;
- placing the satellite into at least a second translunar orbit;
- placing the satellite into at least a second lunar flyby maneuver, whereby the inclination of the orbit of the satellite with respect to the earth is additionally significantly reduced;
- and
- placing the satellite into the final geosynchronous orbit about the earth.
A method for transferring a satellite from a quasi-geosynchronous transfer orbit, the quasi geosynchronous transfer orbit having a first inclination, to a geosynchronous earth orbit, the geosynchronous earth orbit having a second inclination substantially lower than the first inclination, by using at least two lunar gravity-assist flyby maneuvers, the method comprising the steps of:
- placing the Satellite into the quasi-geosynchronous transfer orbit the quasi-geosynchronous transfer orbit having an apogee significantly lower than lunar radius;
- placing the satellite into a first translunar orbit, the first translunar orbit having an apogee near lunar radius;
- placing the satellite into a first leading-edge lunar flyby maneuver whereby the inclination of the orbit of the satellite with respect to the earth is initially significantly reduced;
- placing the satellite into a first earth-return orbit, the first earth-return orbit having a perigee near geostationary radius;
- placing the satellite into at least a second lunar flyby maneuver whereby the inclination of the orbit of the satellite with respect to the earth in additionally reduced;
- and
- placing the satellite into the geosynchronous earth orbit.
Dependencies are inferred from the claim text.