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A method is provided for using a lunar flyby maneuver 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, resulting in a geostationary orbit, provided that the satellite is launched in March or September.

Inventors: Jeremiah O. Salvatore, Cesar A. Ocampo
Original Assignee: Hughes Electronics Corporation
Current U.S. Classification: 244/158.5
International Classification: B64G 110

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Citations

Cited PatentFiling dateIssue dateOriginal AssigneeTitle
US5158249Oct 12, 1990Oct 27, 1992Ball CorporationOrbital systems for cislunar travel
US5507454Jan 28, 1991Apr 16, 1996Centre National d'Etudes SpatialesSatellite and method to place this satellite in orbit by gravitational assistance
US5511748Nov 12, 1993Apr 30, 1996Method for extending the useful life of a space satellite
US5716029Oct 31, 1995Feb 10, 1998Hughes ElectronicsConstant sun angle transfer orbit sequence and method using electric propulsion

Referenced by

Citing PatentFiling dateIssue dateOriginal AssigneeTitle
US6302354Jun 7, 2000Oct 16, 2001The Aerospace CorporationSpace vehicular fly-by guidance method
US6327523Jan 21, 1999Dec 4, 2001Hughes Electronics CorporationOverhead system of inclined eccentric geosynchronous orbitting satellites
US6389336Jun 20, 2001May 14, 2002Hughes Electronics CorporationOverhead system of inclined eccentric geosynchronous orbiting satellites
US6766987Aug 28, 2002Jul 27, 2004Hughes Electronics CorporationSatellite system and method of deploying same
US7184761Mar 27, 2000Feb 27, 2007The DirecTV Group, Inc.Satellite communications system
US7369809Oct 30, 2000May 6, 2008The DIRECTV Group, Inc.System and method for continuous broadcast service from non-geostationary orbits
US7480506Jan 16, 2007Jan 20, 2009The DIRECTV Group, Inc.Satellite communication system
US8016240Mar 29, 2007Sep 13, 2011The Boeing CompanySatellites and satellite fleet implementation methods and apparatus

Claims

1. 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 substantially lower than the first inclination, by using a lunar gravitation-assist flyby maneuver, the method comprising the steps of:

placing the satellite into the initial orbit about the earth, the initial orbit having an apogee substantially lower than lunar radius;
placing the satellite into a translunar orbit, the translunar orbit having an apogee near lunar radius;
placing the satellite into a lunar flyby maneuver near apogee of the translunar orbit, whereby the inclination of the orbit of the satellite with respect to the earth is significantly reduced;
placing the satellite into an earth-return orbit, the earth-return orbit having a perigee near geostationary radius; and
placing the satellite into the final geosynchronous orbit about the earth.

2. The method of claim 1, wherein the step of placing the satellite into the translunar orbit comprises a step of placing the satellite into a series of phasing orbits, each phasing orbit having an apogee altitude higher than that of the previous phasing orbit.

3. 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 orbit having a second inclination substantially lower than the first inclination, by using a lunar gravitation-assist flyby maneuver, the method comprising the steps of:

placing the satellite into the quasi-geosynchronous transfer orbit;
placing the satellite into a translunar orbit, the translunar orbit having an apogee near lunar radius;
placing the satellite into a lunar flyby maneuver whereby the inclination of the orbit of the satellite with respect to the earth is significantly reduced;
placing the satellite into an earth-return orbit, the earth-return orbit having a perigee near geostationary radius; and
placing the satellite into the geosynchronous orbit about the earth.

4. The method of claim 3, wherein the step of placing the satellite into the translunar orbit comprises a step of placing the satellite into a series of phasing orbits, each phasing orbit having an apogee altitude higher than that of the previous phasing orbit.

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