Satellite-launch vehicle combination and method
AssigneeSatellite Business Systems
InventorMichael T. Lyons
Life of this patent
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Abstract
A satellite intended for insertion into a quasi-synchronous earth orbit is adapted for efficient launch by minimizing the amount of launch vehicle cargo capacity employed. The satellite includes at least one major thrust source, such as an apogee kick motor, defining a major thrust axis for the satellite. A reusable launch vehicle such as the Space Shuttle, includes a cargo bay whose largest dimension is parallel to the launch vehicle thrust axis. Minimizing satellite use of cargo bay capacity is obtained by adapting the satellite to lie within the cargo bay of the launch vehicle with its thrust axis perpendicular to the thrust axis of the launch vehicle.
Claims14
A reusable satellite launch vehicle and at least one satellite supported therein comprising:
- a launch vehicle having a cargo bay of given dimensions with a thrust axis,
- satellite cradle means mounted within said cargo bay for support of a satellite thereby,
- said satellite mounted within said cradle means and including at least one source of major thrust defining a major thrust axis for said satellite,
- said cradle means supporting said satellite with said major thrust axis substantially perpendicular to said launch vehicle thrust axis.
A satellite launch vehicle and at least one satellite supported therein comprising:
- a reusable launch vehicle having a cargo bay of given dimensions with a thrust axis parallel to a largest of said given dimensions,
- satellite cradle means mounted within said cargo bay for support of a satellite thereby,
- said satellite mounted within said cradle means and including at least one source of major thrust defining a major thrust axis for said satellite,
- said satellite having its major dimension extending parallel to said major thrust axis,
- said cradle means supporting said satellite with said major thrust axis at an angle of about 90.degree. to said launch vehicle thrust axis.
A method of adapting a satellite intended for quasi-synchronous orbit for efficient launch via a reusable launch vehicle with defined cargo bay to minimize use of launch vehicle payload capability comprising the steps of:
- providing said satellite with at least one major thrust motor such as an apogee kick motor whose orientation defines a major thrust axis for said satellite,
- dimensioning said satellite so that when mounted for launch said satellite lies within a portion of said cargo bay wherein the improvement comprising:
- dimensioning said satellite to fit within said cargo bay with said major thrust axis at an angle of about 90.degree. to a launch vehicle thrust axis.
Dependencies are inferred from the claim text.