Method and a system for launching satellites on non-coplanar orb

Details Method and a system for launching satellites on non-coplanar orb Method and a system for launching satellites on non-coplanar orb

1997-12-30

2000-05-09

Poon, Peter M.

Aeronautics and astronautics

Spacecraft

Spacecraft formation, orbit, or interplanetary path

244172, B64G 134

Patent

active

060592338

ABSTRACT:
A first satellite is placed practically directly by a launcher on a first final orbit. A second satellite is placed on the same launcher is initially transferred to a highly elliptical waiting orbit whose semi-major axis points to intercept the torus formed by the sphere of influence of the moon on its orbit, and then during a maneuver at the perigee of the highly elliptical orbit, the second satellite is transferred to lunar transfer orbit. Changes in the perigee altitude and the inclination of an intermediate orbit on which the second satellite is to be found are obtained mainly by gravitational reaction in the sphere of influence of the moon, and during a last maneuver, the second satellite is placed on a final orbit having orbital parameter values that are quite different from those of the orbital parameters of the first final orbit.

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Atzei et al., A., "Soho and Cluster: Europe's Possible Contribution to the STP" ESA Bulletin, No. 41, Feb. 1985, Paris, France, pp. 21-28.
Andrews, D.G. "Aerobraked Orbital Transfer Vehicle Definition", AIAA-81-0279, Jan. 1989.

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