Optimization of the two-impulse rendezvous maneuver of two spacecraft in circular orbit under constraints

Details Optimization of the two-impulse rendezvous maneuver of two spacecraft in circular orbit under constraints Optimization of the two-impulse rendezvous maneuver of two spacecraft in circular orbit under constraints

May 1991

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1991kosis..29..352i&link_type=abstract

Kosmicheskie Issledovaniia (ISSN 0023-4206), vol. 29, May-June 1991, p. 352-366. In Russian.

Physics

Circular Orbits, Orbital Rendezvous, Rendezvous Trajectories, Spacecraft Maneuvers, Transfer Orbits, Earth Orbital Environments, Rendezvous Guidance, Rendezvous Spacecraft

Scientific paper

The optimization problem (in terms of minimal characteristic velocity) of the two-impulse rendezvous maneuver of two spacecraft moving initially in the same circular orbit is investigated. Limits are imposed on the distance from the spacecraft to the center of gravity and on the transfer time. The qualitative and quantitative characteristics of the solutions are analyzed during changes of the initial angular misalignment between the spacecraft.

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