Spacecraft guidance with constant angular velocity of the line of sight

Details Spacecraft guidance with constant angular velocity of the line of sight Spacecraft guidance with constant angular velocity of the line of sight

Mar 1977

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1977kosis..15..192i&link_type=abstract

Kosmicheskie Issledovaniia, vol. 15, Mar.-Apr. 1977, p. 192-197. In Russian.

Astronomy and Astrophysics

Astronomy

Angular Velocity, Rendezvous Guidance, Spacecraft Guidance, Trajectory Optimization, Astrodynamics, Spacecraft Motion, Thrust Vector Control

Scientific paper

Analytical functions are presented for determining characteristics of the relative motion of spacecraft and for selecting optimum parameters for spacecraft guidance with constant angular velocity of the line of sight. Three types of relative-motion trajectories are delineated: rendezvous, grazing approach, and separation. The characteristic velocity needed for realizing relative motion with constant velocity of the line of sight is determined. Combined spacecraft control involving continuous control by means of a regulated-thrust engine and discrete control by means of a constant-thrust engine is considered.

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