For satellite and target orbiting closely in two nearly circular orbits with small inclinations, guidance law of orbital rendezvous is derived based on solution in terms of perturbations from two-impulse transfer; by introducing fictitious satellite, which orbits in circular orbit close to satellite and target during rendezvous period, and which constitutes center of coordinate system of rendezvous problems, linearized equations of motion are solved for fixed-orientation-thrust powered flight and free flight; determination of thrust orientation and thrust duration for two thrusting periods of rendezvous scheme constitutes required guidance law.
Finite-thrust explicit guidance law for nearly circular orbital rendezvous
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 4 , n 1
1967
5 pages
Article (Journal)
English
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