Physics
Scientific paper
May 1993
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1993phdt.........6j&link_type=abstract
Ph.D. Thesis Air Force Inst. of Tech., Wright-Patterson AFB, OH.
Physics
2
Lunar Orbits, Rendezvous Guidance, Space Navigation, Space Rendezvous, Spacecraft Control, Spacecraft Guidance, Three Body Problem, Control Theory, Feedback, Simulation, Stationkeeping
Scientific paper
This research considers the design of a representative end-to-end guidance and navigation system for the terminal phase rendezvous of two spacecraft in the circular restricted three-body problem. It assumes the target vehicle is in a small radius translunar halo orbit; the target vehicle remains passive with respect to the rendezvous profile. The chaser vehicle is in an independent small radius translunar halo orbit and executes all rendezvous maneuvers. First, the halo orbit guidance problem is formulated in the frequency-domain from which an output feedback guidance law is developed using H2 control theory. Linear simulation results validate the guidance law and provide data which quantify the effect of control inputs, noise characteristics and halo orbit characteristics on the steady state halo orbit station-keeping costs. Secondly, a two spacecraft terminal phase rendezvous targeting law is derived; nonlinear simulation results validate the targeting law.
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