Low-thrust perturbation guidance

Details Low-thrust perturbation guidance Low-thrust perturbation guidance

Aug 1982

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1982asdy.confu....b&link_type=abstract

American Institute of Aeronautics and Astronautics and American Astronautical Society, Astrodynamics Conference, San Diego, CA,

Computer Science

Performance

Earth-Mars Trajectories, Feedback Control, Low Thrust, Spacecraft Guidance, Trajectory Control, Transfer Orbits, Optimal Control, Orbit Perturbation, Position Errors, Terminal Guidance, Trajectory Optimization

Scientific paper

Two perturbation guidance schemes, time-to-go guidance and minimum-distance guidance, are reexamined, in the context of a low-thrust orbit transfer problem. The two schemes, which use different techniques for indexing feedback gains, are shown to be comparable in performance. Both schemes are found to produce terminal state errors which are orders of magnitude smaller than those obtained in several previous studies. Various small modifications or enhancements of the algorithms are thought to account for a portion of the dramatic improvement in results. The problem investigated is a hypothetical earth to Mars orbit transfer, with six state variables, two control variables, and six terminal state constraints.

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