Abstract This paper presents a guidance law that allows a vehicle to orbit around a target at a given radius using a side-bearing angle. The global asymptotic stability of the proposed method is demonstrated, and a linear analysis is performed to facilitate the proper selection of the relevant control parameter. Two flight experiments, one with a GPS-based flight control system and the other with a vision-based flight control system, are presented to demonstrate the feasibility and performance of the proposed guidance law.
Circumnavigation with Side-Bearing Angle
15.12.2017
19 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
Fast Satellite Circumnavigation via Continuous Control
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