Geometric optimal control of elliptic Keplerian orbits
نویسندگان
چکیده
This article deals with the transfer of a satellite between Keplerian orbits. We study the controllability properties of the system and make a preliminary analysis of the time optimal control using the maximum principle. Second order sufficient conditions are also given. Finally, the time optimal trajectory to transfer the system from an initial low orbit with large eccentricity to a terminal geostationary orbit is obtained numerically.
منابع مشابه
Averaging and optimal control of elliptic Keplerian orbits with low propulsion
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