Consideration of the problem of optimal ascent from an initial circular planetary orbit to some specified final energy level by a spacecraft equipped with a low-thrust engine. Optimal is defined as minimum time. An accurate small parameter perturbation solution is presented, and the optimal trajectory is analyzed and compared with a tangential thrust trajectory.
Asymptotic solution to the problem of optimal low-thrust energy increase.
AIAA Journal ; 10
1972-12-01
Miscellaneous
No indication
English
Asymptotic Solution for the Two-Body Problem with Low-Thrust
British Library Conference Proceedings | 2012
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