Optimal Low-Thrust Transfers to Lunar L1 Halo Orbit Using Variable Specific Impulse Engine
Publication: Journal of Aerospace Engineering
Volume 28, Issue 4
Abstract
Given the advantages of variable specific impulse (VSI) engine, it is very likely that in the future there will be deep space missions that use this thrust as propulsion system. In this study, a design technique for a fuel optimal Earth-to-Halo transfer using VSI is proposed. The calculus of variations approach and direct parameter optimization are combined to formulate the trajectory optimization problem. The classic stable manifold, developed in dynamical systems theory, is employed to further reduce fuel consumption. Adjoint control transformation (ACT) and analytical gradients are incorporated to improve performance of the algorithm. Four transfer examples—direct transfers from 500 km low Earth orbit (LEO) and 3,629 km medium Earth orbit (MEO) to lunar L1 halo orbit—and indirect transfers with lunar flybys, are presented.
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Published In
Journal of Aerospace Engineering
Volume 28 • Issue 4 • July 2015
Copyright
© 2014 American Society of Civil Engineers.
History
Received: Oct 8, 2013
Accepted: May 1, 2014
Published online: Jul 28, 2014
Discussion open until: Dec 28, 2014
Published in print: Jul 1, 2015
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