Low-energy earth-moon mission analysis using low-thrust optimal and feedback control

Low-energy earth-moon mission analysis using low-thrust optimal and feedback control

A. Almonte, I. Ziccardi, A. Adriani, A. Marchetti, M. Pontani

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Abstract. This work is focused on designing a low-energy orbit transfer in the Earth-Moon system, aimed at reaching stable capture in a highly elliptical lunar orbit, with the use of low-thrust propulsion. The mission at hand includes three different phases: low-energy ballistic transfer starting from Earth, low-thrust minimum-fuel arc, and low-thrust lunar orbit insertion using variable-thrust nonlinear orbit control. First, a reference trajectory is generated in the framework of the Patched Planar Circular Restricted Three-Body Problem (PPCR3BP), leveraging invariant manifold dynamics. Trajectory propagation is performed using the Bicircular Restricted Four-Body Problem (BR4BP) model. Particle swarm optimization is applied for trajectory refinement and to detect the subsequent minimum-fuel low-thrust arc. Finally, the lunar orbit is entered thanks to the use of variable-thrust nonlinear orbit control.

Earth-Moon Transfers, Low Energy Transfers, Low-Thrust Spacecraft, Optimal Control, Feedback Guidance and Control, Particle Swarm Optimization

Published online 11/1/2023, 5 pages
Copyright © 2023 by the author(s)
Published under license by Materials Research Forum LLC., Millersville PA, USA

Citation: A. Almonte, I. Ziccardi, A. Adriani, A. Marchetti, M. Pontani, Low-energy earth-moon mission analysis using low-thrust optimal and feedback control, Materials Research Proceedings, Vol. 37, pp 596-600, 2023

DOI: https://doi.org/10.21741/9781644902813-130

The article was published as article 130 of the book Aeronautics and Astronautics

Content from this work may be used under the terms of the Creative Commons Attribution 3.0 license. Any further distribution of this work must maintain attribution to the author(s) and the title of the work, journal citation and DOI.

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