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Research Article

Comparison between direct and indirect approach to solar sail circle-to-circle orbit raising optimization

Andrea Caruso, Alessandro A. Quarta( ), Giovanni Mengali
Department of Civil and Industrial Engineering, University of Pisa, I-56122, Italy
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Abstract

This paper deals with the optimization of the transfer trajectory of a solar sail-based spacecraft between circular and coplanar heliocentric orbits. The problem is addressed using both a direct and an indirect approach, while an ideal and an optical force model are used to describe the propulsive acceleration of a flat solar sail. In the direct approach, the total flight time is partitioned into arcs of equal duration, within which the sail attitude is assumed to be constant with respect to an orbital reference frame, and a nonlinear programming solver is used to optimize the transfer trajectory. The aim of the paper is to compare the performance of the two (direct and indirect) approaches in term of optimal (minimum) flight time. In this context, the simulation results show that a direct transcription method using a small number of arcs is sufficient to obtain a good estimate of the global minimum flight time obtained through the classical calculus of variation.

Keywords

flat solar sailcircle-to-circle transferheliocentric mission analysistrajectory optimization

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Astrodynamics
Volume 3 Issue 3,
September 2019
Pages 273-284
DOI: 10.1007/s42064-019-0040-x
Cite this article:
Caruso A, Quarta AA, Mengali G. Comparison between direct and indirect approach to solar sail circle-to-circle orbit raising optimization. Astrodynamics, 2019, 3(3): 273-284. https://doi.org/10.1007/s42064-019-0040-x

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Received: 09 August 2018
Accepted: 14 November 2018
Published: 13 April 2019
© Tsinghua University Press 2019
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