High-accuracy trajectory optimization for a trans-earth lunar mission

Hui Yan, Qi Gong, Chan D. Park, I. Michael Ross, Christopher N. D'Souza

Research output: Contribution to journalArticle

23 Citations (Scopus)

Abstract

The trajectory optimization of a spacecraft subject to the gravitational effects of the moon, Earth, and sun are considered. The problem is how to achieve Earth-interface conditions from a low lunar orbit. Practical constraints of maximum thrust, fuel budget, and flight time generates a constrained, nonautonomous, nonlinear optimal control problem. Severe constraints on the fuel budget combined with high-accuracy demands on the endpoint conditions necessitate a high-accuracy solution to the trajectory optimization problem. The problem is first solved using the standard Legendre pseudospectral method. The optimality of the solution is verified by an application of the covector mapping principle. It is shown that the thrust structure consists of three finite burns with nearly linear steering-angle time histories. A singular arc is detected and is interpreted as a singular plane change maneuver. The Bellman pseudospectral method is then employed for mesh refinement to improve the accuracy of the solution.

Original languageEnglish
Pages (from-to)1219-1227
Number of pages9
JournalJournal of Guidance, Control, and Dynamics
Volume34
Issue number4
DOIs
Publication statusPublished - 2011

All Science Journal Classification (ASJC) codes

  • Control and Systems Engineering
  • Aerospace Engineering
  • Space and Planetary Science
  • Electrical and Electronic Engineering
  • Applied Mathematics

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