Abort Guidance During Lunar Powered Descent
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Published:2024-01-18
Issue:
Volume:
Page:1-13
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ISSN:0731-5090
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Container-title:Journal of Guidance, Control, and Dynamics
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language:en
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Short-container-title:Journal of Guidance, Control, and Dynamics
Author:
Sandoval Sergio A.1,
Lu Ping1ORCID,
Hwang John T.2
Affiliation:
1. San Diego State University, San Diego, California 92182
2. University of California, San Diego, California 92093
Abstract
During powered descent of a crewed lunar landing mission, the ability to abort and ascend into a clear pericynthion orbit is critical in case any contingency renders the landing infeasible or excessively risky. In such a case, it is incumbent upon the guidance system to determine autonomously a safe abort trajectory and the associated guidance command. To accomplish this task reliably, a novel two-phase abort guidance strategy is proposed in this paper where a pull-up maneuver redirects the velocity vector to help mitigate any ground collision risk and achieve an appropriate initial ascent condition, followed by a fuel-optimal ascent guidance algorithm to insert the spacecraft into a predefined safe orbit around the moon. Development of the pull-up guidance laws and a description of the fuel-optimal ascent guidance based on the indirect method of optimal control are presented. In-depth investigation is conducted to provide a full understanding of the validity of the abort solutions. The solutions and fuel efficiency of the proposed guidance strategy are independently verified by using a direct method of optimal control. Monte Carlo closed-loop simulations demonstrate the effectiveness and robustness of this method throughout the entire powered descent.
Funder
NASA Space Technology Research Fellowship
NASA Cooperative Agreeement
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Applied Mathematics,Electrical and Electronic Engineering,Space and Planetary Science,Aerospace Engineering,Control and Systems Engineering