Minimum fuel trajectory design using sparse optimal control in three-body problem

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

This study formulates a successive multiple sparse optimal control method to minimize a fuel consumption of spacecraft in three-body problem. This method uses a convex optimization under linearlized dynamics, however it enables to find an optimal solution that satisfies a nonlinear dynamics by successive convexification. Furthermore, the divergence of the state constraint due to the instability of the three-body system can be avoided by dividing the state constraint into several sections. This method is applied to a transfer from Near Rectilinear halo orbit (NRHO) to Low lunar orbit (LLO) in the Earth-Moon system.

Original languageEnglish
Title of host publicationAIAA Scitech 2020 Forum
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105951
DOIs
Publication statusPublished - 2020
EventAIAA Scitech Forum, 2020 - Orlando, United States
Duration: Jan 6 2020Jan 10 2020

Publication series

NameAIAA Scitech 2020 Forum
Volume1 PartF

Conference

ConferenceAIAA Scitech Forum, 2020
CountryUnited States
CityOrlando
Period1/6/201/10/20

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

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