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

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

2 Citations (Scopus)


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
Publication statusPublished - 2020
EventAIAA Scitech Forum, 2020 - Orlando, United States
Duration: Jan 6 2020Jan 10 2020

Publication series

NameAIAA Scitech 2020 Forum
Volume1 PartF


ConferenceAIAA Scitech Forum, 2020
Country/TerritoryUnited States

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering


Dive into the research topics of 'Minimum fuel trajectory design using sparse optimal control in three-body problem'. Together they form a unique fingerprint.

Cite this