Second-order analytical solution to fuel-optimal control problems in satellite formation flying

Sangjin Lee, Sang Young Park

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

Abstract

In this paper, a new analytical solution to optimal control problems in formation flying is presented, including the differential gravity effects to the second order. The perturbation approach and the calculus of variations are applied to the optimal control problems in order to obtain an approximate analytical solution. A nonlinear relative dynamics that includes quadratic terms in the differential gravitational accelerations is used. For the sake of validity, numerical simulations are performed for satellite reconfiguration cases in which the distance between the satellites is large. Finally, the improved accuracy of the new analytical solution ensuring reasonable fuel usage is confirmed.

Original languageEnglish
Title of host publicationSpaceflight Mechanics 2010 - Advances in the Astronautical Sciences
Subtitle of host publicationProceedings of the AAS/AIAA Space Flight Mechanics Meeting
Pages933-948
Number of pages16
Publication statusPublished - 2010 Dec 1
EventAAS/AIAA Space Flight Mechanics Meeting - San Diego, CA, United States
Duration: 2010 Feb 142010 Feb 17

Publication series

NameAdvances in the Astronautical Sciences
Volume136
ISSN (Print)0065-3438

Other

OtherAAS/AIAA Space Flight Mechanics Meeting
CountryUnited States
CitySan Diego, CA
Period10/2/1410/2/17

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Space and Planetary Science

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  • Cite this

    Lee, S., & Park, S. Y. (2010). Second-order analytical solution to fuel-optimal control problems in satellite formation flying. In Spaceflight Mechanics 2010 - Advances in the Astronautical Sciences: Proceedings of the AAS/AIAA Space Flight Mechanics Meeting (pp. 933-948). (Advances in the Astronautical Sciences; Vol. 136).