Near-optimal guidance and control for spacecraft collision avoidance maneuvers

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

2 Citations (Scopus)

Abstract

This study presents a semi-analytic and sub-optimal guidance/control for a controlled/active spacecraft to avoid collision with other free/inactive space objects. The collision avoidance problem is formulated as a typical optimal feedback control problem with a penalty term incorporated into the performance index. The penalty function is designed such that its value increases sharply as a spacecraft approaches other space objects. The Pontryagin's principle is used to form a two point boundary value problem for a standard Hamiltonian system, whose solution is obtained in terms of the generating functions which appear in the theory of canonical transformation. The resultant algorithm allows one to develop near-optimal guidance/control laws as truncated power series in feedback form and generate near-optimal trajectories without any initial guess or iterative process. This procedural advantage over typical direct optimization approaches comes at the expense of reasonable efforts of developing higher-order generating functions and empirically updating the design parameters of penalty function. Numerical examples demonstrate that the proposed algorithm successfully accomplishes collision avoidance by appropriately detouring other space objects or forbidden regions.

Original languageEnglish
Title of host publicationAIAA/AAS Astrodynamics Specialist Conference 2014
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Print)9781624103087
Publication statusPublished - 2014 Jan 1
EventAIAA/AAS Astrodynamics Specialist Conference 2014 - San Diego, CA, United States
Duration: 2014 Aug 42014 Aug 7

Other

OtherAIAA/AAS Astrodynamics Specialist Conference 2014
CountryUnited States
CitySan Diego, CA
Period14/8/414/8/7

Fingerprint

collision avoidance
Electronic guidance systems
maneuvers
Collision avoidance
penalty function
Spacecraft
spacecraft
pontryagin principle
power series
penalties
feedback control
boundary value problems
Hamiltonians
trajectories
Boundary value problems
Feedback control
optimization
collisions
Trajectories
Feedback

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Astronomy and Astrophysics

Cite this

Lee, K., Park, C., & Park, S. Y. (2014). Near-optimal guidance and control for spacecraft collision avoidance maneuvers. In AIAA/AAS Astrodynamics Specialist Conference 2014 American Institute of Aeronautics and Astronautics Inc..
Lee, Kwangwon ; Park, Chandeok ; Park, Sang Young. / Near-optimal guidance and control for spacecraft collision avoidance maneuvers. AIAA/AAS Astrodynamics Specialist Conference 2014. American Institute of Aeronautics and Astronautics Inc., 2014.
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Lee, K, Park, C & Park, SY 2014, Near-optimal guidance and control for spacecraft collision avoidance maneuvers. in AIAA/AAS Astrodynamics Specialist Conference 2014. American Institute of Aeronautics and Astronautics Inc., AIAA/AAS Astrodynamics Specialist Conference 2014, San Diego, CA, United States, 14/8/4.

Near-optimal guidance and control for spacecraft collision avoidance maneuvers. / Lee, Kwangwon; Park, Chandeok; Park, Sang Young.

AIAA/AAS Astrodynamics Specialist Conference 2014. American Institute of Aeronautics and Astronautics Inc., 2014.

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

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Lee K, Park C, Park SY. Near-optimal guidance and control for spacecraft collision avoidance maneuvers. In AIAA/AAS Astrodynamics Specialist Conference 2014. American Institute of Aeronautics and Astronautics Inc. 2014