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Steering law design to control moment gyroscopes for near minimum time attitude maneuver

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Abstract

In this paper a simple and more effective steering law is presented for spacecraft attitude maneuver with control moment gyroscopes (CMG) as actuator. The singularity problem and fast exchanging requirement of angular momentum are taken into consideration. Moreover, a near minimum time rest to rest eigenaxis rotation maneuver algorithm using CMG cluster is also proposed. Finally, simulations have been performed to demonstrate the effectiveness and advantages of the proposed steering law and maneuver algorithm.

Original languageEnglish
Title of host publicationProceedings of the 2010 5th IEEE Conference on Industrial Electronics and Applications, ICIEA 2010
Pages280-285
Number of pages6
DOIs
StatePublished - 2010
Event5th IEEE Conference on Industrial Electronics and Applications, ICIEA 2010 - Taichung, Taiwan, Province of China
Duration: 15 Jun 201017 Jun 2010

Publication series

NameProceedings of the 2010 5th IEEE Conference on Industrial Electronics and Applications, ICIEA 2010

Conference

Conference5th IEEE Conference on Industrial Electronics and Applications, ICIEA 2010
Country/TerritoryTaiwan, Province of China
CityTaichung
Period15/06/1017/06/10

Keywords

  • Attitude maneuver
  • Control moment gyroscopes
  • Singularity
  • Steering law

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