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Fast attitude maneuver of spacecraft based on variable structure control

Research output: Chapter in Book/Report/Conference proceedingConference contributionpeer-review

Abstract

This article chooses large reconnaissance satellites with ultrahigh resolution power for study. It describes the mathematical model of the satellites and proposes a control algorithm based on multi-mode switching of control moment gyros. The proposed algorithm is effective to avoid the singularity of control moment gyros while making the satellite achieve fast attitude maneuver. Sliding-mode variable structure controller is designed to minimize the error attitude and further accelerates the attitude convergence speed. At last, referring to the vibration equation, a strain rate feedback controller is used to suppress the satellite vibration quickly. The effectiveness of the proposed scheme is illustrated with a numerical simulation example.

Original languageEnglish
Title of host publicationProceedings of the 2012 2nd International Conference on Instrumentation and Measurement, Computer, Communication and Control, IMCCC 2012
Pages1480-1484
Number of pages5
DOIs
StatePublished - 2012
Event2012 2nd International Conference on Instrumentation and Measurement, Computer, Communication and Control, IMCCC 2012 - Harbin, Heilongjiang, China
Duration: 8 Dec 201210 Dec 2012

Publication series

NameProceedings of the 2012 2nd International Conference on Instrumentation and Measurement, Computer, Communication and Control, IMCCC 2012

Conference

Conference2012 2nd International Conference on Instrumentation and Measurement, Computer, Communication and Control, IMCCC 2012
Country/TerritoryChina
CityHarbin, Heilongjiang
Period8/12/1210/12/12

Keywords

  • Control moment gyros
  • Fast attitude maneuver
  • Reconnaissance satellite
  • Sliding-mode variable structure controller

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