Fault-tolerant attitude control systems for a satellite equipped with Control Moment Gyros

A. Noumi, M. Takahashi

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

12 Citations (Scopus)

Abstract

In recent years, there has been a requirement for accurate and agile attitude control of satellites. To meet this demand there has been an increasing use of Control Moment Gyros (CMGs), which can generate much higher torque than reaction wheels that are used as conventional spacecraft actuators. Furthermore, it is important for attitude control systems to be fault tolerant. In a conventional 4 CMG system, the CMGs are placed in a pyramid mounting arrangement with a skew angle set to 54.74 degree. The maximum angular momentum of the CMG system is changed according to the skew angle. A suitable skew angle should be designed to consider normal and failure situations. Moreover, the suitable parameters of satellite attitude and CMG control systems are changed according to the skew angle. Therefore, this paper proposes a design method for fault-tolerant attitude control system. In the proposed method, the skew angle and the parameters of the control system are tuned simultaneously using a genetic algorithm. To verify the fault-tolerance of the proposed method, numerical simulations for the case where one CMG has failed are carried out.

Original languageEnglish
Title of host publicationAIAA Guidance, Navigation, and Control (GNC) Conference
Publication statusPublished - 2013 Sep 16
EventAIAA Guidance, Navigation, and Control (GNC) Conference - Boston, MA, United States
Duration: 2013 Aug 192013 Aug 22

Publication series

NameAIAA Guidance, Navigation, and Control (GNC) Conference

Other

OtherAIAA Guidance, Navigation, and Control (GNC) Conference
CountryUnited States
CityBoston, MA
Period13/8/1913/8/22

ASJC Scopus subject areas

  • Aerospace Engineering
  • Control and Systems Engineering
  • Electrical and Electronic Engineering

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  • Cite this

    Noumi, A., & Takahashi, M. (2013). Fault-tolerant attitude control systems for a satellite equipped with Control Moment Gyros. In AIAA Guidance, Navigation, and Control (GNC) Conference (AIAA Guidance, Navigation, and Control (GNC) Conference).