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

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

8 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
EventAIAA Guidance, Navigation, and Control (GNC) Conference - Boston, MA, United States
Duration: 2013 Aug 192013 Aug 22

Other

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

Fingerprint

Attitude control
Satellites
Control systems
Angular momentum
Fault tolerance
Mountings
Spacecraft
Wheels
Actuators
Torque
Genetic algorithms
Computer simulation

ASJC Scopus subject areas

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

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

Fault-tolerant attitude control systems for a satellite equipped with Control Moment Gyros. / Noumi, A.; Takahashi, Masaki.

AIAA Guidance, Navigation, and Control (GNC) Conference. 2013.

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

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, Boston, MA, United States, 13/8/19.
Noumi A, Takahashi M. Fault-tolerant attitude control systems for a satellite equipped with Control Moment Gyros. In AIAA Guidance, Navigation, and Control (GNC) Conference. 2013
Noumi, A. ; Takahashi, Masaki. / Fault-tolerant attitude control systems for a satellite equipped with Control Moment Gyros. AIAA Guidance, Navigation, and Control (GNC) Conference. 2013.
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