Design of feedback control system using nominal inputs for satellite attitude maneuver using Control Moment Gyros

Y. Kusuda, Masaki Takahashi

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

3 Citations (Scopus)

Abstract

Satellites orbiting the earth require large-angle and rapid rotational maneuverability. For this purpose Control Moment Gyros (CMG) needs to be applied to an attitude control actuator of a small agile satellite, because CMG can generate high torque effectively. CMG has a singularity problem which affects energy consumption and rapid actuation of CMG. In order to settle these problems we proposed feed-forward control logic using energy optimal path planning by Fourier Basis Algorithm (FBA). However, this logic does not hold robustness with several errors and disturbances. Therefore, this paper designs a feedback control system so as to obtain robustness with errors of initial CMG gimbal angles generated by natural environmental disturbances. The designed system is characterized by using the system's limit state, which is a new defined variable and is predicted by numerical integrals using nominal control inputs. The results of the several numerical simulations show the availability of the proposed logic about robustness with these errors, energy consumption, and safe use of CMG.

Original languageEnglish
Title of host publicationAIAA Guidance, Navigation, and Control Conference and Exhibit
Publication statusPublished - 2009
Externally publishedYes
EventAIAA Guidance, Navigation, and Control Conference and Exhibit - Chicago, IL, United States
Duration: 2009 Aug 102009 Aug 13

Other

OtherAIAA Guidance, Navigation, and Control Conference and Exhibit
CountryUnited States
CityChicago, IL
Period09/8/1009/8/13

Fingerprint

Feedback control
Satellites
Control systems
Energy utilization
Feedforward control
Maneuverability
Attitude control
Motion planning
Robustness (control systems)
Actuators
Torque
Earth (planet)
Availability
Computer simulation

ASJC Scopus subject areas

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

Cite this

Kusuda, Y., & Takahashi, M. (2009). Design of feedback control system using nominal inputs for satellite attitude maneuver using Control Moment Gyros. In AIAA Guidance, Navigation, and Control Conference and Exhibit [2009-6205]

Design of feedback control system using nominal inputs for satellite attitude maneuver using Control Moment Gyros. / Kusuda, Y.; Takahashi, Masaki.

AIAA Guidance, Navigation, and Control Conference and Exhibit. 2009. 2009-6205.

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

Kusuda, Y & Takahashi, M 2009, Design of feedback control system using nominal inputs for satellite attitude maneuver using Control Moment Gyros. in AIAA Guidance, Navigation, and Control Conference and Exhibit., 2009-6205, AIAA Guidance, Navigation, and Control Conference and Exhibit, Chicago, IL, United States, 09/8/10.
Kusuda Y, Takahashi M. Design of feedback control system using nominal inputs for satellite attitude maneuver using Control Moment Gyros. In AIAA Guidance, Navigation, and Control Conference and Exhibit. 2009. 2009-6205
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