Journal of Astronomy and Space Sciences

The Korean Space Science Society (한국우주과학회)
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OUTPUT FEEDBACK SLEWING CONTROL OF FLEWIBLE SPACECRAFT BY LYAPUNOV STABILITY THEORY

  • Kim, Dae-Sik (Department of Astronomy & Space Science, Chungbuk National University) ;
  • Kim, Chun-Hwey (Department of Astronomy & Space Science, Chungbuk National University) ;
  • Bang, Hyo-Choong (KOREASAT Group, Korea Aerospace Research Institute)
  • Published : 1997.12.01
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Abstract

Slewing maneuver and vibration suppression control of flexible spacecraft model by Lyapunov stability theory are considered. The specific model considered in this paper consists of a rigid hub with an elastic appendage attached to the central hub and tip mass. Attitude control to point and stabilize single axis using reaction wheel type device is tested. To control all flexible modes is so critical to designing an active control law. We therefore considered an direct output feeback control design by using Lyapunov stability theory. It is shown that the ouput feedback control law design with proposed configuration gives satisfactory result in slewing performance and vibration suppression control.

Keywords

References

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