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Semi-Optimal Control Using Shooting Method for Real Time Minimum-Time Maneuver of Satellite with VSCMG

  • Tsuchiya Mitsuyoshi
    連絡先著者(Corresponding author):mitsuyoshi.tsuchiya747@gmail.com 横浜国立大学大学院理工学府機械・材料・海洋系工学専攻
  • Higuchi Takehiro
    横浜国立大学大学院環境情報研究院人工環境と情報部門

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Other Title
  • VSCMG搭載衛星の最短時間マヌーバにおけるシューティング法を用いた リアルタイム準最適制御則

Abstract

<p>This study explores the minimum-time attitude maneuver of satellites using Control Moment Gyros (CMG). The CMG system is able to generate high torque and run for longer term than other actuators. However, it is known that the singular input that cannot generate effective torque appears in the optimal control for the minimum-time maneuver of a rigid spacecraft with a pyramid type SGCMG system. In previous studies, a new system equipped with variable speed CMG (VSCMG) to the CMG where the singular input appeared has been proposed. It is shown that the new system can rotate faster than the normal pyramid type SGCMG system in the simulation based on the optimal control law. However, for applications in actual satellites, numerical optimization cannot be used due to the high calculation cost. The objective of this study is to make the new semi-optimal control law for the minimum time attitude maneuver of the satellite equipped with the VSCMG. The new control law is designed using a rule-based feedforward control combined with feedback control. The result by numerical simulation has shown that the proposed control law enables the satellite to achieve faster maneuver without iterative calculations. </p>

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