對於剛體衛星停止翻滾及水平螺旋狀態之回復，本研究使用搭載於衛星本體的力矩動量輪及三軸磁力致動器，提出兩部份控制方法。第一部份控制法則是藉由所承載的動量輪趨使剛體姿態動態中的類陀螺運動，動量輪旋轉軸裝於平行衛星之主軸方向，此控制方法可藉由操作動量輪，將翻滾或水平螺旋狀態的衛星之主軸方向，校準於系統角動量方向。在校準工作完成後，第二部份控制法則藉由選取角動量轉移參數()將衛星本體之角動量，轉移至動量輪內，或慢慢地卸除大部份角動量於太空中。兩部份控制法則皆根據Lyapunov 穩定度分析，與回授線性化方法推導而成。從停止翻滾及水平螺旋回復模擬結果中，發現在選定參數之兩部份控制法則較其他方法，可花較少時間及能量達到較高的準確度。此外，在模擬中發現，儘管動量輪力矩及磁力偶矩有輸出上限，仍可驗證兩部份控制法則之穩定度。

This research presents an efficient two-part method for detumbling and flat-spin recovery of a rigid spacecraft using an onboard torque wheel and a set of three-axis magnetic torquer. Part-1 control of the proposed method activates the gyroscopic-like motion embedded in the attitude dynamics of a rigid-body by an onboard wheel. The control manipulates the wheel, whose spin axis is parallel to a designated principal axis of the spacecraft to align the principal axis from a tumbling or a flat-spin situation to its total angular momentum vector,HT. Following the alignment, Part-2 control can either quickly stop the spacecraft's rotation by transferring its angular momentum to the wheel or slowly offload most of the momentum into space by setting the momentum-transfer coefficient,η. Control laws for both parts are derived from the Lyapunov stability analysis and the method of feedback linearization. Simulation results from the included detumbling and flat-spin recovery cases indicate that the two-part method with a chosen η effectively takes much less time and energy with better accuracy than using the other methods. In addition, the stability of the two-part method is further substantiated by the hard constraints on the wheel torque and the dipole moment in the simulations.

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