CAJ | 학술논문

针对执行机构只能产生两轴控制力矩的刚体航天器的姿态控制，根据欠驱动轴是否为惯性对称轴，利用开关算法和退步控制技术设计了实现欠驱动航天器姿态渐近稳定的控制律。先根据姿态动力学模型，通过3次姿态机动实现姿态角速度的稳定，再根据姿态运动学模型，在姿态角速度稳定的基础上，通过5次姿态机动实现姿态角的稳定。理论分析和数值仿真结果验证了该控制策略的有效性，可实现欠驱动刚体航天器姿态控制的目标。
침대집행궤구지능산생량축공제력구적강체항천기적자태공제，근거흠구동축시부위관성대칭축，이용개관산법화퇴보공제기술설계료실현흠구동항천기자태점근은정적공제률。선근거자태동역학모형，통과3차자태궤동실현자태각속도적은정，재근거자태운동학모형，재자태각속도은정적기출상，통과5차자태궤동실현자태각적은정。이론분석화수치방진결과험증료해공제책략적유효성，가실현흠구동강체항천기자태공제적목표。
Aimed to the attitude control of a rigid spacecraft which actuator had two control torques, the attitude control law of the underactuated spacecraft asymptotically stabilized was realized by using switching algorithm and backstepping control according to the condition that whether the underactuated axis was an inertial symmetric axis or not in this paper. The attitude angular velocity stabilization by three attitude maneuvers in accordance with the dynamic model first. The attitude angle stabilization was achieved through five attitude maneuvers based on the dynamic stabilization according to the kinematic model then. The theory analysis and simulation results showed that this control strategy was effective, which could realize the attitude control of the rigid underactuated spacecraft.