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针对刚体航天器姿态机动控制问题,结合变速控制力矩陀螺(VSCMG)执行器的特性,提出一种自适应动态滑模控制律,提高了姿态机动控制的扰动抑制能力和鲁棒性。此控制律采用自适应方法对扰动力矩进行估计,通过给出控制力矩变化率并对其积分得到控制力矩,以此削弱切换控制的抖振对控制力矩时间连续性的影响,从而改善系统的动态性能。仿真分析显示该控制律能够在扰动力矩作用下实现刚体航天器的快速姿态机动,并且有效减弱了滑模控制的抖振现象。
Aiming at the maneuvering attitude control of rigid spacecraft, an adaptive dynamic sliding mode control law is proposed based on the characteristics of variable speed control moment gyro (VSCMG) actuator, which improves the disturbance rejection and robustness of attitude maneuver control. This control law uses the adaptive method to estimate the disturbance torque. By giving the control torque moment of change rate and integrating it to obtain the control moment, the influence of the chattering of the switching control on the time continuity of the control torque is weakened, so as to improve the system dynamics performance. Simulation results show that this control law can achieve the fast attitude maneuver of rigid spacecraft under disturbing torque and effectively reduce the chattering of sliding mode control.