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轨控期间的卫星由于推力器安装偏差,实施推力时会产生较大的干扰力矩,直接影响到卫星姿态稳定。除此,考虑到执行机构提供的力矩是有限的,为保证系统的稳定性,需在设计控制器的过程中考虑输入受限问题。本文针对卫星执行机构故障情况,综合考虑输入受限和干扰问题,提出一种基于输入受限的挠性卫星姿态容错控制策略,并开展了仿真试验,验证了本文设计的姿态容错控制器的有效性。
During the orbit control satellite due to the installation of thrusters deviations, the implementation of thrust will have a greater disturbance torque, a direct impact on satellite attitude stability. In addition to this, considering that the torque provided by the actuator is limited, in order to ensure the stability of the system, input-limited problems need to be considered in designing the controller. In this paper, aiming at the fault condition of the satellite actuator, considering the limited input and interference problems, this paper presents a control strategy based on the limited input of flexible satellite attitude fault tolerant, and carries out a simulation test to verify the effectiveness of the proposed attitude fault tolerant controller Sex.