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针对大型挠性航天器姿态机动过程中的振动抑制问题,提出一种输入成形(IS)与自适应滑模控制(ASMC)相结合的控制策略。该控制策略利用输入成形抑制标称挠性系统的残余振动,并通过滑模控制保证实际系统在参数不确定性和外部干扰的影响下实现对标称系统的跟踪,解决了输入成形对参数不确定性和外部干扰的敏感性问题。进一步采用自适应技术去除了滑模切换增益对参数不确定性和干扰上界的先验性要求。仿真结果表明,在参数不确定性和外界干扰的影响下,该控制方法能够保证在完成姿态机动的同时抑制航天器的挠性振动。
In order to solve the problem of vibration suppression in attitude maneuvering of large flexible spacecraft, a control strategy combining input shaping (IS) and adaptive sliding mode control (ASMC) is proposed. The control strategy uses input shaping to restrain the residual vibration of the nominal flexible system and the sliding mode control ensures that the actual system can track the nominal system under the influence of parameter uncertainty and external disturbance. Sensitivity issues of certainty and external disturbances. Further adaptive techniques are used to remove the priori requirements of sliding mode switching gain on parameter uncertainty and interference upper bound. The simulation results show that under the influence of parameter uncertainties and external disturbances, this control method can ensure the flexible vibration of the spacecraft while completing the attitude maneuvering.