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航天器挠性附件的振动难以直接测量且对航天器的姿态控制精度产生不利影响。为解决这一问题,提出一种基于观测器的鲁棒多目标姿态控制系统设计方法,借助特征结构配置的参数化方法,给出了含有自由参向量的控制器以及观测器的完整参数化形式。通过对自由参向量的多目标优化选取,使控制系统具有良好的鲁棒性和干扰抑制能力,并避免了控制输出饱和现象的发生。对一个挠性航天器的设计实例表明了方法的有效性。
Vibration of spacecraft flexible attachments is difficult to measure directly and adversely affects the spacecraft’s attitude control accuracy. To solve this problem, an observer-based robust multi-target attitude control system design method is proposed. With the help of the parameterized method of feature structure configuration, a complete parameterized form of controller and observer with free parameters is given . By selecting multiple parameters of free parameter vector, the control system has good robustness and interference suppression, and avoids the control output saturation. The design example of a flexible spacecraft shows the effectiveness of the method.