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中文摘要：
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。
英文摘要：
Vibration of spacecraft flexible appendages negatively affectes the spacecraft attitude control accuracy, and is difficult to measure directly. A robust multi-objective attitude control system based on a vibration mode observer is proposed to solve the problem. By employing the parametric eigenstructure assignment method, the analytical forms of feedback controller and observer included a set of free parameters are constructed. By choosing the multi-objective optimization parameters, the designed control system is robustness to spacecraft structural parameters and external disturbances, and also avoids actuator saturation. A design example for a flexible spacecraft is used to illustrate the effectiveness of the proposed method.
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