多柔体航天器姿态与结构振动宽频带耦合控制

Being composed of several flexible structures is a prominent feature of morden high-preformance remote sensing and tel-communication spacecraft structures. Mutual influence and interaction are important characteristics of these spacecrafts. Whereas a fundamental requirement on the structural vibration and attitude control system is that the system stability should be ensured while the high quality wide-band control should be realized. For enhancing the control performance and ensuring the stability to satisfy ever raising demands on the dynamic and control performace of spacecrafts, this proposed project will develop wide-band coupling control theory and methodology that can fuse attitude control and structural vibration control together. The research will start from the modelling method suitable for the wide-band coupling control and study the control method that couples the passive structural vibration control and the attitude jitter control. To enhance the performance of the control system, passive-active integrated coupling control of structural vibration and attitude jitter will also be studied. The solution of non-collocated control problem resulted generated by the introduction of structural flexibility into the attitutde control system loop will be focused, and the robust coupling non-collocated control method will be developed. A purpose of this research is to relax the requirement on the ground modal test precision but in the meantime to ensure the control system performance. Principles and design methodology for attitude and vibration coupling control actuators will also be investigated. According to practical scenarios, coupling control problems will be studied under the conditions of attitude stable state and attitude agile state, respectively.

由多个多柔体结构组成是现代高性能遥感和通讯航天器突出的结构特点，姿态和结构振动控制的相互影响与相互作用是这些航天器的重要特征，保证控制系统的稳定性并实现高质量宽频带控制是对其结构振动与姿态控制系统的基本要求。为满足日益提高的对航天器动力学与控制性能的要求，本项目提出发展将姿态控制和结构振动控制相互融合于一体的宽频带耦合控制理论和方法。研究从建立适用于宽频带耦合控制需要的控制模型建模方法入手，研究结构振动被动控制与姿态抖动控制的耦合控制方法，为实现拓宽控制频带和可实现性的目标，同时研究结构振动与姿态抖动的主被动一体化耦合控制问题，重点解决因结构柔性进入姿态控制系统回路形成的异位耦合控制的鲁棒性问题，以在保证控制系统性能的同时降低结构地面模态试验的难度。此外，还将探索姿态和振动耦合控制作动器的设计原理和设计方法。根据工程实际情况，分别对姿态机动和姿态稳定两种状况下的控制问题进行研究。

由多个多柔体结构组成是现代高性能遥感和通讯航天器突出的结构特点，姿态和结构振动控制的相互影响与相互作用是这些航天器的重要特征，保证控制系统的稳定性并实现高质量宽频带控制是对其结构振动与姿态控制系统的基本要求。为满足日益提高的对航天器动力学与控制性能的要求，本项目发展了姿态控制和结构振动控制相互融合于一体的宽频带耦合控制理论和方法。经过四年的研究工作，本项目完成了预定的计划和实现了预定目标。进行了多方面的研究工作，并发表了多篇英文学术论文。研究工作包括：多柔体航天器的控制模型建模方法，柔性附件展开过程的姿态控制方法，性附件展开后的姿态与结构振动控制方法，基于结构临近稳定阻尼的姿态稳定与结构振动控制，卫星敏捷机动过程的结构振动抑制方法研究，局部非线性结构动力学降阶过程的研究，非线性结构的试验辨识研究，以及挠性附件振动抑制装置研究。通过研究，观察到了异位控制中广泛存在的临界稳定阻尼现象，提出了带分立式隔振器的控制力矩陀螺群组逃离奇异点的改进操作率，提出了单自由度非线性结构辨识的等效动刚度图法.