A distributed coordinated robust control method is proposed in this paper for large flexible spacecraft with distributed actuators and sensors. By dividing the control framework into an attitude dynamic system and a structural vibration system, a consensus observer is designed to estimate the primary system's modal coordinates and the graph theory is used to develop a leader-follower consensus vibration controller to reduce the oscillation of the flexible structures. The robust optimal attitude controller with known averaged vibration modal parameters is also designed to overcome the influence of environmental disturbances and other system uncertainties. The integrated result is an effective pointing controller of large flexible spacecraft, which is also robust to failures and inconsistencies in the control system. A comparative study is presented to show the advantage of the decentralized design over the conventional centralized method. Simulation results are provided to demonstrate the performance of the proposed control method.

提出了一种具有分布式执行器和传感器的大型柔性航天器分布式协调鲁棒控制方法。通过将控制框架分为姿态动力学系统和结构振动系统，设计了一个共识观测器来估计主系统的模态坐标，并使用图论来开发一种跟随者共识振动控制器，以减少柔性系统的振荡。结构。具有已知平均振动模态参数的鲁棒最优姿态控制器也被设计来克服环境干扰和其他系统不确定性的影响。集成结果是大型挠性航天器的有效指向控制器，该控制器对于控制系统中的故障和不一致也具有鲁棒性。提出了一项比较研究，以显示分散设计相对于常规集中式方法的优势。仿真结果表明了所提出控制方法的性能。