执行器故障下挠性航天器自适应边界容错控制

Adaptive Fault-Tolerant Boundary Control of Flexible Spacecrafts Under Actuator Faults

针对执行器故障下的挠性航天器的姿态控制及振动抑制问题,提出了基于模型变换的自适应边界容错控制方案,实现了挠性航天器的姿态跟踪及振动抑制。首先,为了准确刻画航天器刚体与挠性振动之间的强耦合特性,采用互联偏微分方程常微分方程描述挠性航天器的混合动力学;其次,设计辅助信号建立边界条件与内部动力学之间的关系;进而,采用直接自适应控制技术设计边界容错控制律及参数更新律,保证挠性航天器闭环姿态控制系统的渐近跟踪性能;最后,仿真结果验证了所提出的边界容错控制算法的有效性。

This paper studies an attitude control and vibration suppression problem for flexible spacecrafts under actuator faults,using a model transform based adaptive control technique.In order to describe the strong coupling features between the rigid body and flexible motion,the hybrid system dynamics is modeled by an interconnected partial differential equation-ordinary differential equation.A couple of auxiliary signals are designed to establish the relation between the boundary conditions and internal dynamics.A novel adaptive fault-tolerant boundary control scheme is developed to ensure the asymptotic tracking performance and vibration suppression.A simulation study on the attitude control system of flexible spacecrafts effectively verifies the validity of the developed theoretical results.