基于模型参考自适应的高超声速飞行器容错控制

Model Reference Adaptation Based Fault-Tolerant Control for Hypersonic Vehicles

针对执行机构部分失效情况下高超声速飞行器控制器的设计问题,提出了一种模型参考自适应容错控制设计方案。依据线性化的高超声速飞行器名义模型,设计名义反馈控制增益,并确定一个可保证自适应控制安全的参考模型,然后设计自适应补偿控制器消除执行机构控制效益及系统参数不确定性的影响。提出的自适应参数估计律由滤波的误差信号和特别设计的预测误差信号驱动,可实现更好的参数估计。该方案能保证闭环系统的稳定性,并能保证执行机构部分失效及系统参数不确定情况下的控制性能。仿真结果验证了该控制方法的有效性,在执行机构部分失效情况下,控制系统实现了良好的跟踪性能。

A model reference adaptation based fault-tolerant control scheme is proposed for hypersonic flight vehicles to deal with actuator fault. The control scheme is composed of a nominal baseline controller designed for the nominal plant without considering the actuator fault and model uncertainties, and an adaptive controller used to eliminate the effect of model uncertainties and control effectiveness changed due to actuator fault. A reference model is established by the nominal controller and the nominal plant to ensure the safe adaptation. Parameter estimation law is newly designed and driven by the filtered tracking errors and the special designed predictor errors, thus a better parameter estimation can be achieved. Moreover, the control scheme can guarantee the global asymptotical stability of closed-loop system and the control performance in the presence of actuator fault and model uncertainties. Simulation based on a generic air-breathing hypersonic flight vehicle demonstrates the effectiveness of the control scheme.