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针对航空发动机发生故障时系统的容错能力问题,设计了基于特征结构配置方法的容错控制系统。首先分析了被动容错控制的特点和优点,然后采用特征结构配置的方法,在配置系统极点的同时,还配置系统的特征向量,并对系统进行重新调节以获得整个系统在故障发生后的稳定性与可靠性,给出了特征结构配置方法的具体设计步骤。然后,在该方法的基础上,设计了被动容错控制器。最后,针对某型航空发动机的设计工况点模拟系统发生故障,即参数发生摄动时,对所设计的容错控制器系统的鲁棒性进行了仿真分析。仿真结果表明,经过特征结构配置后,系统的稳态输出值能够被调整到原系统稳态输出值的附近,维持系统的性能,即系统具有较好的容错能力。
Aiming at the problem of system fault tolerance in the event of aero-engine failure, a fault-tolerant control system based on the feature configuration is designed. First of all, the characteristics and advantages of passive fault-tolerant control are analyzed. Then, with the method of feature structure configuration, the system’s eigenvectors are also configured while the system poles are configured, and the system is readjusted to obtain the stability of the whole system after the fault occurs And the reliability, the design steps of the method of feature structure configuration are given. Then, on the basis of this method, a passive fault tolerant controller is designed. Finally, aiming at the failure of the simulation system of the design condition point of a certain type of aeroengine, the robustness of the designed fault-tolerant controller system was simulated and analyzed when the parameters perturbed. The simulation results show that after the feature configuration, the steady-state output of the system can be adjusted to the vicinity of the steady-state output of the original system to maintain the system performance, that is, the system has good fault tolerance.