基于故障检测滤波器法的飞行控制系统故障检测

Failure Detection of Flight Control System Based on Fault Detection Filter Method

针对某型无人机飞行控制系统,在分析3种舵面损伤典型故障机理的基础上,利用故障检测滤波器法对其进行故障检测。根据建立飞机舵面发生故障模型并假设其损伤故障表示式,再将滤波器的极点实部大于40,定位于相关平面左半部,使观测器瞬态响应衰减,并使滤波器状态估计值收敛到系统的状态值。仿真证明该方法可行。

For the flight control system of a certain UAV （Unmanned Aerial Vehicle）, the failure detection filter method is adopted to carry out failure detection based on the analysis for the failure mechanism of three typical failures of the flight control surface. According to the failure model of the flight control surfaces and the failure expressions under the research hypothesis, the poles are located in the left half surface and the real parts of the poles are assigned greater than 40, in order to make the temporal response decay as soon as possible and make the state estimated values converge the system states. Simulation proves this way is feasible.