摘要
研究航空发动机控制系统中故障多发部件之一的执行机构故障诊断的问题。目前航空发动机控制系统执行机构故障诊断多采用硬件冗余的方法,因而导致设备重量和费用过高的问题,针对此问题,采用模型的解析余度方法,建立航空发动机执行机构的故障模型,利用卡尔曼滤波器组对发动机进行状态参数估计,构造滤波误差加权平方和作为系统残差,结合容错设计原理实现对执行机构故障的检测与隔离。仿真结果表明,改进方法对发动机燃油计量装置和喷口面积可调装置的执行机构故障诊断准确有效,易于工程实现。
The fault diagnosis of aeroengine actuator was presented, for actuator is one of the fault - prone parts in aircraft engine control system. Hardware redundancy method is widely used in actuator fault diagnosis of aeroengine control system at present, which leads to high weight and expense in equipment, so the engine actuator fault model was established based on the redundant method of analytical model, and the Kalman filter set was used to estimate engine state parameter to realize actuators fault detection and isolation by constructing weighted square error as residual of system, combined with the principle design of fault tolerant. The simulation results show that the presented method can accurately and efficiently diagnose actuator fault in engine fuel metering device and nozzle area system, and is easy to be implemented in project.
出处
《计算机仿真》
CSCD
北大核心
2013年第2期93-96,共4页
Computer Simulation
