基于系统构型替换的固冲发动机故障模式半实物仿真

Fault simulation of ducted rocket based on system configuration switch method

为全面快速验证冲压发动机的故障检测算法,基于构型替换建立了能模拟多种固冲发动机故障的仿真验证平台。基于此平台,搭建了发动机点火故障模型、压强传感器故障模型、设备接口模型,以及与真实控制器中检测算法具有相同外部接口和系统构型的故障检测算法模型等。通过系统构型的切换,将同一个故障模式注入故障检测算法模型和真实发动机系统,并通过对比同一组故障模式下故障检测模型检测结果与发动机控制系统检测结果,来对发动机控制器中的故障检测算法进行快速验证。以无喷管助推器点火的检测为例,讲述了该方法的建模、实验验证及分析过程,此外,该方法还能应用到无喷管助推器关机、进气道前后堵盖打开、燃气发生器点火、燃气流量容错控制等多个故障模式的仿真模拟与验证,具有很强的通用性,能大大地降低控制系统开发与验证的时间成本,具有很强的应用价值。

In order to comprehensively verify the fault detection algorithm in the ducted rocket rapidly,a simulation platform based on system configuration switch method was built,which can simulate various fault mode for ducted rocket.Based on the simulation platform,the ducted rocket ignite fault model,pressure sensor fault model,device interface model and fault detection algorithm model which have a same interface and system configuration with the aircraft engine controller,etc.were built.Compared with the fault detect result of mathematical model and engine control system under a same fault mode,the fault detection algorithm in the engine control system can be verified rapidly.Taking the fault simulation of nozzleless booster ignition as an example,the modeling,the test,the verification,and the process of analysis were narrated.In addition,it is also applicable to the fault simulation and verification of the shutdown of nozzleless booster,the open of air inlet cover,the ignition of gas generator,and fault tolerant control of gas flow,which has strong universality,and can greatly reduce the time cost on system development and verification,and it has a strong applied value.