Small Aircraft Engine Sensor Fault Tolerant Control Technology

In the working process of a missile with a small aviation engine, the absolutepressure sensor behind the high pressure compressor for engine starting, accelerationperformance plays a key role. In recent years, the batch production showed the absolutepressure sensor produced many failures, the probability of failure is much greater.Therefore, it is necessary to consider the absolute pressure sensor redundancy design, toensure that engine can work safely during the sensor failure cases, and the reliabilitylevel is raised.This paper combined with practical engineering needs, for a small aviation engine,about fault tolerant control problem of the flow pressure (P2) sensor behindhigh-pressure compressor, from the sensor hardware redundancy, software redundancyand fault tolerance control system design and simulation research is carried out deeply.A new P2sensor fault tolerant control scheme was designed, to make redundanthardware and software redundancy organic integration. This scheme on the basis offurther study, and to build a P2engine sensor fault tolerant control system simulationmodel, a large number of fault simulation experiment was carried out to study by usingthe system simulation platform, large fault tolerant performance simulation resultsachieved expected effect. The results showed that, the P2sensor fault tolerant controlscheme can provides available flow total pressure signal for the engine controllereffectively, and that can be realized on the P2sensor fault tolerance, which is alsoexamined in this article a design plan for the validity and accuracy.The research on control system for engine performance analysis, sensor faulttolerant system and engine system improvement, modification etc. has a positive guiderole and auxiliary function, which showed a remarkable economy and project value. Theresearch is expected to be applied in the development-oriented engine control system ofa certain type missile.