面向航空发动机推力控制的大气参数测量系统设计

Design of Air-data Parameters Processing System for Aeroengine Thrust Control

为了实现多发飞机推力控制匹配要求,以及提升机载控制参数测量可靠性要求,设计了一套适用于多发飞机的机载环境大气参数测量系统。通过对发动机推力控制需求和适航相关要求的分析,确定了系统设计原则,利用飞机和发动机的有限硬件资源,提出了一种适用于多发飞机的多余度机载环境大气参数测量系统架构。针对不同来源的信号,分别设计了相应信号故障诊断算法、表决算法以及多源信号故障切换逻辑,保证系统在信号发生故障时可及时切换到健康余度。通过仿真和试验对测量系统在信号发生故障时的容错能力进行了验证,结果表明:系统余度设计合理,故障诊断和表决逻辑有效,环境大气参数测量的可靠性和安全性得到了提升;当信号发生故障时,可实现故障重构,且切换过程产生的推力变化小于3%。

In order to meet the thrust control matching requirements of multi-engine aircraft and improve the reliability of airborne control parameters,an air-data parameters processing system for multi-engine aircraft was designed.Based on the analysis of engine thrust control requirements and related airworthiness requirements,the system design principles were determined.Using the limited hardware resources of aircraft and engines,a redundant air-data parameters processing system architecture suitable for multi-engine aircraft was proposed.For signals from different sources,the corresponding signal fault diagnosis algorithm,voting algorithm and multi-source signals fault switching logic were designed to ensure timely switching over to valid signal in case of a signal fault.The fault tolerance of the system in the event of signal fault was verified by simulation and test.The results show that the system redundancy design is reasonable,the fault diagnosis and voting logic are effective,and the reliability and safety of air-data parameters are improved.In case of signal fault,fault reconstruction can be realized,and the thrust change generated in the switching process is less than 3%.