发动机进气道监测系统设计和实现  

Design and Implementation of Engine Inlet Monitoring System

作　　者：张亚维[1] 史强强 张乐 ZHANG Ya-wei;SHI Qiang-qiang;ZHANG Le(School of Aviation Maintenance Engineering,Xi'an Aeronautical Polytechnic Institute,Xi'an 710089,China;Xi'an Yuanfang General Aviation Technology Development Corporation,Xi'an 710089,China)

机构地区：[1]西安航空职业技术学院航空维修工程学院,陕西西安710089 [2]西安远方航空技术发展有限公司,陕西西安710089

出　　处：《测控技术》2022年第8期48-53,共6页Measurement & Control Technology

基　　金：教育部首批国家级职业教育教师教学创新团队课题研究项目(ZD2020050101)。

摘　　要：发动机性能验证时须对发动机与进气道相容性进行飞行监测测试,用实测数据分析进气道畸变与发动机的匹配特性。设计了一种适合多传感器类型的多板卡、实时监测、在线算法诊断的进气道综合监测系统,对多传感器参数完成实时监测、数据预处理、预警等。前端测量传感器主要包含各类气压参数中稳态、压差、总压、动态压力传感器以及进气总温传感器,面对采集通道众多、频率差异化难题,为改善数据的在线监测相关性同步采样和关联参数在线计算处理的能力,采用多板卡级联并行传输总线解决数据实时交互问题,并通过多类型总线接口匹配后端记录、告警、遥测监测设备。经系统验证,设计的方案简单且合理可行,具有一定实用性。During the engine performance verification, the compatibility between the engine and the inlet must be monitored and tested in flight.The matching features of inlet distortion and engine are analyzed with measured data.A multi-board, real-time monitoring and on-line algorithm diagnosis integrated inlet monitoring system that is suitable for multi-sensor type is designed to complete the functions of real-time monitoring, data preprocessing, early warning and so on.Front-end measuring sensor mainly includes steady-state, differential pressure, total pressure, dynamic pressure sensor and the inlet total temperature sensor of various air pressure parameters.Facing the problems of numerous acquisition channels and frequency differentiation, in order to improve the ability of on-line monitoring, correlation synchronous sampling and on-line calculation and processing of correlation parameters, multi-board cascade parallel transmission bus is adopted to solve the problem of real-time data interaction, and the back-end recording, alarm, telemetry and monitoring devices are matched through multi-type bus interface.Through the system verification, the design scheme is simple, reasonable and feasible, and has certain practicability.

关 键 词：发动机进气道畸变 实时监测 在线诊断 飞行试验 

分 类 号：V217.22[航空宇航科学与技术—航空宇航推进理论与工程]