飞机可变几何形状进气道控制系统综合研究

An Integrated Study on Variable Geometry Inlet Control System of Aircraft

论述了飞机进气道可变几何形状控制系统的鲁棒设计方法和系统的综合试验。针对基于发动机压气机增压比πk 参数进行调节的进气道系统 ,给出了试验技术要求和严酷环境条件下的试验结果。

A Robust design approach and integrated test procedure of the aircraft variable geometry inlet control system are discussed.The inlet system is adjusted on π k ,i.e.,pressure ratio of compressor.The test technical requirements and the testing results under harsh environment are given.