S形进气道与小涡喷发动机在高空台的匹配试验研究

EXPERIMENTAL INVESTIGATION OF COMPATIBILITY OF S-SHAPED INLET AND SMALL TURBOJET ENGINE IN THE SIMULATED ALTITUDE CHEMBER

本文介绍了以小涡喷发动机为主动力装置的某导弹所采用的S形进气道与发动机在高空台首次进行匹配试验的情况。文章重点阐述了S形进气道/发动机匹配试验的模拟方法和测量技术。

The present paper describes the first testing conditions of compatibility of S- shaped inlet and small turbojet engine which is main power plant of a missile in the simulated altitude chamber. This paper describes measuring and testing technology and data processing methods for the flow parameters at jet exit of inlet. Meanwhile, the emphasis is placed on providing for testing results of inlet/engine compatibility. This testing proves that speific property of gas dynamics for S-shaped inlet of 'HfwM2-1 D' is good. It will be satisfied with requesting for small trubojet engine of a missile in various flying conditions.