弹用高亚音速嵌入式、半嵌入式进气道设计与试验研究

DESIGN AND EXPERIMENTAL STUDY OF HIGH-SUBSONIC SPEED SUBMERGED AND SEMI-SUBMERGED INTAKE FOR MISSILE

本文介绍了以涡轮喷气发动机为动力装置的飞航式战术导弹的一种新型高亚音速嵌入式、半嵌入式进气道的设计与试验研究结果。提出了弹用高亚音速嵌入式、半嵌入式进气道在弹上的位置、进气道通道截面形状、扩张规律、开口形状、喉道面积、内外唇口以及附面层隔道高度选取等初步设计原则和抽气式测试系统的新的进气道试验技术。

The design and test results of the new type high-subsonic speed submerged and semi-submerged intakes for cruise missile propelled by a turbojet engine have been introduced. The principle for preliminary design of the intake position on board, the duct section shape, the expansion law, the intake configuration, the throat area, the profile of inside and outside lips, as well as the boundary layer diverter height has been outlined. A new technology for intake test on the pumping facility system is presented.