超声速下颔式进气道/前机身一体化方案设计

推进技术 ›› 2002, Vol. 23 ›› Issue (2): 142-145.

超声速下颔式进气道/前机身一体化方案设计

王新月,廉小纯

西北工业大学航空动力与热力工程系陕西西安710072;西北工业大学航空动力与热力工程系陕西西安710072

发布日期:2021-08-15

Supersonic chin inlet/airframe integration design

Dept. of Aeroengine Engineering, Northwestern Polytechnical Univ.,Xi’an 710072,China;Dept. of Aeroengine Engineering, Northwestern Polytechnical Univ.,Xi’an 710072,China

Published:2021-08-15

摘要/Abstract

摘要： 为了改善飞机的作战效能 ,使飞机能安装大功率的雷达 ,对某型飞机的进气道改型为包含头锥激波在内的三波系外压缩下颔形式。将下颔式进气道与前机身进行一体化设计。并设计进气道唇口前掠倾斜 ,解决了雷达与进气道的相互干扰。对进气道的性能参数进行分析计算并与原型机进行对比 ,在性能满足要求的情况下 ,增加了机头空间 ,提高了飞机的作战能力。其唇口设计对飞机隐身也有利

关键词: 超声速进气道;外压式进气道;一体化设计;方案设计

Abstract: In order to improve the abality of aircraft battle and mount big power radar in the head of aircraft,a new design configuration was presented by studing supersonic chin Inlet/Forebody integration issue.The chin inlet of the external compression with three shocks have sweep forward lip.The inlet configuration was anylized and the performance of the inlet was calculated.The space of the airplane head was increased.

Key words: Supersonic inlet;External compression inlet;Integrated design;Tentative design

王新月,廉小纯. 超声速下颔式进气道/前机身一体化方案设计[J]. 推进技术, 2002, 23(2): 142-145.