冲压发动机进气道不起动边界分析

推进技术 ›› 2007, Vol. 28 ›› Issue (3): 269-272.

冲压发动机进气道不起动边界分析

何保成,常军涛,于达仁

哈尔滨工业大学能源科学与工程学院黑龙江哈尔滨150001;航天科工集团公司31研究所;北京100074;;哈尔滨工业大学能源科学与工程学院;黑龙江哈尔滨150001;哈尔滨工业大学能源科学与工程学院;黑龙江哈尔滨150001

发布日期:2021-08-15

Analysis of the unstart boundary for ramjet inlets

School of Energy Science and Engineering,Harbin Institute of Technology,Harbin 150001,China;The 31st Research Institute of CASIC,Beijing 100074,China;School of Energy Science and Engineering,Harbin Institute of Technology,Harbin 150001,China;School of Energy Science and Engineering,Harbin Institute of Technology,Harbin 150001,China

Published:2021-08-15

摘要/Abstract

摘要： 不起动边界是超声速进气道研究的重要内容,它是进气道保护控制的基础和前提。针对这一问题,对冲压发动机进气道进行了不同边界条件下的数值模拟,对稳态流场结果进行了分析。基于仿真数据,利用量纲分析工具对进气道最大抗反压能力进行了分析,讨论并给出了两进气道流动的相似条件。分析结果表明:在不考虑攻角变化的条件下,进气道不起动边界主要与来流马赫数有关。

关键词: 冲压发动机+;进气道;不起动+;边界;保护控制

Abstract: Unstart boundary is one of the most important issues of supersonic inlets,and also the foundation of inlet protection control.To solve this problem,the steady internal flowfield of ramjet inlets at different boundary conditions was simulated and analyzed.Based on the simulation data,the tool of dimensional analysis was introduced to find the variable describing the unstart boundary in this paper.The dimensionless pressure ratios of inlets were analyzed.The flow similar conditions of two hypersonic inlets are discussed.The results show that the unstart boundary of supersonic inlets is mainly concerned with Mach number of freestream without considering the variation of angle of attack.

Key words: Ramjet+;Inlet;Unstart+;Boundary;Protection control

何保成,常军涛,于达仁. 冲压发动机进气道不起动边界分析[J]. 推进技术, 2007, 28(3): 269-272.