前体激波系重构技术及其在高超声速进气道上的应用

李程鸿; 谭慧俊; 宁乐; 李光胜

doi:10.13224/j.cnki.jasp.2016.09.015

前体激波系重构技术及其在高超声速进气道上的应用

doi: 10.13224/j.cnki.jasp.2016.09.015

1. 南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室, 南京 210016;
2. 先进航空发动机协同创新中心, 北京 100191

基金项目:

国家自然科学基金（91216112，11172133）；新世纪优秀人才支持计划（NCTE-11-0831）；国防基础科研资助；江苏省普通高校研究生科研创新计划资助（CXLX11-0217）；江苏高校优势学科建设工程资助

详细信息

作者简介:
李程鸿(1985-),男,湖北十堰人,博士生,主要从事飞行器进排气系统的设计、仿真与实验研究.

中图分类号: V211.3
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出版历程
- 收稿日期: 2014-12-24
- 刊出日期: 2016-09-28

Reconstructing technique of forebody shock system andits applicationin hypersonic inlet

1. Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
2. Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100191, China

摘要

摘要: 提出了一种激波系整体重构的激波控制技术，并对其流动机理和控制规律进行了仿真分析，继而探索了其在定几何可调进气道上的应用.研究结果表明：该激波控制方法可对前体第1级激波进行有效推动，并可减弱第2级激波强度甚至使其完全蜕化，故实现了对前体激波系的重新构造.随着二次流注入缝的角度增大，将前体激波推动至贴口状态所需消耗的二次流流量逐步减少.并且，最多消耗占主流2.04%的二次流，便可使该进气道在马赫数为5.0~6.0范围内保持贴口状态.与已有各级激波独立控制的可调进气道相比，该进气道在调节状态下的总压恢复较高、消耗的二次流较少，具有明显的优势.
- 高超声速 /
- 可调进气道 /
- 二次流 /
- 激波控制 /
- 流动控制
Abstract: A reconstructing technique for the forebody shock system of hypersonic vehicles was proposed. The flow mechanism and the control law of the technique were investigated numerically. The application of the technique in the variable hypersonic inlet with fixed geometry was also explored. The results showed that the first ramp shock was deflected outward effectively and the second ramp shock was weakened and even eliminated when the controlling activity was employed, indicating the forebody shock system was reconstructed entirely. The required secondary mass flow to drive the first ramp shock to the shock-on-lip condition decreased with the increase of the injection angle. The shock-on-lip condition can be maintained within the operating Mach number range of 5 to 6 at a maximum secondary flow ratio of 2.04%. Furthermore, as compared with the variable inlet using previous fluidic shock control technique, the required secondary mass flow ratio of the newly developed variable hypersonic inlet is less and the total pressure recovery at the exit of the inlet is higher.
- hypersonic /
- variable inlet /
- secondary flow /
- shock control /
- flow control

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参考文献(19)

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