自由活塞高焓脉冲风洞发展历程及试验能力综述  

Review on the development of the free-piston high enthalpy impulse wind tunnel and its testing capacities

作　　者：陈星[1] 谌君谋 毕志献[1] 马汉东[1] Chen Xing;Shen Junmou;Bi Zhixian;Ma Handong(China Academy of Aerospace Aerodynamics,Beijing100074,China)

机构地区：[1]中国航天空气动力技术研究院

出　　处：《实验流体力学》2019年第4期65-80,共16页Journal of Experiments in Fluid Mechanics

基　　金：国家自然科学基金项目(11872349)

摘　　要：自由活塞高焓脉冲风洞是研究高温气体效应主要的地面模拟设备之一,具备模拟超高速流动的能力,主要分为自由活塞驱动的高焓激波风洞和高焓膨胀管风洞。经过数十年的发展,自由活塞高焓脉冲风洞不仅能够用于研究飞行器在超高速自由来流条件下的复杂气动热力学和气动光学等问题,还能开展自由飞、超燃冲压发动机和电磁辐射等技术的研究。综述其发展历程,重点介绍理论基础研究阶段、早期探索阶段和实用化发展阶段等3个阶段的研究历程和主要结论,以期为大型自由活塞高焓脉冲风洞及其试验能力的发展和应用提供借鉴和参考。The free-piston high enthalpy impulse wind tunnel is one of the main ground testing facilities for the study of the high enthalpy flow, which is able to simulate the hypervelocity flow and is mainly categorized into two types as the high enthalpy shock wind tunnel and the high enthalpy expansion tube wind tunnel. After decades of development, the free-piston high enthalpy impulse wind tunnel can be used not only to study the complex aerodynamics thermodynamics and aero-optic of the aircraft under the hypervelocity free flow, but also to carry out research on technologies such as the free flight, the scramjet and the electromagnetic radiation measurement. The development process is summarized, focusing on the three stages of the basic theoretical research stage, the early construction stage and the practical development stage, in order to provide reference for the development of the large-scale free-piston high enthalpy impulse wind tunnel and its testing capacities.

关 键 词：自由活塞 高焓脉冲风洞 试验能力 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]