爆轰驱动高能起爆技术实验研究  

Experimental research on high energy initiation technology for detonation driver

作　　者：陆星宇 李进平[1] 陈宏[1,2] 俞鸿儒 LU XingYu;LI JinPing;CHEN Hong;YU HongRu(State Key Laboratory of High Temperature Gas Dynamics, Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190, China;School of Engineering Science, University of Chinese Academy of Sciences, Beijing 100049, China)

机构地区：[1]中国科学院力学研究所高温气体动力学国家重点实验室,北京100190 [2]中国科学院大学工程科学学院,北京100049

出　　处：《中国科学：技术科学》2019年第3期311-319,共9页Scientia Sinica(Technologica)

基　　金：国家自然科学基金项目(编号:11472280);中国科学院"关键技术人才"项目资助

摘　　要：爆轰驱动激波风洞的驱动气体声速较高,擅长模拟高总温、高总压的试验气体.降低驱动气体声速会导致起始爆轰困难,因此在低总温、高总压气体模拟方面能力不足.本研究提出了一种新的高能起爆方法——封闭式点火管,在高浓度氮气稀释的氢氧混气中实现了起始爆轰,成功获得了低声速的驱动气体.通过实验明确了点火管起爆能量的主导因素,给出了封闭式点火管的设计原则.通过实验和计算明确了新方法对激波管/风洞流动过程的影响机理,据此提出了封闭式点火管的使用原则.利用这种新方法获得了低总温、高总压的试验气体,为拓展高超声速飞行条件地面试验能力提供了可行方法.A shock tunnel with gaseous detonation driver is fit for simulating test gas with high total temperature and pressure,since the sound speed of the driving gas is comparatively high.Decreasing the sound speed of the driving gas can lead to initial detonation difficulties and is therefore deficient in low total temperature and high total pressure gas simulations.In this study,a new high-energy detonation initiation method,the closed-type ignition tube,is proposed,in which initial detonation is achieved in high-concentration nitrogendiluted hydrogen-oxygen mixed gas and a low-sound speed driving gas is successfully obtained.By experiment,the dominant factors of igniter tube initiation energy are defined,and the design principles of closed igniter tube are given.Through experiments and calculation,the influence mechanism of the new method on the flow process of shock tubes/tunnels is clarified,and the principle of using the new initiation tube is identified.Using this new method,low total temperature and high total pressure test gas could be obtained,which provides a feasible method for expanding the ground test capability of hypersonic flight conditions.

关 键 词：高超声速 爆轰 起爆 激波风洞 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]