IMECH-IR  > 力学所知识产出(1956-2008)
Thesis Advisor俞鸿儒
Degree Grantor中国科学院研究生院
Place of Conferral北京
Keyword激波管 爆轰波 爆轰驱动 混合 Taylor稀疏波 Shock Tube Detonation Wave Detonation Driver Mix Taylor Rarefaction Waves
Other Abstract为满足超高速飞行器进行真实气体效应、再入物理现象和超声速燃烧地面实验研究,要求激波风洞具有极强的驱动性能,爆轰驱动利用氢氧爆轰波后的高温高压气体,作为激波风洞的驱动气源,产生高焓及高贮室压力的试验气流。这一强激波驱动方式受到当前世界各国的重视。本文针对氢氧爆轰驱动激波管的工作机理、驱动性能以及实现这一方式的关键技术,以实验为基础,在BBF100爆轰试验管以及爆轰驱动激波风洞上进行了系统的实验研究。分析了氢氧混合气体立即起爆的机理,确定了效果良好,性能稳定的爆轰驱动点火装置;以气体动力学为基础,研制出配比精确、混合均匀的高压充气、混合装置;这些技术应用于爆轰驱动激波风洞并获得成功。分析了在驱动段上游串接的卸爆段的作用及其特点,给出了较为系统的反向爆轰驱动以及前向爆轰驱动激波管的性能参数。并对两种爆轰模式的性能及特点进行了分析和对比。采用真实气体平衡流的计算方法,给出了爆轰驱动激波风洞的性能参数,以准一维Euler方程解为基础,采用二阶精度的NDD格式,结合化学反应动力学,建立了爆轰驱动激波管流场数值模拟程序,并进行了实验验证。结果表明:前向爆轰驱动通过采用变截面驱动技术,改善了驱动气流品质,增强了驱动能力,在产生高焓试验气流状态时其驱动能力高出反向模式的驱动能力约一个数量级。但当入射激波马赫数较低时,由于Taylor稀疏波的干扰,入射激波衰减较为严重,,波后流场定常时间有限。因此,前向爆轰驱动宜于用来产生高焓试验气流状态。反向爆轰驱动激波衰减较小,波后流场较为恒定,宜于用来产生高P5(高Re数)试验气流状态。在二维Euler方程数值解的基础上,对优化前向爆轰驱动的变截面驱动段结构,提高前向爆轰驱动激波管的性能提出了改进意见。; The shock-tunnel with high driver performance is urgently needed in order to meet the requirement of the ground hypersonic vehicle experimental research on real gas effects, reentry phenomena and supersonic combustion. The detonation driver which uses high temperature and high pressure product of H_2 and O_2 behind detonation wave as driver gas source has attracted world's attraction. The present thesis is mainly focused on the working mechanism, driver performance and the crux technologies of realizing the method of the detonation driver. Based on the theoretical analysis, systematic experiments were conducted on the BBF100 Detonation Test Tube and the Detonation Driver Shock Tunnel. The initiation device which is proved of good performance has been developed by analyzing initiation the mechanism of hydrogen-oxygen detonation. The device for filling and mixing high pressure gas uniformly and accurately was developed based on the gasdynamics theory. The character of the dump tank attached to the end of driver section was analyzed in detail. All above the results were successfully applied in the design of detonation shock tunnel. Both the backward and forward detonation drivers' capability parameters are provided and compared. According to the experiments, the performance parameters are given by means of the real-gas equilibrium-flow method. The numerical code to simulate the flow in the detonation driver is composed based on the nonviscous gasdynamics Euler equations with the NND scheme, where the chemical reaction dynamics is also taken into account. All the numerical results has been verified by experiments. The results indicates that the performance is considerably improved. The driver capability is enhanced by applying the varied cross section in the driver section. The capability of producing high enthalpy test flows is one order of magnitude higher than that of the backward detonation mode. Attenuation of the incidence shock wave caused by the Taylor rarefaction waves is serious when the Mach number is low, and the stabilizing time behind the incidence shock wave is limited. Therefore, the forward detonation driver is suitable for producing the high enthalpy test flow. Although with lower capability than the forward detonation driver, the backward detonation driver's attenuation of the incidence shock wave is smaller. Furthermore, the flow behind the incidence shock wave appears relatively steady. Hence, it is more suitable for producing the condition of high P5 pressure. By means of numerical solution of two-dimension gasdynamic Euler equations, some measures have been proposed to optimize the driver structure with varying section to improve the performance of the forward detonation driver.
Document Type学位论文
Recommended Citation
GB/T 7714
赵伟. 利用氢氧爆轰产生高焓试验气流装置的性能研究[D]. 北京. 中国科学院研究生院,1999.
Files in This Item:
File Name/Size DocType Version Access License
利用氢氧爆轰产生高焓试验气流装置的性能研(17556KB) 开放获取LicenseApplication Full Text
Related Services
Recommend this item
Usage statistics
Export to Endnote
Google Scholar
Similar articles in Google Scholar
[赵伟]'s Articles
Baidu academic
Similar articles in Baidu academic
[赵伟]'s Articles
Bing Scholar
Similar articles in Bing Scholar
[赵伟]'s Articles
Terms of Use
No data!
Social Bookmark/Share

Items in the repository are protected by copyright, with all rights reserved, unless otherwise indicated.