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Study of real gas effects by using a Mach 20 hypersonic shock tube

使用20马赫高超音速激波管研究真实气体效应

基本信息

批准号：
10044119
负责人：
TAKAYAMA Kazuyoshi
金额：
$ 2.75万
依托单位：
TOHOKU UNIVERSITY
依托单位国家：
日本
项目类别：
Grant-in-Aid for Scientific Research (B).
财政年份：
1998
资助国家：
日本
起止时间：
1998 至 1999
项目状态：
已结题

来源：
https://kaken.nii.ac.jp/grant/KAKENHI-PROJECT-10044119/
关键词：
Shock tube Holographic interferometry Detonation Real gas effect quickly opening valve Fourier fringe analysis Hypersonic flow フーリエ稿解析ホログラフィー法

项目摘要

In simulating experimentally atmospheric re-entry of space vehicles, shock wave technology is best used to create high temperature conditions which are otherwise impossible to generate by any together methods. The high temperature so far appearing during the atmospheric re-entry exceed 10,000 K so that air molecules will dissociate and then ionized. This process is name real gas effect. The present study aims to experimentally verify the hypersonic real gas effect by using a 100 mm x 180 mm hypervelocity shock tube that has been transported from the Institute of Aerospace Studies, University of Toronto in 1994. The present study is to refurbish this shock tube by adopting a detonation driver system in which the reflection of detonation waves in stoichiometric oxyhydrogm mixture is used and to quantitatively visualize hypersonic shock waves using double exposure holography interferometry.The result obtained are summarized as following :(1) A diaphragmless operation system has been adopted successfully in this shock tube. Its characteristics have been throughly investigated. Its higher degree of repeatability that has not been achieved among existing shock tubes has been confirmed.(2) To ensure the initiation of detonations in the high pressure chamber, the transition from deflagration driven shock waves to detonation waves has been visualized using double exposure holographic interferometry. The effect of small particles shattering from the surface of micro-charges which initiate the chemical reaction.(3) Finite fringe holographic interferometry has been applied to the experiments in (2). Finite fringe interferograms were quantitatively analyzed by using Fourier fringe analysis. Its measuring system has been established.(4) Results obtained during two years of research works have been presented at international symposia. International collaboration with the Institute of Aerospace Studies, University of Toronto has been conducted.

在模拟航天器重返大气层的实验中，最好使用冲击波技术来创造高温条件，否则任何其他方法都不可能产生这种高温条件。目前在重返大气层期间出现的高温超过10，000 K，因此空气分子将解离然后电离。这个过程就是所谓的真实的气体效应。本研究的目的是通过使用1994年从多伦多大学航空航天研究所运来的100 mm x 180 mm超高速激波管来实验验证高超音速真实的气体效应。本文采用爆轰波在化学计量比的氢氧混合物中反射的爆轰驱动系统对该激波管进行了二次曝光，并利用二次曝光全息干涉术对高超声速激波进行了定量显示，取得了如下结果：（1）该激波管成功地采用了无干涉操作系统。对其特性进行了深入研究。它的高度重复性，还没有达到现有的激波管已被证实。(2)为了确保高压室中引爆，使用双曝光全息干涉术可视化了从爆燃驱动冲击波到爆轰波的转变。微电荷表面的小粒子碎裂而引发化学反应的效应。(3)有限条纹全息干涉术已应用于（2）中的实验。用傅里叶条纹分析法对有限条纹干涉图进行了定量分析。建立了其测量系统。(4)在国际研讨会上介绍了两年研究工作期间取得的成果。与多伦多大学航空航天研究所开展了国际合作。