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A Study on Detonation Driven High Enthalpy Expansion Tube for Hyperbolic Orbital Velocity

爆震驱动高焓膨胀管双曲线轨道速度研究

基本信息

批准号：
12555273
负责人：
ASO Shigeru
金额：
$ 8.51万
依托单位：
KYUSHU UNIVERSITY
依托单位国家：
日本
项目类别：
Grant-in-Aid for Scientific Research (B)
财政年份：
2000
资助国家：
日本
起止时间：
2000 至 2001
项目状态：
已结题

来源：
https://kaken.nii.ac.jp/en/grant/KAKENHI-PROJECT-12555273/
关键词：
Detonation Expansion tube High enthalpy flow Hyper-orbital velocity Hyperbolic orbit Aerodynamic heating Sample return mission Entry problel 超軌道速度

项目摘要

On the atmospheric reentry of spacecraft of sample return mission or planet entry of various probes, extremely severe aerodynamic heating to the spacecraft occur. The incoming Mach number to the spacecraft is more than 20 and temperature behind shock wave is over 10,000 degrees, In this conditions air is dissociated and ionized and chemically and thermally non-equilibrium flows around the spacecraft should be investigated. For the study of such high enthalpy flow experimental facility of the ground testing are necessary.The purpose of the present study is to survey the possibility and conditions of high enthalpy flow test facility and build such a test facility. In the present study a new type of test facility is proposed. The high pressure and high temperature gas, which is produced with detonation, is used as driver gas of shock tube. Next to the shock tube a acceleration tube is attached in order to accelerate the high speed flow to hyper-orbital velocity. Since the proposed test fa … More cility has no flow stagnation condition and hyper-orbital velocity can be realized by flow acceleration, the test facility could produce hyper-velocity flow without dissociation and ionization. In the present studies the following studies have been conducted.1) Characteristics of expansion tube are investigated and carefully designed. The expansion tube succeeded to produce maximum shock Mach number of 34.5 and estimated flow velocity is 9.8 km/s, which is hyper-velocity.2) Characteristics of detonation tube is investigated and carefully designed. The detonation tube with initiation tube is used in order to produce high pressure and high temperature gas. The stoichiometric mixture of hydrogen gas and oxygen gas is used for the testing gas. The detonation tube tube with initiation tube could produce Chapman-Jouget detonation yelocity.3) The combination of the detonation tube with initiation tube and shock tube are produced and tested in order to obtain high shock Mach number. The combination test facility could produce shock Mach number of 7.4 and this shock Mach number is possible to increase the initial pressure of stoichiometric mixture of hydrogen gas and oxygen gas of detonation tube. Less

在样品返回使命航天器再入大气层或各种探测器进入行星大气层时，航天器会受到极其严重的气动加热。飞行器来流马赫数大于20，激波后温度超过10，000度，在这种条件下，空气被离解和电离，需要研究飞行器周围的化学和热非平衡流动。为了研究这种高焓流实验装置的地面试验是必要的，本研究的目的是探讨高焓流实验装置的可能性和条件，并建立这样的实验装置。在本研究中，提出了一种新型的测试设备。利用爆轰产生的高温高压气体作为激波管的驱动气体。在激波管旁边，连接有加速管，以便将高速流加速到超轨道速度。由于拟议的试验法 ...更多信息 cility没有流动停滞条件，超轨道速度可以通过流动加速实现，该试验装置可以产生无离解和电离的超高速流动。本文主要进行了以下几方面的研究：1）对膨胀管的特性进行了研究和设计。膨胀管成功地产生了最大马赫数为34.5的激波，估计的气流速度为9.8km/s，为超高速。2）研究了爆轰管的特性，并进行了设计。为了产生高压高温气体，采用了带起爆管的爆轰管。氢气和氧气的化学计量混合物用于测试气体。为了获得高的激波马赫数，制作了爆轰管、起爆管和激波管的组合，并进行了实验。该组合试验装置可产生马赫数为7.4的激波，该激波马赫数可用于提高爆震管中氢氧混合气的初始压力。少