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Studies on Atmospheric Entry Flight of the Winged Space Vehicle

Studies on Atmospheric Entry Flight of the Winged Space Vehicle
有翼航天器进入大气层飞行研究
批准号:
60420022
负责人:
MAEDA Hiroshi
金额:
$20.86万
依托单位:
依托单位国家:
日本
项目类别:
Grant-in-Aid for General Scientific Research (A)
财政年份:
1985
资助国家:
日本
项目状态:
已结题
起止时间:
1985 至 1986

项目摘要

项目成果

MAEDA Hiroshi的其他基金

相关文献

中文摘要
翻译
众所周知,在美国命名为“航天飞机”的有翼空间飞行器已经投入实际使用,它们对空间发展做出了很大贡献。在欧洲,有翼空间飞行器已经被提议被称为HERMES(法国),HOTOL(英国)和HORUS(德国),并且技术问题现在正在调查中。在我国,日本的国家航天实验室和国家空间开发机构也开始了有翼航天器的研究。为了开发这样的交通工具,需要进行基础研究。由于飞行器周围的流场从进入大气层的高超声速状态到低空飞行的亚音速状态变化很大,所要解决的气动问题包括非常复杂的现象。本研究的目的是通过技术、数值计算和风洞试验两种方法来研究作用在飞行器上的气动力和再入气动加热。空间飞行器在进入大气层时遇到的最重要的问题之一是由很强的激波引起的空气动力加热(M bbb25)。在如此强烈的冲击波后面,空气被分解,然后由于高温而电离。针对这一问题,我们通过数值求解包含空气化学效应的激波层方程,成功地计算了车辆表面的热流密度。这些结果将为未来空间飞行器的设计提供有用的数据。在低速风洞中对某带翼飞行器模型进行了气动性能测试,并通过计算技术对其进行了揭示。
英文摘要
It is well known that in USA winged space vehicles named "Space Shuttle" have already brought to practical use and that they have much contributed to the space development. In Europe, winged space vehicles have been proposed which are called HERMES (France), HOTOL (GB) and HORUS (Germany), and the technical problems are now been investigating. Also in our country, the studies of winged space vehicle have started in National Aerospace Laboratory and National Space Development Agency of Japan. In order to develop such vehicles, the fundamental research is needed. Since the flowfield around the vehicle varies from hypersonic conditions at atmospheric entry to subsonic conditions in low altitude flights, the aerodynamic problems to be solved include very complicated phenomena. The aim of the present studies is to revwal aerodynamic force acting on the vehicle and reentry aerodynamic heating by means of both techniques, numerical calculations and wind tunnel testing.One of the most important problems which are encountered by the space vehicles at atmospheric entry is aerodynamic heating caused by very strong shock waves (M > 25). Behind such a strong shock wave, the air is dissociated and then ionized due to high temperature. For this problem, we succeeded in evaluating heat flux on the vehicle surface by numerically solving the shock layer equations including the effect of air chemistry. These results will serve as useful data for design of future space vehicles.Aerodynamic performance of a winged space vehicle model has been tested in a low speed wind tunnel, and also it has been revealed by the computational technique.
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