Development of Shock Tube for Ground Testing Reentry Aerothermodynamics
Development of Shock Tube for Ground Testing Reentry Aerothermodynamics
复制标题
地面测试再入空气热力学激波管的研制
DOI：
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发表时间：
2011
期刊：
影响因子：
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通讯作者：
K. Fujita
中科院分区：
文献类型：
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作者：
G. Yamada;Toshiyuki Suzuki;H. Takayanagi;K. Fujita
为研究激波后的热化学非平衡现象，研制了一种截面为70×70 mm的自由活塞双隔膜激波管。本文介绍了激波管的性能和新研制的测量系统。对第一隔板的破裂压力、低压管、高压管和压缩管中的初始压力等各种操作参数进行了实验研究，以阐明其特性。在特性实验的基础上，通过改变激波管的工作参数，得到激波管的性能图。结果表明，激波管可以产生与超轨道再入飞行条件相对应的激波后条件。新开发的测量系统使我们能够以高空间和时间分辨率获得冲击波背后的光谱的空间分布。文中给出了测量系统的描述和测量光谱的典型实例。
A free-piston double-diaphragm shock tube with 70×70 mm cross-section at test section is newly developed to investigate thermochemical nonequilibrium phenomena behind a shock wave. This paper presents the performance of the shock tube and the measurement system newly developed. Experimental investigations to clarify its characteristics are conducted for various operational parameters, such as rupture pressure of the first diaphragm and initial pressures in the low-pressure tube, the high-pressure tube, and the compression tube. Based on the characteristics experiment, a performance map of the shock tube is obtained by changing the operation parameters. The result shows that the shock tube can generate the post-shock condition corresponding to super-orbital reentry flight conditions. The newly developed measurement system enables us to obtain a spatial distribution of spectra behind a shock wave with high spatial and time resolution. A description of the measurement system and typical examples of the measured spectra are presented.