| 高超声速多体干扰与分离试验 |
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| 引用本文： | 王元靖,吴继飞,陶洋,罗新福,钱丰学.高超声速多体干扰与分离试验[J].航空动力学报,2010,25(4):902-906. |
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| 作者姓名： | 王元靖 吴继飞 陶洋 罗新福 钱丰学 |
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| 作者单位： | 1. 中国空气动力研究与发展中心,空气动力学国家重点实验室,绵阳,621000;中国空气动力研究与发展中心,高速空气动力研究所,绵阳,621000
2. 中国空气动力研究与发展中心,高速空气动力研究所,绵阳,621000 |
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| 基金项目： | 空气动力学国家重点实验室基金，863项目，国际科技合作项目 |
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| 摘 要： | 进行了高超声速飞行器多体系统分离过程中存在的气动力干扰试验研究.试验模型是某构型的可重复使用航天飞行器,由助推器以及再入体两部分组成.研究在FL-31风洞中进行,试验马赫数为Ma=6.97.试验结果表明:分离过程中助推器和再入体之间存在复杂的激波干扰现象,多体系统分离过程中的气动干扰本质上是激波干扰引发的.
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| 关 键 词： | 高超声速 飞行器 风洞试验 多体干扰与分离 激波干扰 |
| 收稿时间： | 2009/4/17 0:00:00 |
| 修稿时间： | 2009/6/10 0:00:00 |
Hypersonic experimental investigation on interference and stage separation of a multi-body system |
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| WANG Yuan-jing,WU Ji-fei,TAO Yang,LUO Xin-fu and QIAN Feng-xue.Hypersonic experimental investigation on interference and stage separation of a multi-body system[J].Journal of Aerospace Power,2010,25(4):902-906. |
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| Authors: | WANG Yuan-jing WU Ji-fei TAO Yang LUO Xin-fu and QIAN Feng-xue |
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| Abstract: | Investigation on aerodynamic interference during stage separation of a hypersonic multi-body system is conducted in this paper. A typical reusable space vehicle was applied in this research, which was composed of a booster and a reentry part. The test was conducted in FL-31 wind tunnel, and the Mach number is 6.97. The results show that complicated shock wave interference exists in the multi-body system and this aerodynamic interference during stage separation is essentially induced by thus shock wave interference. |
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| Keywords: | hypersonic vehicle wind tunnel test multi-body interference and stage separation shock wave interference |
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