| 某运载火箭级间分离喷流干扰风洞试验研究 |
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| 引用本文： | 王志坚,;伍贻兆,;林敬周.某运载火箭级间分离喷流干扰风洞试验研究[J].气动实验与测量控制,2009(2):15-19. |
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| 作者姓名： | 王志坚 ;伍贻兆 ;林敬周 |
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| 作者单位： | [1]南京航空航天大学航空宇航学院,江苏南京210016; [2]中国空气动力研究与发展中心,四川绵阳621000 |
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| 摘 要： | 对某运载火箭级间分离特性进行了风洞试验研究，内流采用冷喷流模拟技术，获得了助推器与芯级同时分离和助推器先分离时，两级在有、无喷流、同轴变迎角情况下的气动力系数，试验结果表明，助推器与芯级同时分离和助推器先分离两种情况下，一、二级箭体各自的气动力系数变化很小，这说明助推器与芯级同时分离的方案是可行的。风洞试验研究结果为运载火箭级间分离方案设计和火箭控制系统参数设计提供了依据。
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| 关 键 词： | 运载火箭 高超声速 风洞试验 级间分离 喷流干扰 |
Wind tunnel test on effect of the jet flow interaction on stage separation of launch vehicle |
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| Institution: | WANG Zhi-jian, WU Yi-zhao, LIN Jing-zhou ( 1. College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;2. China Aerodynamics Research ＆ Development Center, Mianyang Sichuan 621000, China) |
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| Abstract: | This paper presents the wind tunnel test on aerodynamics of launch vehicle during stage separation. The method of cold jet is used to simulate internal flow. Satisfying test results and many flow filed configuration photographs have been obtained. The experimental data indicate that the aerodynamic difference between two cases of the first stage separation with or without booster is little, so the first stage and booster separation at same time is feasible. The tests results could be taken as a reference in the designing of launch vehicle. |
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| Keywords: | launch vehicle hypersonic wind tunnel test stage separation jet flow interaction |
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