摘要
针对运载火箭一级底部喷流热环境的问题,从风洞试验研究和数值仿真分析2方面对国内外研究现状进行论述。试验内容包括4喷管火箭的试验研究、美国SLS运载火箭风洞试验及中国早期开展的脉冲燃烧风洞试验;仿真分析内容包括日本H-ⅡA火箭仿真分析、4喷管火箭仿真分析及模拟真实燃气组分的仿真。归纳得出:喷流试验中外部流场会降低风洞试验的热流结果,使试验环境更加接近真实飞行环境;采用BSL和SST 2种修正的k-ω湍流模型可较为准确地模拟火箭底部热环境;加入化学反应使得对流热流的仿真结果增大。以中国目前的仿真和试验条件,可以先期开展小尺寸、大缩比模型的喷流风洞试验,建立试验能力的同时摸索试验方法和规律,并辅助数值仿真分析手段。
The research status of the thermal environment of the first stage bottom jet in launch vehicle was reviewed from the aspects of wind tunnel test and numerical simulation at home and abroad.The review in the aspect of wind tunnel test included the experimental research of the four nozzles rocket,the wind tunnel test of SLS in the United States,as well as the early impulse combustion wind tunnel test in China.While the review in the aspect of numerical simulation included the research of the Japanese H-ⅡA rocket,the four nozzles rocket and the research of the real gas components.It was concluded that the external flow field in the jet test could reduce the heat flux results in the wind tunnel test and made the test environment closer to the real working environment.The two modified turbulence models of BSL and SST could be used to simulate the thermal environment of rocket base accurately.The simulation results of heat flux increased with the addition of chemical reaction.Based on the current simulation and test conditions at home,wind tunnel test with small size and large shrinkage model was suggested to be carried out in advance to establish the experimental capability.At the same time,the simulation should be used to assist the research.
作者
闫指江
吴彦森
张耘隆
沈丹
唐伟
YAN Zhijiang;WU Yansen;ZHANG Yunlong;SHEN Dan;TANG Wei(Beijing Institute of Astronautical Systems Engineering,Beijing 100076,China)
出处
《载人航天》
CSCD
北大核心
2021年第2期262-268,共7页
Manned Spaceflight
关键词
运载火箭
喷流
热环境
风洞试验
仿真
launch vehicle
jet
thermal environment
wind tunnel test
simulation
