高超声速导弹弹头对流冷却仿真研究
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摘要
针对高超声速导弹头部剧烈的气动热问题,采用内部铺设管道用气体直接吹拂球头的对流式主动冷却方案,对球头进行降温,并用流固流多场耦合的方法进行数值模拟计算,得到不同冷却气体、不同温度、不同流速下导弹内部温度场分布。结果证明设计方案能有效降低材料表面温度,降低传入导弹内部热流。比较气体性质,提供了可供参考的性能较好的气体。可以为以后高超声速导弹主动式热防护设计方案提供经验和借鉴。
For the severe aerodynamic heating problems of hypersonic missile warhead,laying pipes full of flowing gas were used to blow the warhead by actively convectional cooling way to reduce the severe temperature. Different temperature field distribution of different gas,different temperature of gas and different velocity of gas were obtained by numerical simulation of fluid-solid-fluid multi field couping method. The results show that the design scheme can effectively reduce the surface temperature of the material and the incoming heat flow of the missile interior. By contrast,a better reference gas is provided. These studies may provide experience and reference for future hypersonic missile active thermal protection system design.
For the severe aerodynamic heating problems of hypersonic missile warhead,laying pipes full of flowing gas were used to blow the warhead by actively convectional cooling way to reduce the severe temperature. Different temperature field distribution of different gas,different temperature of gas and different velocity of gas were obtained by numerical simulation of fluid-solid-fluid multi field couping method. The results show that the design scheme can effectively reduce the surface temperature of the material and the incoming heat flow of the missile interior. By contrast,a better reference gas is provided. These studies may provide experience and reference for future hypersonic missile active thermal protection system design.
引文
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[5] 蔡国飙,徐大军.高超声速飞行器技术[M].北京:科学出版社,2012.
[6] 王晓兵,李菁,廖忠全,王维保.基于FLUENT的弹丸外流场数值仿真[J].计算机辅助工程,2010,19(1):92-94.