高超声速飞行器复合热防护系统数值研究及结构参数对声腔的影响

2021 12th International Conference on Mechanical and Aerospace Engineering (ICMAE) Pub Date : 2021-07-16 DOI:10.1109/ICMAE52228.2021.9522459

Xin Sheng, Xi Lu, Jianrun Zhang

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引用次数: 0

摘要

采用半球形钝面模型和数值模拟方法，研究了不同结构参数下对置射流与声腔组合的热防护效果。数值转换和求解器的选择使仿真更加精确。结果表明，激波结构与空腔高度呈负相关。超声速飞行器喷管设计应综合考虑长径比。

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Numerical Study on Combined Thermal Protection System on Hypersonic Vehicle and Structure Parameters Influence of Acoustic Cavity

Hemispherical blunt model and numerical simulation method are used to investigate the thermal protection effects of combinational opposing jet and acoustic cavity concept with various structural parameters. Value conversion and solver selection are operated for more accurate simulation. The results illustrate that the shock wave structure has a negative relation with the height of cavity. Length-to- diameter ratio should be comprehensive considered when designing the nozzle of supersonic vehicles.

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2021 12th International Conference on Mechanical and Aerospace Engineering (ICMAE)

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