摘要
为研究高超声速飞行器头部全覆盖保护情况下的气动热分布特征,文章提出一种微孔射流的主动气膜热防护方案,并对射流微孔分布进行优化;通过数值求解N-S方程,得到高超声速飞行器头部的驻点压力及表面、附近温度分布。研究结果表明,在主动气膜冷却热防护下,高超声速飞行器壁面温度可以降到1000 K以下。该方案可为未来高超声速飞行器的外壳设计提供参考。
For studying the thermal distribution on the hypersonic vehicle head in the case of full coverprotection,this paper proposes a thermal protection scheme with the active film cooling based on micro jet,andan optimization of the distribution of the film holes.By solving the Navier-Stokes equations,the hypersonicstagnation pressure and the surface temperature distribution of the vehicle front are obtained.It is shown that thetemperature at the wall of the hypersonic vehicle could be below1000K under the active thermal protection.This scheme provides a new idea for the future hypersonic vehicle design.
作者
郭春海
张文武
向树红
张敏捷
童靖宇
GUO Chunhai;ZHANG Wenwu;XIANG Shuhong;ZHANG Minjie;TONG Jingyu(Ningbo Institute of Materials Technology and Engineering, Chinese Academy of Sciences, Ningbo 315201, China;Science and Technology on Reliability and Environmental Engineering Laboratory,Beijing Institute of Spacecraft Environment Engineering, Beijing 100094, China)
出处
《航天器环境工程》
2017年第2期132-137,共6页
Spacecraft Environment Engineering
基金
可靠性与环境工程技术重点实验室开放基金
宁波市自然科学基金(编号:2015A610102
2015A610105)
