高超声速飞行器主动气膜冷却热防护数值仿真研究

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 cover protection, this paper proposes a thermal protection scheme with the active film cooling based on micro jet, and an optimization of the distribution of the film holes. By solving the Navier-Stokes equations, the hypersonic stagnation pressure and the surface temperature distribution of the vehicle front are obtained. It is shown that the temperature at the wall of the hypersonic vehicle could be below 1000K under the active thermal protection. This scheme provides a new idea for the future hypersonic vehicle design.