Computational Study on Radiative Aerothermodynamics of a Reentry Space Vehicle

Qi Li, Sijun Zhang
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Abstract

Under hypersonic flight conditions, a vehicle travelling through the atmosphere could excite the air that flows around the body to very high temperatures as the kinetic energy of the vehicle is dissipated to the gas. Depending on the flight velocity, various chemical reactions will be produced behind a shock wave for stagnation region. These reactions greatly change the properties of air and cause considerable deviation from those of a thermally and calorically perfect gas. A vehicle flying through the higher altitude of the atmosphere at high velocities may also experience thermal non-equilibrium since the lower density reduces the collision frequency and the high velocity results in smaller transit times for the air molecules. Under such extremely thermal circumstances, the heat transfer by convection and radiation around a vehicle has been one of key issues for thermal protection system (TPS). In this paper, the computational aerothermodynamics with fully coupled radiative heat transfer is developed. To validate the proposed approach, it is employed to simulate the thermal and chemical nonequilibrium flows over Stardust. The computed results on the reentry space vehicle reveal both of convective flux and radiative flux are in good agreements with other predicted results.
再入空间飞行器辐射空气热力学计算研究
在高超音速飞行条件下,一架穿越大气层的飞行器可以将环绕在机体周围的空气激发到非常高的温度,因为飞行器的动能被消散到气体中。随着飞行速度的不同,滞止区激波后会产生不同的化学反应。这些反应极大地改变了空气的性质,并与热和热量完美的气体产生了相当大的偏差。在高海拔大气中高速飞行的飞行器也可能经历热不平衡,因为低密度降低了碰撞频率,高速度导致空气分子的过境时间更短。在这种极端热环境下,车辆周围的对流和辐射传热已成为热防护系统的关键问题之一。本文建立了考虑全耦合辐射传热的计算空气热力学。为了验证所提出的方法,采用该方法模拟了星尘上空的热和化学不平衡流动。对再入飞行器的计算结果表明,对流通量和辐射通量与其他预测结果吻合较好。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
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