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首页> 外文期刊>International Journal of Aerodynamics >Earth re-entry capsule CFD simulations taking into account surface roughness and mass injection at the wall
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Earth re-entry capsule CFD simulations taking into account surface roughness and mass injection at the wall

机译：土再入舱CFD模拟考虑了表面粗糙度和壁上的质量注入

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摘要

Future space exploration missions will likely use capsule type ballistic re-entry vehicles that will re-enter the earth atmosphere at very high speed (velocities in the order of 11.7 km/s or higher, this compared to 7.5 km/s for the US Space Shuttle). Passive concepts will be employed for the deceleration, and the thermal protection system (TPS) needs to be dimensioned to protect the vehicle and samples from the effects of the aerodynamic heating. The technology readiness level of these passive concepts is today still rather low, leading to large design margins. This paper is concerned with the design of a possible earth re-entry capsule, it discusses the re-entry trajectory and heat loads encountered during descent. Detailed CFD simulations were made for three selected points on the re-entry trajectory. The ablation of the TPS material was taken into account through a mass injection boundary condition. The turbulence models employed in the study were modified to account for surface roughness due to ablation. Calculated heat fluxes and shear stresses for a smooth wall are compared with results from empirical correlations and showed a fairly good agreement. For rough walls, the CFD results show a substantial increase in convective heat flux, while the injection of mass at the wall reduces the convective heat flux.
机译：未来的太空探索任务可能会使用胶囊型弹道再入飞行器，该飞行器将以很高的速度重新进入地球大气层（速度约为11.7 km / s或更高，而美国航天飞机的速度为7.5 km / s穿梭）。被动概念将用于减速，并且热保护系统（TPS）的尺寸需要确定，以保护车辆和样品免受空气动力加热的影响。如今，这些被动概念的技术准备水平仍然很低，导致了很大的设计余量。本文涉及可能的地球再入舱的设计，讨论了下降过程中遇到的再入轨迹和热负荷。针对重入轨迹上的三个选定点进行了详细的CFD仿真。通过质量注入边界条件考虑了TPS材料的烧蚀。修改了研究中使用的湍流模型，以解决由于烧蚀造成的表面粗糙度。计算出的光滑壁的热通量和切应力与经验相关性的结果进行了比较，并显示出相当好的一致性。对于粗糙的墙壁，CFD结果显示对流热通量显着增加，而在壁上注入质量会降低对流热通量。

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