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A NEW PHILOSOPHY FOR THE DESIGN OF REENTRY VEHICLES

机译：再入车辆设计的新哲学

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The paper wants to report on a prefeasibility analysis of a new reentry philosophy for manned missions based on a longer and a more gradual conversion of the kineti and potential energy of the vehicle into thermal energy, addressing all the questions that must be necessarily answered before a real implementation of the concept can be made. The vehicle (schematized by a point mass) enters the Earth's atmosphere at very small entry angles, is characterized by a high reference surface to mass ratio (S_r/m) and adopts sharp leading edges made of ultra-high-temperature ceramics. The reentry trajectories are characterized by high convective heat fluxes localized at the front tip edges (fuselage and wings) allowing a thermal boundary layer protection of the remaining structure. During the reentry, the radiative equilibrium wall temperature at the stagnation point is maintained below the maximum temperature tolerable by the material of the leading edgesose. The analysis identifies the values of S_r/m, the aerodynamic efficiency (L/D), the entry angle (θ_e), and the vehicle piloting capabilities necessary to achieve low-risk reentry trajectories for a crew return vehicle from LEO (e.g., from the International Space Station).
机译：本文希望对载人飞行任务的一种新的再入哲学进行可行性分析报告，该理论基于将车辆的动能和势能转换为热能的时间更长，更渐进，从而解决了必须解决的所有问题。可以真正实现该概念。车辆（以点质量表示）以很小的进入角进入地球大气层，其特征在于较高的参考表面质量比（S_r / m），并采用由超高温陶瓷制成的锋利的前缘。再入轨迹的特征是位于前尖端边缘（机身和机翼）的高对流热通量允许对其余结构进行热边界层保护。在折返过程中，停滞点的辐射平衡壁温度保持在前缘/鼻孔材料所能承受的最高温度以下。该分析确定了S_r / m的值，空气动力学效率（L / D），进入角（θ_e）以及为从LEO（例如，来自LEO）返回机组的低风险再入轨所必需的车辆驾驶能力国际空间站）。

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