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Aeroshape design of reusable re-entry vehicles by multidisciplinary optimization and computational fluid dynamics

机译：通过多学科优化和计算流体动力学的可重复使用重新进入车辆的Aeroshape设计

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This paper deals with the development of a multidisciplinary design framework for reusable space vehicles, able to provide a round-trip crew transport capability to low Earth orbit, and especially for the support and supply services of the International Space Station. Design activities rely on a shape optimization procedure adopted as a priori knowledge to find concept aeroshapes able to satisfy specific mission objectives and requirements. Optimization results are obtained with a floating point version of a Multi-Objective Genetic Algorithm. A detailed engineering-based aerodynamic analysis of a promising design candidate is provided throughout descent flight regimes considering the range of Mach numbers from 25 to 0.3. Aerodynamic computations in high speed range of re-entry corridor are performed with an hypersonic panel code which relies on Surface Impact Methods. Additionally, a subsonic panel code based on potential flow theory is adopted to evaluate low speed coefficients. Trade-off candidate eligible for a phase-A design is then validated creating a CFD test matrix in a set of forty specified way-points along with the re-entry trajectory. Finally, preliminary considerations about viability of the configuration are given with reference to longitudinal stability margin. (C) 2020 Elsevier Masson SAS. All rights reserved.
机译：本文涉及为可重复使用的空间车辆开发多学科设计框架，能够为低地球轨道提供往返机组传输能力，特别是对于国际空间站的支持和供应服务。设计活动依赖于作为先验知识所采用的形状优化程序，以查找能够满足特定的任务目标和要求的概念稳定性。用多目标遗传算法的浮点版本获得优化结果。考虑到25到0.3的马赫数范围，提供了一个有前途设计候选人的详细的基于工程的空气动力学分析。利用超声波面板代码执行高速进入走廊的高速范围内的空气动力学计算，依赖于表面影响方法。另外，采用基于电位流理论的亚音图面板代码来评估低速系数。然后验证了符合阶段设计的权衡候选者，并以一组40个指定的方式与重新输入轨迹一起验证了创建CFD测试矩阵。最后，参考纵向稳定性裕度给出关于配置的存活率的初步考虑因素。 （c）2020 Elsevier Masson SAS。版权所有。

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