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Phase-A design of a reusable re-entry vehicle
Acta Astronautica ( IF 3.5 ) Pub Date : 2021-06-29 , DOI: 10.1016/j.actaastro.2021.06.034
Andrea Aprovitola , Luigi Iuspa , Giuseppe Pezzella , Antonio Viviani

In this paper, a design procedure developed to obtain a Phase-A compliant optimal aeroshape is presented. The proposed vehicle performs a low Earth orbit re-entry and a landing on a horizontal runway. A conceptual aeroshape design obtained by a multi-disciplinary, multi-objective optimization is modified by the addition of two functionally independent body flaps to the concept windside to envisage the aeroshape control along both the longitudinal and later-directional axes. Body flaps are also added on the rearward sections of the spacecraft leeside. Aerodynamic analyses are carried out throughout the speed regimes expected during re-entry, to address the feasibility of the vehicle design. Furthermore, CFD computation are specifically performed at very low Mach numbers to address body flaps effects on spacecraft aerodynamics at landing conditions. Flowfield results are also provided, with a particular focus on the vortex lift phenomenon generated by the delta planform shape of the vehicle configuration. Specifically, the flow pattern at landing angle of attack is highlighted to account for safety landing conditions. Finally, a single objective optimization is performed to find the best guidance law allowing a safer re-entry compatible with the assigned operational constraints. In doing this, two kinds of re-entry strategies are compared, namely Shuttle-like and heat-flux tracking profiles.



中文翻译:

可重复使用的再入飞行器的A阶段设计

在本文中,提出了为获得符合 A 阶段的最佳外形而开发的设计程序。提议的飞行器执行低地球轨道再入和在水平跑道上着陆。通过多学科、多目标优化获得的概念飞机外形设计通过在概念风侧添加两个功能独立的机身襟翼进行修改,以设想沿纵向和后向轴的飞机外形控制。在航天器背风侧的后部也增加了身体襟翼。空气动力学分析在再入期间预期的整个速度范围内进行,以解决飞行器设计的可行性。此外,CFD 计算专门在非常低的马赫数下执行,以解决着陆条件下机身襟翼对航天器空气动力学的影响。还提供了流场结果,特别关注由车辆配置的三角形平面形状产生的涡流升力现象。具体而言,突出显示着陆迎角的流动模式以考虑安全着陆条件。最后,执行单一目标优化以找到最佳制导法则,允许与指定的操作约束兼容的更安全的再入。为此,比较了两种再入策略,即类航天飞机和热流跟踪剖面。执行单一目标优化以找到最佳制导法则,允许与指定的操作约束兼容的更安全的再入。为此,比较了两种再入策略,即类航天飞机和热流跟踪剖面。执行单一目标优化以找到最佳制导法则,允许与指定的操作约束兼容的更安全的再入。为此,比较了两种再入策略,即类航天飞机和热流跟踪剖面。

更新日期:2021-07-02
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