Aerothermodynamic analysis for deformed membrane of inflatable aeroshell in orbital reentry mission
Aerothermodynamic analysis for deformed membrane of inflatable aeroshell in orbital reentry mission
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轨道再入飞行中充气壳体变形膜气动热力学分析
DOI：
10.1016/j.ast.2019.06.047
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发表时间：
2019
影响因子：
5.6
通讯作者：
Yamada Kazuhiko
中科院分区：
文献类型：
--
作者：
Takahashi Yusuke;Koike Taiki;Oshima Nobuyuki;Yamada Kazuhiko
膜式气动减速器是未来空间运输再入、降落和着陆阶段的一项很有前途的关键技术。薄膜气动壳体一般是在飞行气动力作用下发生变形的，但这种变形对气动加热的影响尚不清楚。在这里，我们用流场模拟和结构分析相结合的方法研究了充气再入飞行器泰坦斯在高超声速状态下的气动加热。数值模拟了攻角在0°~40°范围内的热化学非平衡流动。在Aoas为0°和40°时，薄膜气动壳体的最大变形位移分别为直径的6.7%和6.6%。由于前激波形状的显著变化，变形形状和刚性形状之间的热流密度差异非常显著，对于188.8°的角度而言，这是因为前激波形状发生了显著变化。同时，由于在0°的情况下观察到的冲击波形状并没有发生显著的变化，因此在40°时薄膜的变形对充气环面上的峰值热流密度影响不大。研究发现，薄膜气动壳体上的局部皱纹是通过变形而形成的，由于表面局部温度梯度的增加，从而导致热流密度增大。
An inflatable aerodynamic decelerator with a membrane aeroshell is a promising key technology in the reentry, descent, and landing phases of future space transportation. The membrane aeroshell is generally deformed by the in-flight aerodynamic force; however, the effects of the deformation on the aerodynamic heating are unclear. Here, we investigated aerodynamic heating for an inflatable reentry vehicle, Titans, in the hypersonic regime using flow field simulation coupled with structural analysis. Thermochemical nonequilibrium flows around the Titans with a deformed membrane aeroshell were reproduced numerically for an angle of attack (AoA) values between 0° and 40°. The maximum displacements of the membrane aeroshell by deformation at the AoAs of 0° and 40° were 6.7% and 6.6% of the diameter of the Titans, respectively. The difference in heat fluxes between the deformed and rigid shapes was a remarkable 188.8% for a 0° AoA owing to the considerable changes in the front shock wave shape. Meanwhile, it was indicated that membrane deformation at an AoA of 40° insignificantly affected the peak heat flux value on the inflatable torus because the considerable change in the shock wave shape observed for the case of 0° AoA did not occur. It was found that local wrinkles on the membrane aeroshell were formed by deformation, thus causing the heat flux to increase owing to an increase in local temperature gradient on the surface.
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影响因子：
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DOI：
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发表时间：
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期刊：
The Institute of Space and Astronautical Science report. S.P
影响因子：
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作者：
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