Fluid-structure interaction characteristics of inflatable reentry aeroshell at subsonic speed
Fluid-structure interaction characteristics of inflatable reentry aeroshell at subsonic speed
复制标题
亚音速充气式再入气壳流固耦合特性
DOI：
10.1016/j.ast.2023.108112
复制
发表时间：
2023
影响因子：
5.6
通讯作者：
Shibata Ryoichi
中科院分区：
文献类型：
--
作者：
Saha Sanjoy Kumar;Tobari Junki;Takahashi Yusuke;Oshima Nobuyuki;Moriyoshi Takahiro;Yamada Kazuhiko;Shibata Ryoichi
由柔性膜和加压充气环组成的充气气囊在进入大气层时会经历巨大的空气动力载荷。气动力使轻质柔性薄膜发生变形，这种变形改变了流场，改变了气动特性，进一步增加了变形。因此，对这些问题的流固耦合建模对于可靠地预测此类再入飞行器的性能是至关重要的。该研究提供了亚音速流固耦合风洞实验结果，重点研究了为验证耦合模拟而设计的气动壳体变形和振荡行为。利用亚音速缩尺薄膜气动壳体模型进行了风洞实验。在自由流马赫数为0.3的情况下，测量了气动系数、模型尾部的压力和结构振动。为了分析流场特性的详细分布，采用分区的方式建立了双向耦合的FSI模型，并用实验数据进行了验证。该模型基于开源流体解算器OpenFOAM、计算结构解算器CalculiX和耦合库PreCICE。目前的FSI分析模型很好地再现了实验中观察到的摇摆运动、膜变形和流场模拟中的尾迹等基本特征。结果表明，车身前后侧压力差较大时，车膜表面受气动力作用发生弹性变形。尾涡的不断产生和脱落导致了流场的非定常行为，进而导致了机壳的小幅度振荡。由于这种振动的频率与固有频率不对应，所以外部气动力引起了振动。
Inflatable aeroshells, made of flexible membranes and pressurized inflatable torus, experience significant aerodynamic loads during atmospheric entry. The aerodynamic forces deform the lightweight, flexible membrane, and such deformation changes the flow field, changing the aerodynamic characteristics and increasing the deformation even further. Thus, fluid-structure coupled modeling of these problems is crucial for the reliable performance prediction of such reentry vehicles. This study provides wind tunnel experimental results on subsonic fluid-structure interaction (FSI), focusing on the aeroshell deformation and oscillatory behavior designed to validate coupled simulations. Wind tunnel experiments were conducted using a scaled membrane aeroshell model for subsonic speed. Aerodynamic coefficients, pressures at the rear of the model, and structural vibrations were measured for freestream Mach number of 0.3. A two-way coupled FSI model was set up in a partitioned manner for analyzing detailed distributions of the flow field properties, which was validated by the experimental data. The model was based on the open-source fluid solver OpenFOAM, computational structural solver CalculiX and coupling library preCICE. The present FSI analysis model well reproduced fundamental features such as swing motion, membrane deformation, and the wake in the flow field simulation, which were observed in the experiment. The results indicated that the membrane surface deforms elastically by aerodynamic force caused by the large pressure difference between the front and rear sides of the vehicle. The continuous generation and shedding of the wake vortex caused unsteady behavior in the flow field, followed by the small amplitude oscillation of the aeroshell. An external aerodynamic force caused the oscillation because the frequency of this oscillation did not correspond to that of natural frequencies.
登录
查看更多内容
海王星的巴鲁特航空捕获轨迹
DOI：
10.2514/6.2004-5181
发表时间：
2004
期刊：
--
影响因子：
--
作者：
D. Lyons;W. Johnson
通讯作者：
W. Johnson
高超音速充气气动减速器（HIAD）任务应用研究
DOI：
10.2514/6.2013-1389
发表时间：
2013
期刊：
--
影响因子：
--
作者：
David M. Bose;R. Winski;J. Shidner;C. Zumwalt;C. Johnston;D. Komar;F. Cheatwood;S. Hughes
通讯作者：
S. Hughes
静态形状变形对高超声速充气气动减速器气动和气动热力学的影响
影响因子：
3.5
作者：
Jinghui Guo;G. Lin;Xueqin Bu;S. Fu;Y. Chao
通讯作者：
Y. Chao
张力锥充气气动减速器的气动和气动弹性特性
DOI：
10.2514/6.2009-2967
发表时间：
2009
期刊：
--
影响因子：
--
作者：
I. Clark;J. Cruz;M. Hughes;J. Ware;Albert Madlangbayan;R. Braun
通讯作者：
R. Braun
地球再入期间充气再入和下降技术停电的飞行后分析
影响因子：
1.6
作者：
P. Reynier;David Evans
通讯作者：
David Evans