Fluid-structure interaction study of the supersonic parachute using large-eddy simulation
Fluid-structure interaction study of the supersonic parachute using large-eddy simulation
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DOI：
10.1108/ec-06-2016-0195
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发表时间：
2018-03
影响因子：
1.6
通讯作者：
Xue Yang;Li Yu;Xiao-Shun Zhao
中科院分区：
文献类型：
--
作者：
Xue Yang;Li Yu;Xiao-Shun Zhao
目的建立超声速盘带式开伞的动力学模型。设计/方法/途径采用贴体网格的流固耦合方法对超声速降落伞进行数值模拟。采用大涡模拟（LES）模拟可压缩流。针对贴体网格的负体积问题，提出了一种基于罚函数的虚拟接触域接触算法。采用非结构网格自动生成和网格自动移动技术来处理复杂的座舱变形。结果打开的盘间隙带降落伞模拟使用马赫数2.0，模拟结果与风洞试验数据吻合良好。结果表明，大涡模拟能够成功地预测大尺度湍流旋涡。本研究也证明了本FSI方法作为一种工具来预测冠层的冲击振荡和呼吸现象的能力。独创性/价值-基于惩罚函数与虚拟接触域的接触算法提出了第一次。该方法可用于解决流场中动网格的负体积问题。
Purpose The purpose of this study is to model the dynamic characteristics of an opened supersonic disk-gap-band parachute. Design/methodology/approach A fluid-structure interaction (FSI) method with body-fitted mesh is used to simulate the supersonic parachute. The compressible flow is modeled using large-eddy simulation (LES). A contact algorithm based on the penalty function with a virtual contact domain is proposed to solve the negative volume problem of the body-fitted mesh. Automatic unstructured mesh generation and automatic mesh moving schemes are used to handle complex deformations of the canopy. Findings The opened disk-gap-band parachute is simulated using Mach 2.0, and the simulation results fit well with the wind tunnel test data. It is found that the LES model can successfully predict large-scale turbulent vortex in the flow. This study also demonstrates the capability of the present FSI method as a tool to predict shock oscillation and breathing phenomenon of the canopy. Originality/value The contact algorithm based on the penalty function with a virtual contact domain is proposed for the first time. This methodology can be used to solve the negative volume problem of the dynamic mesh in the flow field.