Porosity models and computational methods for compressible-flow aerodynamics of parachutes with geometric porosity
Porosity models and computational methods for compressible-flow aerodynamics of parachutes with geometric porosity
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几何孔隙率降落伞可压缩流空气动力学孔隙率模型及计算方法
DOI：
10.1142/s0218202517500166
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发表时间：
2016
期刊：
影响因子：
--
通讯作者：
and T. Kanai
中科院分区：
文献类型：
--
作者：
K. Takizawa;T.E. Tezduyar;and T. Kanai
航天器降落伞的设计经常包括由数百个缝隙和缝隙形成的几何孔洞，这些缝隙和缝隙是水流通过的。对这些降落伞进行计算流体-结构相互作用(FSI)分析具有极大的挑战性，因此对几何孔隙度的准确建模对于可靠的FSI分析是至关重要的。基于几何孔隙率均匀建模的时空FSI(STFSI)方法在猎户座航天器降落伞不可压流计算分析和设计研究中是可靠的。本文介绍了具有几何孔隙率的降落伞可压缩流动空气动力学的孔隙度模型和ST计算方法。我们使用的ST计算框架的主要组成部分是前面介绍的可压缩流ST SUPG方法和我们在这里介绍的可压缩流ST滑移界面方法。通过对降落伞的计算，验证了孔隙率模型和ST计算方法的有效性。
Spacecraft-parachute designs quite often include “geometric porosity” created by the hundreds of gaps and slits that the flow goes through. Computational fluid–structure interaction (FSI) analysis of these parachutes with resolved geometric porosity would be exceedingly challenging, and therefore accurate modeling of the geometric porosity is essential for reliable FSI analysis. The space–time FSI (STFSI) method with the homogenized modeling of geometric porosity has proven to be reliable in computational analysis and design studies of Orion spacecraft parachutes in the incompressible-flow regime. Here we introduce porosity models and ST computational methods for compressible-flow aerodynamics of parachutes with geometric porosity. The main components of the ST computational framework we use are the compressible-flow ST SUPG method, which was introduced earlier, and the compressible-flow ST Slip Interface method, which we introduce here. The computations we present for a drogue parachute show the effectiveness of the porosity models and ST computational methods.