最小二乘无网格方法及其在近空间解体碎片绕流场模拟应用  

Least-square Gridless Method and Its Application in the Debris Flowfield Simulation during Spacecraft Disintegration

作　　者：罗万清 梁剑寒[1] 李海燕[2] 李志辉[2,3] LUO Wanqing;LIANG Jianhan;LI Haiyan;LI Zhihui(Science and Technology on Scramjet Laboratory,National University of Defense Technology,Changsha 410073,China;Hypervelocity Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China;National Laboratory for Computational Fluid Dynamics,Beijing 100191,China)

机构地区：[1]国防科技大学高超声速冲压发动机技术重点实验室,长沙410073 [2]中国空气动力研究与发展中心超高速空气动力研究所,绵阳621000 [3]国家计算流体力学实验室,北京100191

出　　处：《载人航天》2020年第5期557-565,共9页Manned Spaceflight

基　　金：国家重点基础研究发展计划(2014CB744100),国家自然科学基金项目(11325212,91530319)。

摘　　要：针对航天器再入解体碎片绕流问题,通过分析无网格方法计算原理,推导了基于泰勒级数展开确定点云结构上的空间离散与适用于最小二乘无网格方法的无粘通量求解格式,采用三阶Strong Stability Preserving型Runge-Kutta时间推进与特征基础边界条件数值处理,研究建立了求解二维无粘气体流动的无网格数值方法。通过对典型算例和碎片简化模型等问题进行计算分析,表明设计的无网格方法通量格式能够很好地捕捉Euler方程描述的流场特征,具有较强的收敛适应性与鲁棒性。研究表明建立的最小二乘无网格数值方法具备推广应用到航天器解体碎片绕流模拟的潜在能力。Aiming at the flow around debris while spacecraft reentering the atmosphere,the principle of gridless method was analyzed,the spatial discretization of the point cloud based on the Taylor series expansion,and the inviscid flux scheme suitable for the least-squares gridless method were derived.The three order Strong Stability Preserving(SSP)type Runge-Kutta iterative method and characteristic basis boundary conditions were adopted and a gridless numerical method for solving two-dimensional inviscid gas flow was established.The typical examples and simplified debris model were calculated and analyzed.The results demonstrated that the devised flux scheme of the gridless numerical simulation method could well capture the flow characteristics described by Euler equations,and revealed strong convergence and robustness.The results showed that the least-square gridless method had the potential to be extended to simulate the flow around spacecraft debris.

关 键 词：航天器解体 碎片绕流 无网格方法 最小二乘法 

分 类 号：V411.4[航空宇航科学与技术—航空宇航推进理论与工程]