| 基于ALE方法的群伞稳降阶段的数值模拟 |
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| 引用本文： | 连 亮,王中阳,张红英,秦福德 李方.基于ALE方法的群伞稳降阶段的数值模拟[J].航天返回与遥感,2014(1):21-28. |
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| 作者姓名： | 连 亮 王中阳 张红英 秦福德 李方 |
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| 作者单位： | [1]南京航空航天大学航空宇航学院,南京210016 [2]空降兵研究所,孝感432100 |
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| 基金项目： | 国家自然科学基金（11002070）;航空科学基金（2010ZC52027） |
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| 摘 要： | 随着计算机技术和数值模拟的兴起，精确描绘降落伞力学特性成为可能。文章采用任意拉格朗日-欧拉法对美国“阿波罗”飞船降落伞回收系统的稳降阶段进行了数值模拟。通过建立结构动力学与计算流体力学的耦合模型，研究了3具环帆伞的流固耦合过程，并模拟了降落伞的外形变化和伞衣内外流场的变化。流固耦合计算结果表明，各伞最终稳定在20＆#176;左右，环帆伞的群伞效率因数约为0.93，比C-9伞大。文章的分析结果对中国探月工程回收系统的主伞设计具有参考意义。
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| 关 键 词： | 降落伞 稳降阶段 流固耦合 任意拉格朗日-欧拉法 航天返回 |
Numerical Simulation of Cluster Parachute System During Steady-state Descent Phase Based on ALE Method |
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| LIAN Liang,WANG Zhongyang,ZHANG Hongying,QIN Fude,LI Fang.Numerical Simulation of Cluster Parachute System During Steady-state Descent Phase Based on ALE Method[J].Spacecraft Recovery & Remote Sensing,2014(1):21-28. |
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| Authors: | LIAN Liang WANG Zhongyang ZHANG Hongying QIN Fude LI Fang |
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| Institution: | 1 College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China ) ( 2 Airborne Institute, Xiaogan 432100, China ) |
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| Abstract: | With the rise of computer technology and numerical simulation, it is possible to describe accu-rately the dynamic chatacteristics of parachute. Based on arbitrary Lagrangian-Eulerian method, the steady-state descent phase of parachute recovery system of Apollo spacecraft is numerically simulated. With the establishment of coupled model of structural dynamics and CFD（Computational Fluid Dynamics）, the fluid-structure interaction study of three ring-sail parachutes was carried out, and the change of canopy shape and flow field is simulated. Results of Fluid-solid coupling calculation show that the parachute is steady around 20＆#176;, with the efficiency factor of cluster parachute system being about 0.93, which is bigger than that of C-9 parachute. This paper provides reference to the design of main parachute recovery system of Chinese Lunar Exploration Program. |
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| Keywords: | parachute steady-state descent phase fluid-structure interation arbitrary Lagran-gian-Eulerian method spacecraft recovery |
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