基于索膜有限元模型的翼伞气动变形仿真

汪龙芳; 贺卫亮

doi:10.13700/j.bh.1001-5965.2016.0017

基于索膜有限元模型的翼伞气动变形仿真

doi: 10.13700/j.bh.1001-5965.2016.0017

汪龙芳,
贺卫亮^,

北京航空航天大学宇航学院, 北京 100083

详细信息

作者简介:
汪龙芳,男,博士研究生。主要研究方向:飞行器设计

通讯作者:
贺卫亮,男,博士,研究员,博士生导师。主要研究方向:飞行器设计。E-mail:heweiliang@buaa.edu.cn.

中图分类号: V215.3⁺2
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- 被引次数: 0
出版历程
- 收稿日期: 2016-01-05
- 录用日期: 2016-02-29
- 网络出版日期: 2017-01-20

Parafoil aerodynamic deformation simulation based on cable-membrane finite element model

WANG Longfang,
HE Weiliang^,

School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

More Information

Corresponding author: E-mail:heweiliang@buaa.edu.cn

摘要

摘要:
对定常状况下翼伞的流固耦合变形问题进行了三维数值模拟。使用有限体积法计算了飞行时的气动载荷，分析了前缘切口和翼肋开孔对压强分布的影响；基于翼伞结构大位移小应变的特点建立了非线性索膜有限元模型，伞衣由不能承受弯矩的膜单元模拟，伞绳和切口加强带由只能单向拉伸受力的索单元模拟，仿真了受气动载荷后翼伞相对于理想设计位置的变形和应力分布。结果表明：该翼伞展长相对于设计值减小，“鼓包”形成后翼型最大厚度增大，伞衣变形后产生了额外的后掠角和攻角；最大等效应力主要集中在翼肋上的开孔和伞绳连接点处，需合理布置加强带以满足强度要求。
- 翼伞 /
- 气动变形 /
- 几何非线性 /
- 膜单元 /
- 索单元
Abstract:
The fluid-structure coupling deformation of the parafoil was numerically simulated under steady condition. The finite volume method was used to compute the aerodynamic load, and the effect of leading-edge cut and ribs on the pressure distribution was analyzed simultaneously. Nonlinear cable-membrane finite element model was established based on the large displacement-small strain characteristics of parafoil structure. Canopy was modeled by membrane element which was unable to bear bending moment, and ropes and reinforcing tapes were modeled by cable element which could only bear uniaxial tension. The deformation relative to ideal configuration and stress distribution of parafoil were simulated on aerodynamic load. The results show that the span decreases compared with design value in flight, the maximum thickness of airfoil profile increases after bumps appear, and extra angle of attack and sweepback arise from canopy deformation; the maximum equivalent stress is mainly concentrated around holes and rope joints of ribs, and reinforcing tapes must be arranged properly in order to satisfy the strength requirements.
- parafoil /
- aerodynamic deformation /
- geometric nonlinearity /
- membrane element /
- cable element

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图 1 翼伞的理想外形

Figure 1. Ideal configuration of parafoil

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图 2 流体网格弦向剖面

Figure 2. Chordwise cross-section of fluid meshes

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图 3 中部气室弦向剖面的压力分布云图

Figure 3. Pressure distribution contours of chordwise cross-section of middle air chamber

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图 4 边缘气室内腔速度矢量

Figure 4. Interior velocity vector of bilateral air chamber

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图 5 翼伞外表面压力分布云图

Figure 5. Pressure distribution contours of exterior surface of parafoil

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图 6 开口附近的加强带

Figure 6. Reinforcing tape around opening

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图 7 翼伞结构网格示意图

Figure 7. Sketch map of structural meshes of parafoil

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图 8 翼伞位移分布云图

Figure 8. Displacement distribution contour of parafoil

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图 9 翼伞变形正视图

Figure 9. Front view of parafoil deformation

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图 10 飞行中的仿真对象

Figure 10. Simulation object in flight

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图 11 变形后翼伞外表面压力分布云图

Figure 11. Pressure distribution contours of exterior surface of deformed shape of parafoil

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图 12 翼肋的等效应力云图

Figure 12. Equivalent stress contours of ribs

下载: 全尺寸图片幻灯片

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