留言板

尊敬的读者、作者、审稿人, 关于本刊的投稿、审稿、编辑和出版的任何问题, 您可以本页添加留言。我们将尽快给您答复。谢谢您的支持!

姓名
邮箱
手机号码
标题
留言内容
验证码

基于索膜有限元模型的翼伞气动变形仿真

汪龙芳 贺卫亮

汪龙芳, 贺卫亮. 基于索膜有限元模型的翼伞气动变形仿真[J]. 北京航空航天大学学报, 2017, 43(1): 47-52. doi: 10.13700/j.bh.1001-5965.2016.0017
引用本文: 汪龙芳, 贺卫亮. 基于索膜有限元模型的翼伞气动变形仿真[J]. 北京航空航天大学学报, 2017, 43(1): 47-52. doi: 10.13700/j.bh.1001-5965.2016.0017
WANG Longfang, HE Weiliang. Parafoil aerodynamic deformation simulation based on cable-membrane finite element model[J]. Journal of Beijing University of Aeronautics and Astronautics, 2017, 43(1): 47-52. doi: 10.13700/j.bh.1001-5965.2016.0017(in Chinese)
Citation: WANG Longfang, HE Weiliang. Parafoil aerodynamic deformation simulation based on cable-membrane finite element model[J]. Journal of Beijing University of Aeronautics and Astronautics, 2017, 43(1): 47-52. doi: 10.13700/j.bh.1001-5965.2016.0017(in Chinese)

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
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

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

More Information
  • 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。

     

  • 图 1  翼伞的理想外形

    Figure 1.  Ideal configuration of parafoil

    图 2  流体网格弦向剖面

    Figure 2.  Chordwise cross-section of fluid meshes

    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

    图 4  边缘气室内腔速度矢量

    Figure 4.  Interior velocity vector of bilateral air chamber

    图 5  翼伞外表面压力分布云图

    Figure 5.  Pressure distribution contours of exterior surface of parafoil

    图 6  开口附近的加强带

    Figure 6.  Reinforcing tape around opening

    图 7  翼伞结构网格示意图

    Figure 7.  Sketch map of structural meshes of parafoil

    图 8  翼伞位移分布云图

    Figure 8.  Displacement distribution contour of parafoil

    图 9  翼伞变形正视图

    Figure 9.  Front view of parafoil deformation

    图 10  飞行中的仿真对象

    Figure 10.  Simulation object in flight

    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

    图 12  翼肋的等效应力云图

    Figure 12.  Equivalent stress contours of ribs

  • [1] KALRO V,ALIABADI S,GARRARD W,et al.Parallel finite element simulation of large ram-air parachutes[J].International Journal for Numerical Methods in Fluids,1997,24(12):1353-1369. doi: 10.1002/(ISSN)1097-0363
    [2] KALRO V, TEZDUYAR T E.A parallel 3D computational method for fluid-structure interactions in parachute systems[J].Computer Methods in Applied Mechnics and Engineering,2000,190(3-4):321-332. doi: 10.1016/S0045-7825(00)00204-8
    [3] IBOS C,LACROIX C,GOY A,et al.Fluid-structure simulation of a 3D ram air parachute with SINPA software:AIAA-1999-1713[R].Reston:AIAA,1999.
    [4] FOGELL N,SHERWIN S J,COTTER C J,et al. Fluid-structure interaction simulation of the inflated shape of ram-air parachutes[C]//Aerodynamic Decelerator Systems Technology Conference. Reston:AIAA,2013:1-15.
    [5] ALTMANN H. Fluid-structure interaction analysis of ram-air parafoil wings[C]//Aerodynamic Decelerator Systems Technology Conference. Reston:AIAA,2015:1-10.
    [6] 朱旭,曹义华. 翼伞平面形状对翼伞气动性能的影响[J].航空学报,2011,32(11):1998-2007. http://www.cnki.com.cn/Article/CJFDTOTAL-HKXB201111006.htm

    ZHU X,CAO Y H.Numerical simulation of platform geometry effect on parafoil aerodynamic performance[J]. Acta Aeronautica et Astronautica Sinica,2011,32(11):1998-2007(in Chinese). http://www.cnki.com.cn/Article/CJFDTOTAL-HKXB201111006.htm
    [7] 朱旭,曹义华.翼伞弧面下反角、翼型和前缘切口对翼伞气动性能的影响[J].航空学报,2012,33(7):1189-1200. http://www.cnki.com.cn/Article/CJFDTOTAL-HKXB201207005.htm

    ZHU X,CAO Y H. Effects of arc-anhedral angle,airfoil and leading edge cut on parafoil aerodynamic performance[J].Acta Aeronautica et Astronautica Sinica,2012,33(7):1189-1200(in Chinese). http://www.cnki.com.cn/Article/CJFDTOTAL-HKXB201207005.htm
    [8] 陆伟伟,张红英,连亮.大型翼伞的三维气动性能分析[J].航天返回与遥感,2015,36(3):1-10. http://www.cnki.com.cn/Article/CJFDTOTAL-HFYG201503002.htm

    LU W W,ZHANG H Y,LIAN L. A three-dimensional analysis on aerodynamic performance of a large parafoil[J].Spacecraft Recovery & Remote Sensing,2015,36(3):1-10(in Chinese). http://www.cnki.com.cn/Article/CJFDTOTAL-HFYG201503002.htm
    [9] 张春,曹义华.基于弱耦合的翼伞气动变形数值模拟[J].北京航空航天大学学报,2013,39(5):605-609. http://bhxb.buaa.edu.cn/CN/abstract/abstract12611.shtml

    ZHANG C,CAO Y H.Numerical simulation of parafoil aerodynamics and structural deformation based on loose coupled method[J].Journal of Beijing University of Aeronautics and Astronautics,2013,39(5):605-609(in Chinese). http://bhxb.buaa.edu.cn/CN/abstract/abstract12611.shtml
    [10] BALAJI R,MITTAL S,RAI A K. Effect of leading edge cut on the aerodynamics of ram-air parachutes[J].International Journal for Numerical Methods in Fluids,2005,47(1):1-17. doi: 10.1002/(ISSN)1097-0363
    [11] MOHAMMADI M A,JOHARI H. Computation of flow over a high-performance parafoil canopy[J].Journal of Aircraft,2010,47(4):1338-1345. doi: 10.2514/1.47363
    [12] 毛国栋.膜索结构设计方法研究[D].杭州:浙江大学,2004:29-30.

    MAO G D.The design investigation of cable-reinforced membrane structures[D].Hangzhou:Zhejiang University,2004:29-30(in Chinese).
    [13] 王勖成.有限单元法[M].北京:清华大学出版社,2003:629-631.

    WANG X C.Finite element method[M].Beijing:Tsinghua University Press,2003:629-631(in Chinese).
    [14] 唐建民,卓家寿.悬索结构大位移分析改进的两节点索单元[J].河海大学大学学报(自然科学版),1999,27(4):16-19. http://www.cnki.com.cn/Article/CJFDTOTAL-HHDX199904003.htm

    TANG J M,ZHUO J S.An improved two-node cable element for large deformation analysis of cable structures[J].Journal of Hohai University(Natural Sciences),1999,27(4):16-19(in Chinese). http://www.cnki.com.cn/Article/CJFDTOTAL-HHDX199904003.htm
    [15] 贾贺,荣伟,陈国良.基于LS-DYNA的降落伞伞衣织物透气性参数仿真验证[J].航天返回与遥感,2009,30(1):15-20. http://www.cnki.com.cn/Article/CJFDTOTAL-HFYG200901004.htm

    JIA H,RONG W,CHEN G L.The use of LS-DYNA to simulate the permeability parameters of the parachute canopy[J].Spacecraft Recovery & Remote Sensing,2009,30(1):15-20(in Chinese). http://www.cnki.com.cn/Article/CJFDTOTAL-HFYG200901004.htm
  • 加载中
图(12)
计量
  • 文章访问数:  627
  • HTML全文浏览量:  2
  • PDF下载量:  605
  • 被引次数: 0
出版历程
  • 收稿日期:  2016-01-05
  • 录用日期:  2016-02-29
  • 刊出日期:  2017-01-20

目录

    /

    返回文章
    返回
    常见问答