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零泊松比蜂窝芯等效弹性模量研究 被引量:7

Equivalent Elastic Modulus of Zero Poisson's Ratio Honeycomb Core
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摘要 采用柔性悬臂梁模型和欧拉梁模型分别对零泊松比蜂窝芯斜壁板大变形条件下的弯曲变形和蜂窝芯横壁板小变形条件下的变形进行分析,推导出了零泊松比蜂窝芯面内等效弹性模量理论计算公式,并将理论计算结果和有限元仿真及力学模型实验进行对比分析。结果表明:理论计算公式正确、有效;零泊松比蜂窝芯大变形方向等效弹性模量具有明显的非线性特征;等效弹性模量的计算应根据受力方向及应变大小选择相应的计算公式进行计算;壁板之间的夹角θ对等效弹性模量的影响很大,零泊松比蜂窝结构参数可设计性较强。 A flexible cantilever beam model and Euler beam model were used to analyze zero Poisson's ratio honeycomb core compression deformation under the conditions of large deformation oblique wall bending deformation and horizontal siding small deformation respectively. The plane elastic modulus calculation formula of the zero Poisson's ratio honeycomb core were derived. Moreover, the results of theoretical calculations, finite element simulation and mechanical model experiments were also com- pared and analyzed. The results show that: theoretical formula are correct and effective; elastic modu- lus of zero Poisson's ratio honeycomb core in the direction of large deformation presents obvious non- linear characteristics; equivalent elastic modulus calculations are based both on the size of the strain and the direction of the force; the angle ~? of the walls has strong influence on the calculation of equivalent elastic modulus. Therefore zero Poisson's ratio honeycomb structure parameters can be de- signed appropriately.
出处 《材料工程》 EI CAS CSCD 北大核心 2013年第12期80-84,共5页 Journal of Materials Engineering
基金 国家自然科学基金资助项目(51075380) 国家自然科学基金重大研究计划重点项目资助(90816026)
关键词 柔性蒙皮 蜂窝芯 零泊松比 等效弹性模量 flexible skin honeycomb core zero Poisson' s ratio equivalent elastic modulus
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参考文献16

  • 1JHA A K,KUDVA J N.Morphing aircraft concepts,classifications,and challenges[A].ANDERSON E H.Smart Structures and Materials 2004:Industrial and Commercial Applications of Smart Structures Technologies[C].San Diego,CA:SPIE,2004.213-224.
  • 2崔尔杰,白鹏,杨基明.智能变形飞行器的发展道路[J].航空制造技术,2007,50(8):38-41. 被引量:48
  • 3KUDVA J N.Overview of the DARPA smart wing project[J].Journal of Intelligent Material Systems and Structures,2004,15(4):261-267.
  • 4THILLC,ETCHES J,BOND I,et al.Morphing skins[J].The Aeronautical Journal,2008,112(1129):117-139.
  • 5MEHTA V,FRECKER M,LESIEUTRE G.Contact-aided compliant mechanisms for morphing aircraft skin[A].LINDNER D K.Modeling,Signal Processing,and Control for Smart Structures 2008[C].San Diego,CA:SPIE,2008.9260-9268.
  • 6PROEK BRIAN C,WEISSHAAR TERRENCE A,CROSSLEY WILLIAM A.Morphing airfoil shape change optimization with minimum actuator energy fits as an objective[A].9th AIAA/ISS MO Symposium on Multidisciplinary Analysis and Optimization 2002[C].Atlanta,Georgia:AIAA,2002.1-13.
  • 7牟常伟,王帮峰,葛瑞钧,宁素娟.可主动变形的波纹式蒙皮基体制备及驱动特性[J].兵器材料科学与工程,2010,33(2):11-14. 被引量:9
  • 8XU X F,QIAO P Z,DAVALOS J F.Transverse shear stiffness of composite honeycomb core with general configuration[J].Journal of Engineering Mechanics-ASCE,2001,127(11):1144-1151.
  • 9BARTLEY-CHO JONATHAN D,WANG DONNY P,MARTIN CHRISTOPHER A,et al.Development of high-rate,adaptive trailing edge control surface for the smart wing phase 2 wind tunnel model[J].Journal of Intelligent Material System and Structures,2004,15(4):279-291.
  • 10OLYMPIO K R,GANDHI F.Zero-v cellular honeycomb flexible skins for one-dimensional wing morphing[A].48th AIAA/ASME/ASCE/AHS/ASC Structures,Structural Dynamics,and Materials Conference[C].Honolulu,Hawaii:American Institute of Aeronautics and Astronautics,2007.23-26.

二级参考文献31

  • 1王永贵,陈永清,侯军生.先进复合材料构件波纹梁的成型工艺[J].航空制造技术,2005,48(7):64-67. 被引量:8
  • 2崔光育.蜂窝夹层壳非线性静动力分析.清华大学博士学位论文[M].,1995..
  • 3蘧时胜.复合材料多层板有限元法及其参数识别.清华大学博士学位论文[M].,1996..
  • 4Rodriguez Armando R. Morphing aircraft technology survey [C]. AIAA,2007-1258.
  • 5Jason Bowman, Brian Sanders ,Bryan Cannon. Development of next generation morphing aircraft structures [C ]. AIAA,2007- 1730.
  • 6Reich Gregory W,Sanders Brian. Development of skins for morphing aircraft applications via topology optimization [C]. AIAA, 2007-1738.
  • 7Olympio Kingnide R,Gandhi Farhan. Zero-v cellular honeycomb flexible skins for one-dimensional wing morphing [C]. AIAA, 2007-1735.
  • 8Bartley-Cho Jonathan D,Wang Donny P,Martin Christopher A,et al. Development of high-rate,adaptive trailing edge control surface for the smart wing phase 2 wind tunnel model [J]. Journal of Intelligent Material System and Structures,2004,15 (4) :279.
  • 9Prock Brian C ,Weisshaar Terrence A,Crossley William A. Morphing airfoil shape change optimization With minimum actuator energy as an objective[C]. AIAA,2002-5401.
  • 10Olympio K R, Gandhi F. Zero-v cellular honeycomb flexible skins for one-dimensional wing morphing [ A ]. 48th AIAA/ASME/ ASCE/AHS/ASC Structures, Structural Dynamics, and Ma- terials Conference [ C ], 23 - 26 April 2007, Honolulu, Hawaii.

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