复合材料帽形加筋壁板剪切屈曲性能

doi:10.7527/S1000-6893.2019.22889

固体力学与飞行器总体设计

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

复合材料帽形加筋壁板剪切屈曲性能

汪厚冰, 林国伟, 韩雪冰, 李新祥

中国飞机强度研究所全尺寸飞机结构静力/疲劳航空科技重点实验室, 西安 710065

收稿日期:2019-01-02 修回日期:2019-03-18 出版日期:2019-08-15 发布日期:2019-04-17
通讯作者: 汪厚冰 E-mail:wanghoby@sina.com
基金资助:
民机科研项目（MJ-2015-F-038）

Shear buckling performance of composite hat-stiffened panels

WANG Houbing, LIN Guowei, HAN Xuebing, LI Xinxiang

Aeronautics Science and Technology Key Laboratory of Full Scale Aircraft Structure and Fatigue, Aircraft Strength Research Institute of China, Xi'an 710065, China

Received:2019-01-02 Revised:2019-03-18 Online:2019-08-15 Published:2019-04-17
Supported by:
Civil Aircraft Scientific Research Project (MJ-2015-F-038)

摘要/Abstract

摘要： 对碳纤维增强树脂基复合材料（CFRP）帽形加筋壁板的剪切屈曲进行了试验、理论分析和数值模拟。根据线弹性理论推导了复合材料帽形加筋壁板蒙皮的应变分布；针对复合材料帽形加筋壁板3种蒙皮板条单元截取宽度和两种边界条件，利用理论公式和半经验公式计算了加筋壁板的剪切屈曲载荷；利用特征值法和几何非线性法进行了剪切屈曲模拟分析；将得到的分析结果与试验结果进行了对比。结果表明：根据线弹性理论得到的蒙皮应变分布与试验结果一致，验证了推导结果的正确性；选择合适的边界条件和蒙皮板条单元截取宽度，利用理论公式和半经验公式可得到加筋壁板较准确的屈曲载荷；利用特征值法得到的屈曲载荷较试验屈曲载荷高，选择合适的几何初始缺陷系数利用几何非线性分析方法可模拟复合材料帽形加筋壁板在剪切载荷作用下的屈曲过程。

关键词: 复合材料, 帽形加筋壁板, 剪切屈曲, 特征值法, 几何非线性, 初始缺陷

Abstract: The shear buckling of the Carbon Fiber Reinforced Polymer composite (CFRP) hat-stiffened panels is studied through experiment, theoretical analysis, and numerical simulation. Composite hat-stiffened panels are tested via the distributed load technique. The strain distribution of the skin of composite hat-stiffened panels is deduced based on the composite linear elasticity theory under shear load. Theoretical and semi-experiential approaches are proposed to predict the initial buckling load of hat-stiffened panels with two boundary conditions and three strip widths of skin. Finite element analysis is used to simulate shear buckling with the eigenvalue analytical method and the geometrical nonlinearity method. The analytical results and experimental results are compared. The results show that the strain distribution of skin of panels and test data are consistent, which verifies the effectiveness of strain formula of skin. Adopting theoretical and semi-experiential approaches, a relatively accurate shear buckling load can be obtained with proper boundary conditions and strip widths of the skin. The buckling load derived through the eigenvalue analytical method is higher than the experimental load. The buckling process can be simulated with appropriate initial imperfection through the geometrical nonlinearity method.

Key words: composite, hat-stiffened panels, shear buckling, eigenvalue analytical method, geometrical nonlinearity, initial imperfection

中图分类号:

V214.8
TB332

汪厚冰, 林国伟, 韩雪冰, 李新祥. 复合材料帽形加筋壁板剪切屈曲性能[J]. 航空学报, 2019, 40(8): 222889-222889.

WANG Houbing, LIN Guowei, HAN Xuebing, LI Xinxiang. Shear buckling performance of composite hat-stiffened panels[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(8): 222889-222889.

参考文献 35

[1]	马文博, 余康. 民用飞机中后机身壁板结构设计分析[J]. 中国科技信息, 2016(12):85-86. MA W B, YU K. Design and analysis on middle and rear fuselage panel of civil aircraft[J]. China Science and Technology Information, 2016(12):85-86(in Chinese).
[28]	MCCARTHY M A,MCCARTHY C T, PADHI G S. A simple method for determining the effects of bolt-hole clearance on load distribution in single-column multi-bolt composite joints[J]. Composite Structures, 2006, 73(1):78-87.
[29]	中国航空研究院. 复合材料结构稳定性分析指南[M]. 北京:航空工业出版社,2002:130-141. Chinese Aeronautical Establishment. Stability handbook of composites structure design[M]. Beijing:Aviation Industry Press, 2002:130-141(in Chinese).
[2]	ZIMMERMANN R, ROLFES R. POSICOSS-improved postbuckling simulation for design of fibre composite stiffened fuselage structures[J]. Composite Structures, 2006, 73(2):171-174.
[30]	UPENDRA K M, AKHIL U. Buckling of laminated composite stiffened panels subjected to in-plane shear:A parametric study[J]. Thin-Walled Structures, 2006, 44(3):354-361.
[3]	DEFENHARDT R, ROLFES R, ZIMMERMANN R, et al. COCOMAT-improved material exploitation of composite airframe structures by accurate simulation of postbuckling and collapse[J]. Composite Structures, 2006, 73(2):175-178.
[31]	LOUGHLAN J. The influence of bend-twist coupling on the shear buckling response of thin laminated composite plates[J]. Thin-Walled Structures, 1999, 34(2):97-114.
[4]	GHILAI G, FELDMAN E, DAVID A. COCOMAT design and analysis guidelines for CFRP-stiffened panels[J]. International Journal of Structural Stability and Dynamics, 2010, 10(4):917-926.
[5]	MO Y M, GE D Y, ZHOU J F. Experiment and analysis of hat-stringer-stiffened composite curved panels under axial compression[J]. Composite Structures, 2015, 123:150-160.
[32]	SIMULIA. Abaqus analysis user's manual 6.11[M]. Providence, RI:SIMULIA, 2011.
[6]	GAL E, LEVY R, ABRAMOVICH H, et al. Buckling analysis of composite panels[J]. Composite Structures, 2006, 73(2):179-185.
[33]	MEYER-PIENING H R, FARSHAD M, GEIER B, et al. Buckling loads of CFRP composite cylinders under combined axial and torsion loading-Experiments and computations[J]. Composite Structures, 2001, 53(4):427-435.
[7]	BISAGNI C, CORDISCO P. An experimental investigation into the buckling and post-buckling of CFRP shells under combined axial and torsion loading[J]. Composite Structures, 2003, 60(4):391-402.
[34]	REITINGER R, RAMM E. Buckling and imperfection sensitivity in the optimization of shell structure[J]. Thin-Walled Structures, 1995, 23(1-4):159-177.
[35]	孙伟, 关志东,黎增山,等. 纤维增强复合材料薄壁圆管扭转失效分析[J].复合材料学报, 2016, 33(10):2187-2196. SUN W, GUAN Z D, LI Z S,et al. Failure analysis of fiber reinforced composite thin-walled circular tubes under torsion load[J]. Acta Materiae Compositae Sinica, 2016, 33(10):2187-2196(in Chinese).
[8]	ZIMMERMANN R, KLEIN H, KLING A. Buckling and postbuckling of stringer-stiffened fibre composite curved panels tests and computations[J]. Composite Structures, 2006, 73(2):150-161.
[9]	MÖCKER T, REIMERDES H G. Postbuckling simulation of curved stiffened composite panels by the use of strip elements[J]. Composite Structures, 2006, 73(2):237-243.
[10]	LAUTERBACH S, ORIFICI A C, WAGNER W, et al. Damage sensitivity of axially loaded stringer-stiffened curved CFRP panels[J]. Composite Science Technology, 2010, 70(2):240-248.
[11]	臧伟锋, 董登科,张海英. 机身壁板内压载荷强度试验方法研究[J]. 机械强度, 2015, 37(5):972-977. ZANG W F, DONG D K, ZHANG H Y. Research on test method of fuselagepanel subjected to internal pressure load[J]. Journal of Mechanical Strength, 2015, 37(5):972-977(in Chinese).
[12]	孙为民, 童明波,董登科,等. 民机大型加筋曲板在剪切载荷下失效破坏试验[J]. 南京航空航天大学学报, 2008, 40(4):521-525. SUN W M, TONG M B, DONG D K,et al. Failure damage experiments of stiffened panels subjected to shear loading[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2008, 40(4):521-525(in Chinese).
[13]	WAGNER H.Flat sheet metal girder with very thin metal web-Part I:General theories and assumptions:NACA-TM-604[R]. Washington, D.C.:NACA, 1931.
[14]	MURPHY A, PRICE M, LYNCH C, et al. The computational post-buckling analysis of fuselage stiffened panels loaded in shear[J]. Thin-Walled Structures, 2005, 43(9):1455-1474.
[15]	ROTHWELL A. An experimental investigation of the post-buckled efficiency of Z-section stringer-skin panels[J]. The Aeronautical Journal, 1981, 85(840):29-33.
[16]	CRICRI G, PERRELLA M, CALI C. Experimental and numerical post-buckling analysis of thin aluminium aeronautical panels under shear load[J]. Strain, 2014, 50(3):208-222.
[17]	冯宇, 何宇廷,邵青,等. 复合材料加筋板剪切屈曲特性研究[J]. 机械强度, 2013, 35(3):288-291. FENG Y, HE Y T, SHAO Q,et al. Study on shear stability performance of composite stiffened panel[J]. Journal of Mechanical Strength, 2013, 35(3):288-291(in Chinese).
[18]	JUNG W Y, HAN S C. Shear buckling responses of laminated composite shells using a modified 8-node ANS shell element[J]. Composite Structures, 2014, 109:119-129.
[19]	GE D Y, MO Y M, HE B L, et al. Experimental and numerical investigation of stiffened composite curved panel under shear and in-plane bending[J]. Composite Structures, 2016, 137:185-195.
[20]	CORDISCO P, BISAGNI C. Cyclic buckling tests under combined compression and shear on composite stiffened panels[J]. AIAA Journal, 2009, 47(12):2879-2893.
[21]	ABRAMOVICH H, WELLER T, BISAGNI C. Buckling behavior of composite laminated stiffened panels under combined shear-axial compression[J]. Journal of Aircraft, 2008, 45(2):402-412.
[22]	柴亚南, 李崇,王力立,等. 一种能够均匀施加轴向压缩和剪切载荷的试验装置:ZL 201210528616.7[P]. 2015-04-29. CHAI Y N, LI C, WANG L L, et al. A test fixture of uniform load of axial compress and shear:ZL 201210528616.7[P]. 2015-04-29(in Chinese).
[23]	杨晓宇, 里程遥,李翰飞. 基于有限元法的机械连接静力分析的研究[J]. 北京石油化工学院学报, 2009, 17(1):15-18. YANG X Y, LI C Y, LI H F. Research on the static analysis of the mechanical connection based on FEM[J]. Journal of Beijing Institute of Petro-Chemical Technology, 2009, 17(1):15-18(in Chinese).
[24]	王武, 陶华,刘风雷,等. 复合材料多排螺栓连接钉载分配的研究[J]. 绝缘材料, 2006, 28(1):28-32. WANG W, TAO H, LIU F L,et al. Research on pin load distribution of multiple bolt-jointed composite laminate[J]. Insulating Materials, 2006, 28(1):28-32(in Chinese).
[25]	赵美英, 阎国良,顾亦磊,等. 复合材料层板钉群连接载荷分配计算方法研究[J]. 航空计算技术, 2006, 36(3):97-101. ZAHO M Y, YAN G L, GU Y L, et al. Design of computation methods of the load distribution in composite fastener group joints[J]. Aeronautical Computing Technique, 2006, 36(3):97-101(in Chinese).
[26]	MCCARTHY C T,GRAY P J. An analytical model for the prediction of load distribution in highly torqued multi-bolt composite joints[J]. Composite Structures, 2011, 93(2):287-298.
[27]	张明星. T800碳纤维复合材料混合连接层合板钉载分布及有限元计算[J]. 玻璃钢/复合材料, 2011, 62(5):62-66. ZHANG M X. Load distribution and finite element calculation of T800 carbon fiber hyper joints composite laminates[J]. Fiber Reinforced Plastics/Composites, 2011, 62(5):62-66(in Chinese).
[28]	MCCARTHY M A,MCCARTHY C T, PADHI G S. A simple method for determining the effects of bolt-hole clearance on load distribution in single-column multi-bolt composite joints[J]. Composite Structures, 2006, 73(1):78-87.
[29]	中国航空研究院. 复合材料结构稳定性分析指南[M]. 北京:航空工业出版社,2002:130-141. Chinese Aeronautical Establishment. Stability handbook of composites structure design[M]. Beijing:Aviation Industry Press, 2002:130-141(in Chinese).
[30]	UPENDRA K M, AKHIL U. Buckling of laminated composite stiffened panels subjected to in-plane shear:A parametric study[J]. Thin-Walled Structures, 2006, 44(3):354-361.
[31]	LOUGHLAN J. The influence of bend-twist coupling on the shear buckling response of thin laminated composite plates[J]. Thin-Walled Structures, 1999, 34(2):97-114.
[32]	SIMULIA. Abaqus analysis user's manual 6.11[M]. Providence, RI:SIMULIA, 2011.
[33]	MEYER-PIENING H R, FARSHAD M, GEIER B, et al. Buckling loads of CFRP composite cylinders under combined axial and torsion loading-Experiments and computations[J]. Composite Structures, 2001, 53(4):427-435.
[34]	REITINGER R, RAMM E. Buckling and imperfection sensitivity in the optimization of shell structure[J]. Thin-Walled Structures, 1995, 23(1-4):159-177.
[35]	孙伟, 关志东,黎增山,等. 纤维增强复合材料薄壁圆管扭转失效分析[J].复合材料学报, 2016, 33(10):2187-2196. SUN W, GUAN Z D, LI Z S,et al. Failure analysis of fiber reinforced composite thin-walled circular tubes under torsion load[J]. Acta Materiae Compositae Sinica, 2016, 33(10):2187-2196(in Chinese).

E-mail：hkxb@buaa.edu.cn

关于我们

期刊社服务

专业学科

封面文章

友情链接

主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

复合材料帽形加筋壁板剪切屈曲性能

Shear buckling performance of composite hat-stiffened panels

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献 35

相关文章 15

编辑推荐

Metrics

本文评价

[1]	张伟, 王彬文, 樊俊铃, 詹绍正, 焦婷, 杨宇. 基于多模式超声成像的CFRP冲击损伤无损表征与冲击后压缩强度预测[J]. 航空学报, 2023, 44(1): 426635-426635.
[2]	郑锋, 黄薇, 季宏丽, 裘进浩. 复合材料薄板结构中的声学黑洞效应探究[J]. 航空学报, 2023, 44(1): 426453-426453.
[3]	冉庆波, 肖鸿, 杨富鸿, 段玉岗. 含孔曲面自动铺丝轨迹规划算法[J]. 航空学报, 2022, 43(9): 425602-425602.
[4]	曹勇, 张超. 薄层复合材料冲击损伤行为研究进展[J]. 航空学报, 2022, 43(6): 525323-525323.
[5]	万傲霜. 复合材料直升机平尾结构概率损伤容限评估[J]. 航空学报, 2022, 43(6): 525557-525557.
[6]	王育鹏, 吕帅帅, 杨宇, 李嘉欣, 王叶子. 基于域自适应的复合材料结构损伤识别方法[J]. 航空学报, 2022, 43(6): 526752-526752.
[7]	赵天, 李营, 张超, 姚辽军, 黄怿行, 黄治新, 陈诚, 汪万栋, 祖磊, 周华民, 裘进浩, 邱志平, 方岱宁. 高性能航空复合材料结构的关键力学问题研究进展[J]. 航空学报, 2022, 43(6): 526851-526851.
[8]	郭琼, 刘玮, 裴连杰, 郭俊豪. 全尺寸复合材料机身筒段静力/疲劳试验技术[J]. 航空学报, 2022, 43(6): 525816-525816.
[9]	汪厚冰, 王夏涵, 林国伟, 李新祥, 杨胜春. 含离散源损伤的复合材料壁板的剩余强度评估[J]. 航空学报, 2022, 43(6): 525899-525899.
[10]	刘振东, 郑锡涛, 范雯静, 张东健. 固化残余应力对无人机复合材料机翼强度的影响[J]. 航空学报, 2022, 43(6): 526117-526117.
[11]	邓云飞, 周楠, 田锐, 魏刚. S型碳纤维褶皱夹芯结构低速冲击响应特性实验研究[J]. 航空学报, 2022, 43(6): 525446-525446.
[12]	刘增飞, 刘凯, 张斌斌, 李雪枫, 葛敬冉, 黄建, 李超, 孙新杨, 孙煜, 梁军. 纱线规格对3D机织复合材料拉伸性能的影响[J]. 航空学报, 2022, 43(6): 525453-525453.
[13]	李涤尘, 鲁中良, 田小永, 张航, 杨春成, 曹毅, 苗恺. 增材制造——面向航空航天制造的变革性技术[J]. 航空学报, 2022, 43(4): 525387-525387.
[14]	赵可汗, 刘多, 朱海涛, 陈斌, 胡胜鹏, 宋晓国. 钎焊温度对C/C/AgCuTi+C_f/TC4接头组织及力学性能的影响[J]. 航空学报, 2022, 43(4): 525007-525007.
[15]	张加波, 张开虎, 范洪涛, 路明雨, 高泽, 张孝辉. 纤维复合材料激光加工进展及航天应用展望[J]. 航空学报, 2022, 43(4): 525735-525735.