|
|
- 2018
复合材料帽形加筋壁板轴压屈曲与后屈曲性能
|
Abstract:
针对2种边界条件和3种板元宽度情况，采用几种屈曲方法对轴压载荷作用下的复合材料帽形加筋壁板进行了计算，得到了不同情况下的屈曲载荷，通过对复合材料加筋壁板几种计算方法的计算结果与试验结果的对比，得到一种更简单有效计算复合材料帽形加筋壁板轴压屈曲载荷的方法；依据帽形加筋壁板的结构特点和试验后的破坏模式，提出一种估算复合材料帽形加筋壁板轴压破坏载荷的方法，用该方法在几个项目上的计算结果与试验结果进行比较，发现两者较吻合，验证了复合材料帽形加筋壁板轴压承载能力估算方法的合理性，为结构设计人员在初始设计阶段对复合材料帽形加筋壁板轴压强度评估提供了一种简洁的途径。 To analyze composite hat-stiffened panels, several calculation methods were adopted firstly for calculating the compression buckling performance of composite hat-stiffened panels under axial compression to obtain the buckling load under two boundary conditions and three widths of sample. The buckling loads of different calculation methods were obtained. The calculation results were compared with the test results in order to find out a simple and effective method of obtaining buckling load of hat-stiffened composite panels under axial compression. According to dense stiffener in hat-stiffened panel of current aircraft structure, the structure characters and failure patterns of hat-stiffened composite panels, a simple calculation method was proposed to estimate the failure loads of hat-stiffened composite panels under axial compression. Calculation results accord with the test results well, which validates the rationality of engineering method. It is preferable accuracy to estimate the failure load of composite hat-stiffened panels by the engineering calculation method.
| [1] | REINOSO J, BLAZQUEZ A, PARIS F, et al. Postbuckling behaviour of a pressurized stiffened composite panel-part I:Experimental study[J]. Composite Structures, 2012, 94:1533-1543. |
| [2] | AMBUR D R, JAUNKY N, DAVILA C G, et al. Progressive failure studies of composite panels with and without cutouts, NASA/CR-2001-211223[R]. Washington:NASA, 2001. |
| [3] | BASU S, WAAS A M, AMBUR D R. Prediction of progressive failure in multidirectional composite laminated panels[J]. International Journal of Solids & Structures, 2007, 44(9):2648-2676. |
| [4] | MAIMI P, CAMANHO P P, MAYUGO J A, et al. A continuum damage model for composite laminates:Part I-Constitutive model[J]. Mechanics of Materials, 2007, 39(10):897-908. |
| [5] | CAMANHO P P, DAVILA CG, MOURA M F D. Numerical simulation of mixed-mode progressive delamination in composite materials[J]. Journal of Composite Materials, 2003, 37(16):1415-1438. |
| [6] | BERTOLINI Julien, CASTANIE Bruno, BARRAU Jean-jacques, et al. Multi-level experimental and numerical analysis of composite stiffener debonding Part 1:Non-specific specimen level[J]. Composite Structures, 2009, 90(4):381-391. |
| [7] | KRUEGER R, CVITKOVITCH M K, O'BRIEN T K, et al. Testing and analysis of composite skin/stringer debonding under multi-axial loading[J]. Journal of Composite Materials, 2000, 34(15):1263-1300. |
| [8] | IARVE E V. Mesh independent modeling of cracks by using higher order shape functions[J]. International Journal for Numerical Methods in Engineering, 2003; 56(6):869-882. |
| [9] | 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. Institute of Aeronautics China. Stability handbook of composites structure design[M]. Beijing:Aviation Industry Press, 2002(in Chinese). |
| [10] | 陈昊. 顶部壁板加筋板试验报告, 中国飞机强度研究所技术报告, 623S-201301-372[R]. 2013. CHEN Hao. Test report of top stiffened panels. Aircraft strength research institute of china technology report, AVIC/623S-201301-372[R]. 2013(in Chinese). |
| [11] | 唐见茂. 航空航天复合材料发展现状及前景[J]. 航天器环境工程, 2013, 30(4):352-359. TANG Jianmao. A review of aerospace materials[J]. Spacecraft Environment Engineering, 2013, 30(4):352-359(in Chinese). |
| [12] | BISAGNI C, VESCOVINI R, DáVILA C G. Single-stringer compression specimen for the assessment of damage tolerance of post buckled structures[J]. Journal of Aircraft, 2011, 48(2):495-502. |
| [13] | BISAGNI C, DáVILA C G. Experimental investigation of the postbuckling response and collapse of a single-stringer specimen[J]. Composite Structures, 2014, 108(1):493-503. |
| [14] | MO Yuming, GE Dongyun, ZHOU Jiangfan. Experiment and analysis of hat-stringer-stiffened composite curved panels under axial compression[J]. Composite Structures, 2015, 123:150-160. |
| [15] | ORIFICI A C, ALBERDI I O D Z, THOMSON R S, et al. Compression and post-buckling damage growth and collapse analysis of flat composite stiffened panels[J]. Composites Science and Technology, 2008, 68(15):3150-3160. |
| [16] | MAINI P, CAMANHO P P, MAYUGO J A, et al. A continuum damage model for composite laminates:Part Ⅱ-Computational implementation[J]. Mechanics of Materials, 2007, 39(10):909-919. |
| [17] | KRUEGER R. The virtual crack closure technique:History, approach and applications:NASA/CR-2002-211628[R]. Washington:NASA, 2002. |
| [18] | BISAGNI Chiara. Progressive delamination analysis of stiffened composite panels in post-buckling. Structures, Structural Dynamics & Materials Conference Adaptive Structures Conference, 2013, 10(2):161-162. |
| [19] | ORIFICI A C, THOMSON R S, DEGENHARDT R, et al. A finite element methodology for analysing degradation and collapse in postbuckling composite aerospace structures[J]. Journal of Composite Materials, 2009, 43(26):3239-3263. |
| [20] | DAVILA G C, CAMANHO P P, TURON A. Effective simulation of delamination in aeronautical structures using shells and cohesive elements[J]. Journal of Aircraft, 2008, 45(2):663-672. |
| [21] | TURON A, CAMANHO P P, COSTA J, et al. A damage model for the simulation of delamination in advanced compo-sites under variable-mode loading[J]. Mechanics of Materials, 2006, 38(11):1072-1089. |
| [22] | BENZEGGAH M L, KENANE M. Measurement of mixed-mode delamination fracture toughness of unidirectional glass/epoxy composites with mixed mode bending apparatus[J]. Composites Science & Technology, 1996, 56(4):439-449. |
| [23] | 汪厚冰. 复合材料帽形长桁加筋曲面壁板稳定性与损伤容限试验报告, 中国飞机强度研究所技术报告, Y14WX15-60SY0156[R]. 2016. WANG Houbing. Test report of stability and damage tolerance of composite hat-stiffened panels, AVIC/Y14WX15-60SY0156[R]. 2016(in Chinese). |
