[1] 贺利乐, 李书宝, 郑建校, 等. 考虑剪切非线性的复合材料层合板渐进损伤数值模拟[J]. 复合材料科学与工程, 2024(1): 45-53. [2] 吴义韬. 复合材料层合板强度的数值模拟理论研究与试验验证[D]. 南京: 南京航空航天大学, 2014. [3] 李秋漳. 复合材料层合板缺口强度的CDM三维数值模型[D]. 南京: 南京航空航天大学, 2016. [4] 徐颖. 复合材料层合板冲击损伤及冲击后疲劳寿命研究[D]. 南京: 南京航空航天大学, 2007. [5] TSAI S W. Strength characteristics of composite materials: NASA CR-224[R]. Washington D.C.: National Aeronautics and Space Administration, 1965. [6] HOFFMAN O. The brittle strength of orthotropic materials[J]. Journal of Composite Materials, 1967, 1(2): 200-206. [7] HASHIN Z. Failure criteria for unidirectional fiber composites[J]. Journal of Applied Mechanics, 1980, 47(2): 329-334. [8] HASHIN Z, ROTEM A. A fatigue failure criterion for fiber reinforced materials[J]. Journal of Composite Materials, 1973, 7(4): 448-464. [9] PUCK A, SCHÜRMANN H. Failure analysis of FRP laminates by means of physically based phenomenological models[J]. Composites Science and Technology, 2002, 62(12/13): 1633-1662. [10] PINHO S T, VYAS G M, ROBINSON P. Material and structural response of polymer-matrix fibre-reinforced composites: part B[J]. Journal of Composite Materials, 2013, 47(6/7): 679-696. [11] PINHO S T, DARVIZEH R, ROBINSON P, et al. Material and structural response of polymer-matrix fibre-reinforced composites[J]. Journal of Composite Materials, 2012, 46(19/20): 2313-2341. [12] PINHO S T, DÁVILA C G, CAMANHO P P, et al. Failure models and criteria for FRP under in-plane or three-dimensional stress states including shear non-linearity: NASA/TM-2005-213530[R]. Hampton: Langley Research Center, 2005. [13] DAVILA C, JAUNKY N, GOSWAMI S. Failure criteria for FRP laminates in plane stress [C]//44th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Norfolk, Virginia: AIAA, 2003. [14] WANG K K, ZHAO L B, HONG H M, et al. A strain-rate-dependent damage model for evaluating the low velocity impact induced damage of composite laminates[J]. Composite Structures, 2018, 201: 995-1003. [15] SHOKRIEH M M, TAHERI-BEHROOZ F. Progressive fatiguedamage modeling of cross-ply laminates, Ⅰ: modeling strategy[J]. Journal of Composite Materials, 2010, 44(10): 1217-1231. [16] SHOKRIEH M M, LESSARD L B. Progressive fatigue damage modeling of composite materials, part Ⅱ: material characterization and model verification[J]. Journal ofComposite Materials, 2000, 34(13): 1081-1116. [17] SHOKRIEH M M, LESSARD L B. Multiaxial fatigue behaviour of unidirectional plies based on uniaxial fatigue experiments — Ⅰ.Modelling[J]. International Journal of Fatigue, 1997, 19(3): 201-207. [18] 刘向民, 姚卫星, 陈方. 复合材料层合板结构冲击损伤数值模拟的损伤力学模型[J]. 航空学报, 2016(10): 3054-3063. [19] 吴义韬, 姚卫星, 吴富强, 等. 基于应变能耗散的复合材料层合板面内缺口强度分析CDM模型[J]. 复合材料学报, 2014, 31(4): 1013-1021. [20] LAFARIE-FRENOT M C, TOUCHARD F. Comparative in-plane shear behaviour of long-carbon-fibre composites with thermoset orthermoplastic matrix[J]. Composites Science and Technology, 1994, 52(3): 417-425. [21] HAHN H T, TSAI S W. Nonlinear elastic behaviorof unidirectional composite laminae[J]. Journal of Composite Materials, 1973, 7(1): 102-118. [22] 刘伟先, 周光明, 高军, 等. 考虑剪切非线性影响的复合材料连续损伤模型及损伤参数识别[J]. 复合材料学报, 2013(6): 221-226. [23] 拓宏亮, 马晓平, 卢智先. 基于连续介质损伤模型的复合材料连接件失效分析[J]. 西北工业大学学报, 2018, 36(5): 848-855. [24] 李秋漳, 姚卫星, 陈方. 复合材料层合板缺口强度的CDM三维数值模型[J]. 复合材料学报, 2016, 33(12): 2766-2774. [25] 张嘉睿, 吴富强, 姚卫星. 复合材料冲击损伤数值仿真模型评估[J]. 航空工程进展, 2019, 10(6): 767-779. [26] 王轩, 石强斌, 高俊福. 玻璃纤维平纹编织层合板面内剪切渐进失效分析[J]. 科学技术与工程, 2023, 23(6): 2656-2663. [27] 杨凤祥, 陈静芬, 陈善富, 等. 基于剪切非线性三维损伤本构模型的复合材料层合板失效强度预测[J]. 复合材料学报, 2020, 37(9): 2207-2222. [28] 段永照, 姚卫星, 陈方. 面向纤维增强复合材料低速冲击损伤的非线性混合模型[J]. 南京航空航天大学学报, 2018, 50(1): 16-23. [29] MAA R, CHENG J. A CDM-based failure model for predicting strength of notched composite laminates[J]. Composites Part B: Engineering, 2002, 33(6): 479-489. [30] 陈静芬. 基于弹塑性损伤本构模型的复合材料层合板破坏荷载预测[J]. 复合材料学报, 2017, 34(4): 773-785. [31] 张健, 陈秀华, 陈勇, 等. 单向热塑性复合材料层压板偏轴拉伸试验及其数值模拟[J]. 上海交通大学学报, 2023, 57(2): 201-212. [32] SOKOLINSKY V S, INDERMUEHLE K C, HURTADO J A. Numerical simulation of the crushing process of a corrugated composite plate[J]. Composites Part A: Applied Science and Manufacturing, 2011, 42(9): 1119-1126. [33] CHENG Z Q, XIONG J J. Progressive damage behaviors of woven composite laminates subjected to LVI, TAI and CAI[J]. Chinese Journal of Aeronautics, 2020, 33(10): 2807-2823. |