[1] 穆志韬, 曾本银, 等. 直升机结构疲劳[M]. 北京: 国防工业出版社,2009. [2] Rose L R F. A Cracked Plate Repaired by Bonded Reinforcements [J]. International Journal of Fracture,1982,18: 135-144. [3] A. Albedah, B. Bachir Bouiadjra, W. Ouddad, et al. Elastic Plastic Analysis of Bonded Composite Repair in Cracked Aircraft Structures[J]. Journal of Reinforced Plastics of Composites,2011,30(1):66-72. [4] Qudad W, B. Bachir Bouiadjra, Belhouari M, et al. Analysis of the Plastic Zone Size Ahead of Repaired Cracks with Bonded Composite Patch of Metallic Aircraft Structures[J]. Computer Material Science,2009,46:950-954. [5] 李庆芬, 等. 断裂力学及其工程应用[M]. 哈尔滨工程大学出版社,2004. [6] 赵立涛. 复合材料胶接修补金属裂纹板及其应力强度因子的研究[D]. 南京:南京航空航天大学,2010. [7] 杨孚标. 复合材料修补含中心裂纹铝合金板的静态与疲劳特性研究[D]. 长沙: 国防科学技术大学, 2006. [8] 王遵. 复合材料单面补强含裂纹铝合金薄板的残余热应力及其影响研究[D]. 长沙: 国防科学技术大学,2007. [9] 张移山,华庆祥. 复合材料补片参数对裂纹尖端应力强度因子的影响[J]. 机械强度, 2004, 100-103. [10] 文思维. 硼-环氧复合材料补片修补含中心裂纹铝合金厚板研究[D]. 长沙: 国防科技大学,2008. [11] G C Tai,S B Shen. Fatigue Anlaysis of Cracked Thick Aluminum Plate Bonded with Composite Patches[J]. Composite Structures,2004,64:79-90. [12] Muller R, Fredell R, Guijt C, et al. Experimental Verification of Rose's Constant K Solution in Bonded Crack Patching[J]. Apply composite materials,1999,6(4):205-216. [13] Schubbe JJ,Mall S. Investigation of a Cracked Thick Aluminum Panel Repaired with a Bonded Composite Patch[J]. Engineer Fracture Mechanics,1999,63:305-323. [14] Ki-Hyun Chung,Won-Ho Yang. A Study on the Fatigue Crack Growth Behavior of Thick Aluminum Panels Repaired with a Composite Patch[J]. Composite Structure,2003,60:1-7. |