Determination of damage tolerance and remaining lifefor aeroengine crankcase

[1] 航空工业部科学技术委员会.飞机结构损伤容限设计指南[M].北京:航空工业部科学技术情报研究所,1985 Aviation Industry Science and Technology Commission.Guide to damage tolerance design of aircraft structure[M].Beijing:.Aviation Industry Science and Technology Commission,1985 (in Chinese) [2] GJB776-89,军用飞机损伤容限要求[S] GJB776-89,Military airplane damage tolerance requirements[S] [3] 孙克淋,安伟光,王滨生,等.航天飞机薄壁结构的可靠性分析[J].哈尔滨工程大学学报,2004,25(3):327-331 Sun Kelin,An Weiguang,Wang Binsheng,et al.Reliability analysis of thin-walled structures for shuttle[J].Journal of Harbin Engineering University,2004,25(3):327-331 [4] 李亚智,张向.整体加筋壁板的破损安全特性与断裂分析[J].航空学报,2006,27(5):842-846 Li Yazhi,Zhang Xiang.An analysis of fail-safety and fracture control of integreally stiffened panels[J].Acta Aeronautica et Astronautica Sinica,2006,27(5):842-846 [5] 黄其青,刘进征,殷之平.整体翼梁结构断裂特性分析方法与研究[J].航空计算技术,2006,36(2):114-119 Huang Qiqing,Liu Jinzheng,Yu Zhiping.Fracture characteristics analysis method and study of wing-bean integrated structure[J].Aeronautical Computing Technique,2006,36(2):114-119 [6] Schodel M,Zerbst U,Donne C D.Application of the european flaw assessment procedure SINTAP to thin wall structures subjected to biaxial and mixed mode loadings[J].Engineering Fracture Mechanics,2006,73(5):626-642 [7] BS 7910:2005:Guide to methods for assessing the acceptability of flaws in metallic structures[S] [8] API 579-1/ASME FFS-1:Fitness-for-service[S] [9] R6:Assessment of the integrity of structure containing defect.Revision 4[S]