[1] TONG Y C.Literature review on aircraft structural risk and reliability analysis:DSTO-TR-1110[R].Melboure:DSTO Aeronautical and Maritime Research Labratory,2001.
[2] RUDD J L,GRAY T D.Quantification of fastener-hole quality[J].Journal of Aircraft,1978,15(3):143-147.
[3] RUDD J L.Applications of the equivalent initial quality method:AFFDL-TM-76-83-FBE[R].Dayton:Wright-Patterson AFB,1977.
[4] MANNING S D,YANG J N,SHINOZUKA M.USAF durability design handbook:Guidelines for the analysis and design of durable aircraft structures:AFFDL-TR84-3027[R].Dayton:Wright-Patterson AFB,1984.
[5] YANG J N.Statistical estimation of economic life for aircraft structures[J].Journal of Aircraft,1980,17(7):528-535.
[6] BARTER S A,MOLENT L.Fatigue cracking from a corrosion pit in an aircraft bulkhead[J].Engineering Failure Analysis,2014,39(4):155-163.
[7] MOLENT L.A review of equivalent pre-crack sizes in aluminium alloy 7050-T7451[J].Fatigue & Fracture of Engineering Materials & Structures,2014,37(10):1055-1074.
[8] MOLENT L,SUN Q,GREEEN A J.Characterisation of equivalent initial flaw sizes in 7050 aluminium alloy[J].Fatigue & Fracture of Engineering Materials & Structures,2006,29(11):916-937.
[9] MATTRAND C,BOURINET J M,THÉRET D.Analysis of fatigue crack growth under random load sequences derived from military in-flight load data[C]//ICAF 2011 Structural Integrity:Inuence of Eciency and Green Imper-atives.Berlin:Springer-Verlag,2011:399-413.
[10] MATTRAND C,BOURINET J M.Random load sequences and stochastic crack growth based on measured load data[J].Engineering Fracture Mechanics,2011,78(17):3030-3048.
[11] XIANG Y,LIU Y. EIFS-based crack growth fatigue life prediction of pitting-corroded test specimens[J].Engineering Fracture Mechanics,2010,77(8):1314-1324.
[12] FAWAZ S A.Equivalent initial flaw size testing and analysis of transport aircraft skin splices[J].Fatigue & Fracture of Engineering Materials & Structures,2003,26(3):279-290.
[13] WANG D Y.An investigation of initial fatigue quality:STPZ8860S[R].West Conshohocken:ASTM Special Technical Publication,1982.
[14] 航空航天部AFFD系统办公室.美国空军耐久性手册背景材料:第Ⅷ卷[M]西安:航空航天部AFFD系统办公室,1989.AFFD System Engineering Office of the Department of Aeronautics and Astronautics. The background information of USAF durability design handbook:Vol.Ⅷ[M].Xi'an:AFFD System Engineering Office of the Department of Aeronautics and Astronautics,1989(in Chinese).
[15] YANG J,MANNING S,RUDD J,et al.Effect of specimen size and notch geometry on equivalent initial flaw size distribution[C]//AIAA/ASME/ASCE/AHS/ASC Structures,Structural Dynamics,and Materials Conference and Exhibit.Reston:AIAA,1996:385-397.
[16] 曹淑森,贺小帆,杨博霄,等.夹持边界条件下表面裂纹应力强度因子求解[J].北京航空航天大学学报,2014,40(11):1637-1642.CAO S S,HE X F,YANG B X,et al.Solution of stress intensity factor of surface cracked geometry with clamped ends[J].Journal of Beijing University of Aeronautics and Astronautics,2014,40(11):1637-1642(in Chinese).
[17] 张行.断裂力学[M].北京:中国宇航出版社,1990:72-169.ZHANG X.Fracture mechanics[M].Beijing:China Aerospace Press,1990:72-169(in Chinese).
[18] 刘文珽.概率断裂力学与概率损伤容限/耐久性[M].北京:北京航空航天大学出版社,1999:144-181.LIU W T.Probabilistic fracture mechanics and probability damage tolerance/durability[M]. Beijing:Beihang University Press,1999:144-181(in Chinese).
[19] PROVAN J W.Probabilistic fracture mechanics and reliability[M]. Leiden:Martinus Nijhoff Publishers,1987:70-72.
[20] 高镇同.疲劳应用统计学[M]. 北京:国防工业出版社,1986:277-295.GAO Z T. Fatigue application statistics[M]. Beijing:National Defence of Industry Press,1986:277-295(in Chinese). |