[ 1 ] Fredell R, The development of inspection and repairmethods for the C-17 Aircraft cargo door [R]. Faculty of Aerospace Engineering, Delft University. The Netherands, Report LR-704, 1992

[ 2 ] Gunnink J W, van der Schee P A. Design of the AR-ALLF一27 lower wing fatigue panel [A], Proceedings of the 4th Intermational Conference on Composite Strsctures [C]. Scodand 1987

[ 3 ] Marisen R. Fatigue cack growthing ARALL: A hybrid aluminum - aramid composite material crack growth mechanisms and quantitative predictions of the crack growth rates [D].Ph, D Thess, Delft University of Technology. The Netherlands 1988

[ 4 ] Schijve J. Development of fber-meta laminates(AR-ALL and GLARE), New Fatigue Resistant Material [A]. Proceedings of Fatigue 93 [C], Eds, Bailon, DiclsonL. EAMS 1993

[ 5 ] Guo Y J, Wu X R, A theoreteal model for predicting fatigue crack growth  rates in fiber reinforced metal Iaminates [J], Fatigue Fraet,Mater, Struct, 1998,21:1133一1145

[ 6 ] Guo Y J. Wu X R, Bridging stress disuibation incenter-cracked tension(CCT) specimen of fiber reinforced metal laminates (FRMLS): modeling and experiment [J]. Engng.Fract,Mech,1999,63:147-1637

[ 7 ] Wu X R, Carlson A J . Weight functions and stress intensity factor solutions [M], Pergamon Press 1991

[ 8 ] Guo Y J, Wu X R,Zhang Z L, Characterization of delamination growth behavior of hybrid bond laminates[J], Fatigue Fraet, Mater, Struct,,1997,20:1699一1708

[ 9 ] Guo Y J. Wu X R, Factors affecting fatigue crack growth rates of fiber reinforced metal laminates[J]. Chinese Journal of Aeronauties,1998,11(2):152一156

[10] Guo Y J. Wu X R, Aphenomenological model for predicting crack growth in fiber reinforced metal laminates under constant amplitude loading [J], Composites Science and Technology, 1999,59:1825一1831