The local stress/strain approach has been used to predict the fatigue lives of notched composite components. The method was based on a microstress analysis and the application of a multiaxial fatigue parameter incorporating the alternating strain components on the critical plane. This parameter was able to correlate the fatigue lives obtained under a variety of multiaxial loading and geometrical configurations, enabling a generalized fatigue life curve to be determined on the basis of limited experimental data.The ability of the multiaxial fatigue parameter to relate the fatigue behaviour of composites was illustrated by predicting the locations of crack initiation sites in a unidirectional silicon carbide fibre reinforced titanium plate containing a circular hole tested under constant amplitude cyclic loading. The same approach was also successfully employed to predict the fatigue lives of graphite reinforced epoxy composite tubes with circular holes tested under several combinations of cyclic tension and torsion.
NOMENCLATUREA , K, m =material constants A , , Bij = coefficients relating macrostresses S, and microstresses u,, in deformation states I, 11, I11 (using A o ) and IV, V (using 4 ) respectively EL, & = axial and transverse elastic moduli for a unidirectional laminate measured with respect to the fibre direction E: , E: = elastic moduli for multilayer laminate in I and y directions G,,, G: Y = shear modulus for a unidirectional and multilayer laminate respectively k = subscript defining kth ply n = numbers of plies in a laminate M = laminate stiffness matrix Q, = lamina stiffness coefficients (Q,), =transformed stiffness coefficients in kth ply R =stress ratio ( R = Sm~o/S,,,ax) Sii, 5j = macro-and microstress components ( i , j = 1,2,3, R, 0, x, y ) S,, = amplitudes of macrostress components V , = volume fraction of fibres pk = angle between loading direction and fibre axis in k th ply 7, Tl3 =shear strain amplitude on critical plane and X,-X3 plane respectively a* = multiaxial strain parameter h , , 6, = elastic proportionality factors 1, f, =thickness of a multilayer laminate and thickness of the kth ply in a laminate E = amplitude of strain component normal to the critical plane vLT, vTL = Poisson's ratios in the parallel and transverse directions to fibre v :~ = Poisson's ratio for a multilayer laminate R = volume 77 78 G. SHEN et (11.