Issue 41

J.V. Sahadi et alii, Frattura ed Integrità Strutturale, 41 (2017) 106-113; DOI: 10.3221/IGF-ESIS.41.15 110                         f n f N N G ' b c ,max ' max f f ' yield 1 2 2 2 (4) where Δγ max /2 is the maximum shear strain amplitude and σ n,max is the maximum normal stress on the plane where Δγ max /2 occurs. The material parameter  represents the influence of the normal stress, σ n,max . In addition, σ ’ yield represents the cyclic yield strength of the material and is included to make the maximum normal stress component dimensionless and proportional to the shear strain. τ ' f and b γ are the shear fatigue strength coefficient and exponent respectively. γ ' f and c γ are the shear fatigue ductility coefficient and exponent respectively. The material parameter  is given as:                                            f f f f f N N G N N N E ' b c ' ' f f yield ' b ' b c ' f e f p f 2 2 1 2 1 2 1 2 (5) Fig. 3(a) illustrates the evolution of the Fatemi-Socie (FS) parameter presented in Eq. (4) and (5), the shear strain amplitude (Δγ/2) and the normal stress (σ n ) as a function of the angle θ, varying from 0 to 180º. Considering the angle orientation presented in Fig. 1 (b), for all the tests analysed in here the critical planes predicted by this parameter are orientated at 45º and 135º from the y-axis. (a) (b) Figure 3 : (a) Evolution of Fatemi-Socie parameter (FS), Δγ/2 and σ n as a function of angle θ for proportional loading. (b) Evolution of Smith-Watson-Topper parameter (SWT), Δε 1 /2 and σ n as a function of angle θ for proportional loading. Smith-Watson-Topper The second damage parameter considered was proposed by Smith et al. [59], SWT, and was proposed for predicting fatigue life under uniaxial tension-compression conditions. The parameter was originally defined as,            f a f f N N E ' 2 2b b+c ' ' n, max f f 2 2 , (6) where σ ’ f and b are the axial fatigue strength coefficient and exponent respectively. Similarly ε ’ f and c represents the axial fatigue ductility coefficient and exponent. This parameter was modified for proportional and non-proportional multiaxial loading conditions of materials that fail predominantly by crack growth on planes of maximum tensile strain or stress, according to crack Mode I. In these materials, cracks nucleate in shear, but early life is controlled by crack growth on planes perpendicular to the maximum principal stress and strain. Socie [16] proposed a modification to the SWT parameter in order to take into account only stresses and strains occurring in the critical plane. This became the most well-known form of the parameter and is mathematically represented by 0 50 100 150 0 5 10 -3 0 200 400 600 800 1000 0 5 10 -3 0 50 100 150 -5 0 5 0 200 400 600 800 1000 0 2 4 10 -3