Page 290 - Marine Structural Design
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266                                                     Part N Ultimate Strength


                       om = min(ouf ,cup)                                            (13.41)
                  where o~ and  cup are the ultimate beam-column failure values  of the panel when  lateral
                  pressure causes compression of stiffener flange and plating respectively. According to Hughes
                  (1983), a solution may be obtained by solving the following equations for stiffener failure,

                                                                                     (13.42)

                  and for plate failure,




                  where A  is  the  initial  eccentricity, So and  Mo are  the  maximum  deflection and  bending
                  moment  due to  lateral  load  alone;  A,,  is  the  eccentricity caused by  reduced  stiffness of
                  compressed plating; I and A are respectively the second moment and the sectional area of the
                  panel,  considering bp (panel width)  is  fully effective where  as I,  and  A,  are the  similar
                  properties but for transformed section replacing b,  by  b,  (effective width); y  is the distance
                  from the panel neural axis to the stiffener flange and yp to the plating of the transformed
                  section; @ is the magnification factor for combined loading.
                  13.4.3  Crack Propagation Prediction
                  To predict the crack propagation and fatigue life, the Paris-Erdogan equation is used
                       da
                       -=   CAK"                                                     (13.44)
                       dN
                  where a is the crack size, N is the number of cycles, AK is the stress range intensity factor and
                  C and m are material parameters. The stress intensity factor is given by:
                       AK = AoY(a)&                                                  (13.45)

                  where Aois the stress range and Y(a) is the geometry function.
                  If Y(a)=Y is a constant and tn&,  then integration of Eq(13.44) gives
                                                   -
                                                    I
                       a(t) = [ai'*'   +(1  -~)C(ACTY&)"'~,~]'-~                     (1 3.46)
                                     2
                  where a,,  is the initial crack size, and the complete fatigue life T, is equaI to the sum of the
                  time to crack propagation Tp and the time to crack initiation
                         = kTp                                                       (1 3.47)
                  where k can vary from 0.1 to 0.15. The crack size is assumed to have a normal distribution
                  with the mean and variance, see Guedes Soares and Garbatov (1996,1999).
                  Two types of cracks are considered in the stiffened panel, one propagating away from the
                  stiffener in a transverse direction decreasing the width of attached plating, and the other across
                  the web of stiffener decreasing the web height.
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