Propagation rate of large cracks in stiffened panels under tension loading

Towards a Unified Fatigue Life Prediction Method for Marine Structures

“…The selected case is the fatigue test of a large stiffened plate with a throughthickness crack simulating the deck cracks of a tanker by Mahmoud and Dexter (2005). Based on the calculated SIFs of the center penetrated crack in the stiffened plate using the finite element method, the UFLP model was used to predict the fatigue crack growth of the stiffened plate considering the effect of the residual stress.…”

“…The weld residual stress distribution along the transection of the stiffened plate, which is taken from the reference (Mahmoud and Dexter, 2005), is shown in Fig. The weld residual stress distribution along the transection of the stiffened plate, which is taken from the reference (Mahmoud and Dexter, 2005), is shown in Fig.…”

Fatigue strength determination of ship structural joints

“…The design curve Np -considered as a line which defines fatigue life up to a given phase of cracking (usually up to complete damage of a joint) -is defined as a line parallel to the basic one, shifted to the left by a multiple of the standard deviation d, namely: (4) where: N p -fatigue life of element under the stress σ, A -constant which describes the curve σ-N, d -standard deviation of log(N p ) value, m -material constant, k -coefficient.…”

“…1÷4 are presented examples of fatigue cracks detected on various ships and located in different zones of their structure [3,4,5,6]. This paper initiates the series of publications devoted to the determining of fatigue strength of ship structure joints, in which problems of fatigue cracking and estimation of fatigue life of ship structure joints will be successively discussed both on local and zone level.…”

Retardation of fatigue crack growth in aircraft aluminium alloys via laser heating – Numerical prediction of fatigue crack growth

“…Hence, because precise predictions of fatigue crack growth are required for damage tolerant design, several recent studies have addressed the prediction of fatigue crack growth in integral aircraft aluminium structures including residual stress effects [4][5][6]. The approach that has found common acceptance consists of the following steps [4,6,[9][10][11][12][13][14][15][16][17][18][19]:…”