A linear elastic stress analysis was made of a centrally cracked sheet stiffened by riveted, uniformly spaced and sized stringers. The stress intensity factor for the sheet and the load concentration factor for the most highly loaded stringer were determined for various numbers of broken stringers. A broken stringer causes the stress intensity factor to be very high when the crack tip is near the broken stringer, but causes little effect when the crack tip extends beyond several intact stringers. A broken stringer also causes an increase in the load concentration factor of the adjacent stringers. The calculated residual strengths and fatigue-crack-growth lives of a stiffened aluminum sheet with a broken stringer were only slightly less than...
The problem of cracked plates stiffened by three-dimensional stringers is investigated using transmi...
A theoretical formulation is presented for determining stress intensity factors for cracks in an inf...
The article presents two-stage fatigue life evaluation of a stiffened aluminium aircraft fuselage pa...
A coefficient is obtained for determining the effect of a reinforcing stringer on the stress concent...
The effect of several stringers on the stress intensity factors at the tips of a crack is considered...
This paper presents a stress intensity factor solution for cracks located in panels reinforced with ...
Several intact or broken stringers which are continuously attached to a cracked orthotropic sheet th...
This paper presents a stress intensity factor solution for cracks located in panels reinforced with ...
This thesis presents a study about the determination of the stress intensity factors in cracked shee...
The publications on fracture of metals emphasize the importance of avoiding so far as possible al...
The deformation of two sheet-stringer panels subjected to end compression under carefully controlled...
The stress-intensity factors are determined for a cracked orthotropic sheet adhesively bonded to an ...
A closed form solution of the Stress Intensity Factor (SIF) for stiffened flat sheets, typically use...
A method of strength analysis of short sheet-stringer panels subjected to compression is presented w...
Stress-intensity factors are determined for a cracked infinite sheet adhesively bonded to a stringer...
The problem of cracked plates stiffened by three-dimensional stringers is investigated using transmi...
A theoretical formulation is presented for determining stress intensity factors for cracks in an inf...
The article presents two-stage fatigue life evaluation of a stiffened aluminium aircraft fuselage pa...
A coefficient is obtained for determining the effect of a reinforcing stringer on the stress concent...
The effect of several stringers on the stress intensity factors at the tips of a crack is considered...
This paper presents a stress intensity factor solution for cracks located in panels reinforced with ...
Several intact or broken stringers which are continuously attached to a cracked orthotropic sheet th...
This paper presents a stress intensity factor solution for cracks located in panels reinforced with ...
This thesis presents a study about the determination of the stress intensity factors in cracked shee...
The publications on fracture of metals emphasize the importance of avoiding so far as possible al...
The deformation of two sheet-stringer panels subjected to end compression under carefully controlled...
The stress-intensity factors are determined for a cracked orthotropic sheet adhesively bonded to an ...
A closed form solution of the Stress Intensity Factor (SIF) for stiffened flat sheets, typically use...
A method of strength analysis of short sheet-stringer panels subjected to compression is presented w...
Stress-intensity factors are determined for a cracked infinite sheet adhesively bonded to a stringer...
The problem of cracked plates stiffened by three-dimensional stringers is investigated using transmi...
A theoretical formulation is presented for determining stress intensity factors for cracks in an inf...
The article presents two-stage fatigue life evaluation of a stiffened aluminium aircraft fuselage pa...