Pages that link to "Item:Q1207273"
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The following pages link to Analysis of cracks in aging aircraft structures, with and without composite-patch repairs (Q1207273):
Displaying 16 items.
- Mixed-mode 3-D crack propagation of repaired thin aluminum panels using single-side composite patches (Q373369) (← links)
- Fracture and fatigue analysis of curved or kinked cracks near fastener holes (Q671731) (← links)
- Approximate methods for analyzing the growth of large cracks in fatigue damaged aircraft sheet material and lap joints (Q671733) (← links)
- Mixed mode fatigue growth of curved cracks emanating from fastener holes in aircraft lap joints (Q1271599) (← links)
- Analysis of out-of-plane bending in one-sided bonded repair (Q1282804) (← links)
- Residual strength of aircraft panels with multiple site damage (Q1315902) (← links)
- Recent advances in the alternating method for elastic and inelastic fracture analyses (Q1365612) (← links)
- Theoretical modeling of crack arrest by inserting interference fit fasteners (Q1412696) (← links)
- Fracture analysis of cracked orthotropic skin panels with riveted stiffeners (Q1573197) (← links)
- Boundary element analysis of stiffened panels with repair patches (Q1654703) (← links)
- An elastic-plastic finite element alternating method for analyzing wide- spread fatigue damage in aircraft structures (Q1892690) (← links)
- Residual strength prediction for aircraft panels with multiple site damage, using the ''EPFEAM'' for stable crack growth analysis (Q1898444) (← links)
- Effects of geometric nonlinearities on damage propagation in patched beam-plates subjected to pressure loading (Q1956293) (← links)
- DBEM and FEM analysis on non-linear multiple crack propagation in an aeronautic doubler-skin assembly (Q2489077) (← links)
- An aging aircraft's wing under complex multiaxial spectrum loading: Fatigue assessment and repairing (Q2489084) (← links)
- Global/Local FEM-BEM Stress Analysis of Damaged Aircraft Structures (Q3117458) (← links)
