Pages that link to "Item:Q1315902"
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The following pages link to Residual strength of aircraft panels with multiple site damage (Q1315902):
Displaying 10 items.
- 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)
- Ensuring structural damage tolerance of russian aircraft (Q1016285) (← links)
- Fatigue, residual strength and non-destructive tests of an aging aircraft's wing detail (Q1016306) (← links)
- The elastic-plastic finite element alternating method (EPFEAM) and the prediction of fracture under WFD conditions in aircraft structures. III: Computational predictions of the NIST multiple site damage experimental results (Q1365780) (← links)
- Corrosion fatigue and multiple site damage reliability analysis. (Q1422002) (← links)
- Approximate method for stress intensity factors determination in case of multiple site damage (Q2285271) (← links)
- An aging aircraft's wing under complex multiaxial spectrum loading: Fatigue assessment and repairing (Q2489084) (← links)
- Analytical prediction of crack coalesce in multiple site damaged structures (Q2576481) (← links)
- (Q3126654) (← links)