NDLI: Advances in fatigue and fracture mechanics analyses for metallic aircraft structures

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Advances in fatigue and fracture mechanics analyses for metallic aircraft structures

Content Provider	NASA Technical Reports Server (NTRS)
Author	Newman Jr., J. C.
Copyright Year	2000
Description	This paper reviews some of the advances that have been made in stress analyses of cracked aircraft components, in the understanding of the fatigue and fatigue-crack growth process, and in the prediction of residual strength of complex aircraft structures with widespread fatigue damage. Finite-element analyses of cracked metallic structures are now used to determine accurate stress-intensity factors for cracks at structural details. Observations of small-crack behavior at open and rivet-loaded holes and the development of small-crack theory has lead to the prediction of stress-life behavior for components with stress concentrations under aircraft spectrum loading. Fatigue-crack growth under simulated aircraft spectra can now be predicted with the crack-closure concept. Residual strength of cracked panels with severe out-of-plane deformations (buckling) in the presence of stiffeners and multiple-site damage can be predicted with advanced elastic-plastic finite-element analyses and the critical crack-tip-opening angle (CTOA) fracture criterion. These advances are helping to assure continued safety of aircraft structures.
File Size	2655709
File Format	PDF
Language	English
Publisher Date	2000-04-01
Access Restriction	Open
Subject Keyword	Metals And Metallic Materials Metal Fatigue Stress Concentration Stress Analysis Fracture Mechanics Riveted Joints Metals Crack Closure Residual Strength Crack Propagation Finite Element Method Cracks Stress Intensity Factors Plastic Properties Damage Aircraft Structures Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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