NASA Logo

NTRS - NASA Technical Reports Server

Back to Results
Advances in Fatigue and Fracture Mechanics Analyses for Metallic Aircraft StructuresThis 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.
Document ID
20000040431
Acquisition Source
Langley Research Center
Document Type
Technical Memorandum (TM)
Authors
Newman, J. C., Jr. (NASA Langley Research Center Hampton, VA United States)
Date Acquired
September 7, 2013
Publication Date
April 1, 2000
Subject Category
Metals And Metallic Materials
Report/Patent Number
NASA/TM-2000-210084
L-17955
NAS 1.15:210084
Report Number: NASA/TM-2000-210084
Report Number: L-17955
Report Number: NAS 1.15:210084
Meeting Information
Meeting: Aeronautical Fatigue
Location: Seattle, WA
Country: United States
Start Date: July 12, 1999
End Date: July 16, 1999
Funding Number(s)
PROJECT: RTOP 706-11-11-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

There are no records associated with this record.
No Preview Available