NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Development of a laminate fatigue analysisA fatigue analysis technique developed to predict damage growth in notched laminates is described. Features of the analysis include: criteria to relate matrix failure to cyclic stresses in and between plies; correlation of delamination growth with strain-release rate; and in-plane shear modulus change is related to cyclic shear stresses. A simplified finite element model is used to determine stresses in laminates that contain matrix damage. Failure criteria are integrated with the finite element model to form the fatigue analysis.
Document ID
19800019938
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Roderick, G. L. (NASA Langley Research Center Hampton, VA, United States)
Obrien, T. K. (Army Aviation Research and Development Command Hampton, VA, United States)
Whitcomb, J. D. (NASA Langley Research Center)
Date Acquired
August 10, 2013
Publication Date
January 1, 1980
Publication Information
Publication: Selected NASA Res. in Composite Mater. and Struct.
Subject Category
Composite Materials
Accession Number
80N28439
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Document Inquiry

Available Downloads

There are no available downloads for this record.

Related Records

IDRelationTitle19800019935Collected WorksSelected NASA research in composite Materials and structures
No Preview Available