NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Micromechanics of compression failures in open hole composite laminatesThe local softening in the damage zone that precedes compression failures in laminates with holes was modeled using a Dugdale-type approach, and the calculated load to damage-size relationships were compared to the actual data obtained in two composite systems, AS4/PEEK and T2C145/F155, loaded to compression. The comparison indicates that the Dugdale model, which works well for metals, did not accurately predict the load-damage zone size relationship in these specimens. Possible reasons for the poor agreement are considered to be the fact that the constitutive relationship used in the Dugdale model is not an accurate description of material response in the crush zone, and the fact that the crush zone size is measured on the surface of the specimen, while this size is not an accurate indication of the actual crush zone size through the laminate.
Document ID
19890048938
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Guynn, E. Gail
(Texas A&M Univ. College Station, TX, United States)
Bradley, Walter L.
(Texas A & M University College Station, United States)
Elber, Wolf
(U.S. Army, Aerostructures Directorate, Hampton VA, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1989
Subject Category
Structural Mechanics
Meeting Information
Meeting: Symposium on Composite Materials: Fatigue and Fracture
Location: Cincinnati, OH
Country: United States
Start Date: April 27, 1987
End Date: April 28, 1987
Accession Number
89A36309
Funding Number(s)
CONTRACT_GRANT: NAG1-659
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available