NDLI: Fatigue behavior of adhesively bonded joints

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Fatigue behavior of adhesively bonded joints

Content Provider	NASA Technical Reports Server (NTRS)
Author	Mall, S.
Copyright Year	1983
Description	The fatigue damage mechanism of composite to composite adhesively bonded joints was characterized. The mechanics of the possible modes of fatigue damage propagation in these joints when subjected to constant amplitude cyclic mechanical loading were investigated. The possible failure modes in composite bonded joints may be cyclic debonding (i.e., progressive separation of the adhesive), interlaminar damage (delamination), adherend fatigue or a combination of these. Two composite systems - graphite/epoxy adhesively bonded to graphite/epoxy and Kevlar 49/epoxy adhesively bonded to Kevlar 49/epoxy were investigated. Both composite systems consisted of quasi-isotropic lay-ups, i.e., 0 deg/-45 deg/+45 deg/90 degs. The two adhesives, employed in the study were (1) EC 3445 with cure temperature of 250 F for secondary bonding and (2) FM 300 with cure temperature of 350 F for co-cure bonding.
File Size	226064
Page Count	11
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19830028238
Archival Resource Key	ark:/13960/t46q6sj3d
Language	English
Publisher Date	1983-08-31
Access Restriction	Open
Subject Keyword	Structural Mechanics Joints Junctions Airframes Helicopters Fatigue Materials Failure Modes Curing Graphite-epoxy Composites Adhesive Bonding Peeling Kevlar Trademark 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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