Accession Number : ADA305823
Title : Cyclic Debonding of Adhesive Joints, Summary Report.
Corporate Author : BOEING COMMERCIAL AIRPLANE CO SEATTLE WA
Personal Author(s) : Hoffman, D. J. ; June, R. R.
PDF Url : ADA305823
Report Date : JUN 1973
Pagination or Media Count : 67
Abstract : Bonded lap joints were manufactured and tested under static and fatigue loading. Specimens were designed to fail in the bondline, and all fatigue tests included monitoring the crack growth to failure. Detailed crack length readings for 106 fatigue specimens are contained in NASA CR-112219--Cyclic Debonding of Adhesive joints: Data Report. Test specimens included aluminum details joined by two different adhesives. Specimens also included titanium and boron-epoxy details joined by an epoxy laminating resin. Additional program variables included bondline thickness, adherend and spice plate thickness, specimen width, and specimen fabrication procedure. Adhesive aging, a previously unobserved effect, was found to be generally detrimental to the lives of most of the specimens bonded with one adhesive system. Adhesive material was found to have a major influence on debond rate. Co-cured titanium/boron-epoxy specimens were found to resist debonding better than specimens fabricated with a sequential cure. Splice plate thickness and test section width were found to have little effect on debond rate. The data also suggested the existence of an optimum bondline thickness. jg p3
Descriptors : *BONDED JOINTS, *EPOXY RESINS, *ADHESIVE BONDING, THICKNESS, AGING(MATERIALS), MATERIALS, LAMINATES, LOADS(FORCES), FAILURE, FABRICATION, TEST EQUIPMENT, CRACK PROPAGATION, PLATES, ALUMINUM, LENGTH, FATIGUE(MECHANICS), TITANIUM, BORON, STATICS, ADHESIVES, FATIGUE TESTS(MECHANICS), SPLICES.
Subject Categories : Adhesives, Seals and Binders
Distribution Statement : APPROVED FOR PUBLIC RELEASE