Accession Number : ADP005169

Title :   Composite Repair of Cracked Aluminum Structure,

Corporate Author : AIR FORCE WRIGHT AERONAUTICAL LABS WRIGHT-PATTERSON AFB OH

Personal Author(s) : Kelly,Larry G.

Report Date : OCT 1986

Pagination or Media Count : 6

Abstract : This paper discusses the use of bonded composite patches for repair of a wide range of typical fatigue cracked and otherwise damaged aluminum structural panels. Experimental data on stress intensity and crack growth characteristics were obtained to evaluate the advantages of such repairs. A range of metal thickness and patch parameters (thickness, orientation, bonding temperature) were tested. Edge crack 4 inch by 18 inch 2024T3 aluminum panels were patched and fatigue behavior evaluated under constant amplitude and the Falstaff flight spectrum loading. The results showed panel thickness and fatigue test load spectrum to be important parameters.

Descriptors :   *AIRCRAFT MAINTENANCE, *AIRCRAFT PANELS, *COMPOSITE MATERIALS, ALUMINUM ALLOYS, CRACKS, REPAIR, STRESS CONCENTRATION, CRACK PROPAGATION, FATIGUE TESTS(MECHANICS), EPOXY LAMINATES, SYMPOSIA

Distribution Statement : APPROVED FOR PUBLIC RELEASE