Accession Number : ADA324121
Title : A Validated Finite Element Model of an F-111 Lower Wing Skin Structural Detail at Forward Auxilliary Spar Station (FASS) 281.28.
Descriptive Note : Technical note,
Corporate Author : DEFENCE SCIENCE AND TECHNOLOGY ORGANIZATION CANBERRA (AUSTRALIA)
Personal Author(s) : Keeley, D. ; Callinan, R. ; Sanderson, S.
PDF Url : ADA324121
Report Date : JUN 1996
Pagination or Media Count : 35
Abstract : This report describes an AMRL developed and validated Finite Element model of the F-111A lower wing skin (Serial Number A-10-824) at Forward Auxiliary Spar Station (FASS) 281.28 and constitutes part of an extensive AMRL bonded composite repair substantiation program initiated by the RAAF following the discovery of fatigue cracking at FASS 281.28 in an F-111C aircraft Strain data from the FE model is compared with measured strain gauge data from an F-111A static test wing under Cold Proof Loading Test (CPLT) or limit conditions. A relationship between nominal section stress at FASS 281.28 and local bending moment is established. The FE model will be further developed to include the fatigue crack, the adhesive and the boron epoxy patch.
Descriptors : *MATHEMATICAL MODELS, *FINITE ELEMENT ANALYSIS, *WINGS, *SKIN(STRUCTURAL), *SPARS, STRESSES, STATIONS, AUXILIARY, FATIGUE LIFE, VALIDATION, COMPOSITE MATERIALS, CRACKS, REPAIR, STRAIN GAGES, BONDING, FATIGUE(MECHANICS), EPOXY COMPOUNDS, AUSTRALIA, BORON, BENDING MOMENTS.
Subject Categories : Military Aircraft Operations
Distribution Statement : APPROVED FOR PUBLIC RELEASE