Accession Number : ADA322078

Title :   Elastic/Plastic Finite Element Analysis of the F-111 Fuel Flow Vent Hole Number 13.

Descriptive Note : Technical rept.,

Corporate Author : DEFENCE SCIENCE AND TECHNOLOGY ORGANIZATION CANBERRA (AUSTRALIA)

Personal Author(s) : Paul, J. ; Chapman, P. ; Searl, A.

PDF Url : ADA322078

Report Date : NOV 1996

Pagination or Media Count : 93

Abstract : A detailed plasticity finite element stress analysis is presented for a fatigue critical location, at Fuel Flow Vent Hole #13 (FFVH #13) in the Wing Pivot Fitting of the Royal Australian Air Force's F-111 aircraft. The D6ac material behaviour was represented by a unified constitutive model which is considered to be particularly accurate for modeling plastic deformation through several cycles of non-symmetric loading. The aim of the present work is to generate the residual stress distributions following one (or more) applications of Cold Proof Load Test, as an input to the Durability And Damage Tolerance Analyses (DADTA) for FFVH #13. The mesh refinements and the selection of boundary conditions for a substructure model representing the immediate vicinity of FFVH #13 are discussed in detail. The results from the numerical analysis were correlated with full-scale wing test strain data and showed good agreement The residual stress distributions obtained here are considered to be significantly more accurate than what has previously been used for the DADTA of FFVH #13.

Descriptors :   *FITTINGS, *FUEL LINES, *TILT WINGS, PLASTIC DEFORMATION, FINITE ELEMENT ANALYSIS, ASYMMETRY, RESIDUAL STRESS, TOLERANCE, FATIGUE(MECHANICS), AUSTRALIA, PIVOTS, STRESS RELAXATION.

Subject Categories : Pumps, Filters, Pipes, Tubing, Fittings & Vlvs
      Attack and Fighter Aircraft

Distribution Statement : APPROVED FOR PUBLIC RELEASE