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

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.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1996
Accession Number
ADA322078

Entities

People

  • A. Searl
  • J. Paul
  • P. Chapman

Organizations

  • Defence Science and Technology Group

Tags

Communities of Interest

  • Air Platforms
  • Space

DTIC Thesaurus Topics

  • Air Force
  • Aircrafts
  • Airframes
  • Boundaries
  • Damage Tolerance
  • Elements
  • Engineering
  • Finite Element Analysis
  • Geometry
  • Load Distribution
  • Materials
  • Mechanical Engineering
  • Plastic Deformation
  • Stresses
  • Tactical Aircraft
  • Three Dimensional
  • Two Dimensional

Readers

  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)
  • Mechanical Engineering/Mechanics of Materials.
  • Parasitology and Pharmacology of Malaria.