Finite Element Analysis of an F-111 Lower Wing Skin Fatigue Crack Repair.

Abstract

In this report a three dimensional finite element (F. E.) model has been developed for a structural detail in an F-111 lower wing skin. The location of interest is a fuel flow groove in the lower wing skin where cracking had occurred in service on aircraft A8-145. Detailed models were developed for (1) un-cracked structure; (2) he cracked structure and (3) the repaired structure, using bonded composite patch for the repair. The objective of this work is to validate the design analysis used by the RAAF, using an independent approach for the stress analysis. The F.E. model has been validated using strain gauge results from a full scale test wing. The results of the F.E. analysis are shown to compare favourably with closed form solutions used by the RAAF (RAAF Engineering Standard C5033) in the original design of the repair. Thus the present work provides a basis for confidence in the design procedures contained in RAAF Engineering Standard C5033.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1997
Accession Number
ADA324657

Entities

People

  • D. Keeley
  • R. J. Callinan
  • S. Sanderson

Organizations

  • Defence Science and Technology Group

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Adhesives
  • Aircrafts
  • Airframes
  • Composite Materials
  • Engineering
  • Engineers
  • Finite Element Analysis
  • Geometry
  • Materials
  • Materials Testing
  • Mechanical Properties
  • Mechanics
  • Strain Gages
  • Stress Strain Relations
  • Stresses
  • Tensile Strength
  • Three Dimensional

Readers

  • Aerospace Engineering
  • Facility/Structural Engineering.
  • Materials Science (Mechanical Engineering).