Review of Improved Methods for Analysing Load Attraction and Thermal Effects in Bonded Composite Repair Design

Abstract

Adhesive bonded repairs to aircraft involving metallic and composite structures have proven to be an effective, efficient means of repair and life extension. The simplified closed form equations used by the RAAF in an Engineering Standard (DEF(AUST)90O5) have proven to be effective and conservative. Recent work, however, has identified improved equations to account for load attraction into the stiffened repaired area, and evaluate the thermally induced stresses in the repaired structure and the patch. The improved equations were compared with the current methods, using the repair to a 2024-T851 aluminium alloy F-111 lower wing skin with a boron epoxy repair patch, bonded with FM-73 film adhesive. The improved methods will reduce the unnecessary conservatism inherent in DEF(AUST)9OO5 and therefore allow some repairs to proceed where they may otherwise have been rejected. Repairs will also be designed to operate more efficiently.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Dec 01, 2003
Accession Number
ADA424267

Entities

People

  • A. B. Harman
  • K. F. Walker

Organizations

  • Defence Science and Technology Group

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Adhesives
  • Aircrafts
  • Alloys
  • Aluminum
  • Aluminum Alloys
  • Composite Materials
  • Engineering
  • Information Systems
  • Materials
  • Shear Modulus
  • Shear Stresses
  • Standards
  • Stars
  • Stresses
  • Structural Integrity
  • Universities
  • Vehicles

Readers

  • Reinforced Composite Materials
  • Systems Analysis and Design
  • Trauma Surgery or Emergency Medicine.