Engineering Approach to Damage Tolerance Analysis of Fuselage Skin Repairs.

Abstract

A simplified approach to damage tolerance analysis of riveted fuselage skin repairs has been incorporated in a new user-friendly software package, Repair Assessment Procedure and Integrated Design (RAPID). In this study, the damage tolerance analysis methodology in RAPID was evaluated in terms of the fastener loads, stress-intensity factor solutions, crack growth, residual strength, and inspection schedule. Three example problems, each representing a typical fuselage skin repair configuration, were analyzed. The analysis results obtained from RAPID were compared with results generated using a Representative Original Equipment Manufacturer (ROEM) method and a special purpose finite element program for fracture mechanics analysis and crack growth simulation in layered two dimensional structures. In general, results generated using RAPID were in good agreement with results generated using the ROEM method and the finite element code.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1996
Accession Number
ADA320011

Entities

People

  • C. A. Bigelow
  • C. C. Chen
  • J. G. Bakuckas Jr.
  • Jiaxin Yu
  • P. W. Tan

Organizations

  • Federal Aviation Administration

Tags

DTIC Thesaurus Topics

  • Damage
  • Damage Tolerance
  • Engineering
  • Fracture (Mechanics)
  • Fuselages
  • Mechanics
  • Stress Intensity Factors
  • Structural Components
  • Two Dimensional
  • User Friendly

Fields of Study

  • Engineering

Readers

  • Computational Modeling and Simulation
  • Structural Health Monitoring of Composite Structures.