Advances in Structural Integrity Analysis Methods for Aging Metallic Airframe Structures with Local Damage

Abstract

Analysis methodologies for predicting fatigue-crack growth from rivet holes in panels subjected to cyclic loads and for predicting the residual strength of aluminum fuselage structures with cracks and subjected to combined internal pressure and mechanical loads are described. The fatigue-crack growth analysis methodology is based on small-crack theory and a plasticity induced crack-closure model, and the effect of a corrosive environment on crack-growth rate is included. The residual strength analysis methodology is based on the critical crack-tip-opening-angle fracture criterion that characterizes the fracture behavior of a material of interest, and a geometric and material nonlinear finite element shell analysis code that performs the structural analysis of the fuselage structure of interest.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 2003
Accession Number
ADP014079

Entities

People

  • Charles E. Harris
  • James C. Newman Jr.
  • James H. Starnes Jr.
  • Richard D. Young
  • Robert S. Piascik

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircrafts
  • Airframes
  • Aluminum Alloys
  • Buckling
  • Corrosion
  • Crack Tips
  • Fast Fractures
  • Finite Element Analysis
  • Fracture (Mechanics)
  • Fuselages
  • Internal Pressure
  • Measurement
  • Mechanics
  • Structural Components
  • Structural Integrity
  • Three Dimensional
  • Vehicles

Fields of Study

  • Engineering

Readers

  • Materials Science (Mechanical Engineering).
  • Structural Health Monitoring of Composite Structures.