Damage tolerance modelling of fibre/metal laminate fuselage structures

Jack W. Langelaan, Leo J.J. Kok

Research output: Contribution to journalConference article

2 Scopus citations

Abstract

It has been found that load state plays an important role in crack growth rates in fibre/metal laminates. It is expected that material anisotropy is a major cause, and that residual strength of reinforced panels may be affected. Accordingly, an extension of the displacement compatibility method of damage tolerance analysis is presented. The present work accounts for material anisotropy and panel load condition. Comparisons with finite element results show that the extended displacement compatibility method gives accurate stress intensity results for anisotropic panels under tension and under shear loading. The stress intensities obtained using the displacement compatibility method have been used in conjunction with material R-curves to calculate residual strength curves of stiffened panels.

Original languageEnglish (US)
Pages (from-to)2809-2818
Number of pages10
JournalCollection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
Volume4
StatePublished - Jan 1 1997
EventProceedings of the 1997 38th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Part 4 (of 4) - Kissimmee, FL, USA
Duration: Apr 7 1997Apr 10 1997

All Science Journal Classification (ASJC) codes

  • Architecture
  • Materials Science(all)
  • Aerospace Engineering
  • Mechanics of Materials
  • Mechanical Engineering

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