The Dynamic Behaviour of Stiffened Composite Fuselage Shell Structures,

Abstract

This report presents an overview of the development of a computer model for analysing the crash response of stiffened composite fuselage structures together with the experimental validation program. Using a finite element formulation based on Reissner/Mindlin plate theories, the numerical model can treat stiffened laminated shell buckling, large deflections, nonlinear material behaviour and element failure. Numerical results are presented for several 'test cases', although experimental comparisons are not yet available. Details on the design and construction of our first prototype composite fuselage model are also provided together with a description of the crash test facility. (JES)

Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1988
Accession Number
ADP005809

Entities

People

  • J. S. Hansen
  • R. C. Tennyson

Organizations

  • AGARD

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Absorption
  • Aircrafts
  • Airframes
  • Buckling
  • Buildings And Structures
  • Composite Materials
  • Computers
  • Construction
  • Crashworthiness
  • Deflection
  • Fuselages
  • Luxembourg
  • Materials
  • Mechanical Structure
  • Models
  • Structural Components
  • Test Facilities

Fields of Study

  • Engineering
  • Physics

Readers

  • Computer Science.
  • Structural Dynamics.