AIRCRAFT CRASHES ON THE RUNWAY: DEVELOPMENT OF SUPER ELEMENT FOR NONLINEAR ANALYSIS OF BEAM

CRASH DES AVIONS SUR PLATE: DEVELOPPMENT D'UN SUPER-ELEMENT POUR L'ANALYSE NON LINEAIRE D'UNE POUTRE

A thin shell super finite element was developed to study the pre and post elastoplastic buckling behavior of an embedded beam subject to a lateral load. The finite element is derived from a local behavior law analogous in its form to the law of the global behavior of the structure. Analysis results and quasi-static and dynamic tests on reduced scale models of aircraft structures were compared. This element alone cannot be a solution to the response. It is necessary to simultaneously introduce into the finite element model extra degrees of freedom to represent the plastic joints, and to restrain the displacement of the super element nodes to be representative of the real displacements of the structure. By replacing a large part of a structure by a large element, specific to a given behavior, computation time is considerably reduced.

• Corporate Authors:

  Institut de Mecanique des Fluides

  Lille,   France 
• Authors:
  • Geoffroy, P
• Publication Date: 1987-12-15

Language

• French

Media Info

• Pagination: 35 p.

Subject/Index Terms

• TRT Terms: Aircraft; Buckling; Finite element method; Nonlinear systems; Structural analysis
• Uncontrolled Terms: Lateral loads; Nonlinearity
• Subject Areas: Aviation; Highways; Safety and Human Factors; Vehicles and Equipment;

Filing Info

• Accession Number: 00484724
• Record Type: Publication
• Source Agency: National Technical Information Service
• Report/Paper Numbers: ETN-88-93101
• Files: TRIS
• Created Date: Jun 30 1989 12:00AM