24th Congress of International Council of the Aeronautical Sciences, 29 August-3, September 2004, Yokohama, Japan
Paper ICAS 2004-5.4.R.1

VIRTUAL TESTING OF AIRCRAFT FUSELAGE STIFFENED PANELS

P. Linde, J. Pleitner, W. Rust*
Airbus, Hamburg, Germany ; *CAD-FEM GmbH, Burgdorf & University of Applied Sciences, Hannover, Germany

Keywords: stiffened shell structure, FE limit load analysis, quasi-static dynamic solution, virtual testing

The virtual testing of stiffened fuselage panels, described here, is based on a development project aiming at reducing the amount of experimental tests, and narrowing the numerical predictions to experimental results. Parametric modelling of these panels, including skin, stringer, frames, clips and connections is described.

view full paper