State-of-the-art nonlinear finite element analysis techniques are evaluated by applying them to a realistic aircraft structural component. A wing panel from the V-22 tiltrotor aircraft is chosen because it is a typical modern aircraft structural component for which there is experimental data for comparison of results. From blueprints and drawings, a very detailed finite element model containing 2284 9-node Assumed Natural-Coordinate Strain elements was generated. A novel solution strategy which accounts for geometric nonlinearity through the use of corotating element reference frames and nonlinear strain-displacement relations is used to analyze this detailed model. Results from linear analyses using the same finite element model are presented in order to illustrate the advantages and costs of the nonlinear analysis as compared with the more traditional linear analysis.
An accurate nonlinear finite element analysis and test correlation of a stiffened composite wing panel
1991-01-01
Aufsatz (Konferenz)
Keine Angabe
Englisch
"Buckling Predictions of Stiffened Wing Panels Using Nonlinear Finite Element Analysis"
British Library Conference Proceedings | 2000
|All new multi-purpose internally stiffened composite wing sub-panel
Europäisches Patentamt | 2024
|ALL NEW MULTI-PURPOSE INTERNALLY STIFFENED COMPOSITE WING SUB-PANEL
Europäisches Patentamt | 2022
|WING ASSEMBLY HAVING DISCRETELY STIFFENED COMPOSITE WING PANELS
Europäisches Patentamt | 2022
|Wing assembly having discretely stiffened composite wing panels
Europäisches Patentamt | 2023
|