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Detailed Analysis and Test Correlation of a Stiffened Composite Wing Panel
D.D. Davis Jr.
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 (shown in Fig. 1) 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 supplied by the Bell Helicopter Textron Corporation, a very detailed finite element model containing 2284 9-node Assumed Natural-Coordinate Strain (ANS) elements was generated. A novel solution strategy which accounts for geometric nonlinearity through the us~ 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. Strain predictions from both the linear and nonlinear stress analyses are shown to compare well with experimental data up through the Design Ultimate Load (DUL) of the panel. However, due to the extreme nonlinear response of the panel, the linear analysis was not accurate at loads above the DUL. The nonlinear analysis more accurately predicted the strain at high values of applied load, and even predicted complicated nonlinear response characteristics, such as load reversals, at the observed failure load of the test panel. In order to understand the failure mechanism of the panel, buckling and first-ply failure analyses were performed. The buckling load was 17% above the observed failure load while first-ply failure analyses indicated significant material damage at and below the observed failure load.
17th European Rotorcraft Forum 1991, Berlin
21,0 x 29,7 cm, 15 Seiten
DGLR-Bericht, 1991, 1991-08, 17th European Rotorcraft Forum Proceedings; 1991; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn
Dieser Aufsatz ist nicht Teil der Veröffentlichung!
Stichworte zum Inhalt:
loads (forces), tilt rotor aircraft, structural design, structural dynamic analysis, v-22 tilt rotor aircraft, buckling
Dieses Dokument ist Teil einer übergeordneten Publikation:
17th European Rotorcraft Forum Proceedings