Title: Analysis of Wing Flexure Deformation Based on ANSYS
Author(s): Xueyan Zhang, Yan Zhao, Fan Si
Published in: Proceedings of IEEE/ION PLANS 2018
April 23 - 26, 2018
Hyatt Regency Hotel
Monterey, CA
Pages: 190 - 196
Cite this article: Zhang, Xueyan, Zhao, Yan, Si, Fan, "Analysis of Wing Flexure Deformation Based on ANSYS," Proceedings of IEEE/ION PLANS 2018, Monterey, CA, April 2018, pp. 190-196.
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Abstract: To explore the mechanical effects of the wing subjected to the aerodynamic loads and turbulence during the flight, this paper presents a finite element analysis of wing flexure deformation. Firstly, a large-aspect-ratio wing model is established. Taking material characteristics, wing structure and design principle into account, the assembly wing model consists of the thin skin, two spars and multi ribs. NACA2412 is chosen as the airfoil, because it shows a better aerodynamic performance according to the calculation. Two spars mainly bear the bending moment and shear force, which are made of titanium alloy to ensure sufficient rigidity. The skin and wing ribs are made of aluminum alloy in order to lighten the structural weight. Then, a modal analysis is applied. The natural frequencies and modal shapes of the first four orders are obtained through the pre-stress modal analysis, which provides data for further studies, especially the harmonic response analysis. The results of the modal analysis help designers to minimize excitation on the natural frequencies and prevent the wing from the flutter. Finally, a transient structural dynamic analysis is carried out. During the flight, the wing is mainly subjected to the structural gravity, component’s point force and aerodynamic loads. By simulating multiple load distributions in ANSYS, the deformation, stress and strain of the wing are calculated. According to the results, designers can put emphasis on strengthening and testing the stress concentration area and large deformation area. The obtained deformation angle benefits the modeling of the wing flexure deformation to decrease the influence of wing flexure in transfer alignment. Overall, the simulation results show that the scheme is feasible and improve the informationization degree of the wing.