Analytical methodology for the design of load-bearing anisotropic panels for the wingbox of a light aircraft subject to geometric nonlinearity under compression

Year 2024, Volume: 42 Issue: 6, 1756 - 1762, 09.12.2024

Oleg Mitrofanov Maksim Shkurin

Abstract

The subject of this research is the upper load-bearing anisotropic panels of the wingbox of the forward-swept wing of a light aircraft, exposed mainly to longitudinal compression. The panels are fixed along the long sides. The paper considers how to determine the minimum thickness of these panels at a postbuckling state under loads exceeding the operational level. Based on the analytical solution for geometrically nonlinear problems obtained by the Bub-nov-Galerkin method, a technique for designing anisotropic panels at a postbuckling state is proposed. To determine the panel’s thickness, the strength criteria for a monolayer of the composite material were used. The main result of the work is a nonlinear equation for the panel’s minimum thickness. It incorporates the equivalence of the membrane stresses due to panel buckling and the limit stresses of the composite package monolayer.

Keywords

Geometrically Non-Linear Behavior, Anisotropic Material, Rectangular Panels, Longitudinal Compression

References

• REFERENCES
• [1] Degenhardt R, Teßmer J. Advances in computational stability analysis of composite aerospace structures. AIP Conf Proc 2010:1281. [CrossRef]
• [2] Degenhardt R, Castro S, Arbelo M, Zimmerman R, Khakimova R, Kling A. Future structural stability design for composite space and airframe structures. Thin-Walled Structr 2014;81:29-38. [CrossRef]
• [3] Mitrofanov OV. Applied methods for designing load-bearing panels from composite materials. Moscow, Russia: Sputnik+ Company; 2003.
• [4] Mitrofanov O. Designing load-bearing panels of aircraft structures for the post-buckling state. Moscow: MAI;2020.
• [5] Ni X, Prusty G, Hellier A. Buckling and post-buckling of isotropic and composite stiffened panels: a review on analysis and experiment (2000-2012). Int J of Maritime Eng 2021;157. [CrossRef]
• [6] Gavva L, Firsanov V. Analytical review of account methods and experimental approaches to stress-strain state ınvestigation of structurally-anisotropic aircraft panels made from composite materials. IOP Conf Ser Mater Sci Eng 2020;927:012067. [CrossRef]
• [7] Falzon BG, Aliabadi MH. Buckling and post-buckling structures II: Experimental, analytical and numerical studies. Comput Exp Methods Struct 2018;9:308. [CrossRef]
• [8] Qiao P, Shan L. Explicit local buckling analysis of rotationally restrained composite plates under biaxial loading. Int J Struct Stab Dyn 2007;07:487-517. [CrossRef]
• [9] Qiao P. Dynamics-based damage identification. Health Assess Eng Struct 2013:57-81. [CrossRef]
• [10] Qiao P, Lu K, Lestari W. A combined static/dynamic technique for damage detection of laminated composite plates. Exp Mech 2007;48:17-35. [CrossRef]
• [11] Yu H, Hami SA, Sharif KZ, Aliabadi MH. Structural health monitoring ımpact classification method based on bayesian neural network. Polymers 2022;14:3947. [CrossRef]
• [12] Karmakov S, Aliabadi MH. Deep learning approach to ımpact classification in sensorized panels using self-attention. Sensors 2022;22:4370. [CrossRef]
• [13] Tsai SW. Double-Double: New Family of Composite Laminates AIAA J 2021;59:1-11. [CrossRef]
• [14] Kappel E. Double-Double laminates for aerospace applications - Finding the best laminates for given load sets. Compos Part C 2022;8:100244. [CrossRef]
• [15] Mitrofanov О, Osman M. Assessment of the geometrically nonlinear behavior of thin cleavage type surface defects of the anisotropic structure under shear, J Phys: Conf Ser 2021:1925. [CrossRef]
• [16] Mitrofanov OV. Evaluation of the postbuckling behavior of composite panels in shear, taking into account rigid support along the long sides and at initial deflection. Nat Tech Sci 2019;1:132-135. [CrossRef]
• [17] Lekhnitskii S. Anisotropic Plates. 2nd ed. S.W. Tsai, T. Cheron (Translated Ed.). Yverdon, Switerland ; Philadelphia: Gordon and Breach Science Publication; 1968.
• [18] Mitrofanov O, Osman M. Design of thin orthotropic panels according to the post-buckling state under combined loading taking into account uniform heating, J Aerospace Systems 2022;5:29-36. [CrossRef]
• [19] Mitrofanov O, Lebedevs I, Urbaha M. Design of thin composite skins of the anisotropic structure of bearing panels of aircraft structures in the post-buckling state under combined loading. Eng Rural Dev 2021:1145-1153. [CrossRef]