On the issue of the optimal composite panels reinforcement to exclude buckling
Authors: Tolkachev M.A.
Published in issue: #8(164)/2025
Category: Metallurgy and Science of Materials | Chapter: Powder Metallurgy and Composite Materials
The paper is devoted to establishing an algorithm for optimal design of the composite panels; it is aimed at reducing their weight and strengthening by increasing the critical force of losing structural stability in operation using the curvilinear layer stacking. The paper considers key factors affecting the panel stability. They include the external loads and geometric characteristics. Numerical simulation based on the finite element method (FEM) in combination with approaches from the aircraft structure mechanics is used to establish the critical loads leading to a panel stability loss. In this regard, the paper considers a shell model of the compressed skin panel with the orthotropic stacking using the layer-by-layer simulation approach. The method developed in the paper is based on combining the maximum material stiffness direction with the main moment action direction. It allows raising the critical force in buckling. Besides, the paper provides a review of the existing options in using the curvilinear layer stacking with the design optimization, and describes also their advantages over the traditional reinforcement. Scientific novelty of the research lies in establishing a combined approach that combines FEM, methods for optimizing the composite panels and accounting for the operational limitations in the aviation industry. The algorithm developed within the framework of this approach makes it possible to determine optimal reinforcement of the composite material layers taking into account directions of the main moments and the structure stress-strain state.
EDN NXEHMK
References
[1] Kumar P., Arya R., Sharma N., Hirwani CH.K., Panda S.K. Curved fiber-reinforced laminated composite panel and variable stiffness influence on eigenfrequency responses: a higher-order FE approach. Journal of Vibration Engineering and Technologies, 2023, vol. 5, pp. 2349–2359. DOI: 10.1007/s42417-022-00706-6
[2] Selyugin S.V. Analiz i proektirovanie plastin i paneley iz kompozitsionnykh materialov [Analysis and design of plates and panels from the composite materials]. Preprint, 2023. https://doi.org/10.24108/preprints-3112468
[3] Selyugin S. Analysis of lay-up optimality conditions for buckling optimization of vat (steered fiber) composite plates. Center for Open Science, 2020. https://doi.org/10.31224/osf.io/9n58h
[4] Selyugin S. Some approaches to buckling analysis of flexurally anisotropic composite plates, subjected to combined in-plane loading. Thin-Walled Structures, 2016. https://doi.org/10.1016/j.tws.2015.10.008
[5] Martins J.R.R.A., Kenway G.K.W., Kennedy G.J., Zhoujie Lyu, Brooks T. Multidisciplinary Design Optimization of Aircraft Configurations Part 2: High-fidelity aerostructural optimization. VKI Lecture Series, Brussels, Belgium, May 24, 2016.
[6] Brooks T.R., Martins J.R.R.A., Kennedy G.J. High-fidelity aerostructural optimization of tow-steered composite wings. Journal of Fluids and Structures, 2019, vol. 88, pp. 122–147. https://doi.org/10.1016/j.jfluidstructs.2019.04.005
[7] Zhijun Wang, Daniël Peeters, Roeland De Breuker. An aeroelastic optimisation framework for manufacturable variable stiffness composite wings including critical gust loads. Structural and Multidisciplinary Optimization, 2022, vol. 65, p. 290. https://doi.org/10.1007/s00158-022-03375-x
[8] Lopes C., Gurdal Z., Camanho P. Tailoring for strength of composite steered-fibre panels with cutouts. Composites A, 2010, vol. 41 (12), pp. 1760–1767. https://doi.org/10.1016/j.compositesa.2010.08.011
[9] Khani A., Ijsselmuiden S., Abdalla M., Gurdal Z. Design of variable stiffness panels for maximum strength using lamination parameters. Composites B, 2011, vol. 42 (3), pp. 546–552. https://doi.org/10.1016/j.compositesb.2010.11.005
[10] Ijsselmuiden S.T., Abdalla M.M., Gurdal Z. Optimization of variable-stiffness panels for maximum buckling load using lamination parameters. AIAA J., 2010, vol. 48 (1), pp. 134–143. http://dx.doi.org/10.2514/1.42490
[11] Kasumov E.V. Metodika poiska ratsionalnykh konstruktivnykh parametrov s primeneniem metoda konechnykh elementov [Method of determination of rational design parameters using the finite-element method]. Uchenye zapiski TsAGI, 2015, no. 2, pp. 63–79.
[12] Dassault Systemes Simulia Corp, Abaqus User’s Manual. Available at: http://abaqusdocs.eait.uq.edu.au/v6.11/index.html (accessed 24 March 2025).
[13] Goncharov P.S., Artamonov I.A., Khalitov T.F., Denisikhin S.V., Sotnik D.E. NX Advanced Simulation. Practical guide. Moscow, DMK Press Publ., 2014. ISBN 978-5-97060-142-6
[14] Bolshikh A.A. Metodika proektirovaniya tolstostennogo kompozitnogo kessona kryla shirokofyuzelyazhnogo dalnemagistralnogo samoleta s uchetom defektov: Dis. … kand. tekhn. nauk [Methodology for designing a thick-walled composite wing box of a wide-body long-range aircraft taking into account defects: Diss. … Cand. Sc. (Eng.)]. Moscow, 2024, 102 p.