Certificate of Registration Media number Эл #ФС77-53688 of 17 April 2013. ISSN 2308-6033. DOI 10.18698/2308-6033
  • Русский
  • Английский

Method of parametric optimization in the problems of passenger airliner design

Published: 16.10.2020

Authors: Bolshikh A.A., Eremin V.P.

Published in issue: #10(106)/2020

DOI: 10.18698/2308-6033-2020-10-2022

Category: Aviation and Rocket-Space Engineering | Chapter: Design, construction and production of aircraft

The paper describes current trends in the design of load-bearing structural elements of modern airliners made using polymer composite materials. In modern passenger airliners, polymer composite materials are used to ensure mass perfection of both lightly loaded elements and critical units, including wing and fin boxes. By means of the finite element method, a box model was created using shell finite elements. Parametric optimization was carried out with account for the anisotropic properties of structural materials. The purpose of the work is to develop a methodology for calculating the structural strength elements of the box and justify the required thicknesses with restrictions on compressive / tensile deformations and loss of stability. The developed methodology makes it possible to obtain a box structure with a minimum mass, while maintaining the necessary stiffness and strength characteristics at the stage of preliminary design.

[1] Eger S.M., Mishin V.M., Lieytsev N.K., et al. Proektirovanie samoletov [Aircraft design]. Moscow, Logos Publ., 2005.
[2] Mitrofanov O.V. Aktualnye problemy sovremennoy nauki (Current problems of modern science), 2017, no. 5 (96), pp. 49–53.
[3] Gavva L.M. Buckling Problems of Structurally-Anisotropic Composite Panels of Aircraft with Influence of Production Technology. Materials Science Forum, 2019, no. 971, pp. 45‒50.
[4] Hibbitt K., Karlsson B., Sorensen P. ABAQUS: User’s Manual. Hibbitt, Karlsson & Sorensen, 2018.
[5] Kaw A.K. Mechanics of composite materials. Boca Raton (Florida), Taylor & Francis Group, 2006, 457 p.
[6] Vasilev V.V. Mekhanika konstruktsiy iz kompozitsionnykh materialov [Mecha-nics of structures made of composite materials]. Moscow, Mashinostroenie Publ., 1988, 272 p.
[7] Walker M. The effect of stiffeners on the optimal ply orientational and buckling load of rectangular laminated plates. Comput. and Struct., 2002, no. 4, pp. 30‒44, 125.
[8] Li D., Xiang J. Optimization of Composite Wing Structure for a Flying Wing Aircraft Subject to Multi Constraints. 54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Boston, 2013, AIAA Paper no. 2013-1934, pp. 1–11.
[9] Huang Liang, Sheikh Abdul H., Ching-Tai Ng, Griffith M.C. An efficient finite element model for buckling analysis of grid stiffened laminated composite plates. Comp. Struct., 2015, vol. 122, pp. 41‒45.
[10] Kollar L.P., Springer G.S. Mechanics of Composite Structures. Cambridge, Cambridge University Press, 2003, 469 p.