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- Article name
- Implementation of an optimal size-weight design for structurally reinforced anisotropic composite aircraft panels in the wing-fuselage junction region under refined static strength constraints
- Authors
- GAVVA L. M., , nio1asp@mail.ru, Moscow Aviation Institute (National Research University), Moscow, Russia
HAN T. A., , hanthuaung188495@gmail.com, Moscow Aviation Institute (National Research University), Moscow, Russia
- Keywords
- medium- and large-thickness composite stringer panels / optimal design / analytical constraints / static strength
- Year
- 2026 Issue 3 Pages 3 - 15
- Code EDN
- LQKQLA
- Code DOI
- 10.52190/2073-2562_2026_3_3
- Abstract
- This article presents the formulation and solution of the problem of finding optimal layer thicknesses, stringer spacing, and stacking sequences to minimize the mass of composite panels located in the wing root section of an aircraft. The optimal structural design is based on the condition of constraining the maximum ply equivalent stresses induced under distributed compressive loads applied to the edges in the longitudinal direction. The study of the objective weight function for conditional extrema in a rigorous mathematical formulation is carried out using analytical methods for refined static strength constraints combined with a numerical nonlinear programming method. New mathematical relations are obtained for determining the stress-strain state of structurally anisotropic composite panels of medium and large thickness within the framework of a modified first-order shear deformation theory. The model couples bending with plane stress state, and the boundary value problem involves solving a tenth-order partial differential equation in a rectangular panel. For numerical implementation of the method, a software package has been developed in the MATLAB operating environment. The results of two-level optimal sizing-and-weight designs of carbon-fiber-reinforced plastic stringer panels are presented.
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