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- Article name
- Spectrum of optimal layer thicknesses, stringer pitches and package laying for dimensional and weight design of composite panels for aircraft bearing surfaces with constraints according to the refined buckling theory
- Authors
- KOROLSKII V. V., , korolskiy.vladislav@gmail.com, Moscow Aviation Institute (National Research University), Moscow, Russia
GAVVA L. M., , nio1asp@mail.ru, Moscow Aviation Institute (National Research University), Moscow, Russia
- Keywords
- composite stringer panels / optimal design / analytical constraints / bucling
- Year
- 2025 Issue 2 Pages 17 - 26
- Code EDN
- OTHGWZ
- Code DOI
- 10.52190/2073-2562_2025_2_17
- Abstract
- The problem of finding geometric parameters of longitudinally reinforced aircraft composite panels of minimum mass is discussed. Layer thicknesses and stiffener sizes are unknown variables. Optimal design of the structure is based on the condition of limiting the smaller value of the critical buckling force by the acting compressive load. Critical forces of the general bending and multi-wave torsional buckling modes are compared. The optimal design problem is reduced to studying the weight function of one or more variables using analytical methods for refined buckling theory constraints in combination with the numerical method of nonlinear programming. Mathematical relationships for studying buckling of structurally anisotropic composite panels are presented. The model relates bending to a plane stress state, which leads to a boundary value problem that includes solving an eighth-order partial differential equation in a rectangular region of the panel. For numerical implementation of the problems, a software package has been developed using the MATLAB operating environment: a software package for optimal design of aircraft composite stringer panels. The article considers the influence of design parameters on critical forces of buckling of bending and torsional forms. The results of a new implementation of the optimal dimensional and weight design of carbon fiber stringer panels are presented. The project with restrictions on the refined theory of buckling of structurally anisotropic panels of an aircraft made of composite materials is implemented within the framework of the search for a spectrum of optimal layer thicknesses, stringer pitches, and package layout. Two-level optimal solutions are obtained.
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