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- Article name
- Buckling constraints for optimal design of structurallly anisotropic aircraft skins with medium and large thickness made of composite materials
- Authors
- FIRSANOV V. V., , K906@mai.ru, Moscow Aviation Institute (National Research University), Moscow, Russia
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 panels / transverse shear deformations / bucling / optimal design / analytical constraints
- Year
- 2024 Issue 3 Pages 23 - 30
- Code EDN
- JMCFKA
- Code DOI
- 10.52190/2073-2562_2024_3_23
- Abstract
- The relations of a mathematical model for studying the static strength and buckling of structurally anisotropic composite panels of aircraft with the skins of medium and large thickness taking into account transverse shear deformations are presented. An approach has been developed to solve buckling problems within the framework of a new resolving tenth-order partial differential equation. New analytical constraints on the objective function were implemented for the optimal design of structurally anisotropic composite aircraft skins of medium and large thickness in accordance with the refined theory of buckling. An analysis of the influence of structural design parameters on the level of critical forces was performed. The results of assessing the limits of applicability of the theory of first-order transverse shear deformations and the theory of thin plates for flat rectangular carbon fiber panels compressed in the longitudinal direction are presented. The possibility of using mathematical models reduced to an analytical solution of buckling problems for resolving equations with linear differential operators of the tenth and eighth orders as constraints in the design of structurally anisotropic panels made of composite materials for promising aircraft products is substantiated.
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