New Model and Analytical Review of Approaches to Buckling Problem Investigation of Structurally Anisotropic Aircraft Panels Made from Composite Materials

Conference paper
Part of the Lecture Notes in Electrical Engineering book series (LNEE, volume 622)


The different approaches were analyzed to investigate the buckling problems of structurally anisotropic panels made from composite materials. One considered the studies of scientific schools from 2000 year to present time, mainly. The classification of mathematical models, analytical methods of calculations, numerical methods of calculations, and testing results is presented in this review. Aircraft composite structure design in the field of production technology is the outlook research trend. New mathematical model relations for the buckling investigation of structurally anisotropic panels comprising composite materials are presented in this study. The primary scientific novelty of this research is the further development of the theory of thin-walled elastic ribs related to the contact problem for the skin and the rib with an improved rib model. One considers the residual thermal stresses and the preliminary tension of the reinforcing fibers with respect to panel production technology. The mathematical model relations for the pre-critical stress state investigation of structurally anisotropic panels made of composite materials are presented. Furthermore, the mathematical model relations for the buckling problem investigation of structurally anisotropic panels made of composite materials are presented in view of the pre-critical stress state. The critical force definition of the general bending mode of the thin-walled system buckling and the critical force definition of the multi-wave torsion buckling are of the most interest in accordance with traditional design practices. In both cases, bending is integral with the plane stress state. Thus, the buckling problem results in the boundary value problem when solving for the eighth-order partial derivative equation in the rectangular field. The schematization of the panel as structurally anisotropic has been proposed as a design model when the critical forces of total bending mode of buckling are determined. For a multi-wave torsion buckling study, one should use the generalized function set. The solution is designed by a double trigonometric series and by a unitary trigonometric series. A computer program package is developed using the MATLAB operating environment. The computer program package has been utilized for multi-criteria optimization of the design of structurally anisotropic aircraft composite panels. The influence of the structure parameters on the level of critical buckling forces for bending and for torsion modes has been analyzed. The results of testing series are presented. The results of new calculations are presented.


Review Panels made of composite materials Eccentric longitudinal and lateral set Thin-walled rib Non-symmetric package structure Force and technology temperature action Pre-critical stress state Buckling Bending mode Torsion mode 



The study was performed in the framework of the RFFI (the project № 17-08-00849/17).


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© Springer Nature Singapore Pte Ltd. 2020

Authors and Affiliations

  1. 1.Department of Aircraft Design, Department of Machine ComponentsMoscow Aviation Institute (NRU)MoscowRussia

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