Method for predicting buckling of stiffened wall plate under tension-compression-shear combined load
A technology of reinforced wall panels and composite loads, applied in the direction of testing material strength by applying stable shear force, testing material strength by applying stable tension/compression, measuring devices, etc., can solve the problem of unsatisfactory accuracy, etc. problems, to achieve the effects of authenticity and reliability of evaluation results, reduction of test costs, and high prediction accuracy
Active Publication Date: 2020-11-17
CHINA AIRPLANT STRENGTH RES INST
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Problems solved by technology
In the past, people proposed a simple parabolic correlation formula for isotropic material panels to quickly predict the buckling load under combined tension / compression and shear loads, and tried to apply it to composite material panels, but the accuracy not satisfactory
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[0028] In order to make the objectives, technical solutions and advantages of the implementation of the application clearer, the technical solutions in the implementation modes of the application will be described in more detail below with reference to the drawings in the implementation modes of the application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the present application. The embodiments described below by referring to the figures are exemplary and are intended to explain the present application, and should not be construed as limiting the present application. Based on the implementation manners in this application, all other implementation manners obtained by persons of ordinary skill in the art without creative efforts fall within the scope of protection of this application. Embodiments of the pr...
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The invention belongs to the field of aircraft structural strength design, and relates to a reinforced wallboard buckling prediction method under tension-compression-shear combined load, which comprises the following steps: obtaining a power-level buckling equation consisting of a tension-compression load component quadratic term, a tension-compression load component quadratic term and a shear load component quadratic term; obtaining a shear buckling critical load under the action of a simple shear load, and calculating a coefficient of a quadratic term of a shear load component; solving the coefficient of the tension and compression load component quadratic term and the coefficient of the tension and compression load component quadratic term; and carrying out buckling prediction on the stiffened wall plate based on a power-level buckling equation formed by the coefficient of the shear load component quadratic term, the coefficient of the tension-compression load component quadratic term and the coefficient of the tension-compression load component quadratic term. According to the method, prediction of the initial buckling load of the wallboard structure under the action of the axial load and the shearing load in any proportion can be completed only through single load test data of axial compression, stretching and shearing, and thereby the design efficiency is greatly improved.
Description
technical field [0001] The application belongs to the field of aircraft structural strength design, and in particular relates to a buckling prediction method of a reinforced wall plate under the action of tension-compression-shear composite load. Background technique [0002] Composite materials are increasingly being used in aircraft structures due to their excellent weight-reducing properties, unique material designability and good manufacturability. However, due to the imperfect technical level and too conservative design criteria, the weight reduction effect of the composite material structure is not ideal, especially for the wall plate stability structure. The thin-walled stiffened panel structure usually used in the aircraft body has a long post-buckling load history. The skin of the metal stiffened panel of the subsonic aircraft wing usually allows local buckling at about 50% of the ultimate load, but the current Basically, the design criteria of aircraft composite s...
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IPC IPC(8): G01N3/08G01N3/24G06F17/12
CPCG01N3/08G01N3/24G06F17/12G01N2203/0017G01N2203/0019G01N2203/0025G01N2203/0026G01N2203/0252G01N2203/0282
Inventor 王彬文陈向明王喆成李南杨钧超柴亚南
Owner CHINA AIRPLANT STRENGTH RES INST