Finite element modeling method for aircraft tire cord reinforced rubber composite material
A technology of composite materials and reinforced rubber, which is applied in computer materials science, instruments, symbol schematic diagrams, etc., can solve problems such as complex embedded constraints and long solution time, and achieve the effects of shortening solution time, improving modeling efficiency, and effective accuracy
Pending Publication Date: 2022-05-13
JILIN UNIV
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Problems solved by technology
[0003] Aiming at the problem that the embedded constraints of rubber and cord plane elements are complex and the solution time is long in the traditional modeling method, the present invention provides a finite element modeling method for aviation tire cord reinforced rubber composites
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[0021] The detailed content of the present invention and its specific implementation will be further described below in conjunction with the accompanying drawings.
[0022] The finite element modeling method of aviation tire cord reinforced rubber composite material, the method flow is as follows figure 1 shown, including the following steps:
[0023] Step 1. Carry out grid subdivision for the structure of the aviation tire cord reinforced rubber composite material, specifically: subdivide the rubber body of the aviation tire cord reinforced rubber composite material structure to obtain several rubber matrix units, and in each rubber matrix Create a cord planar element within the element.
[0024] The further details are as follows: use quadrilateral and / or triangular elements to mesh the rubber body of the tire section, and the three-dimensional structure corresponding to the rubber matrix element obtained by meshing with quadrilateral elements is a hexahedral rubber element...
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The invention discloses a finite element modeling method for an aircraft tire cord reinforced rubber composite material, relates to the technical field of aircraft tire structure design, and solves the problems of complex embedded constraint and long solving time of rubber and a cord plane unit in a traditional modeling method. The method comprises the following steps: step 1, dividing a rubber body of the aviation tire cord thread reinforced rubber composite material structure to obtain a plurality of rubber matrix units, and creating a cord thread plane unit in each rubber matrix unit; 2, establishing a rubber matrix unit balance equation and a cord thread plane unit balance equation; step 3, calculating an embedded constraint relationship between the rubber matrix unit and the cord thread plane unit; and step 4, eliminating the degree of freedom of the cord thread plane unit according to the balance equation of the cord thread plane unit in the step 2 and the embedded constraint relation in the step 3 to obtain a final balance equation of the embedded cord thread plane unit of the rubber matrix. The modeling efficiency of the aviation tire cord reinforced rubber composite material is improved, and the solving time of the finite element model is shortened.
Description
technical field [0001] The invention relates to the field of aviation tire structure design, in particular to a finite element modeling method of an aviation tire cord reinforced rubber composite material. Background technique [0002] Aerospace tires are primarily composed of cord-reinforced rubber compounds. The cord structure layering is complex, which determines the stiffness and strength of the tire structure. In the last ten years, thanks to the rapid development of nonlinear finite element theory and computer software and hardware, finite element analysis of tire structure has been able to reduce or replace some tire tests. Therefore, in the simulation analysis of tire finite element complex working conditions, the research on accurate and fast finite element modeling is still the top priority. The finite element model technology of the rubber embedded cord is one of the feasible solutions: firstly, the rubber matrix and the cord structure are meshed separately, the...
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IPC IPC(8): G06F30/15G06F30/17G06F30/23G06F111/04G06F111/12G06F113/26G06F119/14G16C60/00
CPCG06F30/15G06F30/17G06F30/23G16C60/00G06F2111/04G06F2111/12G06F2113/26G06F2119/14
Inventor 白建涛张然左文杰
Owner JILIN UNIV