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Finite element modeling simplification method of honeycomb sandwich structure

A honeycomb sandwich and honeycomb structure technology, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve the problem of inability to accurately simplify the honeycomb sandwich structure, and achieve the effect of improving accuracy

Active Publication Date: 2014-08-13
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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Problems solved by technology

[0003] The purpose of the present invention is: to provide a finite element modeling simplification method of a honeycomb sandwich structure, to solve the problem that the honeycomb sandwich structure cannot be accurately simplified due to grid and model scale limitations in the overall finite element model of the aircraft, so as to achieve accurate structural strength design

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  • Finite element modeling simplification method of honeycomb sandwich structure
  • Finite element modeling simplification method of honeycomb sandwich structure
  • Finite element modeling simplification method of honeycomb sandwich structure

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Embodiment Construction

[0021] The method will be further described in detail through a finite element simplified modeling example of a honeycomb sandwich structure and in conjunction with the accompanying drawings.

[0022] 1. For the specific form of honeycomb sandwich structure, its geometric parameter is that the thickness of the inner and outer skins is t 1 =t 2 =0.8mm, the height of the honeycomb is h=15mm, and the regions are divided according to the change of structural stiffness: edge region 1, transition region 2 and middle region 3.

[0023] 2. According to the structural stiffness of different regions, the mechanical equivalent simplification is carried out:

[0024] In the element properties of the edge area, the in-plane stiffness and bending stiffness parameters are taken as the sum of the thickness of the inner and outer skins of the honeycomb structure, that is, 0.8+0.8=1.6mm;

[0025] In the element properties of the transition area, the in-plane stiffness parameter takes the thic...

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Abstract

The invention belongs to the field of finite element modeling and relates to a finite element modeling simplification method of a honeycomb sandwich structure. The method comprises the following steps: partitioning the honeycomb sandwich structure according to the regionality of rigidity changes; performing mechanics equivalency according to the structural rigidity of different regions; partitioning a finite element grid according to the regions of the honeycomb sandwich structure; establishing spatial topological relation of a unit by use of finite element modeling software by a unit selection plate unit; filling honeycomb structure material property data; filling unit attributes of different regions according to the result of rigidity equivalency of the step 2, and finishing finite element modeling of the honeycomb sandwich structure. The method has the advantages that rigidity equivalency is performed on honeycomb stressed-skin structures of different regions, one honeycomb sandwich structure is simplified into multiple plate units with different rigidity, and simplification is performed respectively on in-plane rigidity and flexural rigidity according to rigidity equivalency, so that finite element modeling simplification of a honeycomb structure under a full-aircraft finite element model of an aircraft is realized, and the airplane structure strength design and calculation accuracy can be improved.

Description

technical field [0001] The invention belongs to the field of finite element modeling and relates to a simplified method for finite element modeling of a honeycomb sandwich structure. Background technique [0002] In the finite element model of the whole aircraft, due to the limitation of the overall grid size, the honeycomb sandwich structure is generally simplified into one or several two-dimensional plate units, and the unit parameters only fill in one thickness parameter, which is usually taken as the difference between the inner and outer skins of the honeycomb. with. The actual honeycomb sandwich structure is divided into edge area, transition area and middle area. The structural stiffness in different areas and the stiffness in different directions in the same area are obviously different. Filling in only one thickness parameter cannot take into account the changes in stiffness in different areas and in different directions in the same area. Contents of the invention...

Claims

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Application Information

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IPC IPC(8): G06F17/50
Inventor 董宏达周丽君王占一刘庆邱春图
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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