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Method for calculating axial pressure bearing capacity of composite stiffened wall plate

A technology of reinforced wall panels and bearing capacity, which is applied in the fields of electrical digital data processing, instruments, geometric CAD, etc., can solve the problems of large errors, many adjustable parameters, and complicated numerical solution methods, and achieves the effect of small errors.

Active Publication Date: 2020-05-12
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology

By comparing the existing engineering calculation methods with the test results, it is found that some results have large errors and some results are dangerously higher than the test values. However, the numerical solution method based on finite element theory is too cumbersome, and there are many adjustable parameters in the calculation. Increases the uncertainty of the results, not suitable for engineering applications
To sum up, at present, there is not a widely recognized calculation method in the engineering field for composite material reinforced wall panels, which is suitable for the estimation of its axial compression bearing capacity

Method used

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  • Method for calculating axial pressure bearing capacity of composite stiffened wall plate
  • Method for calculating axial pressure bearing capacity of composite stiffened wall plate
  • Method for calculating axial pressure bearing capacity of composite stiffened wall plate

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Embodiment Construction

[0034] like figure 1 As shown, a method for calculating the axial compressive bearing capacity of a composite material reinforced panel includes the following steps:

[0035] Step 1: Give the average failure stress σ of the stiffened plate to be calculated co Assign the initial value, specifically: the pressure loss stress σ of the stiffened plate cc Assign the average failure stress σ of the stiffened plate to be calculated co , the initial value σ co = σ co , σ cc Obtained by the pressure loss test of short columns with the same stiffened plate section;

[0036] Step 2: Compute skin effective width b e , the calculation formula is:

[0037]

[0038] where D 11 、D 12 、D 22 、D 66 is the bending stiffness coefficient of the skin; L is the length of the stiffened plate; t is the thickness of the skin; E sk is the equivalent modulus of the skin; is the equivalent axial elastic modulus of the stiffened plate; π is the circumference ratio; m is the buckling half-wa...

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Abstract

The invention discloses a method for calculating the axial pressure bearing capacity of a composite stiffened wall plate. The factor that the modulus of the skin is possibly different from that of thestringer is considered; axial compression breaking load is calculated by considering the stiffened plate section of the skin with the effective width, the bearing capacity of the local buckling skinis superposed, the bearing capacity of the whole stiffened plate is finally obtained, and test results show that the result calculated by the method is small in error, lower than a test value and relatively conservative, and is more suitable for engineering application.

Description

technical field [0001] The invention belongs to the technical field of aviation strength, and in particular relates to a method for calculating the axial compression bearing capacity of a composite material reinforced wall plate. Background technique [0002] In order to reduce weight and fully tap the structural bearing capacity, thin-walled reinforced structures are often used in aircraft design. Due to the high specific modulus and specific strength, it has great advantages in weight reduction. Composite materials are more and more widely used in aircraft structures. Therefore, composite material reinforced panels have naturally become the first choice in aircraft structure design. preferred option. [0003] Axial compression is a main load-bearing form of composite material reinforced panels. How to accurately estimate its axial compression load-bearing capacity is an important basis for ensuring aircraft flight safety and structural weight reduction design, and it is a...

Claims

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Application Information

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IPC IPC(8): G06F30/15G06F119/14
CPCY02T90/00
Inventor 任善杨杰赵占文侯瑞
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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