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Method for calculating axial load bearing capacity of aircraft panel

A technology of aircraft siding and bearing capacity, applied in geometric CAD and other directions, can solve the problems of long cycle, difficult to meet the increasingly high requirements of aircraft design, difficult to meet the rapid iteration of aircraft design, etc., to achieve clear structural stress Effect

Pending Publication Date: 2021-06-29
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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AI Technical Summary

Problems solved by technology

Based on the test method and the semi-theoretical and semi-empirical engineering method of effective width, it is difficult to meet the increasingly high requirements of aircraft design. The finite element method is laborious and laborious, and the cycle is too long to meet the requirements of rapid iteration of aircraft design.

Method used

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  • Method for calculating axial load bearing capacity of aircraft panel
  • Method for calculating axial load bearing capacity of aircraft panel
  • Method for calculating axial load bearing capacity of aircraft panel

Examples

Experimental program
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Embodiment Construction

[0012] Referring to the accompanying drawings, the aircraft panel provided by the present application contains a skin 1 and a plurality of stringers 2, and the design parameters of the aircraft panel are known, for example: skin thickness δ sk , the width b of the skin between the stringers, the elastic modulus E of the skin material, the Poisson's ratio μ of the skin material, and the stringer section parameters and other design parameters.

[0013] The steps to calculate the axial load carrying capacity of aircraft panels are as follows:

[0014] 1) Taking each long stringer as the center, divide the aircraft panel into multiple calculation units;

[0015] Such as figure 1 As shown, the aircraft panel is composed of four long stringers and the skin, with each stringer as the center, the aircraft panel is divided into four calculation units; each calculation unit is as follows figure 2 shown. That is to say, the panel composed of long stringers and 1 / 2 long stringer spaci...

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Abstract

According to the method for calculating the axial load bearing capacity of the aircraft panel, the aircraft panel comprises a skin and a plurality of stringers, the design parameters of the aircraft panel are known, each stringer serves as the center, the aircraft panel is divided into a plurality of calculation units, and the axial load bearing capacity of each calculation unit is calculated; and the bearing capacities of all the calculation units are added to obtain the axial load bearing capacity of the aircraft panel. According to the method, the aircraft panel bearing capacity is subjected to formula derivation calculation based on cosine integral. The method abandones the hypothesis of the concept of effective width of the skin and is closer to a real solution. And a more accurate method is provided for calculating the axial load bearing capacity of aircraft panels of the same type.

Description

technical field [0001] The invention belongs to the technical field of structural design of aviation wing panels, and in particular relates to a method for calculating the axial pressure bearing capacity of aircraft panel panels. Background technique [0002] When the aircraft is flying with heavy overload, the axial compressive load of the aircraft panel tends to reach the peak value, and the panel will buckle or even fail. Therefore, it is very important to accurately predict the axial load bearing capacity of the aircraft panel to ensure the safety of the structure. Most of the existing technologies are based on the rationality of calculating the compressive strength of the panel based on the Johnson-Euler equation of the axial compression test; or calculating the bearing capacity of the panel based on the effective width of the skin; or directly using the finite element method to calculate the bearing capacity of the panel. The solution accuracy of the semi-theoretical ...

Claims

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Application Information

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IPC IPC(8): G06F30/17G06F30/15
Inventor 刘存
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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