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Method for calculating and analyzing fatigue life of airplane structure welding spots

A fatigue life and analysis method technology, applied in the direction of calculation, special data processing applications, instruments, etc., can solve the problem of no solder joint fatigue life analysis method, etc., to achieve the effect of improving fatigue performance and reducing manufacturing costs

Inactive Publication Date: 2014-08-20
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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  • Abstract
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, there is not yet a very effective method for fatigue life analysis of solder joints.

Method used

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  • Method for calculating and analyzing fatigue life of airplane structure welding spots
  • Method for calculating and analyzing fatigue life of airplane structure welding spots
  • Method for calculating and analyzing fatigue life of airplane structure welding spots

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Embodiment Construction

[0026] The present invention will be described in further detail below through specific embodiments and in conjunction with the accompanying drawings.

[0027] An example of life calculation for a welded structure of a high maneuvering aircraft is given below.

[0028] First, the welded structural stress of this type of aircraft is calculated by the finite element method

[0029] Second, the S-N curve of the weld nugget and base metal

[0030] The S-N curves of the weld nugget and the base metal are obtained through the material fatigue performance test.

[0031] Third, compile the stress spectrum of the welded structure of the high maneuvering aircraft

[0032] A basic spectrum block of the random spectrum of this type of aircraft consists of 15 typical subjects, a total of 142 takeoffs and landings, representing 186.52 flight hours. In order to ensure the integrity of the basic spectrum blocks, a spectrum with 13258 flight hours as a complete cycle was constructed, includ...

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Abstract

The invention belongs to the field of calculation and analysis of fatigue life of an airplane structure, and relates to a method for calculating and analyzing fatigue life of airplane structure welding spots. The method is characterized in including the following steps that structure stress of a weld nugget is calculated by means of an equivalent stiffening bar unit simulating the weld nugget, and principal stress with the largest absolute value serves as a damage parameter; by means of material fratigue performance tests, an S-N curve of the weld nugget and a parent material is obtained; the effective stress course of each calculation point is calculated through a quasi-steady-state solution, a stress spectrum is determined, fatigue damage is calculated in a damage accumulation method, and distribution situations of damage and service life of all weld spots are obtained. The method has the advantages that the fatigue life of the weld points can be predicted through calculation in the initial stage of design by putting forward to a weld spot fatigue life calculation model and an analysis method suitable for engineering application, the distribution situations of the weld spots of a whole structure are known, and the number and the distribution mode of the weld spots in the actual process can be guided to be reasonably adjusted.

Description

technical field [0001] The invention belongs to the field of aircraft structure fatigue life calculation and analysis, and relates to an aircraft structure solder joint fatigue life calculation and analysis method. Background technique [0002] As an efficient connection method, spot welding is widely used in the manufacturing process of aircraft parts, which greatly reduces the number of rivets or screw connections, and also reduces a certain structural weight. However, due to the characteristics of welding, a large number of tests have also shown that compared with the base metal, welded connections will greatly reduce the fatigue resistance of the entire structure, so that structures connected by spot welding often occur at the weld during service. Failure to destroy, resulting in accidents. Therefore, if we can calculate the fatigue life of solder joints in the early stage of design to predict the life and understand the distribution of solder joints on the entire struc...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
Inventor 邱春图
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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