Method applied to analysis of damage tolerance feature of stiffened wall panel

Abstract

The invention relates to a method applied to the analysis of the damage tolerance feature of a stiffened wall panel. The method comprises the following steps: firstly selecting a typical section position for estimating the structure of the stiffened wall panel and determining the influence factor; solving a basic stiffening influence factor beta stiffening by an engineering method; solving a structure expansion influence factor beta expansion by the engineering method; introducing a load influence factor and correcting beta load by test data; respectively calculating to obtain a stress strength factor corresponding to the length of each crack as follows: the formula is as shown in the specification; and completing the analysis process of the damage tolerance of the whole stiffened wall panel by combining crack expansion analysis and residual intensity analysis. A detailed, accurate and quick calculation method is provided for analyzing the damage tolerance feature of the stiffened wall panel of an aircraft; the blank of the art in the actual application in China at present is fulfilled. The method applied to the analysis of the damage tolerance feature of a stiffened wall panel has an actual application prospect.

Description

technical field [0001] The invention relates to a damage tolerance characteristic analysis method of a reinforced wall plate, which belongs to the field of structural damage tolerance design. Background technique [0002] In the field of aeronautical design, most modern large transport aircraft are designed with the concept of damage tolerance design, and in the whole damage tolerance analysis, the damage tolerance analysis of the fuselage and wing skin panels plays an extremely important role in the whole damage tolerance analysis. However, its analysis is difficult, the workload is heavy, the calculation time is long, and due to the unreliability of the analysis results, most of them need to be verified by independent research and development or related experiments. At the same time, the design of large transport aircraft in China is still in the initial stage, and the damage tolerance analysis is far from mature, and only simple reinforcement analysis can be performed. A...

AI Technical Summary

Problems solved by technology

[0002] In the field of aeronautical design, most modern large transport aircraft are designed with the concept of damage tolerance design, and in the whole damage tolerance analysis, the damage tolerance analysis of the fuselage and wing skin panels plays an extremely important role in the whole damage tolerance analysis. status, but its analysis is difficult, the workload is heavy, the calculation time is long, and due to the unreliability of the analysis results, most of them need separate research and development or related experiments for verification

At the same time, the design of large transport aircraft in China is still in the early stage, and the damage tolerance analysis is far from mature, and only simple reinforcement analysis can be performed.

At present, there is no detailed analysis method or calculation tool for the damage tolerance of reinforced wall panels in China. The analysis is only to find charts from some design manuals, and these charts are only the results of specific structures, and cannot consider the geometric configuration of the actual structure. The integrity and reliability of the analysis results are far from sufficient due to changes in loading conditions, processing techniques, etc., and from a conservative design point of view, it leads to a thicker aircraft structure and an increase in design costs.

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