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Airplane structure strength checking method and device

A technology for strength verification and aircraft structure, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve the problems of low efficiency of aircraft structure strength verification, improve simplification efficiency, save simplification time, and improve efficiency effect

Active Publication Date: 2015-07-15
COTESOFT BEIJING CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The invention provides a method and device for checking the strength of an aircraft structure to solve the problem of low efficiency in checking the strength of an aircraft structure

Method used

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  • Airplane structure strength checking method and device
  • Airplane structure strength checking method and device
  • Airplane structure strength checking method and device

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Embodiment 1

[0033] refer to Figure 4 , which shows a flow chart of a method for checking the structural strength of an aircraft according to an embodiment of the present invention. This embodiment may specifically include the following steps:

[0034] In step 101, the polygonal plate structure during the strength check of the aircraft structure is used as the original polygon, and a simplified area threshold is set for the original polygon.

[0035] The polygon formed by the polygonal plate structure is called the original polygon in this embodiment. It should be noted that, in this embodiment, a simplified area threshold is set for the original polygon in advance, and the simplified area threshold is an artificially set initial simplified area threshold, and the simplified area threshold is usually set relatively large for recording subsequent points Generated simplified area threshold. The simplified area threshold is the minimum area difference, represented by Smin in this embodimen...

Embodiment 2

[0069] On the basis of the above embodiments, this embodiment continues to discuss the method for checking the strength of the aircraft structure.

[0070] In this embodiment, taking the original polygon as a pentagon as an example, the simplification steps of the polygonal plate structure in the method for checking the strength of the aircraft structure are described, that is, the transformation of the original polygon into a quadrilateral is used as an example to illustrate the above method for checking the strength of the aircraft structure. The simplified steps of the polygonal plate structure correspond to step 101 to step 107 in the embodiment. Figure 5 is the schematic diagram of the original pentagon, Figure 6 ~ Figure 10 A schematic diagram showing a comparison between the original pentagon and the simplified quadrangle according to the embodiment of the present invention is shown.

[0071] In this embodiment, the original pentagon is as Figure 5 As shown, it is ...

Embodiment 3

[0080] On the basis of the above embodiments, this embodiment also discloses an aircraft structure strength checking device.

[0081] refer to Figure 11 , shows a structural block diagram of a simplified device for a polygonal plate structure when checking the strength of an aircraft structure in an embodiment of the present invention. This embodiment may specifically include: a setting module 201, a node combination set module 202, a first judgment module 203, a selection Module 204, second judging module 205, saving and modifying module 206, end simplification module 207, wherein:

[0082] The setting module 201 is configured to use the polygonal plate structure when checking the strength of the aircraft structure as the original polygon, and set a simplified area threshold for the original polygon.

[0083] The node combination set module 202 is configured to select any four nodes of the original polygon for node combination to generate a node combination set.

[0084] T...

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Abstract

The invention provides an airplane structure strength checking method and device, which solve the problem of low airplane structure strength checking efficiency. The airplane structure strength checking method comprises the steps of utilizing a polygonal plate structure in an airplane structure strength checking process as an original polygon, and setting a simplified area threshold for the original polygon; selecting any four nodes of the original polygon to perform node combination to generate a node combination set; when the node combination set comprises un-traversed node combinations, selecting an un-traversed node combination from the node combination set to be utilized as an existing node combination, and forming a quadrangle as an existing quadrangle; when an absolute value of area difference between the existing quadrangle and the original polygon is smaller than the simplified area threshold, saving the existing quadrangle as a simplified quadrangle; performing instability analysis on the simplified quadrangle to obtain allowable stress of the simplified quadrangle, and obtaining safety margin based on a ratio of the allowable stress to working stress. According to the airplane structure strength checking method and device, the airplane structure strength checking efficiency is improved.

Description

technical field [0001] The invention relates to the technical field of aircraft structure strength check, in particular to an aircraft structure strength check method and device. Background technique [0002] In order to ensure the overall strength of the aircraft, the overall strength check is required in the aircraft design stage. Since a large part of the aircraft is a bar-plate structure, the analysis of the instability of the bar-plate structure plays a very important role in the strength check of the entire aircraft structure. effect. When both sides of the thin plate are subjected to horizontal pressure F (such as figure 1 As shown), if the force reaches a certain level, the thin plate will suddenly undergo a large deformation outside the plane of the force and cannot maintain balance (such as figure 2 shown). In actual analysis, plate elements are polygons with different shapes, such as image 3 shown. Since there is only an instability criterion for quadrilate...

Claims

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Application Information

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IPC IPC(8): G06F17/50
Inventor 牟全臣王平李洋洋白绍鹏任如飞
Owner COTESOFT BEIJING CO LTD
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