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An Iterative Method of Boundary Conditions for Progressive Destruction of Structural Damage

A technology of boundary conditions and progressive destruction, applied in instrumentation, geometric CAD, design optimization/simulation, etc., can solve problems such as inaccurate boundary conditions, time-consuming and labor-intensive problems, and achieve the effects of accurate boundary conditions, high accuracy of results, and improved precision

Active Publication Date: 2020-04-21
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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Problems solved by technology

[0005] The purpose of the present invention is to provide a boundary condition iterative method for progressive damage of structural damage to solve the time-consuming and laborious task of extracting boundary conditions from the overall model and applying them to the detail model in the process of calculating the progressive damage of structural damage, and as the damage increases, The problem of progressively inaccurate boundary conditions

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  • An Iterative Method of Boundary Conditions for Progressive Destruction of Structural Damage
  • An Iterative Method of Boundary Conditions for Progressive Destruction of Structural Damage
  • An Iterative Method of Boundary Conditions for Progressive Destruction of Structural Damage

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[0024] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below ...

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Abstract

The invention relates to the field of aircraft structure strength calculation, in particular to a boundary condition iteration method based on progressive failure of structural damage, so as to solve the problems that the operation of extracting a boundary condition from an overall model and applying the boundary condition to a detail model in a calculation process of progressive failure of structural damage wastes time and energy, and the boundary condition is inaccurate gradually with an increase in damage. The boundary condition iteration method based on progressive failure of structural damage comprises the following steps: automatically extracting the boundary condition; establishing the detail model; and performing iterative solving on a constraint condition. According to the method, the change of the boundary condition caused by factors such as gradual damage extension, degeneration of material performance, rigidity and the like, and the like is fully considered, so that the boundary condition is more accurate; and in addition, the calculation process is repeatedly iterated in a full-aircraft model and the detail model, so that the calculation precision is greatly improved and the result accuracy is higher.

Description

technical field [0001] The invention relates to the field of calculation of aircraft structure strength, in particular to a boundary condition iteration method for progressive destruction of structure damage. Background technique [0002] After the aircraft composite material structure is damaged, the strength and stiffness will be greatly reduced, which will also have a great impact on the service life of the aircraft. How to evaluate whether the strength and stiffness of the damaged structure can meet the structural integrity requirements, whether the aircraft can return safely, and whether the strength and stiffness of the original structure can be restored after damage are the key issues that aircraft designers must solve . [0003] The progressive damage analysis method of composite materials is widely used in aircraft engineering practice because it can predict the whole process from initial damage to ultimate failure of composite materials, judge the failure mode, de...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/23G06F30/15G06F113/28
CPCG06F30/15G06F30/23G06F2113/28
Inventor 邱春图董宏达戴亚光管宇
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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