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Aircraft body structure fatigue failure probability evaluation method

A technology for aircraft body and fatigue damage, applied in probabilistic CAD, stochastic CAD, instruments, etc., to achieve the effect of improving safety, simple calculation process, and rapid evaluation

Active Publication Date: 2021-03-05
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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Problems solved by technology

[0004] The purpose of this application is to provide a method for assessing the fatigue damage probability of aircraft body structures to solve at least one problem in the prior art

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  • Aircraft body structure fatigue failure probability evaluation method
  • Aircraft body structure fatigue failure probability evaluation method
  • Aircraft body structure fatigue failure probability evaluation method

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Embodiment Construction

[0046] In order to make the purpose, technical solution and advantages of the application more clear, the technical solution in the embodiment of the application will be described in more detail below in conjunction with the drawings in the embodiment of the application. 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 application. The embodiments described below by referring to the figures are exemplary, and are intended to explain the present application, and should not be construed as limiting the present application. Based on the embodiments in this application, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of this application. Embodiments of the present application will be described in detail below in conjunction with th...

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Abstract

The invention belongs to the field of aircraft design, and particularly relates to an aircraft body structure fatigue failure probability evaluation method. The method comprises the steps of 1, obtaining a probability density function fK of a stress intensity factor K; 2, obtaining a probability density function of the fracture toughness Kc of the material; and 3, based on the probability densityfunction fK of the stress intensity factor K and the probability density function of the material fracture toughness Kc, constructing an aircraft body structure damage probability evaluation model. According to the aircraft body structure fatigue damage probability evaluation method, the flight use safety of the aircraft can be quickly evaluated, the calculation process is simpler and more convenient, engineering use is more convenient, and the method has important significance for improving the flight use safety of the aircraft.

Description

technical field [0001] The application belongs to the field of aircraft design, and in particular relates to a method for evaluating the fatigue damage probability of an aircraft body structure. Background technique [0002] During the use of the aircraft, due to the continuous aerodynamic load, fatigue cracks will inevitably appear. The existence of these cracks and defects directly affects the flight safety of the aircraft. Aircraft flight safety is of great significance. At present, the stress-strength interference model is generally used to evaluate the failure probability of aircraft structures, but it is difficult to obtain accurate representations of the stress distribution and strength distribution functions of aircraft structures, so this method is difficult to give actual conditions in actual engineering. evaluation result. [0003] Therefore, it is desirable to have a technical solution to overcome or at least alleviate at least one of the above-mentioned drawba...

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Application Information

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IPC IPC(8): G06F30/20G06F111/08G06F119/02G06F119/14
CPCG06F30/20G06F2111/08G06F2119/02G06F2119/14
Inventor 张音旋吴德锋陈亮戴亚光
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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