Fatigue life calibration method suitable for structural connection piece

A technology of fatigue life and calibration method, which is applied in special data processing applications, instruments, electrical digital data processing, etc., to achieve high-precision results

Active Publication Date: 2018-06-01
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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Problems solved by technology

[0002] Structural connectors in aircraft are usually fatigue weak parts. When performing fatigue analysis on this part under the random spectrum, due to the complex

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  • Fatigue life calibration method suitable for structural connection piece
  • Fatigue life calibration method suitable for structural connection piece
  • Fatigue life calibration method suitable for structural connection piece

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[0022] 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 discloses a fatigue life calibration method suitable for a structural connection piece, and belongs to the technical field of aircraft strength design. The method comprises the steps of1, establishing a stress spectrum of a key connection part; 2, calculating and establishing a stress severity coefficient of the connection part; 3, obtaining an S-N curve corresponding to the stressseverity coefficient of the key part; 4, determining a most sensitive parameter theoretical fatigue limit C in a nominal stress method; 5, performing optimization on the theoretical fatigue limit C; and 6, performing verification on the determined stress severity coefficient and the corresponding theoretical fatigue limit C. The life prediction under a load spectrum is performed by utilizing parameters obtained by optimization and a stress severity coefficient method, and the predicted and calculated stop life t' under the load spectrum and the actually measured life mid-value under the load spectrum are subjected to error comparison; and the life prediction under other load spectrums is performed by adopting the parameters obtained by the optimization and a nominal stress method through the verification, so that life calculation results under other load spectrums have relatively high precision.

Description

technical field [0001] The invention belongs to the technical field of aircraft strength design, and in particular relates to a fatigue life calibration method suitable for structural connectors. Background technique [0002] Structural connectors in aircraft are usually fatigue weak parts. When performing fatigue analysis on this part under the random spectrum, due to the complex load interaction in the random spectrum, there is currently no universally applicable high-precision damage accumulation model that can better predict its fatigue life. [0003] However, it is found through research that serialized aircraft often have great inheritance in structure and load spectrum, so the fatigue test results of existing models can be used to predict the fatigue life of subsequent models, which is the basic idea of ​​calibration. Based on the above-mentioned basic idea of ​​fatigue life calibration, the present invention proposes a fatigue life calibration method suitable for st...

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/23G06F2119/04G06F2119/06
Inventor 陆华刘思远杨翔宁
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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