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Method for establishing structure fatigue life pre-corrosion influence coefficient curve of aircraft

A technology of fatigue life and influence coefficient, which is applied in the direction of electrical digital data processing, computer-aided design, special data processing application, etc., and can solve the problem that the structure fatigue life pre-corrosion influence coefficient curve is not accurate enough, etc.

Inactive Publication Date: 2016-04-13
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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Problems solved by technology

[0006] The purpose of the present invention is to provide a method for establishing the fatigue life pre-corrosion influence coefficient curve of an aircraft structure, which can solve the problem that the structure fatigue life pre-corrosion influence coefficient curve established by the current method is not accurate enough

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  • Method for establishing structure fatigue life pre-corrosion influence coefficient curve of aircraft
  • Method for establishing structure fatigue life pre-corrosion influence coefficient curve of aircraft
  • Method for establishing structure fatigue life pre-corrosion influence coefficient curve of aircraft

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[0032] 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 corrosion fatigue, in particular to a method for establishing a structure fatigue life pre-corrosion influence coefficient curve of an aircraft, which can solve the problem of an inaccurate structure fatigue life pre-corrosion influence coefficient curve established with an existing method. The method for establishing the structure fatigue life pre-corrosion influence coefficient curve of the aircraft comprises the following steps: designing a simulated test part of a fatigue key part structure; constructing a lab accelerated environment spectrum and an equivalent accelerated relationship for the simulated test part; setting environment test time of the simulated test part; performing an environment test on the simulated test part, then performing a fatigue test, and recording the fatigue life; obtaining a ground parking corrosion correction coefficient of the simulated test part; and finally obtaining an accurate structure fatigue life pre-corrosion influence coefficient curve of the simulated test part.

Description

technical field [0001] The invention relates to the field of aircraft structure corrosion fatigue, in particular to a method for establishing an aircraft structure fatigue life pre-corrosion influence coefficient curve. Background technique [0002] The service life system of aircraft structure includes fatigue life (flight hours) and calendar life (useful years) of first turnaround period, repair interval and total life. The operating environment of the aircraft has a certain impact on the service life of the aircraft structure, especially in coastal humid and hot areas. In order to ensure the safety of the aircraft, after completing the fatigue life assessment under general environmental conditions, it is necessary to determine the operating environment, also known as the corrosive environment. impact on the life of the structure. [0003] The use environment of the aircraft can be divided into two types: the air use environment and the ground parking environment. For so...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/15G06F2119/04
Inventor 宋恩鹏周丽君陆华陈亮
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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