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A Dynamic Monitoring Method for Measurement Data of Aircraft Structure Fatigue Test

A fatigue test and dynamic monitoring technology, applied in the field of aviation fatigue damage tolerance test, can solve problems such as poor operability, long time consumption, large amount of measurement data, etc., and achieve correct theoretical basis, difficult to determine the solution, and clear engineering concept Effect

Active Publication Date: 2022-04-19
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] Aircraft structural fatigue tests generally have a long test cycle, a large amount of measurement data, difficult to monitor the test status, real-time monitoring and analysis of measurement data, and it is difficult to draw conclusions on whether the fatigue test is effective, continuous and stable
[0003] In the fatigue test, for the analysis of measurement data, the conventional practice is to stop the test after a period of time is completed, and set aside time to analyze and judge the validity and stability of the measured strain and displacement in the past period. However, due to the huge amount of data, only relying on naked eye analysis and observation, many human factors are involved, the operability is not strong, and it takes too long

Method used

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  • A Dynamic Monitoring Method for Measurement Data of Aircraft Structure Fatigue Test
  • A Dynamic Monitoring Method for Measurement Data of Aircraft Structure Fatigue Test
  • A Dynamic Monitoring Method for Measurement Data of Aircraft Structure Fatigue Test

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Embodiment

[0028] The present invention will be further described in detail with a specific example below.

[0029] A kind of data dynamic monitoring method of fatigue test of aircraft structure, comprises the following steps:

[0030] A known:

[0031]The total number of peaks and troughs in the load spectrum is N=4 (the load values ​​are 0N, 1200N, -800N, 1500N, -500N, 0N), the strain of the monitoring part (including the main assessment part and the load monitoring part) in the test piece The number of slices M=1, the number of displacement measurement points L=1, and the number of wave blocks passed per minute during the fatigue spectrum run Z=5.

[0032] Step 1: Perform static strain displacement measurement. Under the loads of each peak and trough value, the static strain displacement measurement is carried out. According to the order of the fatigue load spectrum arrangement, and in turn according to the static strain displacement measurement requirements, measure the monitoring ...

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Abstract

The present invention relates to a kind of dynamic monitoring method of aircraft structure fatigue test measurement data, it is characterized in that, comprises the following steps: Step 1, carry out static strain displacement measurement; Step 2, establish static strain displacement measurement basic data template; Step 3, Carry out fatigue strain displacement measurement; step 4, establish a basic data template for fatigue strain displacement measurement; step 5, conduct a formal fatigue test and perform static error calculation and judgment; step 6, conduct a formal fatigue test and perform fatigue error calculation and judgment. The theoretical basis used in the invention is correct, the implementation steps are clear and simple, the computer is easy to control and implement, and the engineering concept is clear. The proposal of the invention solves the problem that it is difficult to determine whether the test runs normally in the aircraft structure fatigue test.

Description

technical field [0001] The invention belongs to the field of aviation fatigue damage tolerance test, in particular to a data dynamic monitoring method of aircraft structure fatigue test. Background technique [0002] Aircraft structural fatigue tests generally have a long test period, a large amount of measurement data, difficult to monitor the test status, real-time monitoring and analysis of measurement data, and it is difficult to draw conclusions about whether the fatigue test is effective, continuous and stable. [0003] In the fatigue test, for the analysis of measurement data, the conventional practice is to stop the test after a period of time is completed, and set aside time to analyze and judge the validity and stability of the measured strain and displacement in the past period. However, due to the huge amount of data, only relying on naked eye analysis and observation, many human factors are involved, the operability is not strong, and it takes too long. [0004...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64F5/60G01N3/32
CPCG01N3/32B64F5/60
Inventor 翟新康
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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