A Method for Determining the Loading Frequency of Aircraft Structure Fatigue Test

A technique for fatigue testing and determining methods, applied in the field of aviation fatigue damage tolerance testing, to achieve the effects of correct theoretical basis, difficult loading coordination, and clear implementation steps

Active Publication Date: 2022-03-15
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Application Information

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Problems solved by technology

[0004] Regarding the research on the loading frequency of the aircraft structure fatigue test, there are few public researches at home and abroad, and it is not possible to provide a feasible method for determining the loading frequency of the structural fatigue test according to the characteristics of the aircraft structure itself, loads and forces.

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  • A Method for Determining the Loading Frequency of Aircraft Structure Fatigue Test
  • A Method for Determining the Loading Frequency of Aircraft Structure Fatigue Test

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Embodiment

[0024] The present invention will be further described in detail with a specific example below.

[0025] A method for determining the loading frequency of an aircraft structure fatigue test, comprising the following steps:

[0026] A known:

[0027] The total number of peaks and troughs in the load spectrum is N=4 (each load value is 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=3.

[0028] Step 1. Static strain measurement is carried out under the loads of various peak and valley values. According to the order of the load spectrum arrangement, and in turn according to the static strain measurement requirements, measure the strain value ε of the strain gauge at the monitoring part under the load of 1200N, -800N, 1500N, and -500N ij , (i=1,2,3...,N; j=1,2,3,...,M).

[0029] Step 2, calculating the average value of the strain measured by the sta...

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Abstract

A method for determining the loading frequency of an aircraft structure fatigue test is characterized in that it comprises the following steps: Step 1, performing static strain measurement under each peak and trough load; Step 2, calculating the static measurement strain average value; Step 3 , Carry out the fatigue spectrum strain measurement; Step 4, calculate the relative error η between the fatigue spectrum strain measurement value and the static measurement strain average value k , judging η k Whether the theoretical basis used in the present invention is correct, the implementation steps are clear and simple, and the engineering concept is clear. The invention solves the problem that the fatigue loading frequency is not easy to determine 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 method for determining the loading frequency of aircraft structure fatigue test. Background technique [0002] Aircraft structural fatigue tests generally have a long test period, and the test period is related to the severity of the load spectrum, low load cutoff, and test loading frequency. [0003] The determination of the severity of the load spectrum and the low-load cut-off shall be determined by the test proposer after extensive theoretical analysis and research in the test planning stage and before the test, and finally specified in the test task book by the test proposer. The loading frequency of the structural fatigue test is determined according to the debugging results during the test debugging process, combined with the test deformation coordination and other conditions. [0004] Regarding the research on the loading frequency of the aircraft ...

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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