Method for determining fatigue life extension test period of aging aircraft

A fatigue test and test cycle technology, applied in the field of aircraft test research

Active Publication Date: 2014-09-03
AIR FORCE UNIV PLA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] It can be seen that the existing aging aircraft fatigue (durability) life extension test technology has the following disadvantages: the aging aircraft fatigue (durability) life extension target has been given, but the remaining fatigue (durability) life of the aging aircraft under different service states The fatigue dispersion coefficient can only be determined by experience, and has no theoretical basis

Method used

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  • Method for determining fatigue life extension test period of aging aircraft
  • Method for determining fatigue life extension test period of aging aircraft
  • Method for determining fatigue life extension test period of aging aircraft

Examples

Experimental program
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Embodiment 1

[0043] 1. Select the fatigue test load spectrum of the life extension testing machine

[0044] The aircraft in service initially served under the fatigue test load spectrum of the new aircraft, and then the load spectrum was aggravated, and the average load spectrum of the subsequent flight was selected as the fatigue test load spectrum of the life extension test aircraft.

[0045] 2. Determine the total equivalent flight hours

[0046] Assume that the number of flight hours of the aircraft in service under the load spectrum of the fatigue (durability) test of the new aircraft is N 1 , the number of flight hours in service under the subsequent flight load spectrum is N 2 , under the same number of flight hours, the damage degree of the follow-up flight load spectrum is 1 times of the damage degree of the fatigue (durability) test load spectrum of the new aircraft, then the service aircraft in the new aircraft fatigue (durability) test load spectrum The total equivalent fligh...

Embodiment 2

[0107] In the case that the aircraft in service initially served under the fatigue test load spectrum of the new aircraft, and the subsequent service load spectrum is aggravated, in the process of selecting the fatigue test load spectrum of the life extension test machine, the average load spectrum of the subsequent flight is usually selected as the life extension The fatigue test load spectrum of the whole testing machine is the case of Example 1.

[0108] In order to shorten the fatigue (durability) test cycle of the life-extension test machine, as an optimal solution, the load spectrum whose damage degree is m' times the average load spectrum damage degree of the subsequent flight is selected as the fatigue test load of the life-extension test machine Spectrum.

[0109] Then, the determination method of aging aircraft fatigue life extension test cycle of the present invention, its realization steps are as follows:

[0110] 1. Select the fatigue test load spectrum of the li...

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Abstract

The invention discloses a method for determining the fatigue life extension test period of an aging aircraft. The method is characterized by including the following steps: (1) selecting fatigue test load spectra of a life extension testing machine, (2) determining the total equivalent flight hours, (3) determining fatigue dispersion coefficients of the remaining fatigue life of the aging aircraft, and (4) determining the fatigue life extension test period of the aging aircraft. The method has the advantages that the fatigue dispersion coefficients of the remaining fatigue life (durability) can be determined according to different flight states of the aging aircraft, and the test period of whole aircraft fatigues (durability) of the aging aircraft is accordingly calculated according to a life extension target; under the condition that an on-service aircraft is on active service under the new whole aircraft fatigue test load spectra, and the load spectra are increased in the follow-up using process, the load spectra with the injury tolerance which is m' times that of the average load spectra of follow-up flights are selected for serving as whole aircraft fatigue test load spectra of the life extension testing machine, and the test period of the whole aircraft fatigues (durability) of the life extension testing machine can be shortened.

Description

technical field [0001] The invention relates to a method for determining the fatigue life extension test period of an aging aircraft, and belongs to the technical field of aircraft test research. Background technique [0002] At present, the fatigue (durability) safety life of an aircraft is generally expressed in flight hours, which is usually obtained by dividing the flight hours of the fatigue (durability) test of the whole aircraft by the fatigue dispersion coefficient. When the flight hours of the aircraft in service reach the initial safe life, in order to further explore the life potential of the aging aircraft, it is usually necessary to conduct a full-flight fatigue (durability) test on the aging aircraft to further extend the service life of the aging aircraft. [0003] The existing aging aircraft fatigue (durability) test usually adopts the following method: Randomly select an aging aircraft that has undergone durability repairs from the aircraft in service fleet ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F19/00
Inventor 何宇廷高潮崔荣洪伍黎明安涛杜金强
Owner AIR FORCE UNIV PLA
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