Aircraft structure safe life determining method based on testing and serving use data fusion

A technology of aircraft structure and safe life, applied in the direction of electrical digital data processing, special data processing applications, instruments, etc., can solve the problem of small sample size

Active Publication Date: 2013-11-27
何宇廷
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[0012] The purpose of the embodiments of the present invention is to provide a method for determining the safety life of aircraft structures based on the fusion of test and service use data, aiming to

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  • Aircraft structure safe life determining method based on testing and serving use data fusion
  • Aircraft structure safe life determining method based on testing and serving use data fusion
  • Aircraft structure safe life determining method based on testing and serving use data fusion

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Embodiment Construction

[0087] In order to make the object, technical solution and advantages of the present invention more clear, the present invention will be further described in detail below in conjunction with the examples. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.

[0088] figure 1 It shows the flow of the method for determining the safety life of the group when the test fatigue life data and service fatigue life data of the same type of aircraft under different load spectrums are subject to the logarithmic normal distribution provided by the present invention. For ease of illustration, only the parts relevant to the present invention are shown.

[0089] The embodiment of the present invention provides a method for determining the safety life of the group when the test fatigue life data and the fatigue life data in service under different load spectra of the same type of aircraft obey...

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Abstract

The invention discloses an aircraft structure safe life determining method based on testing and serving use data fusion. The aircraft structure safe life determining method includes an air fleet safe life determining method when testing fatigue life data and serving use fatigue life data of same-type aircrafts under different load spectrums are in lognormal distribution, and an air fleet safe life determining method of the same-type aircrafts under the same testing load spectrum. The air fleet safe life determining method when the testing fatigue life data and the serving use fatigue life data of the same-type aircrafts under the different load spectrums are in lognormal distribution includes the steps of obtaining the fatigue life data of any right truncation tail of each aircraft structure, calculating fatigue life distribution function parameters of the aircraft structures, and calculating the fatigue life dispersion coefficients and the safe life of an aircraft air fleet. The air fleet safe life determining method of the same-type aircrafts under the same testing load spectrum includes the steps of calculating fatigue damage values, equivalent flight hours or rising and falling times of the serving aircraft structures, obtaining the fatigue life data of any right truncation tail of each aircraft structure, calculating fatigue life distribution function parameters of the aircraft structures, and calculating the fatigue dispersion coefficients and the safe life of the aircraft air fleet.

Description

technical field [0001] The invention belongs to the technical field of aircraft structure safety life calculation, in particular to a method for determining the safety life of aircraft structure based on fusion of test and service use data. Background technique [0002] Fatigue life of aircraft structure is a key parameter reflecting the economy and safety of aircraft structure, which is related to structural quality and service conditions. Due to the influence of uncertain factors, in order to ensure the safety of aircraft structure, it is necessary to carry out life reliability analysis of aircraft structure. The service life of the aircraft structure determined according to the safe life design criteria is called the safe life, and the safe life of the aircraft structure N p，γ is the median fatigue life N of the aircraft structure 50 and the fatigue dispersion coefficient (that is, the fatigue life dispersion coefficient) L f The ratio of , namely: [0003] ...

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Application Information

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IPC IPC(8): G06F19/00
Inventor 何宇廷高潮崔荣洪安涛
Owner 何宇廷
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