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

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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Problems solved by technology

[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 solve the problem of relatively small sample size in the calculation and analysis of the existing aircraft safety life, and to improve the reliability analysis of aircraft structures the accuracy of

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