Fatigue Life Analysis of Aluminum Alloy Notched Specimens under Non-Gaussian Excitation based on Fatigue Damage Spectrum

In this study, a non-Gaussian excitation acceleration method is proposed, using aluminum alloy notched specimens as a research object and measured acceleration signal of a certain airborne bracket, during aircraft flight as input excitations, based on the fatigue damage spectrum (FDS) theory. The ku...

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Autores principales:	Kuanyu Chen, Guangwu Yang, Jianjun Zhang, Shoune Xiao, Yang Xu
Formato:	article
Lenguaje:	EN
Publicado:	Hindawi Limited 2021
Materias:	Physics QC1-999
Acceso en línea:	https://doaj.org/article/bf0a1adbc3e843c9b56983986fb2f57e
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spelling	oai:doaj.org-article:bf0a1adbc3e843c9b56983986fb2f57e2021-11-08T02:35:47ZFatigue Life Analysis of Aluminum Alloy Notched Specimens under Non-Gaussian Excitation based on Fatigue Damage Spectrum1875-920310.1155/2021/6887951https://doaj.org/article/bf0a1adbc3e843c9b56983986fb2f57e2021-01-01T00:00:00Zhttp://dx.doi.org/10.1155/2021/6887951https://doaj.org/toc/1875-9203In this study, a non-Gaussian excitation acceleration method is proposed, using aluminum alloy notched specimens as a research object and measured acceleration signal of a certain airborne bracket, during aircraft flight as input excitations, based on the fatigue damage spectrum (FDS) theory. The kurtosis and skewness of the input signal are calculated and the non-Gaussian characteristics and amplitude distribution are evaluated. Five task segments obey a non-Gaussian distribution, while one task segment obeys a Gaussian distribution. The fatigue damage spectrum calculation method of non-Gaussian excitation is derived. The appropriate FDS calculation method is selected for each task segment and the acceleration parameters are set to construct the acceleration power spectral density, which is equivalent to the pseudo-acceleration damage. A finite-element model is established, the notch stress concentration factor of the specimen is calculated, the large mass point method is used to simulate the shaking table excitation, and a random vibration analysis is carried out to calculate the accelerated fatigue life. The simulation results show that the relative error between the original cumulative damage and test original fatigue life is 15.7%. The shaking table test results show that the relative error of fatigue life before and after acceleration is less than 16.95%, and the relative error of test and simulation is 24.27%. The failure time of the specimen is accelerated from approximately 12 h to 1 h, the acceleration ratio reaches 12, and the average acceleration ideal factor is 1.125, which verifies the effectiveness of the acceleration method. It provides a reference for the compilation of the load spectrum and vibration endurance acceleration test of other airborne aircraft equipment.Kuanyu ChenGuangwu YangJianjun ZhangShoune XiaoYang XuHindawi LimitedarticlePhysicsQC1-999ENShock and Vibration, Vol 2021 (2021)
institution	DOAJ
collection	DOAJ
language	EN
topic	Physics QC1-999
spellingShingle	Physics QC1-999 Kuanyu Chen Guangwu Yang Jianjun Zhang Shoune Xiao Yang Xu Fatigue Life Analysis of Aluminum Alloy Notched Specimens under Non-Gaussian Excitation based on Fatigue Damage Spectrum
description	In this study, a non-Gaussian excitation acceleration method is proposed, using aluminum alloy notched specimens as a research object and measured acceleration signal of a certain airborne bracket, during aircraft flight as input excitations, based on the fatigue damage spectrum (FDS) theory. The kurtosis and skewness of the input signal are calculated and the non-Gaussian characteristics and amplitude distribution are evaluated. Five task segments obey a non-Gaussian distribution, while one task segment obeys a Gaussian distribution. The fatigue damage spectrum calculation method of non-Gaussian excitation is derived. The appropriate FDS calculation method is selected for each task segment and the acceleration parameters are set to construct the acceleration power spectral density, which is equivalent to the pseudo-acceleration damage. A finite-element model is established, the notch stress concentration factor of the specimen is calculated, the large mass point method is used to simulate the shaking table excitation, and a random vibration analysis is carried out to calculate the accelerated fatigue life. The simulation results show that the relative error between the original cumulative damage and test original fatigue life is 15.7%. The shaking table test results show that the relative error of fatigue life before and after acceleration is less than 16.95%, and the relative error of test and simulation is 24.27%. The failure time of the specimen is accelerated from approximately 12 h to 1 h, the acceleration ratio reaches 12, and the average acceleration ideal factor is 1.125, which verifies the effectiveness of the acceleration method. It provides a reference for the compilation of the load spectrum and vibration endurance acceleration test of other airborne aircraft equipment.
format	article
author	Kuanyu Chen Guangwu Yang Jianjun Zhang Shoune Xiao Yang Xu
author_facet	Kuanyu Chen Guangwu Yang Jianjun Zhang Shoune Xiao Yang Xu
author_sort	Kuanyu Chen
title	Fatigue Life Analysis of Aluminum Alloy Notched Specimens under Non-Gaussian Excitation based on Fatigue Damage Spectrum
title_short	Fatigue Life Analysis of Aluminum Alloy Notched Specimens under Non-Gaussian Excitation based on Fatigue Damage Spectrum
title_full	Fatigue Life Analysis of Aluminum Alloy Notched Specimens under Non-Gaussian Excitation based on Fatigue Damage Spectrum
title_fullStr	Fatigue Life Analysis of Aluminum Alloy Notched Specimens under Non-Gaussian Excitation based on Fatigue Damage Spectrum
title_full_unstemmed	Fatigue Life Analysis of Aluminum Alloy Notched Specimens under Non-Gaussian Excitation based on Fatigue Damage Spectrum
title_sort	fatigue life analysis of aluminum alloy notched specimens under non-gaussian excitation based on fatigue damage spectrum
publisher	Hindawi Limited
publishDate	2021
url	https://doaj.org/article/bf0a1adbc3e843c9b56983986fb2f57e
work_keys_str_mv	AT kuanyuchen fatiguelifeanalysisofaluminumalloynotchedspecimensundernongaussianexcitationbasedonfatiguedamagespectrum AT guangwuyang fatiguelifeanalysisofaluminumalloynotchedspecimensundernongaussianexcitationbasedonfatiguedamagespectrum AT jianjunzhang fatiguelifeanalysisofaluminumalloynotchedspecimensundernongaussianexcitationbasedonfatiguedamagespectrum AT shounexiao fatiguelifeanalysisofaluminumalloynotchedspecimensundernongaussianexcitationbasedonfatiguedamagespectrum AT yangxu fatiguelifeanalysisofaluminumalloynotchedspecimensundernongaussianexcitationbasedonfatiguedamagespectrum
_version_	1718443223659053056

Fatigue Life Analysis of Aluminum Alloy Notched Specimens under Non-Gaussian Excitation based on Fatigue Damage Spectrum

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