Total fatigue life prediction for Ti-alloys airframe structure based on durability and damage-tolerant design concept

Ji kui Zhang; Xiao quan Cheng; Zheng neng Li

doi:10.1016/j.matdes.2010.03.052

Total fatigue life prediction for Ti-alloys airframe structure based on durability and damage-tolerant design concept

Ji kui Zhang^*
, Xiao quan Cheng
, Zheng neng Li

^*此作品的通讯作者

航空科学与工程学院

Beihang University

科研成果: 期刊稿件 › 文章 › 同行评审

42 引用（Scopus）

摘要

Based on the concept of the damage-tolerance and durability design, the total fatigue life of titanium alloys is divided into three phases: crack initiation (0-0.3mm), short crack growth (0.3-2mm) and long crack growth (2mm-a_C). Among these three phases, different prediction models are accepted due to different failure mechanisms. A computer program was developed to predict the total fatigue life of the titanium alloy structure. Fatigue testing is also conducted for two types of ELI grade titanium alloy to verify the prediction models. The predicted fatigue life agrees well with experimental results.

源语言	英语
页（从-至）	4329-4335
页数	7
期刊	Materials and Design
卷	31
期	9
DOI	https://doi.org/10.1016/j.matdes.2010.03.052
出版状态	已出版 - 10月 2010

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title = "Total fatigue life prediction for Ti-alloys airframe structure based on durability and damage-tolerant design concept",

abstract = "Based on the concept of the damage-tolerance and durability design, the total fatigue life of titanium alloys is divided into three phases: crack initiation (0-0.3mm), short crack growth (0.3-2mm) and long crack growth (2mm-aC). Among these three phases, different prediction models are accepted due to different failure mechanisms. A computer program was developed to predict the total fatigue life of the titanium alloy structure. Fatigue testing is also conducted for two types of ELI grade titanium alloy to verify the prediction models. The predicted fatigue life agrees well with experimental results.",

keywords = "Damage-tolerant, Titanium alloys, Total fatigue life",

author = "Zhang, \{Ji kui\} and Cheng, \{Xiao quan\} and Li, \{Zheng neng\}",

year = "2010",

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doi = "10.1016/j.matdes.2010.03.052",

language = "英语",

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T1 - Total fatigue life prediction for Ti-alloys airframe structure based on durability and damage-tolerant design concept

AU - Zhang, Ji kui

AU - Cheng, Xiao quan

AU - Li, Zheng neng

PY - 2010/10

Y1 - 2010/10

N2 - Based on the concept of the damage-tolerance and durability design, the total fatigue life of titanium alloys is divided into three phases: crack initiation (0-0.3mm), short crack growth (0.3-2mm) and long crack growth (2mm-aC). Among these three phases, different prediction models are accepted due to different failure mechanisms. A computer program was developed to predict the total fatigue life of the titanium alloy structure. Fatigue testing is also conducted for two types of ELI grade titanium alloy to verify the prediction models. The predicted fatigue life agrees well with experimental results.

AB - Based on the concept of the damage-tolerance and durability design, the total fatigue life of titanium alloys is divided into three phases: crack initiation (0-0.3mm), short crack growth (0.3-2mm) and long crack growth (2mm-aC). Among these three phases, different prediction models are accepted due to different failure mechanisms. A computer program was developed to predict the total fatigue life of the titanium alloy structure. Fatigue testing is also conducted for two types of ELI grade titanium alloy to verify the prediction models. The predicted fatigue life agrees well with experimental results.

KW - Damage-tolerant

KW - Titanium alloys

KW - Total fatigue life

UR - https://www.scopus.com/pages/publications/77953540350

U2 - 10.1016/j.matdes.2010.03.052

DO - 10.1016/j.matdes.2010.03.052

M3 - 文章

AN - SCOPUS:77953540350

SN - 0264-1275

VL - 31

SP - 4329

EP - 4335

JO - Materials and Design

JF - Materials and Design

IS - 9

ER -

Total fatigue life prediction for Ti-alloys airframe structure based on durability and damage-tolerant design concept

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