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

^*Corresponding author for this work

School of Aeronautic Science and Engineering

Beihang University

Research output: Contribution to journal › Article › peer-review

42 Scopus citations

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-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.

Original language	English
Pages (from-to)	4329-4335
Number of pages	7
Journal	Materials and Design
Volume	31
Issue number	9
DOIs	https://doi.org/10.1016/j.matdes.2010.03.052
State	Published - Oct 2010

Keywords

Damage-tolerant
Titanium alloys
Total fatigue life

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10.1016/j.matdes.2010.03.052

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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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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

Abstract

Keywords

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