scholarly journals Prediction of Fatigue Crack Growth under Variable-Amplitude and Spectrum Loading Using a Closure Model

2009 ◽  
pp. 255-255-23 ◽  
Author(s):  
JC Newman
Keyword(s):  
Fatigue Crack ◽  
Fatigue Crack Growth ◽  
Crack Growth ◽  
Closure Model ◽  
Variable Amplitude ◽  
Spectrum Loading

A Modified Compliance Method for Automatically Measuring Fatigue Crack Growth In Situ during Spectrum Fatigue Testing

2014 ◽  
Vol 891-892 ◽  
pp. 732-738
Author(s):  
Wyman Zhuang ◽  
Qian Chu Liu
Keyword(s):  
Fatigue Crack ◽  
Fatigue Crack Growth ◽  
Crack Growth ◽  
Operating Conditions ◽  
Loading Conditions ◽  
Variable Amplitude Loading ◽  
Variable Amplitude ◽  
Marker Band ◽  
Spectrum Loading

The fatigue critical structures of military aircraft are generally subjected to variable amplitude flight spectrum loading. Maintaining aircraft structural integrity to ensure safe operation of the fleet is critically dependent on accurate analysis and reliable prediction of fatigue crack growth in those structures under service operating conditions. To achieve this goal, laboratory experimental methods that can accurately measure and monitor fatigue crack growth under variable amplitude loading are required. This can be challenging as no test standard exists to guide the process of fatigue crack growth measurement under variable amplitude loading conditions to ensure the accuracy of the test results. This challenge was addressed by developing a modified compliance method as described in this paper. The results presented employed a modified compliance method complemented with a travelling microscope technique and marker band loads. The modified compliance method developed is able to measure in-situ, fatigue crack growth of standard compact-tension specimens under a fighter flight spectrum loading. The marker band loads and microscope readings were used to assist the post-test validation using quantitative fractography. The results from this study have demonstrated that the modified compliance method can produce consistent and accurate fatigue crack growth data under variable amplitude loading conditions.

Quantifying Spectrum Loading Effects on Fatigue Crack Growth in 7075-T73 Aluminum

2000 ◽  
Vol 45 (1) ◽  
pp. 11-18
Author(s):  
H. Lewis Zion ◽  
W. Steven Johnson ◽  
Dale L. Ball ◽  
Richard A. Everett
Keyword(s):  
Fatigue Crack ◽  
Fatigue Crack Growth ◽  
Crack Growth ◽  
Loading Effects ◽  
Spectrum Loading
Sign in / Sign up

Export Citation Format

Share Document