Fatigue crack growth and delamination behaviours of advanced Al-Li alloy laminate under single tensile overload
Author:
Affiliation:
1. Beijing Institute of Aeronautical Materials; Beijing 100095 China
2. Beijing Aeronautical Science & Technology Research Institute of COMAC; Beijing 102211 China
Publisher
Wiley
Subject
Mechanical Engineering,Mechanics of Materials,General Materials Science
Link
http://onlinelibrary.wiley.com/wol1/doi/10.1111/ffe.12319/fullpdf
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4. The high velocity impact response of composite and FML-reinforced sandwich structures;Villanueva;Compos. Sci. Technol.,2004
5. Characterising mode I/mode II fatigue delamination growth in unidirectional fibre reinforced polymer laminates;Al-Khudairi;Mater. Des.,2015
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