Affiliation of Author(s):民航学院
Journal:MATERIALS SCIENCE AND ENGINEERING A-STRUCTURAL MATERIALS PROPERTIES MICROSTRUCTURE AND PROCESSING
Key Words:Ceramic-matrix composites (CMCs) Damage evolution Oxidation Matrix multicracking Interface debonding
Abstract:In- this paper, the damage evolution of cross-ply ceramic-matrix composites (CMCs) under stress-rupture and cyclic loading at elevated temperatures in oxidizing atmosphere has been investigated. The BudianskyHutchinson-Evans shear-lag model was used to describe the micro stress field of the damaged composite considering matrix multicracking, interface debonding/wear/oxidation/slip. The damage parameters of fatigue hysteresis dissipated energy, fatigue hysteresis modulus, fatigue peak strain and fatigue hysteresis width have been used to monitor the damage evolution inside of CMCs. The relationship between damage parameters and internal damage of matrix multicracking, interface debonding/slip has been established. The experimental fatigue hysteresis loops, interface slip lengths, fatigue hysteresis dissipated energy and peak strain of cross-ply SiC/MAS composite under cyclic fatigue and stress-rupture at 566 degrees C and 1093 degrees C in air have been predicted.
ISSN No.:0921-5093
Translation or Not:no
Date of Publication:2017-03-14
Correspondence Author:llb
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Lecturer
Education Level:南京航空航天大学
Degree:Doctoral Degree in Engineering
School/Department:College of Civil Aviation
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