Abstract
In this paper, the effect of cyclic fatigue loading on matrix multiple fracture of fiber-reinforced ceramic-matrix composites (CMCs) is investigated using the critical matrix strain energy (CMSE) criterion. The relationships between multiple matrix cracking, cyclic fatigue peak stress, fiber/matrix interface wear, and debonding are established. The effects of fiber volume fraction, fiber/matrix interface shear stress, and applied cycle number on matrix multiple fracture and fiber/matrix interface debonding and interface wear are discussed. Comparisons of multiple matrix cracking with/without cyclic fatigue loading are analyzed. The experimental matrix cracking of unidirectional SiC/CAS, SiC/SiC, SiC/Borosilicate, and mini-SiC/SiC composites with/without cyclic fatigue loading are predicted.
Highlights
Advancements in aerospace technology heavily depend on the development of structural materials that maintain mechanical performance at elevated temperatures
At the matrix cracking stress of of 360 MPa; the fiber/matrix interface debonded length increases from ld/rf = 16.5 to ld/rf = 21.5; the fiber/matrix interface debonding ratio increases from 2ld/lc = 0.9% to 2ld/lc = 57.1%; and, the fiber/matrix interface wear ratio decreases from ζ/ld = 95% to ζ/ld = 73.3%
When the fiber volume content is V f = 35%, the matrix cracking density increases from ψ = 0.06/mm at the first matrix cracking stress of σmc = 258 MPa to ψ = 2.3/mm at the matrix cracking stress of 360 MPa; the fiber/matrix interface debonded length increases from ld /rf = 9.3 to ld /rf = 12; the fiber/matrix interface debonding ratio increases from 2ld /lc = 0.9% to 2ld /lc = 42.3%; and, the fiber/matrix interface wear ratio decreases from ζ/ld = 82.4% to ζ/ld = 63.6%
Summary
Advancements in aerospace technology heavily depend on the development of structural materials that maintain mechanical performance at elevated temperatures. The matrix cracking evolution, saturation matrix cracking stress and density affect the non-linear behavior of CMCs. Under cyclic fatigue loading, the fiber/matrix interface debonding and sliding occurred between matrix crack spacing, leading to interface wear [26,27]. Based on the CMSE criterion [19], the matrix cracking density of fiber-reinforced CMCs remains constant under cyclic fatigue loading. Simon et al [29] investigated the behavior of a SiC/[Si-B-C] composite that was tested under air at 450 ◦ C and static and cyclic fatigue conditions, while using electrical resistivity and acoustic emission measurements in order to monitor the ageing of the material. The effect of cyclic fatigue loading on matrix multiple fracture of fiber-reinforced. The relationships between multiple matrix cracking, cyclic fatigue peak stress, fiber/matrix interface wear, and debonding are established. The proposed model applies at ambient temperatures and it excludes any chemical degradation effect
Sign-in/Register to view highlights & summary Sign-in/Register to access full text options 
Free) 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
