Abstract
In this paper, the effect of stochastic loading on tensile damage and fracture of fiber-reinforced ceramic-matrix composites (CMCs) is investigated. A micromechanical constitutive model is developed considering multiple damage mechanisms under tensile loading. The relationship between stochastic stress, tangent modulus, interface debonding and fiber broken is established. The effects of the fiber volume, interface shear stress, interface debonding energy, saturation matrix crack spacing and fiber strength on tensile stress–strain curve, tangent modulus, interface debonding fraction and fiber broken fraction are analyzed. The experimental tensile damage and fracture of unidirectional and 2D SiC/SiC composites subjected to different stochastic loading stress are predicted. When fiber volume increases, the initial composite strain decreases, the initial tangent modulus increases, the transition stress for interface debonding decreases and the initial fiber broken fraction decreases. When fiber strength increases, the initial composite strain and fiber broken fraction decrease.
Highlights
Ceramic-matrix composites (CMCs) have the advantages of high-temperature resistance, corrosion resistance, low density, high specific strength and high specific modulus [1]
The objective of this paper is to investigate the effect of stochastic loading on tensile damage and fracture of fiber-reinforced ceramic-matrix composites (CMCs) for the first time
The fiber axial stress distribution is affected by the stochastic loading stress level, matrix cracking, interface debonding and fiber failure
Summary
Ceramic-matrix composites (CMCs) have the advantages of high-temperature resistance, corrosion resistance, low density, high specific strength and high specific modulus [1]. The mechanical performance of CMCs depends on the fabrication method. To ensure the reliability and safety of fiber-reinforced CMCs used in hot-section components of an aero engine, it is necessary to develop performance evaluation, damage evolution, strength and life prediction tools for airworthiness certification [2]. Since the applications of fiber-reinforced CMCs involve components with lives that are measured in tens of thousands of hours, the successful design and implementation of CMC components depend on the knowledge of the material behavior over periods of time comparable to the expected service life of the component [3]. Multiple damage mechanisms of matrix cracking, interface debonding and fiber failure occur [4,5,6,7,8]. The tensile stress–strain curves can be divided into four stages, including:
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