Abstract
In this paper, the temperature-dependent vibration damping in C/SiC fiber-reinforced ceramic-matrix composites (CMCs) with different fiber preforms under different vibration frequencies is investigated. A micromechanical temperature-dependent vibration damping model is developed to establish the relationship between composite damping, material properties, internal damage mechanisms, and temperature. The effects of fiber volume, matrix crack spacing, and interface properties on temperature-dependent composite vibration damping of CMCs and interface damage are analyzed. The experimental temperature-dependent composite damping of 2D and 3D C/SiC composites is predicted for different loading frequencies. The damping of the C/SiC composite increases with temperature to the peak value and then decreases with temperature. When the vibration frequency increases from f = 1 to 10 Hz, the peak value of composite damping and corresponding temperature both decrease due to the decrease of interface debonding and slip range, and the damping of 2D C/SiC is much higher than that of 3D C/SiC at temperature range from room temperature to 400 °C. When the fiber volume and interface debonding energy increase, the peak value of composite damping and the corresponding temperature decreases, mainly attributed to the decrease of interface debonding and slip range.
Highlights
Ceramic-matrix composites (CMCs) are the candidate materials for hot section components of aerospace vehicles, high thrust-to-weight-ratio aeroengines, satellite attitude control engines, ramjets, and thermal protection systems [1,2]
For 2D C/SiC, when the vibration frequency increases, the dynamic frictional slip range decreases, which decreases the energy dissipated through frictional slip and composite damping
The composite damping is divided into damping of the fiber and the matrix and the damping caused by frictional dissipated energy
Summary
Ceramic-matrix composites (CMCs) are the candidate materials for hot section components of aerospace vehicles, high thrust-to-weight-ratio aeroengines, satellite attitude control engines, ramjets, and thermal protection systems [1,2]. In the above applications, there exist vibration and noise problems. Failure analysis of rockets and satellites shows that about two-thirds of the failures are related to vibration and noise, leading to reduced operational control accuracy, structural fatigue damage, and shortened safety life [3]. Studying the damping performance of CMCs and improving their reliability in the service environment of vibration and noise is an important guarantee for the safe service of CMCs in various fields [4]. Compared with metals and alloys, CMCs have many unique damping mechanisms due to their internal structure and complex damage mechanisms [5,6,7,8]. Cracks might occur in the matrix, fiber, and interface both between fiber/matrix and neighboring plies [11]
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