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<p>Ceramic matrix composites (CMCs) are widely used in the aerospace industry owing to their excellent physical properties, such as low density, high specific strength, and high-temperature resistance. As multiphase inhomogeneous materials, CMCs exhibit varied damage modes and failure patterns during high-temperature service, which have important implications for structural safety. To clarify the damage mechanism of CMCs, the mesostructural evolution of carbon fiber reinforced carbon and silicon carbide ceramic composites was observed in-situ using synchrotron radiation computed tomography (SR-CT) at both 25℃ and 1200℃. In addition, digital volume correlation (DVC) was employed to measure the deformations. The results indicate that a large number of matrix cracks exist in the initial state of the material. However, these matrix cracks are not the dominant factor governing failure. At 25&#xa0;°C, interfacial debonding is the primary failure mechanism, whereas at 1200&#xa0;°C, with increasing load, the main crack initiates at the edge of the specimen and propagates inward due to fiber breakage and crack coalescence, eventually leading to specimen failure.</p>

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In-Situ Observations of Tensile Damage in C/SiC Composites at Elevated Temperature

  • 期刊论文

  • 发表日期：

    2026年2月18日

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  • Ruisi Xing,
  • Chuantao Hou,
  • Xingyue Sun,
  • Long Wang,
  • Junbai Song,
  • Yueping Zhang

摘要

Ceramic matrix composites (CMCs) are widely used in the aerospace industry owing to their excellent physical properties, such as low density, high specific strength, and high-temperature resistance. As multiphase inhomogeneous materials, CMCs exhibit varied damage modes and failure patterns during high-temperature service, which have important implications for structural safety. To clarify the damage mechanism of CMCs, the mesostructural evolution of carbon fiber reinforced carbon and silicon carbide ceramic composites was observed in-situ using synchrotron radiation computed tomography (SR-CT) at both 25℃ and 1200℃. In addition, digital volume correlation (DVC) was employed to measure the deformations. The results indicate that a large number of matrix cracks exist in the initial state of the material. However, these matrix cracks are not the dominant factor governing failure. At 25 °C, interfacial debonding is the primary failure mechanism, whereas at 1200 °C, with increasing load, the main crack initiates at the edge of the specimen and propagates inward due to fiber breakage and crack coalescence, eventually leading to specimen failure.