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<p>C/SiC composites are crucial materials in hot structures of reusable high-speed aircraft, which are faced by the extreme service environments requiring more stringent material designs. In this work, the thermo-mechanical coupling failure mechanisms and durability of C/SiC composite with jointed features are investigated comprehensively. The study demonstrates that the rivet significantly reduces the stress concentration factor (SCF) of open-hole composite structures from 1.76 to 1.35, while achieving a remarkable fourfold enhancement in fatigue life under identical stress levels. Compared to the constant service environment, it is found that the dynamic thermo-mechanical coupling load would further deteriorate the performances of materials, in which the structural fatigue life has decreased by approximately 40%. Oxidative damage of carbon fibers under cyclic high-temperature oxidative environments constitutes the fundamental mechanism for fatigue life degradation in the material. When superimposed with cyclic stress, this process synergistically exacerbates material degradation, accelerating performance deterioration. Finally, a modified stiffness degradation model considering the oxidation damage resulting from the cyclic thermo-mechanical coupling load is proposed to establish the relationship between the residual performance of C/SiC composites and cyclic numbers. The results of this work provide novel insights into the design of C/SiC composite structures for reusable high-speed aircraft.</p>

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The failure mechanisms and durability of C/SiC composites with jointed features under cyclic thermo-mechanical loading

  • 期刊论文

  • 发表日期：

    2025年6月11日

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  • Peifei Xu,
  • Zhiyong Tan,
  • Zhenqiang Wu,
  • Peiwei Zhang,
  • Yanbin Li,
  • Dahai Zhang,
  • Zhengong Zhou,
  • Qingguo Fei

摘要

C/SiC composites are crucial materials in hot structures of reusable high-speed aircraft, which are faced by the extreme service environments requiring more stringent material designs. In this work, the thermo-mechanical coupling failure mechanisms and durability of C/SiC composite with jointed features are investigated comprehensively. The study demonstrates that the rivet significantly reduces the stress concentration factor (SCF) of open-hole composite structures from 1.76 to 1.35, while achieving a remarkable fourfold enhancement in fatigue life under identical stress levels. Compared to the constant service environment, it is found that the dynamic thermo-mechanical coupling load would further deteriorate the performances of materials, in which the structural fatigue life has decreased by approximately 40%. Oxidative damage of carbon fibers under cyclic high-temperature oxidative environments constitutes the fundamental mechanism for fatigue life degradation in the material. When superimposed with cyclic stress, this process synergistically exacerbates material degradation, accelerating performance deterioration. Finally, a modified stiffness degradation model considering the oxidation damage resulting from the cyclic thermo-mechanical coupling load is proposed to establish the relationship between the residual performance of C/SiC composites and cyclic numbers. The results of this work provide novel insights into the design of C/SiC composite structures for reusable high-speed aircraft.