C/C-ZrC复合材料的制备及结构性能研究
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航天材料及工艺研究所,先进功能复合材料技术重点实验室,北京 100076

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TB332

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Preparation and Structural Properties of C/C-ZrC Composites
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Science and Technology on Advanced Functional Composite Laboratory,Aerospace Research Institute of Materials &Processing Technology,Beijing 100076

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    摘要:

    采用针刺及细编穿刺结构分别引入热解碳和沥青碳的多孔C/C坯体,通过反应熔渗工艺(RMI)与熔融金属Zr反应制备了C/C-ZrC复合材料。研究了预制体结构和基体碳类型对C/C-ZrC复合材料微观结构及力学性能的影响。结果表明:材料熔渗后只由C,ZrC两相组成,孔隙率5%~10%,ZrC质量分数53%~63%。针刺结构的C/C坯体熔渗效果更好,制得的C/C-ZrC复合材料密度最高达到3.21 g/cm3;ZrC质量分数达到62.8%。热解碳基体在熔渗过程中对纤维保护作用更好,C/C-ZrC复合材料的弯曲强度达到148 MPa,压缩强度达到408 MPa。

    Abstract:

    The porous C/C body of pyrolytic carbon and asphaltic carbon was respectively introduced into the porous C/C body by needling and fine woven puncture structure. The C/C-ZrC composites were prepared by reacting melt infiltration (RMI) process with molten metal Zr. The effects of preform structure and matrix carbon type on the microstructure and mechanical properties of C/C-ZrC composites were studied. The results show that the material is only composed of C and ZrC phases after melting, the porosity is between 5% to 10%, and the mass fraction of ZrC is between 53% to 63%. The C/C body with needled structure has better melting effect, and the C/C-ZrC composite with the highest density reaches 3.21 g/cm3. The ZrC mass fraction reaches 62.8%. The pyrolysis carbon matrix has a better protective effect on the fiber during the melting and infiltration process, and the bending strength of C/C-ZrC composites reaches 148 MPa and the compression strength reaches 408 MPa.

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朱家缔,许正辉,宋永忠. C/C-ZrC复合材料的制备及结构性能研究[J].宇航材料工艺,2021,51(3):72-76.

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  • 收稿日期:2021-02-17
  • 最后修改日期:2021-04-15
  • 录用日期:2021-04-06
  • 在线发布日期: 2021-06-03
  • 出版日期:
第十一届航天复合材料成形与加工工艺技术中心交流会 征文通知

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