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Ultrahigh-temperature ceramic modified C/C composite material for aerospace power and preparation method of ultrahigh-temperature ceramic modified C/C composite material
The invention discloses an ultra-high-temperature ceramic modified C/C composite material for aerospace power and a preparation method thereof. The oxidation ablation resistance of the C/C composite material is improved by introducing a ZrC and SiBCN multiphase ultra-high-temperature ceramic matrix into a C/C green body. The C/C-ZrC-SiBCN ultrahigh-temperature ceramic-based composite material is prepared by the following steps: carrying out high-temperature heat treatment on a carbon fiber preform, carrying out chemical vapor-phase oriented deposition on a carbon matrix process, carrying out densification by a high-pressure complex-phase precursor uniform mixing, dipping and co-cracking process, and carrying out post-high-temperature heat treatment until the material density reaches 2.3-2.5 g/cm < 3 >. The specific preparation method comprises the following steps: firstly, carrying out high-temperature heat treatment on a carbon fiber preform, then carrying out PyC interface deposition and matrix carbon preparation by adopting a chemical vapor deposition process, then preparing a ZrC ceramic matrix and a SiBCN matrix, and then carrying out post-high-temperature heat treatment on the formed composite material to obtain the ZrC/SiBCN composite material. Finally, SiC surface coating is conducted through chemical vapor deposition, and the C/C-ZrC-SiBCN ultrahigh-temperature ceramic-based composite material for aerospace power is obtained. The C/C-ZrC-SiBCN ultrahigh-temperature ceramic-based composite material has the advantages of being resistant to ultrahigh temperature, low in expansion coefficient, excellent in oxidation resistance and ablation performance and the like.
一种空天动力用超高温陶瓷改性C/C复合材料及其制备方法，通过在C/C坯体中引入ZrC和SiBCN多相超高温陶瓷基体改善了C/C复合材料抗氧化烧蚀性能。其中所述的C/C‑ZrC‑SiBCN超高温陶瓷基复合材料是将碳纤维预制体经高温热处理、化学气相定向沉积碳基体工艺以及高压复相先驱体均匀混料浸渍共裂解工艺致密化以及后高温热处理工艺至材料密度达到2.3g/cm3~2.5g/cm3。具体制备方法为：首先将碳纤维预制体进行高温热处理，之后采用化学气相沉积工艺进行PyC界面沉积和基体碳制备，然后进行ZrC陶瓷基体和SiBCN基体制备，然后对形成复合材料进行后高温热处理，最后采用化学气相沉积进行SiC表面涂层得到了空天动力用C/C‑ZrC‑SiBCN超高温陶瓷基复合材料，具有耐超高温，低膨胀系数，优异抗氧化和烧蚀性能等优点。
Ultrahigh-temperature ceramic modified C/C composite material for aerospace power and preparation method of ultrahigh-temperature ceramic modified C/C composite material
The invention discloses an ultra-high-temperature ceramic modified C/C composite material for aerospace power and a preparation method thereof. The oxidation ablation resistance of the C/C composite material is improved by introducing a ZrC and SiBCN multiphase ultra-high-temperature ceramic matrix into a C/C green body. The C/C-ZrC-SiBCN ultrahigh-temperature ceramic-based composite material is prepared by the following steps: carrying out high-temperature heat treatment on a carbon fiber preform, carrying out chemical vapor-phase oriented deposition on a carbon matrix process, carrying out densification by a high-pressure complex-phase precursor uniform mixing, dipping and co-cracking process, and carrying out post-high-temperature heat treatment until the material density reaches 2.3-2.5 g/cm < 3 >. The specific preparation method comprises the following steps: firstly, carrying out high-temperature heat treatment on a carbon fiber preform, then carrying out PyC interface deposition and matrix carbon preparation by adopting a chemical vapor deposition process, then preparing a ZrC ceramic matrix and a SiBCN matrix, and then carrying out post-high-temperature heat treatment on the formed composite material to obtain the ZrC/SiBCN composite material. Finally, SiC surface coating is conducted through chemical vapor deposition, and the C/C-ZrC-SiBCN ultrahigh-temperature ceramic-based composite material for aerospace power is obtained. The C/C-ZrC-SiBCN ultrahigh-temperature ceramic-based composite material has the advantages of being resistant to ultrahigh temperature, low in expansion coefficient, excellent in oxidation resistance and ablation performance and the like.
一种空天动力用超高温陶瓷改性C/C复合材料及其制备方法，通过在C/C坯体中引入ZrC和SiBCN多相超高温陶瓷基体改善了C/C复合材料抗氧化烧蚀性能。其中所述的C/C‑ZrC‑SiBCN超高温陶瓷基复合材料是将碳纤维预制体经高温热处理、化学气相定向沉积碳基体工艺以及高压复相先驱体均匀混料浸渍共裂解工艺致密化以及后高温热处理工艺至材料密度达到2.3g/cm3~2.5g/cm3。具体制备方法为：首先将碳纤维预制体进行高温热处理，之后采用化学气相沉积工艺进行PyC界面沉积和基体碳制备，然后进行ZrC陶瓷基体和SiBCN基体制备，然后对形成复合材料进行后高温热处理，最后采用化学气相沉积进行SiC表面涂层得到了空天动力用C/C‑ZrC‑SiBCN超高温陶瓷基复合材料，具有耐超高温，低膨胀系数，优异抗氧化和烧蚀性能等优点。
Ultrahigh-temperature ceramic modified C/C composite material for aerospace power and preparation method of ultrahigh-temperature ceramic modified C/C composite material
一种空天动力用超高温陶瓷改性C/C复合材料及其制备方法
LUO RUIYING (Autor:in) / SUN SHOUYE (Autor:in) / HUANG PENG (Autor:in)
06.12.2024
Patent
Elektronische Ressource
Chinesisch
IPC:
C04B
Kalk
,
LIME
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