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| 固体火箭发动机用C/SiC导流管烧蚀性能研究 | |
| 引用本文： | 潘育松,徐永东,陈照峰,成来飞,张立同,熊党生.固体火箭发动机用C/SiC导流管烧蚀性能研究[J].宇航学报,2005,26(6):789-792. |
| 作者姓名： | 潘育松 徐永东 陈照峰 成来飞 张立同 熊党生 |
| 作者单位： | 1. 西北工业大学,超高温结构复合材料国防科技重点实验室,西安,710072;南京理工大学,材料科学与工程系,南京,210094 2. 西北工业大学,超高温结构复合材料国防科技重点实验室,西安,710072 3. 南京理工大学,材料科学与工程系,南京,210094 |
| 摘 要： | 采用地面试车试验考核了固体火箭发动机用C/SiC导流管的烧蚀性能,并对C/SiC导流管的烧蚀机理进行了探讨。结果表明:导流管轴向线烧蚀率变化较大,沿气流方向呈上升趋势。材料的线烧蚀率从进口处的0.018mm/s增至出口处的0.032mm/s,且导流管中间段烧蚀稳定性明显优于进口段和出口段。同时,C/SiC导流管的烧蚀机制主要是粒子冲刷和机械剥蚀共同作用的结果。 |
| 关 键 词： | 固体火箭发动机 C/SiC导流管 烧蚀机理 |
| 文章编号： | 1000-1328（2005）06-0789-04 |
| 收稿时间： | 10 25 2004 12:00AM |
| 修稿时间： | 2004-10-252005-01-21 |
Analysis of The Ablation Properties of C/SiC Diversion Tube Used in Solid Rocket Motor |
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| PAN Yu-song,XU Yong-dong,CHEN Zhao-feng,CHENG Lan-fei,ZHANG Li-tong,XIONG Dang-sheng.Analysis of The Ablation Properties of C/SiC Diversion Tube Used in Solid Rocket Motor[J].Journal of Astronautics,2005,26(6):789-792. | |
| Authors: | PAN Yu-song XU Yong-dong CHEN Zhao-feng CHENG Lan-fei ZHANG Li-tong XIONG Dang-sheng |
| Abstract: | Ablation properties and the ablation mechanism of the C/SiC diversion tube used in solid rocket motor(SRM) were analyzed by simulation ablation test.The results show that the axis linear ablation rate of the material has a great change and the linear ablation increases along the gas flux direction.The axis linear ablation rate increases from 0.018mm/s at the gas flux inlet to 0.032mm/s at the gas flux outlet.Ablation mechanism of the C/SiC composites is comprised of particle erosion and mechanism erosion. |
| Keywords: | Ablation C/SiC composites Ablation mechanism |
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