| C/C喉衬稳态烧蚀的工程计算 |
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| 引用本文： | 方丁酉,夏智勋,姜春林.C/C喉衬稳态烧蚀的工程计算[J].固体火箭技术,2000,23(2):24-27. |
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| 作者姓名： | 方丁酉 夏智勋 姜春林 |
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| 作者单位： | 国防科技大学航天技术系,长沙,410073 |
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| 摘 要： | 根据固体火箭发动机燃烧中氧化性组分扩散控制喷管喉衬烧蚀和Ａｌ２Ｏ３沉积对喉衬的保护，提出Ｃ／Ｃ喉衬稳态烧蚀的工程方法。３个分动机的烧蚀预示结果与实测结果吻合，该计算方法具有较高的精度。
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| 关 键 词： | 固体推进剂火箭发动机 喷管喉部 烧蚀 工程计算 |
Engineering Calculation of C/C Throat Insert Ablation |
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| FANG Ding-you,XIA Zhi-xun,JIANG Chun-lin.Engineering Calculation of C/C Throat Insert Ablation[J].Journal of Solid Rocket Technology,2000,23(2):24-27. |
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| Authors: | FANG Ding-you XIA Zhi-xun JIANG Chun-lin |
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| Abstract: | Based on the diffusion rate of oxidizing species to nozzle surface and Al 2O 3 deposition on the nozzle surface,during firing tests of the solid rocket motors,an engineering method of ablative calculation for C/C throat insert is presented.The calculated results agree with the experimental results of three experimental motors.It shows that the calculation method has a better precision. |
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| Keywords: | solid propellant rocket motor nozzle throat ablation engineering computation |
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