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| 级间热分离条件下带有延伸喷管的固体火箭发动机尾部流场分析 | |
| 引用本文： | 白宏伟,尤军峰,张铎,姚谦.级间热分离条件下带有延伸喷管的固体火箭发动机尾部流场分析[J].固体火箭技术,2008,31(6). |
| 作者姓名： | 白宏伟 尤军峰 张铎 姚谦 |
| 作者单位： | 1. 海军驻哈尔滨地区航空军事代表室,哈尔滨,150060 2. 中国航天科技集团公司四院四十一所,西安,710025 3. 西北工业大学航天学院,西安,710072 4. 中国人民解放军驻210所军事代表室,西安,710065 |
| 摘 要： | 通过数值方法求解二维轴对称N-S方程,对级间热分离条件下带有延伸喷管的固体火箭发动机尾部流场进行了数值分析。分析表明,展开前,受限尾流使延伸锥、发动机后封头及基础喷管外壁处于严重的热环境中;展开过程中,尾流作用在延伸锥上的气动力变化剧烈。计算结果对发动机的热防护设计及展开机构的驱动力设计提供了依据。 |
| 关 键 词： | 固体火箭发动机 延伸喷管 尾流 级间分离 流场分析 |
Analysis on tail flow field of solid rocket motor with extendible nozzle under stage separation condition |
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| BAI Hong-wei,YOU Jun-feng,ZHANG Duo,YAO Qian.Analysis on tail flow field of solid rocket motor with extendible nozzle under stage separation condition[J].Journal of Solid Rocket Technology,2008,31(6). | |
| Authors: | BAI Hong-wei YOU Jun-feng ZHANG Duo YAO Qian |
| Institution: | BAI Hong-wei1,YOU Jun-feng2,ZHANG Duo3,YAO Qian4 |
| Abstract: | Under stage separation condition,tail flow field of solid rocket motor with extendible nozzle was numerically analyzed by solving 2D axisymmetric N-S equation.The analysis results show that restricted tail flow before exit cone is extended,aft-dome of motor and outside wall of nozzle are exposed in the severe thermal environment;the aerodynamic load of the wake flow on the extendible cone changes violently during extending.The calculation results can provide reference for thermal protection design and actuating force design of extension machanism. |
| Keywords: | solid rocket engine extendible nozzle wake stage separation flow field analysis |
| 本文献已被 CNKI 维普 万方数据 等数据库收录！ | |