| 固体火箭发动机塞式喷管数值模拟和热态试验 |
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| 引用本文： | 任军学,刘宇,廖云飞,谢侃.固体火箭发动机塞式喷管数值模拟和热态试验[J].航空动力学报,2011,26(6):1420-1425. |
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| 作者姓名： | 任军学 刘宇 廖云飞 谢侃 |
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| 作者单位： | 北京航空航天大学宇航学院,北京,100191 |
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| 基金项目： | 国家自然科学基金(50476002) |
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| 摘 要： | 为了考察固体火箭发动机塞式喷管的性能,设计了一套单元内喷管数为16、面积比为25的环簇式固体塞式喷管和一对比用钟型喷管,采用数值模拟方法预估了其推力性能.对塞式喷管进行了地面热态试验,测定了其推力性能.结果表明,环簇式塞式喷管地面燃气流动现象和推力性能的数值模拟结果与试验结果吻合.塞式喷管在地面上的推力效率达92.6%...
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| 关 键 词： | 固体火箭发动机 塞式喷管 推力特性 数值模拟 热态试验 |
| 收稿时间： | 2010/5/31 0:00:00 |
| 修稿时间： | 2010/7/22 0:00:00 |
Numerical simulation and hot test investigation of plug nozzle in solid rocket motor |
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| REN Jun-xue,LIU Yu,LIAO Yun-fei and XIE Kan.Numerical simulation and hot test investigation of plug nozzle in solid rocket motor[J].Journal of Aerospace Power,2011,26(6):1420-1425. |
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| Authors: | REN Jun-xue LIU Yu LIAO Yun-fei and XIE Kan |
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| Institution: | REN Jun-xue,LIU Yu,LIAO Yun-fei,XIE Kan(School of Astronautics,Beijing University of Aeronautics and Astronautics,Beijing 100191,China) |
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| Abstract: | A clustered type of plug nozzle,with 16 unit nozzles and an area ratio of 25,and a compared bell nozzle were designed to gain the performance characteristics of plug nozzle.The thrust performances of the nozzles were evaluated with numerical simulation method.A ground hot test was done to measure the thrust performance the clustered plug nozzle.The result shows that the numerical simulation results of the flow phenomenon and thrust performance accord with the experimental results.The thrust efficient of the... |
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| Keywords: | solid rocket motor plug nozzle thrust characteristic numerical simulation hot test |
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