| 塞式喷管单元发动机实验与数值模拟研究 |
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| 引用本文： | 刘宇,戴梧叶,汤海滨,程显辰,马彬,王一白,覃粒子. 塞式喷管单元发动机实验与数值模拟研究[J]. 宇航学报, 2001, 22(4): 27-33 |
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| 作者姓名： | 刘宇 戴梧叶 汤海滨 程显辰 马彬 王一白 覃粒子 |
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| 作者单位： | 北京航空航天大学宇航学院, |
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| 基金项目： | 国家863-2高技术航天领域[863-2-3-4-10]和国家自然科学基金资助项目[59786001];获奖情况:国防科学技术二等奖(编号:2000GFJ2203) |
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| 摘 要： | 简要介绍固体推进剂模拟塞式喷管单元发动机实验系统，给出了实验塞式喷管型面设计方法和特征线法在塞式喷管流场计算中的应用，癖结了实验研究结果，并同数值模拟计算结果进行了比较，主要结果包括燃烧室压力，底部气锥流量，内膨胀比，侧喷管倾角，底部压缩角等对塞式喷管性能的影响，并得出了塞式喷管单元发动机推力方向与其轴线方向夹角的高度特性。
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| 关 键 词： | 火箭发动机 实验 数值模拟 塞式喷管 固体推进剂 |
| 文章编号： | 1000-1328(2001)04-0027-07 |
| 修稿时间： | 2001-01-08 |
EXPERIMENTAL AND NUMERICAL STUDIES ON A UNIT OF AEROSPIKE NOZZLE |
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| Liu Yu Dai Wuye Tang Haibin Cheng Xianchen Ma Bin Wang Yibai Qin Lizi. EXPERIMENTAL AND NUMERICAL STUDIES ON A UNIT OF AEROSPIKE NOZZLE[J]. Journal of Astronautics, 2001, 22(4): 27-33 |
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| Authors: | Liu Yu Dai Wuye Tang Haibin Cheng Xianchen Ma Bin Wang Yibai Qin Lizi |
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| Abstract: | It gives a brief introduction to the experimental system for the solid propellant simulated tests on a unit aerospike nozzle.The design method of the experimental aerospike nozzle contour and the applications of the Method Of Characteristics (MOC) to the flow flied of the aerospike nozzle are presented.The summarized experimental results are compared to the numerical simulated results consisting of the effects to the aerospike nozzle performances by the different combustor pressure,mass flow rate at base,internal expansion ratio,angle between side nozzle axis and the axis of the spike and compressing angle of the base.The altitude property of the angle between the thrust vector of the unit and the axis of the spike is given too. |
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| Keywords: | Rocket engines Experiment Numerical simulation Aerospike nozzle |
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