| 固液混合火箭发动机喷管流动计算 |
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| 引用本文： | 田辉,蔡国飙,王慧玉,张振鹏.固液混合火箭发动机喷管流动计算[J].航空动力学报,2005,20(1):142-146. |
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| 作者姓名： | 田辉 蔡国飙 王慧玉 张振鹏 |
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| 作者单位： | 北京航空航天大学,宇航学院,北京,100083 |
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| 摘 要： | 利用二维轴对称 N-S方程和组分方程对选用液氧 /端羟基聚丁二烯推进剂的固液混合火箭发动机喷管流动进行了计算。计算采用 LU时间隐式格式、MUSCL空间离散和 Van Leer矢通量分裂方法 ,8组分 1 0反应的化学反应模型 ,对化学源相进行了点隐式处理。喷管入口条件通过燃速计算和热力计算得到 ,计算了多个氧化剂流率和装药长度情况下的喷管流场 ,分析了真空比冲和推力与氧化剂流率的关系 ,为固液混合火箭发动机喷管设计提供了依据
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| 关 键 词： | 航空、航天推进系统 固液混合推进剂火箭 喷管流动 燃烧速度 热力计算 性能计算 |
| 文章编号： | 1000-8055(2005)01-0142-05 |
| 收稿时间： | 2004/1/13 0:00:00 |
| 修稿时间： | 2004年1月13日 |
Nozzle Flow Computation of Classical Hybrid Rocket Motors |
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| TIAN Hui,CAI Guo-biao,WANG Hui-yu and ZHANG Zhen-peng.Nozzle Flow Computation of Classical Hybrid Rocket Motors[J].Journal of Aerospace Power,2005,20(1):142-146. |
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| Authors: | TIAN Hui CAI Guo-biao WANG Hui-yu and ZHANG Zhen-peng |
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| Institution: | School of Astronautics,Beijing University of Aeronautics and Astronautics,Beijing100083,China;School of Astronautics,Beijing University of Aeronautics and Astronautics,Beijing100083,China;School of Astronautics,Beijing University of Aeronautics and Astronautics,Beijing100083,China;School of Astronautics,Beijing University of Aeronautics and Astronautics,Beijing100083,China |
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| Abstract: | Numerical solutions of full Navier-Stokes equations with chemical reaction flow were established for the nozzle flow of the LOX/HTPB hybrid rocket motor.Lower-Upper decomposition scheme and MUSCL-type and VanLeer approach were used.A chemical reaction model with 8 components and 10 elementary reactions was presented.The nozzle entrance condition was obtained by thermodynamic calculation.The nozzle flows under several different oxidizer mass flow rates and grain length were calculated.The relationship between oxidizer mass flow rate and specific impulse was analyzed,which will be useful for the hybrid rocket motor design. |
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| Keywords: | aerospace propulsion system hybrid propellant rockets nozzle flow rate of combustion thermodynamic calculations performance calculation |
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