| N2O_HTPB固液火箭发动机喷管两相流计算 |
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| 引用本文： | 田辉,蔡国飙,孙再庸.N2O_HTPB固液火箭发动机喷管两相流计算[J].航空动力学报,2009,24(1). |
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| 作者姓名： | 田辉 蔡国飙 孙再庸 |
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| 作者单位： | 北京航空航天大学宇航学院,北京航空航天大学宇航学院,航天科工集团六院41所，呼和浩特 |
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| 摘 要： | 利用二维轴对称N-S方程对选用氧化亚氮/丁羟基燃料推进剂的固液混合火箭发动机的喷管两相流进行了计算。计算采用MacCormack时间推进预报校正二步格式，采用了Baldwin－Lomax代数湍流模型和两相平衡流模型。计算了三种氧燃比下四个不同喷管的喷管流场参数，并计算了喷管性能，通过比较两相流和气相流的计算结果，分析了不同氧燃比和喷管形状对喷管性能的影响，认为固液火箭发动机的性能主要受氧燃比的影响，为固液混合火箭发动机的设计提供了依据。
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| 关 键 词： | 固液混合火箭发动机 喷管 两相流 氧化亚氮 丁羟基燃料 |
Computation of Nozzle Two-Phase Flow in a N2O_HTPB Hybrid Rocket Motor |
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| Tian Hui,Cai Guo-biao and Sun Zai-yong.Computation of Nozzle Two-Phase Flow in a N2O_HTPB Hybrid Rocket Motor[J].Journal of Aerospace Power,2009,24(1). |
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| Authors: | Tian Hui Cai Guo-biao and Sun Zai-yong |
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| Institution: | School of Astronautics Beihang University,School of Astronautics Beihang University,The 41st Research Institute, the 6th Academy of CASIC, Hohehot |
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| Abstract: | Numerical solutions of full Navier-Stokes equations were obtained for a nozzle two-phase flow of the nitrous oxide (N2O) /hydroxyl-terminated polybutadiene (HTPB) based fuels hybrid rocket motor. MacCormack decomposition scheme and B-L algebraic turbulence model and two-phase equilibrium flow model were used. The nozzle flow and performance under three oxidizer-to-fuel ratios and four nozzle types were calculated. Effect of oxidizer-to-fuel ratio and nozzle type on nozzle performance was analyzed from the two-phase and gas phase results. Vacuum specific impulse is bound up with oxidizer-to-fuel ratio. This paper will be useful for the hybrid rocket motor design. |
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