药柱含扰流板H2O2/HTPB固液火箭发动机 两相流数值计算
Two-phase flow numerical calculation of H2O2/HTPB hybrid rocket engine with diaphragm in grain
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摘要: 研究了药柱中添加扰流板对固液火箭发动机燃烧性能的影响,以北京航空航天大学φ100mm标准固液火箭发动机为计算模型,针对98%H2O2/HTPB(过氧化氢/端羟基聚丁二烯)推进剂组合,采用二维轴对称气液两相模型计算了不同药柱位置、不同孔径尺寸的扰流板对固液火箭发动机燃烧性能的影响.结果表明:孔径尺寸更小的扰流板且置扰流板于药柱长度的50%~70%时,平均燃料退移速率最大,燃烧效率最高,这将为扰流板设计提供理论依据.Abstract: The effect of diaphragm in grain on combustion performence of hybrid rocket engine was studied.The standard φ 100mm hybrid rocket engine of Beijing University of Aeronautics and Astronautics was selected as a computational model,and 98% hydrogen peroxide(H2O2)/hydroxyl terminated polybutadiene (HTPB) was combined as propellant;different hole diameters of diaphragm setting at different grain positions were computed by 2-D axial symmetry and gas-liquid two-phase flow model.The results show that smaller diameter of diaphragm hole and the diaphragm setting at positions ranging from 50% to 70% of grain length can obtain the largest averaged regression rate of fuel and the highest combustion efficiency.This conclusion will provide a theory evidence for design of the diaphragm.
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Key words:
- hybrid rocket engine /
- diaphragm /
- grain /
- numerical calculation /
- two-phase flow
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[1] 田辉.固液混合火箭发动机工作过程数值仿真.北京:北京航空航天大学,2005. TIAN Hui.Numerical simulation of the operation process of a hybrid rocket motor.Beijing:Beijing University of Aeronautics and Astronautics,2005.(in Chinese) [2] Chiaverini M J,Kuo K K.Fundamental of hybrid rocket combustion and propulsion[M].Reston,US:AIAA,2007. [3] 田辉,蔡国飙,王慧玉,等.固液混合火箭发动机燃烧室和喷管流动数值模拟[J].宇航学报,2006,27(2):281-285. TIAN Hui,CAI Guobiao,WANG Huiyu,et al.Numerical simulation of combustion chamber and nozzle flow in classical hybrid rocket motors[J].Journal of Astronautics,2006,27(2):281-285.(in Chinese) [4] Marxman G A,Wooldridge C E,Muzzy R J.Fundamentals of hybrid boundary combustion[J].Heterogeneous Combustion,Progress in Astronautic and Aeronautics,1964,15:485-521. [5] 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].航空动力学学报,2008,23(6):1146-1150. TIAN Hui,CAI Guobiao,SUN Zaiyong.Computation of nozzle two-phase flow in a N2O/HTPB hybrid rocket motor[J].Journal of Aerospace Power,2008,23(6):1146-1150.(in Chinese) [6] 朱浩,蔡国飙.不同药型固液火箭发动机性能特点[J].航空动力学报,2011,26(10):2347-2351. ZHU Hao,CAI Guobiao.Performance characteristics of hybrid rocket motors with different grain types[J].Journal of Aerospace Power,2011,26(10):2347-2351.(in Chinese) [7] 饶大林,李新田,田辉,等.基于混合优化算法的固液发动机装药优化设计[J].航空动力学报,2010,25(5):1151-1152. RAO Dalin,LI Xintian,TIAN Hui,et al.Optimization of grain design for hybrid rocket engine based on hybrid optimization algorithm[J].Journal of Aerospace Power,2010,25(5):1151-1152.(in Chinese) [8] Kim H,Kim S,Woo K,et al.Investigation on the effect of liquefying diaphragm in hybrid rocket motors using paraffin-based fuel.AIAA-2011-5824,2011. [9] Matthias G,Gerhard S.Development of a hybrid rocket motor using a diaphragm for a small test rocket.AIAA-2008-4831,2008. [10] Matthias G.Effect of a diaphragm on performance and fuel regression of a laboratory scale hybrid rocket motor using nitrous oxide and paraffin.AIAA-2009-5113,2009. [11] Lin J L.Two-phase flow effect on hybrid rocket combustion[J].Acta Astronautic,2009,65(7):1042-1057. [12] Alberto B,Marta L,Nicolas B.Testing and CFD simulation of diaphragm hybrid rocket motors.AIAA-2011-6023,2011. [13] Magnussen B F,Hjertager B H.On mathematical models of turbulent combustion with special emphasis on soot formation and combustion[J].Symposium (International) on Combustion,1977,16(1):719-729. [14] CAI Guobiao,ZENG Peng,LI Xintian,et al.Scale effect of fuel regression rate in hybrid rocket motor[J].Aerospace Science and Technology,2013,24(1):141-146. [15] Shih T H,Liou W W,Shabbir A,et al.A new k-ε eddy-viscosity model for high Reynolds number turbulent flows:model development and validation[J].Computers Fluids,1995,24(3):227-238.
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