固液火箭发动机工作过程三维数值仿真

李新田; 田辉; 曾鹏; 蔡国飙

固液火箭发动机工作过程三维数值仿真

北京航空航天大学宇航学院,北京 100191

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出版历程
- 收稿日期: 2011-07-14
- 刊出日期: 2012-06-28

Three-dimensional numerical simulation of hybrid rocket motor operation process

School of Astronautics, Beijing University of Aeronautics and Astronautics,Beijing 100191,China

摘要

摘要: 根据固体燃料壁面与气相间的流固耦合得出了固体燃料燃速模型,对采用星形装药的H₂O₂/HTPB(hydroxyl-terminated polybutadiene)固液火箭发动机进行了燃烧流动三维数值仿真,得到了流场参数的分布及不同位置的固体燃料燃速,与二维轴对称仿真结果进行了对比.计算结果表明:装药截面的火焰层形状与装药星孔型面形状相似,但火焰层厚度与位置在星根与星角处存在差异;随着轴向位置的增加,氧化剂不断消耗,火焰层向通道中心移动;固体燃料燃速与氧化剂流率及不同装药位置有关,其大小随氧化剂流率的增加而增加,星根处燃速比星角处大;在相同氧化剂流率下,三维星形装药比二维轴对称装药的平均固体燃料燃速大.
- 固液火箭发动机 /
- 三维 /
- 数值仿真 /
- 燃烧 /
- 燃料燃速
Abstract: According to the coupling between the solid fuel and gaseous phases,the solid fuel regression rate model was established.Three-dimensional numerical simulation of a star-shaped fuel grain hybrid rocket motor with hydrogen peroxide(H₂O₂) and hydroxyl-terminated polybutadiene(HTPB) propellants combination was presented.The flow field and the solid fuel grain regression rate distribution were obtained,and the results were compared with that of two-dimensional axial symmetry engine.The results indicate that the flame layer profile is similar with the star-shaped fuel port,while the thickness and the location of the flame makes differences in the root and the slot of the star-shape.With the axial coordinate increasing,the oxidizer consumes continually,and the flame layer shifts toward the centre of the fuel grain port.The solid fuel regression rate relates with the oxidizer mass flux and solid fuel location.It increases with the oxidizer mass flux growing,and is higher in the root of the star-shape than in the slot.The solid fuel regression rate of three-dimensional fuel grain is larger than two-dimensional axial symmetry under the same oxidizer mass flux.
- hybrid rocket motor /
- three dimension /
- numerical simulation /
- combustion /
- solid fuel regression rate

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参考文献(13)

[1]	Chiaverini M J,Kuo K K.Fundamentals of hybrid rocket combustion and propulsion[M].VA:Progress in Astronautics and Aeronautics,2006.
[2]	Tsohas J,Appel B,Rettenmaier A,et al.Development and launch of the Purdue hybrid rocket technology demonstrator .AIAA 2009-4842,2009.
[3]	Dyer J,Doran E,Dunn Z,et al.Design and development of a 100 km nitrous oxide/paraffin hybrid rocket vehicle .AIAA 2007-5362,2007.
[4]	Evans B,Boyer E,Kuo K K.Hybrid rocket investigations at Penn State University’s high pressure combustion laboratory:overview and recent results. .AIAA 2009-5349,2009.
[5]	Marxman G A,Wooldridge C E,Muzzy R J.Fundamentals of hybrid boundary layer combustion //Wolfhard H G.Heterogeneous combustion.NY:AIAA Progress in Astronautics and Aeronautics,1964:485-521.
[6]	Kim H J,Kim Y M.Numerical modeling for combustion processed of hybrid rocket engine .AIAA 2001-4504,2001.
[7]	Venkateswaran S,Merkle C L.Size scale-up in hybrid rocket motors .AIAA 96-0647,1996.
[8]	Chien K.Predictions of channel and boundary layer flows with a low-Reynolds number turbulence model[J].AIAA Journal,1982,20(1):33-38.
[9]	CAI Guobiao,TIAN Hui.Numerical simulation of the operation process of a hybrid rocket motor .AIAA 2006-4506,2006.
[10]	Cheng G C,Farmer R C,Jones H S,et al.Numerical simulation of the internal ballistics of a hybrid rocket motor .AIAA-94-0554,1994.
[11]	田辉,蔡国飙,王慧玉,等.固液混合火箭发动机固体燃料的燃速计算[J].北京航空航天大学学报,2005,31(6):637-641. TIAN Hui,CAI Guobiao,WANG Huiyu,et al.Computation of fuel regression rate in classical hybrid rocket motors[J].Journal of Beijing University of Aeronautics and Astronautics,2005,31(6):637-641.(in Chinese)
[12]	杨玉新,胡春波,孙得川,等.基于流-固耦合的混合火箭发动机固体燃料表面退移速率计算[J].固体火箭技术,2007,29(5):214-218. YANG Yuxin,HU Chunbo,SUN Dechuan,et al.Regression rate calculation for the solid fuel surface of hybrid rocket motor based on fluid-solid coupling technique[J].Journal of Solid Rocket Technology,2007,29(5):214-218.(in Chinese)
[13]	Chiaverini M J,Harting G C,Lu Y C,et al.Pyrolysis behavior of hybrid rocket solid fuels under rapid heating conditions .AIAA 1997-3078,1997.