固体火箭发动机流体喉部推力矢量特性
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摘要
针对采用水作为二次流工质的流体喉部进行了冷流实验及数值模拟研究.研究了该种固体火箭发动机流体喉部的一般规律,包括不同二次流射流方式,不同二次流流量下流体喉部的扼流性能,推力偏角及推力效率,数值模拟及实验结果吻合较好.结果表明:扼流性能与二次流的注射位置、注射角度及流量比有关,且随二次流/主流流量比的增大而增大.喉部二次流喷射能有效的调节有效喉部面积进而调节推力大小,当流量比为0.4时,最大有效喉部面积比为0.8;扩张段二次流喷射能有效调节推力方向,当流量比为0.4时,最大推力偏角为20°;喉部二次流与扩张段二次流入射位置存在相位差可有效降低喉部与扩张段二次流干扰.
A cold-flow experiment and numerical simulation research were performed on the fluidic throat using water as working fluid.The general rules of the fluidic throat for solid rocket motor were studied,including the injection styles choke performance,the thrust angle and the thrust performance of the fluidic throat under different conditions of secondary flow injection styles and secondary flow ratio.Numerical simulations were in good agreement with experimental results.Results show that,the choke performance is related to the point,angle and flow ratio of secondary injection.Meanwhile,the choke performance will be better with the increase of the flow ratio of the secondary flow and main flow.Secondary injection of the nozzle throat can effectively regulate the effective throat area which contributes to the thrust magnitude.When the flow ratio is 0.4,the maximum effective throat area ratio is0.8.Secondary injection at the divergent section can regulate the thrust direction effectively.When the flow ratio is 0.4,the maximum thrust angle is 20°.The phase difference of the throat injection and divergent section injection is used for reducing the interference from throat and divergent segment.
A cold-flow experiment and numerical simulation research were performed on the fluidic throat using water as working fluid.The general rules of the fluidic throat for solid rocket motor were studied,including the injection styles choke performance,the thrust angle and the thrust performance of the fluidic throat under different conditions of secondary flow injection styles and secondary flow ratio.Numerical simulations were in good agreement with experimental results.Results show that,the choke performance is related to the point,angle and flow ratio of secondary injection.Meanwhile,the choke performance will be better with the increase of the flow ratio of the secondary flow and main flow.Secondary injection of the nozzle throat can effectively regulate the effective throat area which contributes to the thrust magnitude.When the flow ratio is 0.4,the maximum effective throat area ratio is0.8.Secondary injection at the divergent section can regulate the thrust direction effectively.When the flow ratio is 0.4,the maximum thrust angle is 20°.The phase difference of the throat injection and divergent section injection is used for reducing the interference from throat and divergent segment.
引文
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[16]戴得志.基于VOF方法的气-液两相流动的数值计算[D].南京:南京航空航天大学,2014.DAI Dezhi.Numerical simulation of gas-liquid two-phase flow based on VOF method[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2014.(in Chinese)
[17]谢侃,刘宇,王一白,.圆孔喷嘴形成气动喉部的定常数值研究[J].航空动力学报,2011,26(4):924-930.XIE Kan,LIU Yu,WANG Yibai.Steady numerical study of aerodynamic throat formed by round injectors[J].Journal of Aerospace Power,2011,26(4):924-930.(in Chinese)
[18]谢侃,刘宇,任军学,等.两相流环缝式喷管理想型面的设计方法[J].固体火箭技术,2007,30(3):223-228.XIE Kan,LIU Yu,REN Junxue,et al.An ideal method for the two-phase ring plug nozzle design[J].Journal of Solid Rocket Technology,2007,30(3):223-228.(in Chinese)
[2]李娟,李江,王毅林,等.喉栓式变推力发动机性能研究[J].固体火箭技术,2007,30(6):505-509.LI Juan,LI Jiang,WANG Yilin.Study on performance of pintle controlled thrust solid rocket motor[J].Journal of Solid Rocket Technology,2007,30(6):505-509.(in Chinese)
[3]谢侃,刘宇,王一白.固体火箭发动机流体喉部的两相流数值模拟[J].推进技术,2010,31(1):56-60.XIE Kan,LIU Yu,WANG Yibai.Simulation for the twophase flow aerodynamic throat of solid rocket motors[J].Journal of Propulsion Technology,2010,31(1):56-60.(in Chinese)
[4]Richard J Z.Thrust vector control by liquid injection for solid propellant rockets[R].AIAA 75-1225,1975.
[5]Berdoyes M.Hot gas thrust vector control motor[R].AIAA 92-3551,1992.
[6]Green C J.Liquid injection thrust vector control[J].AIAA Journal,1963,3(1):573-578.
[7]Miller D N,Catt J A.Conceptual development of fixed-geometry nozzles using fluidic injection for throat-area control[R].AIAA 95-2603,1995.
[8]Ali A,Rodriguez C G,Neely A J,et al.Combination of fluidic thrust modulation and vectoring in a 2Dnozzle[R].AIAA-2012-3780,2012.
[9]谢侃,刘宇,王一白.固体火箭发动机流体喉部喷管技术[M].北京:国防工业出版社,2014.
[10]张建华,谢侃.流体喉部喷管二次流矢量控制方案[J].北京航空航天大学学报,2012,38(3):309-313.ZHANG Jianhua,XIE Kan.Secondary flow thrust vector control study for fluidic throat nozzle[J].Journal of Beijing University of Aeronautics and Astronautics,2012,38(3):309-313.(in Chinese)
[11]乔渭阳,蔡元虎.基于二次流喷射控制推力矢量喷管的实验及数值研究[J].航空动力学报,2001,16(3):273-278.QIAO Weiyang,CAI Yuanhu.A study on the two-dimensional thrust vectoring nozzle with secondary flow injection[J].Journal of Aerospace Power,2001,16(3):273-278.(in Chinese)
[12]Baruzzini D,Domel N,Miller D N,et al.Pulsed injection flow control for throttling in supersonic nozzles:a computational fluid dynamics design study[R].AIAA-2007-4215,2007.
[13]谢侃,刘宇,王一白.固体火箭发动机流体喉部非定常过程[J].推进技术,2011,32(1):103-108.XIE Kan,LIU Yu,WANG Yibai.Unsteady process of aerodynamic throat for solid rocket motor[J].Journal of Propulsion Technology,2011,32(1):103-108.(in Chinese)
[14]刘宏璇.六分力测试方法研究[D].南京:南京理工大学,2008.LIU Hongxuan.Study on six-component test methods[D].Nanjing:Nanjing University of Science and Technology,2008.(in Chinese)
[15]杜长宝,黄莉.固体火箭发动机推力偏心分析与试验研究[J].南京理工大学学报,2006,30(5):550-553.DU Changbao,HUANG Li.Theoretical study and test on thrust misalignment of solid rocket motor[J].Journal of Nanjing University of Science and Technology,2006,30(5):550-553.(in Chinese)
[16]戴得志.基于VOF方法的气-液两相流动的数值计算[D].南京:南京航空航天大学,2014.DAI Dezhi.Numerical simulation of gas-liquid two-phase flow based on VOF method[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2014.(in Chinese)
[17]谢侃,刘宇,王一白,.圆孔喷嘴形成气动喉部的定常数值研究[J].航空动力学报,2011,26(4):924-930.XIE Kan,LIU Yu,WANG Yibai.Steady numerical study of aerodynamic throat formed by round injectors[J].Journal of Aerospace Power,2011,26(4):924-930.(in Chinese)
[18]谢侃,刘宇,任军学,等.两相流环缝式喷管理想型面的设计方法[J].固体火箭技术,2007,30(3):223-228.XIE Kan,LIU Yu,REN Junxue,et al.An ideal method for the two-phase ring plug nozzle design[J].Journal of Solid Rocket Technology,2007,30(3):223-228.(in Chinese)