固体火箭冲压发动机燃气发生器动态特性影响分析
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摘要
建立了燃气发生器/固体火箭冲压发动机/导弹的一体化动态数学模型,通过数值仿真研究得到了在典型飞行弹道下各主要工作参数的变化过程.结果表明,在导弹飞行的爬升和巡航段,燃气发生器实际输出燃料流量和发动机实际输出推力与指令值之间的相对偏差均较小,不超过7%;而在俯冲段,由于容腔效应影响严重,燃料流量相对偏差达到-30%,推力最大相对偏差达-50%.上述因素给导弹飞行速度带来的相对偏差小于5%,射程的相对偏差小于1%.因此,针对所述的爬升-巡航-俯冲弹道,在导弹工作过程仿真中,可忽略燃气发生器的动态特性,不会影响对导弹飞行性能的评估.
An integral model of gas generator/solid propellant ducted rocket/missile was established,and typical performance parameters in the typical trajectory were obtained by simulation.Results showed that,in the climbing and cruising phases,the relative error of the fuel mass flow rate and the thrust of the engine was less than 7%.But in the diving phase,due to the free volume effect,the relative error of the fuel mass flow rate was-30%,and the error of thrust was-50%correspondingly.However,the relative errors of flight velocity and flight range were less than 5% and 1% respectively.Therefore,for this typical climb-cruise-diving flight trajectory described,the dynamic characteristics of gas generator can be ignored in analysis of the missile's working process.
An integral model of gas generator/solid propellant ducted rocket/missile was established,and typical performance parameters in the typical trajectory were obtained by simulation.Results showed that,in the climbing and cruising phases,the relative error of the fuel mass flow rate and the thrust of the engine was less than 7%.But in the diving phase,due to the free volume effect,the relative error of the fuel mass flow rate was-30%,and the error of thrust was-50%correspondingly.However,the relative errors of flight velocity and flight range were less than 5% and 1% respectively.Therefore,for this typical climb-cruise-diving flight trajectory described,the dynamic characteristics of gas generator can be ignored in analysis of the missile's working process.
引文
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[2]Fry R S.A century of ramjet propulsion technology evolution[J].Journal of Propulsion and Power,2004,20(1):27-58.
[3]谢侃,刘宇,王一白,等.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,2015.
[4]谢侃,李博,郭常超,等.固体火箭发动机气动喉部的推力调控特性[J].推进技术,2015,36(2):194-199.XIE Kan,LI Bo,GUO Changchao,et al.Thrust control features for aerodynamic throat for solid rocket motor[J].Journal of Propulsion Technology,2015,36(2):194-199.(in Chinese)
[5]郭常超,于新宇,李博,等.流体喉部推力特性实验[J].航空动力学报,2015,30(4):999-1007.GUO Changchao,YU Xinyu,LI Bo,et al.Experiment on thrust adjustment characteristics of fluidic nozzle throat[J].Journal of Aerospace Power,2015,30(4):999-1007.(in Chinese)
[6]Macinnis D V.Effects of gas generator burn rate variability on variable flow ducted rocket design and performance[R].AIAA-2012-3828,2012.
[7]鲍文,牛文玉,陈林泉,等.固体火箭冲压发动机燃气流量调节特性[J].推进技术,2007,28(4):433-436.BAO Wen,NIU Wenyu,CHEN Linquan,et al.Regulating property of the flow in a solid ducted rocket[J].Journal of Propulsion Technology,2007,28(4):433-436.(in Chinese)
[8]牛文玉,于达仁,鲍文,等.燃气流量可控的固体火箭冲压发动机燃气发生器动态特性[J].固体火箭技术,2008,31(2):145-148.NIU Wenyu,YU Daren,BAO Wen,et al.Dynamic characteristics of controllable flow gas generator in solid rocket ramjet[J].Journal of Solid Rocket Technology,2008,31(2):145-148.(in Chinese)
[9]何洪庆,陈旭扬,孙贵宁,等.固冲发动机的流量调节技术[J].战术导弹技术,2009(2):36-40.HE Hongqing,CHEN Xuyang,SUN Guining,et al.Flow regulation technique of solid ramjet:design of flow regulation system[J].Tactical Missile Technology,2009(2):36-40.(in Chinese)
[10]杨石林,高波,董新刚.滑盘式流量调节燃气发生器动态特性分析[J].固体火箭技术,2009,32(5):506-510.YANG Shilin,GAO Bo,DONG Xingang.Analysis on dynamic characteristics of regulable flow gas generator with sliding discal valve[J].Journal of Solid Rocket Technology,2009,32(5):506-510.(in Chinese)
[11]聂聆聪,刘志明,刘源翔.流量可调燃气发生器压力闭环模糊控制算法[J].推进技术,2013,34(4):551-556.NIE Lingcong,LIU Zhiming,LIU Yuanxiang.Pressureclose loop fuzzy control method of a flow adjustable gas generator[J].Journal of Propulsion Technology,2013,34(4):551-556.(in Chinese)
[12]刘源翔,姚晓先,聂聆聪,等.一种流量可调燃气发生器压强控制算法的研究[J].固体火箭技术,2014,37(1):43-46.LIU Yuanxiang,YAO Xiaoxian,NIE Lingcong,et al.Research on pressure control algorithm for flow adjustable gas generator[J].Journal of Solid Rocket Technology,2014,37(1):43-46.(in Chinese)
[13]Bauer C,Davenne F,Hopfe N,et al.Modeling of a throttleable ducted rocket propulsion system[R].AIAA-2011-5610,2011.
[14]Pinto P C,Kurth G.Robust propulsion control in a flight stages of a throttleable ducted rocket propulsion system[R].AIAA-2011-5611,2011.
[15]Bauer C,Hopfe N,Caldas-Pinto P,et al.Development of a6-DOF simulation of a VFDR propulsion system control[R].AIAA-2012-3827,2012.
[16]董师颜,张兆良.固体火箭发动机原理[M].北京:北京理工大学出版社,1996.
[17]刘兴洲.飞航导弹动力装置:上册[M].北京:宇航出版社,1992.
[18]钱杏芳,林瑞雄,赵亚男.导弹飞行力学[M].北京:北京理工大学出版社,2006.