三种典型固体推进剂排气羽流特性参数的模拟计算
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摘要
为研究典型固体推进剂装药的排气羽流特性,采用能量计算星程序和ANSYS-Fluent软件对双基(DB)推进剂、复合改性双基(CMDB)推进剂及硝酸酯增塑聚醚(NEPE)推进剂燃烧及排气羽流场进行了模型构建和求解,获得了羽流温度和羽流流速等特性参数,采用红外热像仪和TDLAS流速测试系统对其进行了实验验证,并将模拟结果与实验结果进行对比。结果表明,流场计算获得3种推进剂的羽流流速分别为1 002.38、1 279.01、1 243.16m/s。实验中应考虑推进剂羽流流场的非均匀性及实际测试状态与数值模型的一致性;流场计算获得的羽流温度与红外热像仪测试结果定性一致,应改进实验方案获得羽流的真实辐射率,并考虑数值模型的理想化假设带来的偏差。
To study the exhaust plume characteristics of three typical solid propellant charge,the construction and solving of model for the combustion and exhaust plume field of three kinds of solid propellants,double-base(DB)propellant,composite modified double-base(CMDB)propellant and NEPE propellant,were performed by the Energy Calculation Star(ECS)program and ANSYS-Fluent software.The plume characteristic parameters,such as plume temperature and plume velocity were obtained.Thermal Infrared Imager and Tunable Diode Laser Absorption Spectroscopy(TDLAS)velocity measurement system were employed to validate the simulation results and the simulation results were compared with the experimental ones.Results show that the plume velocity of the three propllants calculated by low field are 1 002.38,1 279.01,1 243.16 m/s,respectively.In the experiment,the nonuniformity of propellant flow field and the consistency of actual test condition and numerical model should be considered.The plume temperature calculated by the flow field is qualitatively consistent with the test results obtained by Thermal Infrared Imager.The experimental scheme should be improved to obtain the real radiation coefficient and the deviations from the idealized assumptions of the numerical model should be taken into account.
To study the exhaust plume characteristics of three typical solid propellant charge,the construction and solving of model for the combustion and exhaust plume field of three kinds of solid propellants,double-base(DB)propellant,composite modified double-base(CMDB)propellant and NEPE propellant,were performed by the Energy Calculation Star(ECS)program and ANSYS-Fluent software.The plume characteristic parameters,such as plume temperature and plume velocity were obtained.Thermal Infrared Imager and Tunable Diode Laser Absorption Spectroscopy(TDLAS)velocity measurement system were employed to validate the simulation results and the simulation results were compared with the experimental ones.Results show that the plume velocity of the three propllants calculated by low field are 1 002.38,1 279.01,1 243.16 m/s,respectively.In the experiment,the nonuniformity of propellant flow field and the consistency of actual test condition and numerical model should be considered.The plume temperature calculated by the flow field is qualitatively consistent with the test results obtained by Thermal Infrared Imager.The experimental scheme should be improved to obtain the real radiation coefficient and the deviations from the idealized assumptions of the numerical model should be taken into account.
引文
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[18]张波,吕事桂.基于双响应波段工作的红外热像仪测温原理与误差分析[J].宇航计测技术,2010,30(6):11-15.ZHANG Bo,LüShi-gui.Temperature measurement of the thermal infrared imager based on two response working wavebands and its error analysis[J].Journal of Astronautic Metrology and Measurement,2010,30(6):11-15.
[2]Chastenet J C,Kessel P A,Lawrence R,et al.Rocket motor plume technology,AGARD-LS-188[R].Loughton:AGARD,1993.
[3]李猛,王宏.火箭发动机排气羽流特征信号预示技术研究综述[J].飞航导弹,2010(3):54-57.LI Meng,WANG Hong.A review studies on the technology for prediction of rocket motor plume signature[J].Aerodynamic Missile Journal,2010(3):54-57.
[4]Guery J F,Chang I S,Shimada T,et al.Solid propulsion for space applications:an updated road map[J].Acta Astronautics,2010,66:201-219.
[5]Troyes J,Dubois I,Borie V,et al.Multi-phase reactive numerical simulations of a model solid rocket motor exhaust jet[C]∥42th AIAA/ASME/SAE/ASEE Joint Propulsion Conference&Exhibit.New York:AIAA,2006:1-13.
[6]Wang X Y,Yuko J R.Thermal analysis on plume heating of the main engine on the crew exploration vehicle service module,NASA/TM-215049[R].Washington D C:NASA,2007.
[7]Gueyffier D,Fromentin-Denoziere B,Simon J,et al.Numerical simulation of ionized rocket plumes[C]∥44th AIAA Plasmadynamics and Laser Conference.New York:AIAA,2013:1-13.
[8]李猛,张晓宏,孙美,等.改性双基推进剂两相化学反应羽流特性研究[J].弹箭与制导学报,2012,32(1):123-126.LI Meng,ZHANG Xiao-hong,SUN Mei,et al.The study on plume characteristic of two phase chemical reaction of modified double-base propellant[J].Journal of Projectiles,Rockets,Missiles Guidance,2012,32(1):123-126.
[9]李峥,向红军,张小英.复合推进剂固体火箭发动机喷流流场数值模拟[J].固体火箭技术,2014,37(1):37-42.LI Zheng,XIANG Hong-jun,ZHANG Xiao-ying.Numerical simulation of composite solid propellant rocket motor exhaust plume[J].Journal of Solid Rocket Technology,2014,37(1):37-42.
[10]杨燕京,赵凤起,孙美,等.基于TDLAS技术的双基系推进剂装药排气羽流流速特性研究[J].火炸药学报,2016,39(3):70-74.YANG Yan-jing,ZHAO Feng-qi,SUN Mei,et al.Investigations on the exhaust plume velocity characteristics of double base and CMDB propellants charge based on TDLAS technique[J].Chinese Journal of Explosives&Propellants(Huozhayao Xuebao),2016,39(3):70-74.
[11]杨斌,黄斌,刘佩进,等.利用TDLAS技术评估火箭基组合循环发动机试验性能[J].宇航学报,2015,36(7):840-848.YANG Bin,HUANG Bin,LIU Pei-jin,et al.Test performance evaluation of rocket based combined cycle engine using TDLAS technique[J].Journal of Astronautics,2015,36(7):840-848.
[12]贾良权,刘文清,阚瑞峰,等.波长调制-TDLAS技术测量风洞中氧气流速方法研究[J].中国激光,2015(7):304-311.JIA Liang-quan,LIU Wen-qing,KAN Rui-feng,et al.Study on oxygen velocity measurement in wind tunnel by wavelength modulation-TDLAS technology[J].Chinese Journal of Lasers,2015(7):304-311.
[13]McBride B J,Gordon S.Computer program for calculation of chemical equilibrium compositions and applications:II users manual and program description,NASA RP-1311[R].Washington D C:NASA,1996.
[14]李猛,赵凤起,徐司雨,等.三种能量计算程序在推进剂配方设计中的比较[J].火炸药学报,2013,36(3):73-77.LI Meng,ZHAO Feng-qi,XU Si-yu,et al.Comparison of three kinds of energy calculation programs in formulation design of solid propellants[J].Chinese Journal of Explosives&Propellants(Huozhayao Xuebao),2013,36(3):73-77.
[15]田德余,赵凤起,刘剑洪.含能材料及相关物手册[M].北京:国防工业出版社,2011.
[16]Yakhot V,Orszag S A.Renormalization group analysis of turbulence:I.basic theory[J].Journal of Scientific Computing,1986,1(1):1-51.
[17]仪建华.火箭发动机羽流红外辐射温度动态测量方法:CN,201610846494.4[P].2016-09-23.
[18]张波,吕事桂.基于双响应波段工作的红外热像仪测温原理与误差分析[J].宇航计测技术,2010,30(6):11-15.ZHANG Bo,LüShi-gui.Temperature measurement of the thermal infrared imager based on two response working wavebands and its error analysis[J].Journal of Astronautic Metrology and Measurement,2010,30(6):11-15.