固液火箭发动机动态特性仿真研究综述
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- 英文论文题名：Research Review of the numerical models in hybrid rocket motors' Transient Behaviors
- 论文作者：张源俊 ; 江雅娟 ; 俞南嘉 ; 田辉 ; 蔡国飙
- 英文论文作者：Yuanjun Zhang ; Yajuan Jiang ; Nanjia Yu ; Hui Tian ; Guobiao Cai ; School of Astronautics ; Beihang University ; Beijing Institute of Aerospace Testing Technology
- 年：2016
- 作者机构：北京航空航天大学宇航学院;北京航天试验技术研究所;
- 论文关键词：固液火箭发动机 ; 动态特性 ; 耦合分析 ; 仿真
- 英文论文关键词：hybrid rocket motor ; transient behavior ; coupled analysis ; numerical model
- 会议召开时间：2016-08-17
- 会议录名称：中国航天第三专业信息网第三十七届技术交流会暨第一届空天动力联合会议论文集
- 语种：中文
- 分类号：V430
- 学会代码：HTDZ
- 会议名称：中国航天第三专业信息网第三十七届技术交流会暨第一届空天动力联合会议
- 会议地点：中国陕西西安
- 主办单位：中国航天第三专业信息网、中国航天科技集团公司科技委、中国航天科工集团公司科技委
- 学会名称：中国航天第三专业信息网
- 页数：7
- 文件大小：428k
- 原文格式：D
- 会议级别：全国
摘要
固液火箭发动机是采用液体氧化剂和固体燃料的混合火箭发动机,燃烧发生在固体燃料气化表面的边界层里。固液火箭发动机的动态特性兼具固体和液体火箭发动机的特点,需要综合考虑输送系统与燃烧室特性。固液火箭发动机输送系统与燃烧室耦合会产生低频振荡燃烧,影响发动机性能。因此,有必要开展固液火箭发动机动态特性仿真研究,分析发动机工作原理,为固液火箭发动机设计提供研究基础。
Hybrid rocket motors store propellants in two different states, liquid oxidizer and solid fuel. The flame zone is narrow in the boundary layer. Characteristics of the feed system and the combustion behavior need to be considered in hybrid rocket motors. Low-frequency oscillatory combustion caused by the coupling of the feed system and combustor effects the performance of the hybrid rocket motors. Therefore, numerical model to the transient behaviors is established to analyse the operation principle and design the hybrid rocket motors.
Hybrid rocket motors store propellants in two different states, liquid oxidizer and solid fuel. The flame zone is narrow in the boundary layer. Characteristics of the feed system and the combustion behavior need to be considered in hybrid rocket motors. Low-frequency oscillatory combustion caused by the coupling of the feed system and combustor effects the performance of the hybrid rocket motors. Therefore, numerical model to the transient behaviors is established to analyse the operation principle and design the hybrid rocket motors.
引文
[1]Arif K,Jonny D.Nonlinear Combustion in Hybrid Rockets-Explanation of Spontaneous Shifting in Motor Operation,2009[C].American Institute of Aeronautics and Astronautics.
[2]Karabeyoglu M A.Transient combustion in hybrid rockets[D].California:Stanford University Department of Aeronautics and Astronautics,1998.
[3]陶玉静.液体火箭发动机响应特性研究及稳定性的非线性分析[D].国防科学技术大学,2006.
[4]郭敬,宋晶晶,孔凡超.发动机推进剂增压输送系统建模仿真技术综述[J].火箭推进,2015(05):1-6.
[5]刘亦鹏.低温气液两相弹状流流动特性和流场结构的实验及数值研究[D].上海交通大学,2013.
[6]郭宁,匡波,张中伟,等.低温推进剂火箭发动机循环预冷系统喷泉非稳现象的数值研究[J].低温工程,2013(02):24-35.
[7]徐学文,牟俊林,任建存,等.固体火箭发动机喷管瞬态流场特性分析[J].火箭推进,2015(05):49-53.
[8]王寅虎.火药启动器壳体瞬态温度场的数值模拟分析[J].导弹与航天运载技术,2012(01):7-12.
[9]吴静.固体火箭发动机点火冲击过程流固耦合仿真研究[D].南京理工大学,2013.
[10]Tian H,Li X T,Cai G B.Ignition theory investigation and experimental research on hybrid rocket motor[J].Aerospace Science and Technology,2015,42:334-341.
[11]Sheng Z,Guobiao C,Hui T,et al.Experimental Tests of Throttleable H2O2/PE Hybrid Rocket Motors[M]//American Institute of Aeronautics and Astronautics,2015.
[12]Li J H,Yu N J,Zeng P,et al.Design and integrated simulation of a pressurized feed system of the dual-thrust hybrid rocket motor[J].Science China-Technological Sciences,2013,56:989-1000.
[13]朱浩,孔德帅,蔡国飙.泵压式固液火箭发动机系统仿真与优化设计[J].航空动力学报,2012(09):2128-2133.
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[15]G.M.Combustion instability and the role of chemical kinetics in hybrid combustion,1968[C].American Institute of Aeronautics and Astronautics.
[16]Daneshyar H.One-dimensional Compressible FLow[J].1976,-1:175.
[17]AIAA.Internal ballistic considerations in hybrid rocket design[J].Journal of Spacecraft&Rockets,1967,4(2):255-262.
[18]张育林.液体火箭发动机动力学理论与应用[M].科学出版社,2005.
[19]Pasley G F.Optimization of stored pressurant supply for liquid propulsion systems[J].Journal of Spacecraft&Rockets,2012,7(7).
[20]Zilliac G,Karabeyoglu M.Modeling of Propellant Tank Pressurization:Aiaa/asme/sae/asee Joint Propulsion Conference&Exhibit,2005[C].
[21]AIAA.Numerical Modeling and Test Data Comparison of Propulsion Test Article Helium Pressurization System[J].2000.
[22]魏鹏飞,吴建军,刘洪刚,等.液体火箭发动机一种通用模块化仿真方法[J].推进技术,2005,26(02):147-150.
[23]李家文,张黎辉,张振鹏.液体火箭发动机数值模拟的计算模型建立方法[J].推进技术,2002,23(05):363-365.
[24]刘红军,张恩昭,董锡鉴.补燃循环发动机启动特性仿真研究[J].推进技术,1999,20(03):6-10.
[25]帅彤,王占彬,张占峰,等.闭式增压系统仿真分析[J].导弹与航天运载技术,2012(04):5-9.
[26]马昕晖,栾骁,陈景鹏,等.液氢加注系统中过滤器漏热故障仿真与分析[J].低温与超导,2012,40(07):17-21.
[27]白晓瑞.液体火箭推进系统动态特性仿真研究[D].国防科学技术大学,2008.
[28]杜新.85%H2O2/PE固液火箭发动机工作过程研究[D].西北工业大学,2003.
[29]刘景华.过氧化氢发动机动态特性研究[D].长沙:国防科技大学,2007.
[30]Arif K,Jose S,Brian C.Investigation of Feed System Coupled Low Frequency Combustion Instabilities in Hybrid Rockets,2007[C].American Institute of Aeronautics and Astronautics.
[31]李君海.固液火箭发动机系统设计与喷注效应研究_李君海[D].北京航空航天大学宇航学院,2013.
[32]吴俊峰.固液火箭发动机点火瞬态模型与点火技术研究[D].北京:北京航空航天大学宇航学院,2013.
[33]Tian H,Li Y,Zeng P.Transient simulation of regression rate on thrust regulation process in hybrid rocket motor[J].Chinese Journal of Aeronautics,2014,27(6):1343-1351.
[34]Whitmore S A,Peterson Z W,Eilers S D.Deep Throttle of a Nitrous Oxide and Hydroxyl-Terminated Polybutadience Hybrid Rocket Motor[J].Journal of Propulsion and Power,2014,30(1):78-86.
[35]Whitmore S A,Peterson Z W,Eilers S D.Closed-Loop Precision Throttling of a Hybrid Rocket Motor[J].Journal of Propulsion and Power,2014.
[36]Benjamin S W,Jonah E Z,Brian C,et al.Effects of Injector Design on Combustion Stability in Hybrid Rockets Using Self-Pressurizing Oxidizers,2014[C].American Institute of Aeronautics and Astronautics.
[37]曾鹏.过氧化氢变推力固液火箭发动机研究[D].北京:北京航空航天大学宇航学院,2014.
[38]Barato F,Bellomo N,Faenza M,et al.Numerical Model to Analyze Transient Behavior and Instabilities on Hybrid Rocket Motors[J].Journal of Propulsion and Power,2015,31(2):643-653.
[2]Karabeyoglu M A.Transient combustion in hybrid rockets[D].California:Stanford University Department of Aeronautics and Astronautics,1998.
[3]陶玉静.液体火箭发动机响应特性研究及稳定性的非线性分析[D].国防科学技术大学,2006.
[4]郭敬,宋晶晶,孔凡超.发动机推进剂增压输送系统建模仿真技术综述[J].火箭推进,2015(05):1-6.
[5]刘亦鹏.低温气液两相弹状流流动特性和流场结构的实验及数值研究[D].上海交通大学,2013.
[6]郭宁,匡波,张中伟,等.低温推进剂火箭发动机循环预冷系统喷泉非稳现象的数值研究[J].低温工程,2013(02):24-35.
[7]徐学文,牟俊林,任建存,等.固体火箭发动机喷管瞬态流场特性分析[J].火箭推进,2015(05):49-53.
[8]王寅虎.火药启动器壳体瞬态温度场的数值模拟分析[J].导弹与航天运载技术,2012(01):7-12.
[9]吴静.固体火箭发动机点火冲击过程流固耦合仿真研究[D].南京理工大学,2013.
[10]Tian H,Li X T,Cai G B.Ignition theory investigation and experimental research on hybrid rocket motor[J].Aerospace Science and Technology,2015,42:334-341.
[11]Sheng Z,Guobiao C,Hui T,et al.Experimental Tests of Throttleable H2O2/PE Hybrid Rocket Motors[M]//American Institute of Aeronautics and Astronautics,2015.
[12]Li J H,Yu N J,Zeng P,et al.Design and integrated simulation of a pressurized feed system of the dual-thrust hybrid rocket motor[J].Science China-Technological Sciences,2013,56:989-1000.
[13]朱浩,孔德帅,蔡国飙.泵压式固液火箭发动机系统仿真与优化设计[J].航空动力学报,2012(09):2128-2133.
[14]R J,J C.A preliminary analysis of low frequency pressure oscillations in hybrid rocket motors,1995[C].American Institute of Aeronautics and Astronautics.
[15]G.M.Combustion instability and the role of chemical kinetics in hybrid combustion,1968[C].American Institute of Aeronautics and Astronautics.
[16]Daneshyar H.One-dimensional Compressible FLow[J].1976,-1:175.
[17]AIAA.Internal ballistic considerations in hybrid rocket design[J].Journal of Spacecraft&Rockets,1967,4(2):255-262.
[18]张育林.液体火箭发动机动力学理论与应用[M].科学出版社,2005.
[19]Pasley G F.Optimization of stored pressurant supply for liquid propulsion systems[J].Journal of Spacecraft&Rockets,2012,7(7).
[20]Zilliac G,Karabeyoglu M.Modeling of Propellant Tank Pressurization:Aiaa/asme/sae/asee Joint Propulsion Conference&Exhibit,2005[C].
[21]AIAA.Numerical Modeling and Test Data Comparison of Propulsion Test Article Helium Pressurization System[J].2000.
[22]魏鹏飞,吴建军,刘洪刚,等.液体火箭发动机一种通用模块化仿真方法[J].推进技术,2005,26(02):147-150.
[23]李家文,张黎辉,张振鹏.液体火箭发动机数值模拟的计算模型建立方法[J].推进技术,2002,23(05):363-365.
[24]刘红军,张恩昭,董锡鉴.补燃循环发动机启动特性仿真研究[J].推进技术,1999,20(03):6-10.
[25]帅彤,王占彬,张占峰,等.闭式增压系统仿真分析[J].导弹与航天运载技术,2012(04):5-9.
[26]马昕晖,栾骁,陈景鹏,等.液氢加注系统中过滤器漏热故障仿真与分析[J].低温与超导,2012,40(07):17-21.
[27]白晓瑞.液体火箭推进系统动态特性仿真研究[D].国防科学技术大学,2008.
[28]杜新.85%H2O2/PE固液火箭发动机工作过程研究[D].西北工业大学,2003.
[29]刘景华.过氧化氢发动机动态特性研究[D].长沙:国防科技大学,2007.
[30]Arif K,Jose S,Brian C.Investigation of Feed System Coupled Low Frequency Combustion Instabilities in Hybrid Rockets,2007[C].American Institute of Aeronautics and Astronautics.
[31]李君海.固液火箭发动机系统设计与喷注效应研究_李君海[D].北京航空航天大学宇航学院,2013.
[32]吴俊峰.固液火箭发动机点火瞬态模型与点火技术研究[D].北京:北京航空航天大学宇航学院,2013.
[33]Tian H,Li Y,Zeng P.Transient simulation of regression rate on thrust regulation process in hybrid rocket motor[J].Chinese Journal of Aeronautics,2014,27(6):1343-1351.
[34]Whitmore S A,Peterson Z W,Eilers S D.Deep Throttle of a Nitrous Oxide and Hydroxyl-Terminated Polybutadience Hybrid Rocket Motor[J].Journal of Propulsion and Power,2014,30(1):78-86.
[35]Whitmore S A,Peterson Z W,Eilers S D.Closed-Loop Precision Throttling of a Hybrid Rocket Motor[J].Journal of Propulsion and Power,2014.
[36]Benjamin S W,Jonah E Z,Brian C,et al.Effects of Injector Design on Combustion Stability in Hybrid Rockets Using Self-Pressurizing Oxidizers,2014[C].American Institute of Aeronautics and Astronautics.
[37]曾鹏.过氧化氢变推力固液火箭发动机研究[D].北京:北京航空航天大学宇航学院,2014.
[38]Barato F,Bellomo N,Faenza M,et al.Numerical Model to Analyze Transient Behavior and Instabilities on Hybrid Rocket Motors[J].Journal of Propulsion and Power,2015,31(2):643-653.
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