全部 标题 作者
关键词 摘要

OALib Journal期刊
ISSN: 2333-9721
费用:99美元

查看量下载量

相关文章

更多...
弹道学报  2015 

超声速燃气射流流场特性的三维数值模拟

Keywords: 固体火箭发动机,超声速燃气射流,大涡模拟(LES),喷管尺寸

Full-Text   Cite this paper   Add to My Lib

Abstract:

针对固体火箭发动机燃气射流特性,建立了高温高压燃气射流的三维计算模型,采用大涡模拟(LES)对不同尺寸喷管形成的欠膨胀超声速射流流场进行了数值模拟。计算结果表明,超声速燃气射流与周围大气剧烈掺混过程中形成了重复出现拟周期的膨胀压缩波结构。在射流中心轴线上,静压、速度等参数在出喷口后出现了较大的波动,随着离喷口距离的增加,波动幅度逐渐减小至平稳变化。射流速度沿径向开始在核心区基本不变,到剪切层后衰减梯度较大。随着喷管尺寸的增加,射流在轴向和径向的扰动区域都增大。

References

[1]  赵承庆,姜毅.气体射流动力学[M].北京:北京理工大学出版社,1998.
[2]  ZHAO Cheng-qing,JIANG Yi.Gas jet dynamics[M].Beijing:Beijing Institute of Technology Press,1998.(in Chinese)
[3]  邹宁.超声速喷管设计及其数值模拟和实验研究[D].南京:南京航空航天大学,2008.
[4]  ZOU Ning.Supersonic nozzle design and its investigation with numerical and experimental methods[M].Nanjing:Nanjing University of Aeronautics and Astronautics,2008.(in Chinese)
[5]  武瑞清,阮文俊,李昕,等.单兵火箭燃气消焰设计的试验研究与数值模拟[J].弹箭与制导学报,2009,29(3):153-156.
[6]  WU Rui-qing,RUAN Wen-jun,LI Xin,et al.The experimental research and numerical simulation of flame damper design of shoulder launched rocket[J].Journal of Projectiles,Rockets,Missiles and Guidance,2009,29(3):153-156.(in Chinese)
[7]  常见虎,周长省,李军.高低空环境下火箭发动机射流流场的数值分析[J].系统仿真学报,2007,19(16):3 672-3 675.
[8]  CHANG Jian-hu,ZHOU Chang-sheng,LI Jun.Numerical analysis around flow field of rocket in high-low altitude[J].Journal of System Simulation,2007,19(16):3 672-3 675.(in Chinese)
[9]  陈二云,马大为,赵改平,等.燃气自由射流的高精度间断有限元数值模拟[J].弹道学报,2009,21(1):79-82.
[10]  CHEN Er-yun,MA Da-wei,ZHAO Gai-ping,et al.Numerical simulation of gas free-jet using high-precision discontinuous finite element method[J].Journal of Ballistics,2009,21(1):79-82.(in Chinese)
[11]  孙振华,徐东来,何国强.飞行参数对导弹发动机羽流的影响[J].固体火箭技术,2005,28(3):188-191.
[12]  SUN Zhen-hua,XU Dong-lai,HE Guo-qiang.Effect of flight status parameters on missile motor plume[J].Journal of Solid Rocket Technology,2005,28(3):188-191.(in Chinese)
[13]  RODIONOW A V.New space-marching technique for exhaust plume simulation,AIAA 2000-3390[R].2000.
[14]  于胜春,汤龙生.固体火箭发动机喷管及羽流流场的数值分析[J].固体火箭技术,2004,27(2):95-97.
[15]  YU Sheng-chun,TANG Long-sheng.Numerical analysis of nozzle and plume flow field of a solid rocket motor[J].Journal of Solid Rocket Technology,2004,27(2):95-97.(in Chinese)
[16]  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.
[17]  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.(in Chinese)
[18]  赵娜,余永刚,刘东尧,等.小孔流量发生器喷口流场特性的数值模拟[J].弹道学报,2010,22(2):81-85.
[19]  ZHAO Na,YU Yong-gang,LIU Dong-yao,et al.Numerical simulation of nozzle flowfield characteristic of orifice flow generator[J].Journal of Ballistics,2010,22(2):81-85.(in Chinese)
[20]  张福祥.火箭燃气射流动力学[M].哈尔滨:哈尔滨工程大学出版社,2004.
[21]  ZHANG Fu-xiang.Dynamics of the rocket jet flow[M].Harbin:Harbin Engineering University Press,2004.(in Chinese)

Full-Text

Contact Us

service@oalib.com

QQ:3279437679

WhatsApp +8615387084133