进气角与注水规律对燃气-蒸汽弹射的影响

李仁凤; 乐贵高; 马大为; 靳青梅

doi:10.13224/j.cnki.jasp.2017.04.023

进气角与注水规律对燃气-蒸汽弹射的影响

doi: 10.13224/j.cnki.jasp.2017.04.023

1.
南京理工大学机械工程学院,南京 210094
2.
中国兵器工业集团公司西北机电工程研究所，陕西咸阳 712099

基金项目: 预先研究项目(B2620110005)

计量
- 文章访问数: 820
- HTML浏览量: 0
- PDF量: 400
- 被引次数: 0
出版历程
- 收稿日期: 2015-09-05
- 刊出日期: 2017-04-28

Influence of inlet angle and injection water law on gas-steam ejection

摘要

摘要: 为了研究弯管进气角和注水规律对燃气-蒸汽弹射过程中流场和内弹道的影响,采用Mixture多相流模型，Renormalization group (RNG) k-ε湍流模型和动网格技术,建立了燃气-蒸汽弹射数值模型.通过与文献数据的对比,验证了数值方法的可靠性,分析了注水规律与弯管进气角度对燃气-蒸汽弹射过程流场和内弹道的影响.研究结果表明:当弯管进气角为60°时,燃气-蒸汽介质的能量能得到最大利用,发射筒内的温度分布较均匀；另外在同样的注水量下,缓慢注水导弹出筒时间相对较短,但波动较大；快速注水导弹运动平稳,但出筒时间较长.结果可为导弹燃气-蒸汽弹射动力系统的设计提供参考.
- 燃气-蒸汽弹射 /
- 进气角 /
- 注水规律 /
- 内弹道 /
- 气液两相流 /
- 动网格技术
Abstract: To study the influence of inlet angle and injection water law on flow field and interior ballistics, the Mixture multi-phase flow model, Renormalization group (RNG) k-ε turbulence model and dynamic mesh technology were adopted to build gas-steam ejection numeric calculation model. Comparing the calculation results with the literature data, it proved that the numerical method was effective. And on this basis, the influences of inlet angle and injection water law on gas-steam ejection power system were analyzed. The results show that when inlet angle is 60°, it can make the most use of the gas-steam medium energy and the launcher temperature is more uniform. Moreover, under the condition of the same water quantity, slow water injection can obtain short time out of tube but its acceleration is larger; on the contrary, quick water injection enables steady launching but the time out of tube is longer. The result can provide reference for gas-steam ejection power system design.
- gas-steam ejection /
- inlet angle /
- injection water law /
- interior ballistics /
- gas-liquid two-phase flow /
- dynamic mesh technology

HTML

参考文献(18)

[1]	李广裕.战略导弹弹射技术的发展［J］.国外导弹与航天运载器,1990(7):38-49.LI Guangyu.Development of strategic missile ejection［J］.Foreign Missile and Space Vehicle,1990(7):38-49.(in Chinese)
[2]	李咸海,王俊杰.潜射导弹发射动力系统［M］.哈尔滨:哈尔滨工程大学出版社,2000.
[3]	Edquist C T.Prediction of the launch pulse for gas generator launched missiles［R］.AIAA 88-3290,1988.
[4]	Edquist C T,Rommin G.Canister gas dynamics of gas generator launched missiles［R］.AIAA 80-1186,1980.
[5]	赵险峰,王俊杰.潜地弹道导弹发射系统［M］.哈尔滨:哈尔滨工程大学出版社,2000.
[6]	芮守祯,邢玉明.几种导弹弹射动力系统内弹道性能比较［J］.北京航空航天大学学报,2009,35(6):766-770.RUI Shouzhen,XING Yuming.Comparative studies of interior ballistic performance among several missile eject power systems［J］.Journal of Beijing University of Aeronautics and Astronautics,2009,35(6):766-770.(in Chinese)
[7]	张仁军,鲍福廷.两种不同注水方式的燃气蒸汽式发射系统内弹道性能比较［J］.固体火箭技术,2005,28(1):5-9.ZHANG Renjun,BAO Futing.Comparison of internal ballistic properties between gas and steam launching systems in two different models of water injection［J］.Journal of Solid Rocket Technology,2005,28(1):5-9.(in Chinese)
[8]	肖虎斌,赵世平.燃气蒸汽式发射动力装置复杂内流场数值模拟［J］.固体火箭技术,2009,32(4):392-395.XIAO Hubin,ZHAO Shiping.Numerical simulation of the complex flow field in combustion gas-steam launching system［J］.Journal of Solid Rocket Technology,2009,32(4):392-395.(in Chinese)
[9]	肖虎斌.潜射导弹燃气-蒸汽发射装置的内弹道建模［J］.舰船科学技术,2010,32(2):35-38.XIAO Hubin.Interior ballistics modeling of submarine-based missile launching unit［J］.Ship Science and Technology,2010,32(2):35-38.(in Chinese)
[10]	芮守祯,邢玉明,梁材.高温高压超声速气液两相流场数值模拟［J］.航空动力学报,2011,26(5):991-996.RUI Shouzhen,XING Yuming,LIANG Cai.Numerical simulation of gas-liquid two-phase flow in high temperature and high pressure supersonic cross flow［J］.Journal of Aerospace Power,2011,26(5):991-996.(in Chinese)
[11]	刘伯伟,姜毅.汽化效应对燃气蒸汽式弹射气液两相流场的影响［J］.固体火箭技术,2014,37(2):156-160.LIU Bowei,JIANG Yi.Influence of vaporization effect on gas-liquid two-phase flow field of ejection in combustion gas and vapor mode［J］.Journal of Solid Rocket Technology,2014,37(2):156-160.(in Chinese)
[12]	白俊华,胡馨博.进气角度和初始粒径对发射筒内流动特性的影响［J］.固体火箭技术,2013,36(2):165-169.BAI Junhua,HU Xinbo.Impact of injection angle and initial particles diameter on interior flow characteristic of silo［J］.Journal of Solid Rocket Technology,2013,36(2):165-169.(in Chinese)
[13]	胡晓磊,乐贵高,马大为,等.水下燃气-蒸汽弹射气-液两相流场数值研究［J］.航空动力学报,2015,30(1):164-172.HU Xiaolei,LE Guigao,MA Dawei.Numerical study of gas-steam ejection gas-liquid two-phase flow field under water［J］.Journal of Aerospace Power,2015,30(1):164-172.(in Chinese)
[14]	Hiltunen K,Jasberg A,Kallio S,et al.Multiphase flow dynamics:theory and numerics［R］.Helsinki,Finland:VTT Publications 722,2009.
[15]	马艳丽,姜毅,王伟臣,等.湿式同心筒自力垂直热发射技术降温效果研究［J］.弹道学报,2010,22(4):89-93.MA Yanli,JIANG Yi,WANG Weichen.Research on launching process cooling effect of wet concentric canister launcher［J］.Journal of Ballistics,2010,22(4):89-93.(in Chinese)
[16]	郝继光,姜毅,韩书永,等.一种新的动网格更新技术及其应用［J］.弹道学报,2007,19(2):88-92.HAO Jiguang,JIANG Yi,HAN Shuyong.A new dynamic mesh update method and its applications［J］.Journal of Ballistics,2007,19(2):88-92.(in Chinese)
[17]	Yakhot V,Orszag S A.Renormalization group analysis of turbulence:Ⅰ basic theory［J］.Journal of Scientific Computing,1986,1(1):3-51.
[18]	周帆,姜毅,郝继光.火箭发动机尾焰流场注水降温效果初探［J］.推进技术,2012,33(2):249-252.ZHOU Fan,JIANG Yi,HAO Jiguang.Exploring on cooling effect of water injection on rocket motor exhaust［J］.Journal of Propulsion Technology,2012,33(2):249-252.(in Chinese)