可变流量固冲发动机一体化流场研究  

Investigation of Integrated Flow Field of Variable-ducted Rocket

作　　者：牛楠[1] 董新刚[1] 霍东兴[1] 李璞[1] 

机构地区：[1]中国航天科技集团公司第四研究院第41所,西安710025

出　　处：《弹箭与制导学报》2013年第2期85-87,91,共4页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：国防基础科研基金资助

摘　　要：以某可变流量固冲发动机为研究对象,建立进气道/补燃室一体化流场数值模型,结合地面直连试验,研究了空燃比对固冲发动机性能和流场结构的影响。结果表明:导弹飞行状态不变,减小空燃比可有效提高固冲发动机的推力但比冲减小,导弹射程减小;大空燃比调节时,补燃室内流场结构未发生显著变化,空燃比减小到7时,大量燃气沿补燃室中上部流动;空燃比减小使进气道的结尾激波向上游推移,进气道裕度减小。The integrated flow field implemented for variable flow ducted rocket. Compared with direct-connected ground test, the influence of air-fuel ratio on the performance and flow field of ducted rocket analyzed. The results show that the rocket thrust has been efficiently en- hanced, together with specific impulse descending and range of missile reducing, by keeping missile flight state constant and reducing air-fuel ratio. While air-fuel ratio reduces to 7, the configuration of flow field in combustor changes, then a mass of fuel flows along the middle of combustor. The terminal shock wave of inlet moves toward the intake and the margin of inlet reduce by reduced air-fuel ratio.

关 键 词：固冲发动机 进气道 补燃室 空燃比 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]