空燃比对固体火箭超燃冲压发动机性能的影响  

Effects of Air-fuel Ratio on the Solid-rocket Scramjet Performance

作　　者：刘仔 陈林泉[1] 吴秋 LIU Zai;CHEN Linquan;WU Qiu(The 41st Institute of the Fourth Academy,CASC,Xi’an 710025,China)

机构地区：[1]中国航天科技集团公司第四研究院第41研究所,西安710025

出　　处：《弹箭与制导学报》2017年第6期93-95,101,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：为了研究空燃比对固体火箭超燃冲压发动机补燃室性能的影响,文中对不同空燃比下补燃室掺混燃烧流场进行了模拟。采用基于密度的二阶迎风格式对补燃室掺混燃烧进行模拟,湍流模型和燃烧模型分别采用SST k-ω模型和涡团耗散模型。结果表明,化学反应速率随着空燃比的增加而增大;燃烧效率与总压恢复系数随着空燃比的增大而增大;补燃室推力与比冲也随着空燃比的增大而增大。空燃比的选择原则是保证导弹武器的推阻比最佳。In this work,we simulated the mixing combustion flow field of second combustor under different air-fuel ratio to study the influence of air-fuel ratio on the second combustor performance of solid-rocket scramjet.The mixing combustion of the second combustor was simulated by using the two order upwind scheme based on the density,and the turbulence model and combustion model adopted SST k-ωmodel and eddy dissipation model,respectively.The result indicated that the chemical reaction rate,combustion efficiency,and total pressure recovery coefficient increased with the increase of air-fuel ratio.In a word,the selection principle of air-fuel ratio is to ensure the thrust-drag ratio is the best.

关 键 词：固体火箭超燃冲压发动机 空燃比 补燃室性能 SST k-ω模型 涡团耗散模型 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]