固体火箭冲压发动机补燃室的响应面法优化设计  

Ducted rocket secondary chamber optimization with response surface methodology

作　　者：胡建新[1] 夏智勋[1] 赵建民[1] 郭健[1] 张炜[1] 罗振兵[1] 缪万波[1] 

机构地区：[1]国防科学技术大学航天与材料工程学院,湖南长沙410073

出　　处：《推进技术》2004年第6期491-494,共4页Journal of Propulsion Technology

摘　　要：影响固体火箭冲压发动机补燃室燃烧效率的因素很多,且各因素对燃烧效率的影响很难用精确的解析函数式来表示。采用基于正交多项式的响应面法结合数值模拟的优化方法对某实验发动机补燃室进行了设计,结果表明:这种优化方法可以减少为得到近似函数式而对补燃室流场进行计算的次数,节省计算时间,能方便地对发动机补燃室各个参数进行优化与分析。The work described represents an attempt to direct the design of secondary combustor in order to increase combustion efficiency of unchoked ducted rocket. It is a key technique for ducted rockets to make the secondary chamber operate at high efficiency and stability, The process of mixing and chemical reaction in the secondary chamber is very complicated, and many factors affect the combustion efficiency. A simple reacting flow model of secondary combustor based on Eddy Break-Up model is established and used in simulation. The method combining computation fluid dynamic with orthogonal-polynomial based response surface methodology (RSM) is applied successfully to optimize the effects of air intakes and gas generator nozzle. Some meaningful results are obtained and it shows the effectiveness of this method.

关 键 词：冲压火箭发动机 突扩燃烧室 响应面法 优化设计 数值仿真 

分 类 号：V236[航空宇航科学与技术—航空宇航推进理论与工程]