含硼推进剂固冲发动机补燃室响应面优化设计  

Design optimization of secondary chamber response surface of boron-based propellant ducted rocket motor

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,长沙410073

出　　处：《航空动力学报》2007年第12期2113-2118,共6页Journal of Aerospace Power

基　　金：自然科学基金(50376072)

摘　　要：影响含硼推进剂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.首先建立了发动机补燃室内两相湍流燃烧数值模拟模型,然后提出了选用基于正交多项式的响应面方法来解决含硼推进剂固体火箭冲压发动机补燃室结构优化问题.这种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,能比较方便地对固体火箭冲压发动机补燃室各个参数进行优化与分析.There are a variety of influential factors to the combustion efficiency of secondary chamber of boron-based propellant ducted rocket motor, which are difficult to be expressed accurately by analytical functions. A two-phase turbulent flow combustion value simulation model was firstly established within the secondary chamber of the rocket motor. Then, the structural optimization of secondary chamber of Boron-based propellant ducted rocket motor was achieved through the response surface based on orthogonal polynomial. This method allows to compute less frequently the flow field of secondary chamber in obtaining the approximate functions, and makes it easier to optimize and analyze the parameters of secondary chamber of boron-based propellant ducted rocket motor.

关 键 词：航空 航天推进系统 固体火箭冲压发动机 含硼推进剂 响应面法 优化设计 数值模拟 燃烧过程 两相流 

分 类 号：V438[航空宇航科学与技术—航空宇航推进理论与工程]