摘要
采用基于部分正交多项式的响应面法结合数值模拟试验对某实验发动机气体二次喷射推力矢量控制系统进行优化设计,结果表明:这种优化方法可以减少为得到近似函数式而对主/次流干扰流场进行计算的次数,节省计算时间,能方便地对气体二次喷射系统各个参数进行优化与分析.
The secondary gas injection thrust vector control system of a test engine was optimized using partial orthogonal-polynomial based response surface methodology (RSM) along with numerical simulation. The results show that such optimization method could reduce and save the calculation time of primary/secondary interference flow field for approximate functional equation, and enable you to optimize and analyze easily the parameters of secondary gas injection system.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2007年第9期1569-1572,共4页
Journal of Aerospace Power
基金
武器装备预研基金
国家863高新技术项目
关键词
航空、航天推进系统
气体二次喷射
推力矢量控制
响应面法(RSM)
优化设计
数值模拟
aerospace propulsion system
secondary gas injection
thrust vector control
response surface methodology (RSM)
optimization design
numerical simulation