摘要
通过CFD手段建立尾喷管推力系数和升力系数计算代理模型,利用遗传算法对尾喷管在Ma=2.5、5.0、8.0处进行单目标优化,利用优化结果分析喷管几何参数在全速域对喷管性能的影响。对喷管进行多目标优化,得到多目标优化前沿,并以此为依据,通过加权系数法建立喷管在全速域下的优化目标函数,对此目标函数进行优化,得到最终优化结果,该优化结果综合考虑喷管在全速域下的推力和升力性能,优化出的喷管构型能保证其在整个飞行范围内正常高效工作。
The surrogate models of thrust and lift coefficients were established by CFD.Single objective optimization was done by genetic algorithms at Mach 2.5,5.0 and 8.0.The effect of geometry parameters on the performance of nozzle was analyzed by the optimum results.The multiobjective optimization on the nozzle was performed to obtain the optimum Pareto,and establish the objec- tive function in all fly range by the weighting coefficient.The optimization results consider the thrust and lift performance in all veloc- ity range, and the nozzle can work normally and efficiently in all fly range.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2013年第6期758-762,共5页
Journal of Solid Rocket Technology
关键词
宽马赫数
尾喷管
优化设计
wide roach number
nozzle
optimum design
