激波矢量控制喷管性能分析与结构优化设计  

Performance Analysis and Optimization Design of Shock Vector Control Nozzle

作　　者：李丽[1] 张琳琳 吕锡昌 李东明[1] LI Li;ZHANG Linlin;LV Xichang;LI Dongming(School of Mechanical Engineering, Dalian Jiaotong University,Dalian 116028,China)

机构地区：[1]大连交通大学机械工程学院,辽宁大连116028

出　　处：《大连交通大学学报》2018年第1期61-64,共4页Journal of Dalian Jiaotong University

基　　金：辽宁省自然科学基金资助项目(2015020133)

摘　　要：采用试验设计方法进行激波矢量控制喷管气动性能数值分析与优化设计,综合研究了二次流几何参数对二元收扩喷管气动性能的影响.基于超拉丁立方设计方法得到喷管二次流参数近似拟合模型和最优解区域,并利用多岛遗传算法寻找最优解.研究的设计参数包括二次流口距离、二次流口宽度及二次流长度.数值仿真结果表明,二次流口距离对矢量偏转角的影响最大,二次流口宽度次之,二次流长度对矢量偏转角的影响最小.The aerodynamic performance and optimization of shock vector control nozzle are analyzed with design of experiment(DOE)method,and the effects of three parameters are simulated on the two dimensional converging diverging nozzle.The approximate model of control parameters and optimal solution region are obtained by Latin hypercube design method,and the optimum solution is achieved by the multi island genetic algorithm.The design parameters include the distance between the secondary jet and the nozzle exit,the width and the length of the secondary jet flow.The numerical simulation results show that the distance of the secondary jet is the biggest influence on the thrust pitching angle,the width of the secondary jet is the second,and the length of the secondary jet is the least.

关 键 词：推力矢量喷管 激波矢量控制 试验设计 超拉丁立方设计 多岛遗传算法 推力矢量角 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]