固体火箭发动机特型喷管造型设计与优化  

Profile Design and Optimization of SRM Nozzle

作　　者：虞跨海[1,2] 莫展[2] 张亮[2] 梁斌[1] 

机构地区：[1]河南科技大学规划与建筑工程学院,河南洛阳471003 [2]中国空空导弹研究院,河南洛阳471009

出　　处：《弹箭与制导学报》2012年第4期137-138,142,共3页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：国家自然科学基金(51105132);河南省基础与前沿技术研究计划项目(112300410166);河南省教育厅自然科学基金(2011B590001);河南科技大学博士科研启动基金资助

摘　　要：采用双三次样条方法建立了某型固体火箭发动机特型喷管扩张段型面;考虑燃气流动和温度的耦合影响,采用二维轴对称可压缩N-S方程进行数值仿真分析。以发动机推力和总压恢复系数最大为优化目标,模拟退火算法寻优进行了特型喷管的优化设计,与初始设计方案相比,轴向推力提高2.38%,总压恢复系数提高2.22%。结果表明:特型喷管性能远优于锥形喷管,通过对型面的优化设计可以提高喷管性能。A new profile design method for SRM nozzle was proposed, and the profile optimization was completed to improve the nozzle per- formance. Bi-cubic spline was used to construct the nozzle divergent section profile. Two-dimensional compressible axisymmetric N-S equa- tions were used to do the numerical simulation with considering the coupling effects of gas flow and heat transfer. Finally, the adaptive sim- ulated annealing algorithm was used to complete the profile optimization, with the objectives of the maximum thrust and minimum total pres- sure loss. The optimization increases the axial thrust of engine by 2.38% , and enhances the total pressure recovery coefficient by 2, 22%. The result shows that the shortened nozzle has much better performance than conical nozzle when they are the same long as divergent sec- tion. The result also shows that the nozzle performance can be improved through the optimization of section profile.

关 键 词：固体火箭发动机 特型喷管 参数化设计 优化设计 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]