固体火箭发动机特型喷管的型面设计  

Counter Design for Length-shorted Nozzle of Solid Rocket Engine

作　　者：王筱蓉[1] 周长省[1] 鞠玉涛[1] 姜根柱[1] 

机构地区：[1]南京理工大学机械工程学院,南京210094

出　　处：《弹道学报》2008年第4期77-80,共4页Journal of Ballistics

摘　　要：为了提高发动机的推力,采用双圆弧法设计了固体发动机的特型喷管,利用自动优化平台,集成了参数化建模和喷管流场数值模拟,以发动机推力为优化目标,运用模拟自适应退火算法和序列二次规划算法组合优化策略对喷管内型面进行了气动优化,利用Gambit内部函数解决了参数空间配对问题.优化后,喷管的能量转化率得到了提高,推力提高了3.07%.此方法可用于喷管的实际设计中.To improve the thrust of engine, double-arc technology was used to design the lengthshorted nozzle. By using auto-optimize platform ,the model of parameter and the numerical simulation on flowfield of the nozzle were assembled . The optimized goal was engine thrust, and the strategy combined by adapt simulated annealing and sequential quadratic programming was used to optimize the nozzle internal-contour . To resolve the partnership in parameter spaces , Gambit software internal function was used. After the optimization, the transfer efficiency of nozzle energy is improved, and the thrust is improved by 3.07%. The results show that the technology can be used to design the nozzle of solid rocket engine.

关 键 词：特型喷管 固体火箭发动机 型面优化 数值仿真 有限体积法 

分 类 号：TK243.3[动力工程及工程热物理—动力机械及工程] N945.15[自然科学总论—系统科学]