一体化变几何冲压发动机控制规律研究  

Study on Control Law for Integrated Variable Geometry Ramjet Engine

作　　者：杨云铠[1] 陈玉春[1] 黄兴[2] 孙祥逢[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072 [2]中国飞行试验研究院,陕西西安710089

出　　处：《计算机仿真》2010年第6期62-66,92,共6页Computer Simulation

摘　　要：为达到减轻导弹发射总重和提高导弹机动性的目的,建立了基于能量法的一体化超声速导弹/冲压发动机控制规律优化设计模型,通过合理调节尾喷管喉部面积,减小进气道的亚声速溢流阻力和提高总压恢复系数,降低冲压发动机的耗油率,实现一体化控制规律,在优化设计模型中,包含导弹升阻特性预测模型、冲压发动机特性与安装特性计算模型。将相应的计算程序在iSIGHT软件平台中进行集成并利用其优化功能,实现了尾喷管最优控制规律设计。对某型冲压发动机的计算结果表明,通过优化调整尾喷管喉部面积,可以显著降低导弹的发射总重,并明显提高导弹机动性。A control law design optimization model of supersonic missile/ramjet integration based on energy method is presented. By reasonably adjusting nozzle throat area, inlet subsonic overflow drag is reduced and inlet supersonic pressure recovery coefficient is increased, and specific fuel consumption of the ramjet is reduced, as a result, the missile＇s total launch weight is reduced. The design optimization model includes a model of predicting the missile lift - drag characteristic and a model of computating the ramjet characteristic and installation characteristic, a model of integrating constrain analysis and mission analysis. Composingof missile weight is also taken into account in the de- sign optimization model. The computer program was integrated into iSIGHT software, and the optimization tools of iSIGHT are employed to implement control law design optimization. Computing results of some ramjet engine show that optimally adjusting nozzle throat area can obviously reduce missile launch weight and increase missile maneuverability.

关 键 词：飞/发一体化设计 冲压发动机 可调尾喷管 控制规律 优化设计 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]