助推滑翔导弹滑翔段优化研究  

Optimization Research on Glide Trajectory of Glide Missile

作　　者：郭飞帅[1] 张高瑜[1] 刘冬[1] 

机构地区：[1]第二炮兵工程学院603教研室,西安710025

出　　处：《四川兵工学报》2011年第8期27-30,39,共5页Journal of Sichuan Ordnance

摘　　要：介绍了助推滑翔的导弹滑翔段的特点和平衡滑翔工程定义。建立了滑翔飞行的模型,进行了仿真研究,并提出了2种最大升阻比的滑翔控制方案,即分别以高程和气动力函数式为基准的滑翔控制方案。对控制方案分别进行了仿真研究,分析了其优缺点。At first,it introduced the characteristics of glide trajectory and engineering definition of balancing glide.Secondly,it buit a model of gliding flight,and carried on the simulation study.Finally,the two gliding control scheme of the biggest lift-drag ratio were respectively proposed,namely the height-based and aerodynamic functional-based glide control program.And it made the simulation research for the control solution,and analyzed their advantages and disadvantages.

关 键 词：助推滑翔导弹 优化设计 滑翔弹道 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]