变推力固体火箭发动机战术导弹弹道优化研究  

Trajectory Optimization Design of Tactical Missile with Variable Thrust Solid Rocket Engine

作　　者：于建国[1] 郑咏岚[1] 

机构地区：[1]北京电子工程总体研究所,北京100854

出　　处：《现代防御技术》2014年第4期20-23,38,共5页Modern Defence Technology

摘　　要：在给定发射初始条件、目标逃逸方式及控制律条件下进行了导弹性能仿真,给出了采用变推力固体火箭发动机的战术导弹最大发射弹目距离和变推力固体火箭发动机二级推力所对应的关系,形成了仿真条件下的变推力发动机控制律,丰富了采用变推力发动机的导弹制导律设计维数,并分析了发动机二级推力调节对弹道设计的影响,对采用变推力固体火箭发动机的导弹弹道优化设计具有一定的指导意义。The performance of missile was simulated under given conditions of launch type,escape method and control law.Meanwhile,the relationship between maximum launch distance and variable thrust was obtained and the control law of the variable thrust solid rocket engine was formed.The result enlarged the dimension of control law in the trajectory design.At the same time,the influence of variable thrust was analyzed in the trajectory design.The research may be helpful for the tactical missile trajectory design with variable thrust solid rocket engine.

关 键 词：变推力固体火箭发动机 二级推力调节 战术导弹 弹道优化 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程] TJ013.2[兵器科学与技术—兵器发射理论与技术]