一种变射面飞行导弹的弹上迭代制导方法  

Iterative guidance method of changeable launching plane flight missile

作　　者：王继平[1] 魏诗卉[1] 肖龙旭[1] 林红斌[1] 葛培红[2] 

机构地区：[1]第二炮兵装备研究院 [2]中国人民解放军96271部队

出　　处：《飞行力学》2015年第3期243-247,252,共6页Flight Dynamics

摘　　要：针对变射面飞行的弹道导弹,制导方法需要满足射面变换起控点的位置、速度和姿态要求。提出了一种变射面飞行导弹的弹上迭代制导方法,以各射面弹道终点的弹道倾角为约束,弹上迭代计算虚拟目标和需要速度,求取导引姿态角进而进行导引控制。仿真算例表明,该制导方法能够实现变射面飞行的制导控制要求,且方法误差较小。The guidance method that the ballistic missile of changeable launching plane flight adopted must meet the demands of the position, velocity and attitude in the start control point of the launching plane transform. An iterative guidance method of changeable launching plane flight missile was put ward, the method iteratively calculated the virtual target point and required velocity in the missile, for- and gets the attitude angle for guidance and control under the restriction of the ballistic obliquity of ballistic end-point of every launching plane. It is proved that the guidance method can realize the guidance and control demands of changeable launching plane flight by simulation calculation, and the error is very small.

关 键 词：变射面飞行 迭代制导 虚拟目标 需要速度 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程]