一种新的导弹航向平面导引律  

A New Yaw Plane Guidance Law for Missiles

作　　者：张友安[1] 程继红[1] 于进勇[1] 

机构地区：[1]海军航空工程学院,山东烟台264001

出　　处：《弹箭与制导学报》2003年第S6期4-6,共3页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：2001年航空支承基金项目 No.01C66001

摘　　要：根据导弹与目标之间的相对运动方程,应用李雅普诺夫稳定性理论设计一种新的导弹航向平面导引律。该导引律需要获得目标切向加速度、目标的机动、目标速度的大小和速度方位信息,为此,文中进一步给出了其估算方法。仿真结果表明,该制导算法有较高的制导精度,在接近目标时,所需过载量小,弹道也比较平直。According to the dynamic equation of relative motion between the missile and the target,Lyapunov stability theory is used to design a new yaw plane guidance law for missiles.The presented guidance law needs accurate information on the accelerations of the target both in tangential direction and in normal direction,and on the value of velocity and velocity heading angle of the target,and hence,their estimation methods are also given. Simulation results have shown that the proposed guidance law has a higher guidance accuracy,and no biggish acceleration command of missile is required in the final stage of the engagement,and the final ballistic trajectory is almost a straight line.

关 键 词：导引律 李雅普诺夫稳定性 航向平面 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]