带导引头视场限制的多约束导引律及剩余时间估计  

Guidance law with multiple constraints and seeker field-of-view limit and the time-to-go estimation

作　　者：马国欣[1,2] 张友安[1] 李君[3] 

机构地区：[1]海军航空工程学院控制工程系 [2]中国人民解放军93132部队 [3]齐齐哈尔大学计算中心

出　　处：《系统工程与电子技术》2014年第8期1609-1613,共5页Systems Engineering and Electronics

基　　金：国家自然科学基金(61273058)资助课题

摘　　要：具有攻击角度约束的导引律能够使导弹按指定方向打击目标,具有攻击时间约束的导引律能够使导弹按指定时间打击目标。相比于传统的导引方法(如比例导引律),此类导引律均带来额外的机动,从而可能导致目标超出导引头视场(即使对于静止目标)。针对该问题,利用余弦函数的非线性特性,首先构造了一种带有导引头视场限制及攻击角度约束偏置项的比例导引律,并推导了该导引律的剩余时间估计。然后通过附加剩余时间误差反馈项,得到了一种带导引头视场限制并同时具有攻击角度约束与攻击时间约束的导引律。仿真结果验证了所提方法的有效性。The guidance law with impact angle constraint can enable missiles to hit the target in a designated direction,and the guidance law with impact time constraint can enable missiles to hit the target at a designated time.Compared with the traditional guidance approach （e.g.the proportional navigation guidance law）,these guidance laws all result in additional maneuvers,which may cause the target to move out of the missile seeker’s field-of-view （even for a stationary target）.To solve this problem,by utilizing the nonlinearity of the cosine function,proportional navigation guidance law with a biased item composed of the seeker field-of-view limit and impact angle constraint is constructed firstly,and the time-to-go estimation of this guidance law is derived. Then,by adding the feedback of the time-to-go error,a guidance law with seeker field-of-view limit and both impact angle and impact time constraints is proposed.Simulation results show the validity of the proposed ap-proach.

关 键 词：导引 导弹 攻击时间 攻击角度 视场限制 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]