拦截大航路目标的终端角度约束中制导律设计  

Design of Midcourse Guidance Law with Terminal Impact Angle Constraints for Intercepting Large Airway Angle Target

作　　者：王重阳[1] 葛致磊[1] 周军[1] 

机构地区：[1]西北工业大学精确制导与控制研究所,陕西西安710072

出　　处：《计算机仿真》2013年第8期100-104,共5页Computer Simulation

摘　　要：研究舰载防空导弹制导精度优化问题。拦截大航路反舰导弹会造成弹目交会角较大降低引信频谱识别的启动概率而不利于引战配合,过去的终端角度约束制导律在逆轨拦截时容易造成末段过载过大甚至发散,使导弹末段可用过载不足而脱靶。为解决上述问题,提出导弹圆周运动过载稳定,利用几何方法设计了一种具有终端角度约束的圆周中制导律,根据圆的几何特性精确计算出了中末制导预测交班点和中制导起始时刻的最优到位角。通过仿真,验证了上述制导方法在过载平稳性、收敛性以及脱靶量等方面的性能优于一般的终端角度约束制导律。证明上述方法解决了终端角度约束造成的末段过载过大甚至发散的问题,有效提高了对大航路反舰导弹的逆轨拦截精度。Accuracy optimization of air-defense missile guidance was researched.General guidance law will cause a large engagement angle in intercepting anti-ship missile with large airway angle.Past guidance law with terminal impact angle constraints will cause large overloads in terminal time.A midcourse circular guidance law with terminal impact angle constraints was designed based on the circular motion of missile.The predicted handover point and the optimal angle of incidence can be accurately calculated based on the characteristic of the circular trajectory in this guidance law.Through mathematic simulation,the performance of this midcourse guidance law on overload and miss distance is better than the normal guidance law with terminal impact angle constraints.The accuracy of guidance for intercepting anti-ship missile with large airway angle is improved.

关 键 词：中制导律 航路角 圆周制导 预测交班点 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程]