考虑导引头耦合作用的带落角约束制导律设计

Design of Guidance Laws with Falling Angle Constraint andCoupling of Seeker Dynamics

针对制导火箭弹弹体与导引头之间的动力学耦合等问题,提出了一种带落角约束的制导律设计方法。首先,考虑到飞行过程中导引头和弹体之间的耦合作用,建立了方位俯仰捷联式导引头的二自由度数学模型以及制导火箭弹的六自由度数学模型,然后,考虑到实际工程应用中导引头与弹体之间的动力学耦合因素,将导引头框架偏转角作为制导信息,设计了一种带落角约束的制导律,实现最大毁伤效果。最后,通过仿真分析验证了所设计的带落角约束制导律能够在保证落角精度的同时降低脱靶量。

Aiming at the problems of the dynamic coupling between the guided rocket projectile body and the seeker,a guidance law design method with falling angle constraint is proposed.Firstly,considering the coupling effect between the seeker and the projectile body during flight,the two-degree-of-freedom mathematical model of azimuth-pitch strapdown seeker and the six-degree-of-freedom mathematical model of guided rocket are established.Then,considering the dynamic coupling factor between the seeker and the projectile body in practical engineering applications,the deflection angle of the seeker frame is used as the guidance information,and a guidance law with falling angle constraints is designed to achieve the maximum damage effect.Finally,the simulation analysis verifies that the designed guidance law with falling angle constraint can reduce the miss distance while ensuring the falling angle accuracy.