带有导引头视场限制的攻击时间控制导引律

摘要

The field-of-view(FOV) of seeker is limited in the maneuvering flight for missile.From the dynamic equation of the target look-angle of seeker,a terminal guidance law was designed for anti-ship missile with impact time control and seeker FOV limit by adding a feedback to the proportional navigation guidance law and utilizing the nonlinearity of cosine function.The stability of this closed-form guidance system was analyzed by Lyapunov stability theory.Compared to the switching logic method,the method of designing guidance law directly avoids the instant jump of the guidance command between different guidance laws.The actual target maneuvering may cause bad control precision of the impact time and even cause failure to hit the target for missile.For this reason,the missile was guided by the information of the predicted impact point of missile and target calculated in real time according to the desired impact time.Consequently,the guidance problem with multiple constraints against maneuvering target was solved.Simulation results show the validity of the proposed approach.%针对导弹机动飞行中的导引头视场受限问题,从导引头目标视角的动力学方程出发,通过在比例导引律基础上附加反馈项并利用余弦函数的非线性特性,设计了一种带有攻击时间控制及导引头视场限制的反舰导弹末制导律.采用Lyapunov稳定性理论,分析了闭环导引系统的稳定性.相比于切换逻辑的方法,这种直接设计导引律的方法避免了制导指令在不同导引律切换时的瞬间跳变.实际目标的机动使得攻击时间的控制精度变差,甚至导致导弹脱靶.对此,按照期望的攻击时间实时解算导弹与目标的预测遭遇点,并以遭遇点信息制导导弹,从而解决了目标机动情况下的多约束制导问题.仿真结果表明,本文方法是有效的.