Impact Time Control Guidance-law With Seeker Field-of-view Limit

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.