Terminal guidance method in glide attack phase of aerodynamic missile

On basis of trimming glide and horizontal flight modes, the Mini-derivative linearization model of aeromarine aerodynamic missile is constructed. As the mathematical model of missile plant, inertia component and rudder are combined, the PID parameters and lead/lag correction network is designed by frequency domain method to ensure the stability margin of attitude inner loop and the maneuverability of outer loop. The ballistic obliquity and height of missile are controlled in longitudinal plane. At the same time, the anticipant overload command is gained by revised proportional navigation law in lateral plane. Simulation results show that this terminal guidance method in glide attack phase can realize efficiently aeromarine horizontal flight in longitudinal plane and tracking target warship quickly with little miss distance.