Abstract:

Under the assumptions that the target is stationary and the velocity of missile is constant， based on the dynamics and kinematics of the relative motion between missile and target, and according to the error between the real impact angle and the designated impact angle, the desired kinematics of line of sight(LOS) is analyzed and designed. Then, a threedimensional guidance law is designed by using Lyapunov stability theory. In order to predict and control the impact time, it is supposed that the velocity of missile is constant or timevarying with a constant positive/negative acceleration, the missile is guided to the designated impact angle, and the time-to-go is estimated according to the range-to-go. Then, the accelerations and time periods for missile maneuver along specifically designed circular arcs is determined according to the impact time error which is then compensated by the determined maneuver. Finally, the missile is guided to impact the target by the designed guidance law. Simulation results are given.

Key words: navigation,  , guidance , and , control,  , threedimensional , guidance,  , Lyapunov , stability,  , impact , angle,  , impact , time