On-off guidance law design for exo-atmospheric interceptor via nonsmooth linear Lipschitz thresholds

On-off guidance law design problem of terminal guidance system is studied for exo-atmospheric interceptor with pulse divert thrusters. Nonsmooth linear Lipschitz thresholds are constructed due to the relative motion equations of the missile and the target. The dynamics of the closed-loop system is described in the sense of Filippov´s differential inclusion since the pulse control input is discontinuous, thus the stability of the terminal guidance system is analyzed with contingent cone criteria in the frame of nonsmooth analysis. Finally, the validity of the method and its superiority in decreasing the on-off counts of the divert thruster are illustrated by a numerical simulation.