A new adaptive finite time nonlinear guidance law to intercept maneuvering targets

A new adaptive nonlinear guidance law for homing missiles to intercept maneuvering targets in terminal phase is proposed. This guidance law generates smooth acceleration commands and is able to stabilize the relative lateral velocity in a desired finite time. The proposed guidance law uses bounds of the target acceleration and jerk and is consisting of two adaptive terms. It is proved that the first adaptive term of the proposed guidance law converges to the target acceleration normal to the line of sight. Finite time stability of the guidance loop is proved by using Lyapunov stability theorem. Numerical simulations are performed to illustrate the proposed guidance law potential.