Integrated guidance and control for missile in the presence of input saturation and angular constraints

An adaptive dynamic surface control algorithm is developed for integrated missile guidance and control system with input saturation and terminal angular constraints. An auxiliary system of the elevator is first introduced into the integrated guidance and control model for the pitch channel. A kind of smooth function is exploited to approximate saturation nonlinearity. An adaptive dynamic surface control law is adopted to deal with unmatched uncertainties in the time-varying system. The proposed control scheme guarantees not only the stability of the missile dynamics under saturation but also the desired interception performance with a desired terminal attitude angle. For the yaw and roll channels, the similar control schemes are utilized. Nonlinear 6-DOF simulation results are carried out to demonstrate the efficacy of our proposed approach.