Command filtered adaptive control for integrated missile guidance and autopilot with terminal angular constraint
For homing missiles considering terminal angular constraint, integrated design of guidance and control utilizing adaptive command filtered backstepping is studied in this paper. The proposed control scheme guarantees not only the stability of the missile dynamics with state constraints but also the interception performance with a desired terminal attitude angle. An adaptive law is introduced to compensate unknown uncertainties in the varying-time system. Simulation results are further presented to show the effectiveness and performance of the proposed approach.