Missile Angle of Attack Tracking Using Integrator Backstepping

Abstract

This paper deals with missile longitudinal dynamics control. The angle of attack tracking problem is considered for an unpowered flight phase of a short range tail-controlled missile with the zero engine thrust. For the control synthesis, a simplified missile dynamics model that includes the actuator dynamics is used. The tracking control law is designed using the integrator backstepping approach. The aerodynamic polynomials dependence on absolute values of the angle of attack is considered from the perspective of applying the integrator backstepping technique.