Adaptive Sliding Mode Control with Backstepping Approach for a Moving Mass Hypersonic Spinning Missile

Abstract

The dynamics model of a hypersonic spinning missile with two moving masses is established. Considering the inherent uncertainties of the mathematical model and the aerodynamic parameters, an affine model with external disturbances is established and an attitude adaptive sliding mode controller is designed following the backstepping approach. The stability of the closed-loop system is proved by means of Lyapunov method. A saturation function is introduced to eliminate the chattering of the sliding mode controller, and the numerical simulations show that the attitude controller is effective. Introduction Moving mass control generates the control torque by changing the positions of the internal masses to control the attitude of the aircraft [1]. Compared with the pneumatic rudder control, moving mass control can ensure the aerodynamic configuration of the aircraft, and reduce the aerodynamic drag and the rudder surface ablation [2], which is why the moving mass control is very suitable to hypersonic vehicles. A kinetic energy interceptor was well controlled via moving mass control [1]. The influence of moving masses on the rolling speed of a spinning missile was studied in [3]. When the moving mass control technique is employed to control a hypersonic spinning missile, both the radial control and the axial control of the centroid offset should be conducted [3]. As shown in Fig.1, there are two moving masses ( p mass and q mass) which are located along the axial direction and the radial direction, respectively. y