Sliding-Mode-Based Missile-Integrated Attitude Control Schemes Considering Velocity Change

A sliding-mode-based control scheme is proposed for integrated roll–pitch–yaw attitude control of a fin-controlled skid-to-turn missile during the boost phase. The missile aerodynamics accompany nonlinear, partially unstable, and cross-coupling effects among input channels so that integrated control is required. A mathematical model of the attitude dynamics and aerodynamics is constructed regarding the inertial property variations. Two possible architectures (the single-loop control scheme employing the higher-order sliding mode controller and the separated control scheme based on the traditional sliding mode controller) are proposed. For the integrated attitude control of the missile, multiple sliding surfaces are chosen for simultaneous tracking of the attitude commands. To demonstrate the performance of the proposed control scheme, numerical simulations are performed using a nonlinear six degrees-of-freedom missile model in the presence of uncertainties.