Dynamic output feedback sliding mode control for spacecraft attitude monoeuvres

This paper studies a dynamic output sliding mode control law design for 3-axis attitude stabilization of a rigid spacecraft. A first-order sliding mode control combining the state-dependent Riccati equation (SDRE) technique is applied to quaternion-based attitude regulation with external disturbances and an uncertainty inertia matrix. An additional dynamic compensator is added into the design of the sliding surface. Stability of the closed-loop system and external disturbance attenuation can be ensured when the system is in the sliding mode. The SDRE approach is used in the design procedure to determine some controller gains. The second method of Lyapunov is used to show that robust stabilization is achieved. An example of multiaxial attitude manoeuvres is presented and simulation results are given to verify the usefulness of the proposed controller.