Abstract
Robust finite-time control algorithms for satellite attitude maneuvers are proposed in this paper. The standard sliding mode is modified, hence the inherent robustness could be maintained, and this fixed sliding mode is modified to dynamic, therefore the finite-time stability could be achieved. First, the finite -time sliding mode based on attitude quaternion is proposed and the loose finite-time stability is achieved by enlarging the sliding mode parameter. In order to get the strict finite-time stability, a sliding mode based on the Euler axis is then given. The fixed norm property of the Euler axis is used, and a sliding mode parameter without singularity issue is achieved. System performance near the equilibrium point is largely improved by the proposed sliding modes. The singularity issue of finite-time control is solved by the property of rotation around a fixed axis. System finite-time stability and robustness are analyzed by the Lyapunov method. The superiority of proposed controllers and system robustness to some typical perturbations such as disturbance torque, model uncertainty and actuator error are demonstrated by simulation results.
Highlights
With regard to the matter of satellite attitude control, the standard sliding mode is a mature and widely used control algorithm
A finite time controller based on a dynamic sliding mode will be proposed based on a standard sliding mode surface; the advantage of a fast convergence rate and strong robustness would be combined in this proposed method
A system finite time stability is achieved by implementing the update law of sliding mode parameters and the singularity issue is avoided by using the property when angular velocity is reversed to the attitude quaternion
Summary
With regard to the matter of satellite attitude control, the standard sliding mode is a mature and widely used control algorithm. The focus of his work is the structure of finite-time controllers for classic nonlinear systems and the standard structure of the terminal sliding mode. In order to get finite-time stability, the design of the controller needs some special modifications and the system loses the inherent strong robustness to perturbations. Gui [28] designed finite-tine attitude maneuver controllers considering the disturbance torque with Gauss white noise character and sine function character. Designed finite-time sliding modes for satellite attitude control, and the convergence time is estimated by the proposed methods and disturbance torque with consideration of the upper bounded norm. A finite time controller based on a dynamic sliding mode will be proposed based on a standard sliding mode surface; the advantage of a fast convergence rate and strong robustness would be combined in this proposed method.
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