Abstract
For the attitude stabilization of spacecraft with actuator dynamics, this paper proposed a finite-time control law. Firstly, the dynamic property of the actuator is analyzed by an example. Then, a basic control law is derived to achieve the finite-time stability using the double fast terminal sliding mode manifold. When there is no prior knowledge of time matrix of the actuator, an adaptive law is proposed to estimate the unknown information. An adaptive control law is derived to guarantee the finite-time convergence of the attitude, and a Lyapunov-based analysis is provided. Finally, simulations are carried out to demonstrate the effectiveness of the proposed control law to the attitude stabilization with the actuator dynamics. The results show that the high-precision attitude control performance can be achieved by the proposed scheme.
Highlights
Spacecraft mission success often relies on performance of the attitude control system, which consists of different types of actuators, such as thrusters and the reaction wheel, etc
In the attitude control problem, the actuator is often assumed to be the ideal dynamic [1,2,3,4] and must be able to deliver the exact torque desired by the controller immediately, which does not always conform to the actual situation [5]
If the actuator dynamics are neglected for high-precision attitude control, it may have an impact on the control performance
Summary
Spacecraft mission success often relies on performance of the attitude control system, which consists of different types of actuators, such as thrusters and the reaction wheel, etc. Hu [1] proposed a novel time-varying fast terminal sliding mode manifold to derive a finite-time controller in the presence of external disturbance, input saturation, and inertia uncertainty. A controller was proposed using the fast nonsingular terminal sliding mode manifold with a weighted homogeneous extended state observer estimating unknown disturbance. Due to its dynamics in practice, the actuator cannot deliver the desired torque provided by the controller instantaneously This will degrade the control performance for the high-precision attitude stabilization. With most actuators performing similar dynamical behavior, it is useful to establish a general dynamic model of actuator For this problem, this paper studies the attitude stabilization control with a general dynamics of the actuator. A basic control law and an adaptive control law are derived using the double fast terminal sliding mode (FTSM) manifold. Several simulations are performed and we conclude the paper
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