Abstract
In this paper, an observer-based adaptive backstepping attitude maneuver controller (briefly, OBABC) for flexible spacecraft is presented. First, an observer is constructed to estimate the flexible modal variables. Based on the proposed observer, a backstepping control law is presented for the case where the inertia matrix is known. Further, an adaptive law is developed to estimate the unknown parameters of the inertia matrix of the flexible spacecraft. By utilizing Lyapunov theory, the proposed OBABC law can guarantee the asymptotical convergence of the closed-loop system in the presence of the external disturbance, incorporating with the L2-gain performance criterion constraint. Simulation results show that the attitude maneuver can be achieved by the proposed observer-based adaptive backstepping attitude control law.
Highlights
A new generation of large spacecraft have a complex structure that can include flexible appendages such as solar panels, antennas, and space manipulators
Some other control approaches have been investigated for the attitude control problem of flexible spacecraft, such as the angular velocity feedback control without angular velocity measurement [9] and finite-time control technique [10]
This controller was designed for attitude maneuver and vibration reduction with external disturbance and inertia matrix uncertainty
Summary
A new generation of large spacecraft have a complex structure that can include flexible appendages such as solar panels, antennas, and space manipulators. On the basis of previous research work, a robust adaptive controller was proposed with angular velocity bounded in [22] This controller was designed for attitude maneuver and vibration reduction with external disturbance and inertia matrix uncertainty. Motivated by the above discussion, we design an observer-based adaptive backstepping attitude controller in this paper for a flexible spacecraft in the presence of external disturbance, unknown inertia matrix parameters, and flexible appendage vibrations. Lyapunov stability analysis shows that the proposed control law guarantees asymptotical convergence of the attitude angle and angular velocity of the flexible spacecraft in the presence of bounded disturbance, incorporating the L2-gain performance criterion constraint. These results are illustrated through various numerical simulations. Compared with the designed control law in [27, 28], the proposed controller in this paper possesses better performance
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