Abstract
The three-axis attitude tracking manoeuvre and vibration suppression of a flexible spacecraft in the presence of external disturbances are investigated in this paper. The spacecraft consists of a rigid hub and two flexible appendages. The Euler–Bernoulli beam theory is used to model the flexible parts. The attitude dynamic equations of motion are derived using the law of conservation of angular momentum, and the flexural equations are derived. The attitude of the spacecraft is represented using the quaternion parameters. The controller is designed based on the super-twisting sliding mode control. The sliding surfaces are introduced and the global asymptotic stability of the flexible spacecraft on the sliding surfaces is assured via Lyapunov method. The control law is designed such that the sliding condition is satisfied and the system reaches the sliding surfaces in finite time. The simulation results verify the performance of the controller in the presence of bounded disturbances, sensor noises and abrupt changes in parameters.
Highlights
Attitude dynamics and control of a flexible spacecraft is one of the most widely studied areas in the past three decades, and it has received so much attention
In order to stabilize the attitude of a flexible spacecraft and suppress the vibration of panels, an adaptive controller is designed to robust against limited disturbances and parametric uncertainties
The sliding surfaces were introduced and their asymptotic stability was proved via Lyapunov method
Summary
Attitude dynamics and control of a flexible spacecraft is one of the most widely studied areas in the past three decades, and it has received so much attention. Keywords Flexible spacecraft, attitude tracking, sliding mode control, Lyapunov method In Hu et al.,11 assuming all state variables are limited and using the slide mode control, only the asymptotic stability of the attitude dynamics of the spacecraft is shown and the vibration suppuration of the flexible components is not shown in this work.
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