Super-twisting sliding mode control design based on Lyapunov criteria for attitude tracking control and vibration suppression of a flexible spacecraft
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 par...
| Main Authors: | , , , |
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| Format: | Article |
| Language: | English |
| Published: |
SAGE Publishing
2019-09-01
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| Series: | Measurement + Control |
| Online Access: | https://doi.org/10.1177/0020294019847696 |
| Summary: | 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. |
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| ISSN: | 0020-2940 |