Sliding mode maneuvering control and active vibration damping of three-axis stabilized flexible spacecraft with actuator dynamics |
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Authors: | Qinglei Hu |
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Institution: | (1) Department of Control Science and Engineering, Harbin Institute of Technology, Harbin, 150001, China |
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Abstract: | This paper presents a dual-stage control system design method for the three-axis-rotational maneuver control and vibration
stabilization of a spacecraft with flexible appendages embedded with piezoceramics as sensor and actuator. In this design
approach, the attitude control system and vibration suppression were designed separately using a lower order model. Based
on the sliding mode control (SMC) theory, a discontinuous attitude control law in the form of the input voltage of the reaction
wheel is derived to control the orientation of the spacecraft actuated by the reaction wheel, in which the reaction wheel
dynamics is also considered from the real applications point of view. The asymptotic stability is shown using Lyapunov analysis.
Furthermore, an adaptive version of the proposed attitude control law is also designed for adapting the unknown upper bounds
of the lumped disturbance so that the limitation of knowing the bound of the disturbance in advance is released. In addition,
the concept of varying the width of boundary layer instead of a fixed one is also employed to eliminate the chattering and
improve the pointing precision as well. For actively suppressing the induced vibration, modal velocity feedback and strain
rate feedback control methods are presented and compared by using piezoelectric materials as additional sensors and actuators
bonded on the surface of the flexible appendages. Numerical simulations are performed to show that rotational maneuver and
vibration suppression are accomplished in spite of the presence of disturbance torque and parameter uncertainty. |
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Keywords: | Sliding mode control Flexible spacecraft Vibration control Attitude maneuver Actuator dynamics |
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