| Citation: | LIU S Y，YANG H L，ZHANG Z G，et al. Vibration control of flexible spacecraft with output constraints and external disturbances[J]. Journal of Beijing University of Aeronautics and Astronautics，2024，50（5）：1560-1567 （in Chinese） doi: 10.13700/j.bh.1001-5965.2022.0622
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A vibration control with direct joint torque input is presented for flexible spacecraft systems subject to external disturbances and output limits. Firstly, the dynamic characteristics of the system are described by a distributed parameter model which is composed of partial differential equation (PDE) and ordinary differential equation (ODE). Secondly, the tangential barrier Lyapunov function is used to ensure that the output constraints of vibration errors and attitude angle errors are met by a nonlinear disturbance observer that is intended to adjust for external disturbances. The asymptotic stability of the system is proved by extended LaSalle’s invariance principle and semigroup theory. It not only realizes the position control of attitude angle, but also restrains the elastic vibration of flexible spacecraft. Finally, the effectiveness of the proposed control method is verified by comparison simulations.
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