Due to the lightweight requirements of spacecraft structures

the application of large flexible space truss structure has become increasingly widespread. Since it has low-damping and large-flexible features

large oscillation is easy to be motivated on the orbit and it will affect the normal operation of the spacecraft. A finite-time control scheme based on terminal sliding-mode technique is developed to suppress the vibration of the sensor/actuation-integrated space intelligent truss structure. Based on the modal decoupling characteristics of independent modal space control theory

the extended state observer is utilized to estimate the general system disturbances consisted of external disturbances and model perturbations in real-time. Then

the terminal sliding-mode controller is designed based on "linear dynamics compensation" method. Compared with the traditional finite-time controller based on homogeneous method

simulation results show that the proposed vibration suppression controller can reduce the modal vibration amplitude caused by transient disturbance force and periodic disturbance force significantly in a shorter settling time. The proposed controller has good robustness and finite time vibration convergence characteristics.