Active vibration control of large flexible space structure is a challenging topic in the system dynamics and control of spacecraft. This paper proposes a novel approach for vibration control on a large hoop truss structure, typically used as mesh satellite antenna. First, to suppress the first-order bending modal response of the hoop truss structure with an initial disturbance, a piezoelectric bending actuator with excellent bending actuation performance was carefully designed as a key component of an active vibration control system. Then, the actuating characteristics of the actuator and the dynamic equations of the active structure were analyzed and formulated based on a finite element method. In order to improve the vibration-attenuating effect of the control system, a Mamdani-type fuzzy logic algorithm was employed in a closed-loop control system. Finally, simulations and experiments were implemented to validate the effectiveness of the proposed active control approach and structure. The experimental results showed that the decay time of first-order bending modal response (around 0.34 Hz) of control system reduces by 75% compared with that of the uncontrolled system. The results demonstrate that the proposed active vibration control system has good application potential in controlling the bending modes of a large flexible spacecraft.

This paper presents multimode vibration absorbing methods which employ negative resistance (NR) and negative inductance negative resistance (NINR) electromagnetic shunt damping vibration absorbers. The NR and NINR shunts can change the impedance of an electromagnet so as to change the control force of the absorber. The governing equation of the coupling system is established. What is more, some numerical simulations are carried out and the results show that the absorbers with NR or NINR shunt can effectively suppress the multimode vibration. Furthermore, the root locus is analyzed to design the resistance of a shunt.