Modeling and analysis of the influence caused by micro-vibration on satellite attitude control system

Li, Lin; Yu, Yang; Wang, Li; Yuan, Li; Zhang, Lei; Gong, Xiaoxue; Wu, Yanpeng; Zheng, Ran

doi:10.1016/j.actaastro.2023.08.047

Cited by 4 publications

(2 citation statements)

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“…To establish the damping force, the piezoelectric actuator adopts a viscous damping model [40,41], which is also used for hyperelastic materials to simplify the dynamic model. Furthermore, the nonlinear elastic characteristics of hyperelastic materials are not considered because of the small vibration magnitude of the spacecraft [18,42].…”

Section: Dynamic Modelmentioning

confidence: 99%

“…of hyperelastic materials are not considered because of the small vibration magnitude of the spacecraft [18,42]. In Figure 2, kc and cc represent the stiffness and damping of the piezoelectric actuator; mi is the intermediate mass; kr and cr represent the stiffness and damping of the hyperelastic material, respectively; and mp is the payload mass.…”

Section: Dynamic Modelmentioning

confidence: 99%

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Modeling and Analysis of Bio-Inspired, Reconfigurable, Piezo-Driven Vibration Isolator for Spacecraft

Zhang,

Wang,

et al. 2024

Biomimetics

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The positioning accuracy of spacecraft in orbit is easily affected by low-frequency micro-vibrations of the environment and internal disturbances caused by the payload. Inspired by the neck structure of birds, this study devised a piezo-driven active vibration isolation unit with high stiffness. First, a dynamic model and two-sensor feedback control method for the isolation unit were developed, and the isolation mechanism and anti-disturbance characteristics were analyzed. Further, the stability of the closed-loop was verified. Simulation models of serial and parallel systems based on the proposed vibration isolation unit were implemented to demonstrate its feasibility. The results indicate that the proposed isolation units can provide excellent low-frequency vibration isolation performance and inertial stability and that they can effectively resist the internal disturbance of the payload. Moreover, its performance can be further improved via serial or parallel reconfiguration that facilitates its adaptation to the varied isolation requirements of spacecraft.

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