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Satellites are subject to various severe vibration during different phases offlight. The concept of satellite smart adapter is proposed in this study toachieve active vibration control of launch vehicle on satellite. The satellitesmart adapter has 18 active struts in which the middle section of each strut ismade of piezoelectric stack actuator. Comprehensive conceptual design of thesatellite smart adapter is presented to indicate the design parameters,requirements and philosophy applied which are based on the reliability anddurability criterions to ensure successful functionality of the proposedsystem, also fabrication process of the proposed piezoelectric stack actuatoris discussed in detail. The coupled electromechanical virtual work equation forthe piezoelectric stack actuator in each active strut is derived by applyingD'Alembert's principle to calculate the consistent mass matrix, the stiffnessmatrix and the load vector using finite element approximation. Modal analysisis performed to characterize the inherent properties of the smart adapter andextraction of a mathematical model of the system. Active vibration controlanalysis was conducted using fuzzy logic control with triangular membershipfunctions and acceleration feedback. The control results conclude that theproposed satellite smart adapter configuration which benefits frompiezoelectric stack actuator as elements of its 18 active struts has highstrength and shows excellent robustness and effectiveness in vibrationsuppression of launch vehicle on satellite.

Active Vibration Control of Launch Vehicle on Satellite Using Piezoelectric Stack Actuator