  Satellites are subject to various severe vibration during different phases of
flight. The concept of satellite smart adapter is proposed in this study to
achieve active vibration control of launch vehicle on satellite. The satellite
smart adapter has 18 active struts in which the middle section of each strut is
made of piezoelectric stack actuator. Comprehensive conceptual design of the
satellite smart adapter is presented to indicate the design parameters,
requirements and philosophy applied which are based on the reliability and
durability criterions to ensure successful functionality of the proposed
system, also fabrication process of the proposed piezoelectric stack actuator
is discussed in detail. The coupled electromechanical virtual work equation for
the piezoelectric stack actuator in each active strut is derived by applying
D'Alembert's principle to calculate the consistent mass matrix, the stiffness
matrix and the load vector using finite element approximation. Modal analysis
is performed to characterize the inherent properties of the smart adapter and
extraction of a mathematical model of the system. Active vibration control
analysis was conducted using fuzzy logic control with triangular membership
functions and acceleration feedback. The control results conclude that the
proposed satellite smart adapter configuration which benefits from
piezoelectric stack actuator as elements of its 18 active struts has high
strength and shows excellent robustness and effectiveness in vibration
suppression of launch vehicle on satellite.
