تلخیص
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.
Mehran Makhtoumi. (2018) Active Vibration Control of Launch Vehicle on Satellite Using Piezoelectric Stack Actuator, Journal of Space Technology , Volume 8, Issue 1.
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