| Summary: | 碩士 === 國立成功大學 === 航空太空工程學系 === 86 === Because of its light weight and low power consumption,
flexiblestructures are widely used in aerospace and mechanical
systems, such as solar panels, antennas of earth satellite and
robot arms. However,the vibration of flexible structure may
degrade the accuracy of posi-tioning and attitude. Therefore, it
is worthy to study how to the atti-tude and position of flexible
structures under the effect of vibrationare being controlled.In
this research, we use a simple experimental system to simulate
the attitude control of a satellite with flexiblestructure. The
position of the experimental system is controlled bya momentum
wheel driven by a stepping motor while utilizing the law of
angular momentum conversation. The experimental set-up includes
a potential meter is used to measure the angular motion of the
rotator angle. A strain gauge and a piezoelectric plate are
used to measure and to suppress the vibration of the flexible
beam.To derive the governing equations of the system, the
Hamilton*s principle was applied.In the controller designs ,
LQR, CDM (Coefficient Diagram Method), and unmodel sampling
method(Data-Based Controller Synthesis) are used. The
simulation and experiment results are compared and the
advantages and the disadvantages of different controllers
applied in the system arediscussed.
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