Abstract
We conduct comprehensive investigation of a semiactive vibration suppression method using piezoelectric transducers attached to structures. In our system, piezoelectric transducers are connected to an electric circuit composed of the diodes, an inductance, and a selective switch. Our method (SSDI) makes better use of counterelectromotive force to suppress the vibration, instead of simple dissipation of vibration energy. We use an actual artificial satellite to verify their high performance compared to conventional semi-active methods. As a consequence, we demonstrate that our semi-active switching method can suppress the vibration of the real artificial satellite to as much as 50% amplitude reduction. In our experiment, we reveal that the suppression performance depends on how multiple piezoelectric transducers are connected, namely, their series or parallel connection. We draw two major conclusions from theoretical analysis and experiment, for constructing effective semi-active controller using piezoelectric transducers. This paper clearly proves that the performance of the method is the connection (series or parallel) of multiple piezoelectric transducers and the their resistances dependent on frequency.
Highlights
Space structures, such as the space station or artificial satellites, are built for the purpose of highly demanding space missions
We find a discrepancy between theoretical analysis result and experimental result
The connection of the transducers is composed of m parallel and n series, where m and n are integers. It means that 50 transducers are divided into n groups that are composed of m transducers. m transducers in each group are connected in parallel, and the n groups are connected in series. m × n always equals 50
Summary
Space structures, such as the space station or artificial satellites, are built for the purpose of highly demanding space missions. Since the launch ability of rockets strictly limits the payload weight, space structures have to extremely minimize their weight, which results in the use of flexible structures and spindly members. They are more prone to vibrations compared with structures on earth with less weight restriction. Space structures and artificial satellites are exposed to severe vibration environment at the launch stage. The relaxation of such a severe condition is an important issue in order to improve their reliability and to reduce their development costs. Many methods of vibration suppression have been studied and proposed [1,2,3,4,5,6]
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