Abstract
In spacecraft, severe vibrations induced by the launch vehicle may cause damage to theprecision payload. Therefore active adapters with vibration suspending characteristics areneeded. This paper presents theoretical studies of the active vibration controlcharacteristics of conical shells with laminated piezoelectric actuators. A diagonalpiezoelectric actuator is proposed to control the axial, lateral and transverse vibrations ofthe conical shell. Modal functions are designed to represent the free vibrations of theconical shell with clamped-free boundary conditions. General formulae of the modal controlforce and corresponding components are derived based on the converse piezoelectriceffects and then specified for the diagonal actuators. By using an open-loop controlmethod, the modal control characteristics of diagonal actuator segments at differentlocations are investigated and compared, and the axial, lateral and transversevibrations of two conical shell models are evaluated. The optimal locations ofactuator segments for the control of different natural modes are also investigated.
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