Vibration control with electrodynamic actuators
Vibration control with electrodynamic actuators
This thesis deals with different configurations of an electrodynamic actuator that is used to control vibrations of mechanical structures. Stability and vibration reduction performance are investigated both with theoretical and experimental studies on the model problem of an aircraft panel.
At first a conventional, electrodynamic, reactive actuator acting on the aircraft panel and reacting against a fixed based is studied. Direct velocity feedback with ideal velocity sensor and force actuator, with an accelerometer sensor and with different self-sensing control schemes such as a shunted resistor, positive current feedback induced voltage feedback and induced voltage feedback with inductance compensation are compared.
Then the design of a more practical, lightweight, electrodynamic, inertial actuator is studied. Important design considerations for the mechanical and the electrical parts are highlighted and some designed characteristics are validated at a prototype actuator.
Finally the lightweight, electrodynamic, inertial actuator is applied on the aircraft panel and vibration reduction is compared to passive means of vibration reduction. First internal relative velocity and external absolute velocity feedback are investigated considering ideal sensors. In practice, the external velocity feedback loop is implemented using a commercial accelerometer while the internal velocity feedback loop is implemented with self-sensing control schemes or, as an alternative, with a secondary coil sensor. Then internal and external direct velocity feedback loops are implemented simultaneously using either the accelerometer – self-sensing or accelerometer – secondary coil sensor combination.
University of Southampton
Paulitsch, Christoph
7ac64382-416f-437c-b17c-e39aa07c96b8
2005
Paulitsch, Christoph
7ac64382-416f-437c-b17c-e39aa07c96b8
Paulitsch, Christoph
(2005)
Vibration control with electrodynamic actuators.
University of Southampton, Doctoral Thesis.
Record type:
Thesis
(Doctoral)
Abstract
This thesis deals with different configurations of an electrodynamic actuator that is used to control vibrations of mechanical structures. Stability and vibration reduction performance are investigated both with theoretical and experimental studies on the model problem of an aircraft panel.
At first a conventional, electrodynamic, reactive actuator acting on the aircraft panel and reacting against a fixed based is studied. Direct velocity feedback with ideal velocity sensor and force actuator, with an accelerometer sensor and with different self-sensing control schemes such as a shunted resistor, positive current feedback induced voltage feedback and induced voltage feedback with inductance compensation are compared.
Then the design of a more practical, lightweight, electrodynamic, inertial actuator is studied. Important design considerations for the mechanical and the electrical parts are highlighted and some designed characteristics are validated at a prototype actuator.
Finally the lightweight, electrodynamic, inertial actuator is applied on the aircraft panel and vibration reduction is compared to passive means of vibration reduction. First internal relative velocity and external absolute velocity feedback are investigated considering ideal sensors. In practice, the external velocity feedback loop is implemented using a commercial accelerometer while the internal velocity feedback loop is implemented with self-sensing control schemes or, as an alternative, with a secondary coil sensor. Then internal and external direct velocity feedback loops are implemented simultaneously using either the accelerometer – self-sensing or accelerometer – secondary coil sensor combination.
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Published date: 2005
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Local EPrints ID: 465699
URI: http://eprints.soton.ac.uk/id/eprint/465699
PURE UUID: f6a0025d-dc6e-4884-9267-8b860f1c94ba
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Date deposited: 05 Jul 2022 02:39
Last modified: 16 Mar 2024 20:19
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Author:
Christoph Paulitsch
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