Active vibration control of a space truss using a lead zirconate titanate stack actuator
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Authors
Song, G.
Vlattas, J.
Johnson, S.E.
Agrawal, B.N.
Subjects
active vibration control
piezoceramic material
flexible spacecraft
space truss
piezoceramic material
flexible spacecraft
space truss
Advisors
Date of Issue
2001
Date
Publisher
IMechE
Language
Abstract
This paper presents design, implementation and experimental results of active vibration control of Naval Postgraduate School (NPS) space truss using a piezoelectric ceramic stack actuator. The NPS space truss represents a flexible spacecraft structure that may support interferometer, antenna and other vibration-sensitive instrumentation. To simulate the effects of a spacecraft disturbance on the truss, a proof mass actuator is incorporated on the structure to excite the truss. To reduce the vibrations caused by the proof mass actuator, an active strut member is installed along a diagonal of the base bay of the truss. The active strut element consists of a piezoelectric ceramic actuator stack, a force transducer and mechanical interfaces. An integral plus double-integral force controller is designed to suppress vibration of the truss. Experimental results demonstrate that the active piezoceramic strut actuator can effectively reduce truss vibration.
Type
Article
Description
Series/Report No
Department
Mechanical and Aerospace Engineering (MAE)
Organization
Naval Postgraduate School
Identifiers
NPS Report Number
Sponsors
Funding
Format
7 p.
Citation
Song, G., et al. "Active vibration control of a space truss using a lead zirconate titanate stack actuator." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 215.6 (2001): 355-361.
Distribution Statement
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States