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Layerwise Finite Elements for Smart Piezoceramic Composite Plates in Thermal EnvironmentsAnalytical formulations are presented which account for the coupled mechanical, electrical, and thermal response of piezoelectric composite laminates and plate structures. A layerwise theory is formulated with the inherent capability to explicitly model the active and sensory response of piezoelectric composite plates having arbitrary laminate configurations in thermal environments. Finite element equations are derived and implemented for a bilinear 4-noded plate element. Application cases demonstrate the capability to manage thermally induced bending and twisting deformations in symmetric and antisymmetric composite plates with piezoelectric actuators, and show the corresponding electrical response of distributed piezoelectric sensors. Finally, the resultant stresses in the thermal piezoelectric composite laminates are investigated.
Document ID
19960047606
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Saravanos, Dimitris A.
(Ohio Aerospace Inst. Cleveland, OH United States)
Lee, Ho-Jun
(NASA Cleveland, OH United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1996
Subject Category
Composite Materials
Report/Patent Number
NAS 1.15:106990
AIAA Paper 96-1277
NASA-TM-106990
E-10290
Report Number: NAS 1.15:106990
Report Number: AIAA Paper 96-1277
Report Number: NASA-TM-106990
Report Number: E-10290
Meeting Information
Meeting: Structures, Structural Dynamics, and Materials Conference and Exhibit
Location: Salt Lake City, UT
Country: United States
Start Date: April 15, 1996
End Date: April 17, 1996
Sponsors: American Helicopter Society, Inc., American Society of Mechanical Engineers, American Society of Civil Engineers, Alpha STAR Corp., American Inst. of Aeronautics and Astronautics
Accession Number
96N33243
Funding Number(s)
PROJECT: RTOP 505-63-5B
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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