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Static aeroelastic behavior of an adaptive laminated piezoelectric composite wingThe effect of using an adaptive material to modify the static aeroelastic behavior of a uniform wing is examined. The wing structure is idealized as a laminated sandwich structure with piezoelectric layers in the upper and lower skins. A feedback system that senses the wing root loads applies a constant electric field to the piezoelectric actuator. Modification of pure torsional deformaton behavior and pure bending deformation are investigated, as is the case of an anisotropic composite swept wing. The use of piezoelectric actuators to create an adaptive structure is found to alter static aeroelastic behavior in that the proper choice of the feedback gain can increase or decrease the aeroelastic divergence speed. This concept also may be used to actively change the lift effectiveness of a wing. The ability to modify static aeroelastic behavior is limited by physical limitations of the piezoelectric material and the manner in which it is integrated into the parent structure.
Document ID
Document Type
Conference Paper
Weisshaar, T. A.
(Purdue University West Lafayette, IN, United States)
Ehlers, S. M.
(Purdue Univ. West Lafayette, IN, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1990
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 90-1078
Meeting Information
AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference(Long Beach, CA)
Accession Number
Funding Number(s)
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