Research Papers

Post-Buckled Precompressed Techniques in Adaptive Aerostructures: An Overview

[+] Author and Article Information
Roelof Vos

Faculty of Aerospace Engineering, Delft University of Technology, 2600 GB Delft, The Netherlandsr.vos@tudelft.nl

Ron Barrett

Department of Aerospace Engineering, University of Kansas, Lawrence, KS 66045barrettr@ku.edu

J. Mech. Des 132(3), 031004 (Mar 19, 2010) (11 pages) doi:10.1115/1.4001202 History: Received October 06, 2008; Revised February 01, 2010; Published March 19, 2010; Online March 19, 2010

An overview of the development and application of post-buckled precompressed (PBP) piezoelectric actuators is presented. It has been demonstrated that PBP actuators outperform conventional piezoelectric actuators by relying on axial compression to counter the inherent stiffness in the actuator element. In doing so, the mechanical work output has been shown to increase threefold compared with conventional bimorph actuators. Actuator stroke has been demonstrated to increase up to 300% without compromising the blocked force capability. This has resulted in an expansion of the design space of piezoelectric bender elements and has made them excellent candidates for potentially replacing certain classes of conventional electromechanical flight control actuators. The successful application of PBP elements can be found in unmanned aerospace systems ranging from subscale vertical-take-off-and-landing vehicles to supersonic missile fins. With respect to conventional electromechanical servoactuators, it is demonstrated that PBP actuator elements induce a lower systems weight fraction, a substantially higher bandwidth, and an order of magnitude lower power consumptions and part count.

Copyright © 2010 by American Society of Mechanical Engineers
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Figure 1

Operating principle of PBP actuator (14)

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Figure 2

Bimorph piezoelectric actuator element

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Figure 3

Terms and conventions for analysis of the PBP actuator arrangement

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Figure 4

End rotation amplifications due to axial compression as predicted by Eq. 10 for various applied moments

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Figure 5

Model problem for the dynamic analysis of PBP actuator elements

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Figure 6

Effect of axial force on amplitude response of PBP actuator element

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Figure 7

Effect of lumped inertia on first natural frequency of PBP actuator element

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Figure 8

Effect of torsional stiffness on first natural frequency of PBP actuator element

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Figure 9

Relation between end peak-to-peak rotation and axial force for example PBP bimorph actuator element

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Figure 10

Transfer efficiency of axially loaded transducer elements (21)

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Figure 11

Axially compressed double unimorph piezoelectric actuator (22)

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Figure 12

PBP/DEAS actuator element (24-25)

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Figure 13

Schematic representation of facing sheet engagement and definitions (25)

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Figure 14

Stiffening effect due to DEAS in PBP actuator element

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Figure 15

Increase in design space by switching from plain bimorph piezoelectric actuator to PBP bimorph actuator

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Figure 16

The active experimental device: placement of the MFC actuators (left) and the assembled device in experimental test fixture (right) (27)

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Figure 17

Experimental setup for PBP snap-through experiment (32)

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Figure 18

Application of PBP flight control actuators (14)

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Figure 19

Subscale UAV employing PBP actuated morphing panels (38)

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Figure 20

PBP actuated synthetic jet (39)

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Figure 21

PBP actuated flight control surface for micro aerial vehicle (41)

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Figure 22

PBP/DEAS experimental test article actuator core and assembly into aeroshell (42)




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