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Research Papers

Design of Shape Memory Alloy Actuators for Morphing Laminar Wing With Flexible Extrados

[+] Author and Article Information
Thomas Georges

Department of Mechanical Engineering, École de Technologie Supérieure (ETS), 1100 Notre-Dame Street West, Montréal, QC H3C 1K3, Canadathomas.georges.1@ens.etsmtl.ca

Vladimir Brailovski

Department of Mechanical Engineering, École de Technologie Supérieure (ETS), 1100 Notre-Dame Street West, Montréal, QC H3C 1K3, Canadavbrailovski@mec.etsmtl.ca

Emeric Morellon

Department of Mechanical Engineering, École de Technologie Supérieure (ETS), 1100 Notre-Dame Street West, Montréal, QC H3C 1K3, Canadaemeric.morellon@gadz.org

Daniel Coutu

Department of Mechanical Engineering, École de Technologie Supérieure (ETS), 1100 Notre-Dame Street West, Montréal, QC H3C 1K3, Canadadaniel.coutu.4@ens.etsmtl.ca

Patrick Terriault

Department of Mechanical Engineering, École de Technologie Supérieure (ETS), 1100 Notre-Dame Street West, Montréal, QC H3C 1K3, Canadapatrick.terriault@etsmtl.ca

J. Mech. Des 131(9), 091006 (Aug 18, 2009) (9 pages) doi:10.1115/1.3160310 History: Received December 01, 2008; Revised May 27, 2009; Published August 18, 2009

An active structure of a morphing wing designed for subsonic cruise flight conditions is composed of three principal subsystems: (1) flexible extrados, (2) rigid intrados, and (3) an actuator group located inside the wing box. The four-ply laminated composite flexible extrados is powered by two individually controlled shape memory alloy (SMA) actuators. Fulfilling the requirements imposed by the morphing wing application to the force-displacement characteristics of the actuators, a novel design methodology to determine the geometry of the SMA active elements and their adequate assembly conditions is presented. This methodology uses the results of the constrained recovery testing of the selected SMA. Using a prototype of the morphing laminar wing powered by SMA actuators, the design approach proposed in this study is experimentally validated.

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Copyright © 2009 by American Society of Mechanical Engineers
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Figures

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Figure 1

Conceptual design of the morphing laminar wing

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Figure 2

Actuators and flexible extrados

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Figure 3

Force-displacement characteristics of the four-ply-two-actuator active structure for 49 benchmark flow cases: (a) Actuator 1, (b) Actuator 2, and (c) Actuators 1 and 2 (10)

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Figure 4

Schematic representation and simplified mechanical models of the actuator in (a) nominal extrados position and (b) deployed extrados position

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Figure 5

Experimental testing bench for SMA characterization

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Figure 6

SMA design diagram (stress-strain space)

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Figure 7

SMA design diagram in strain-stress space with delimited actuation area

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Figure 8

Manufacturing setup of the flexible extrados (2)

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Figure 9

Schema of the flexible extrados testing bench

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Figure 10

Schema of the extrados testing bench for characterization of the flexible skin and the transmission system

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Figure 11

Force-displacement characteristics of the active structure (Actuator 1 is active and Actuator 2 is passive)

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Figure 12

Force-displacement characteristics of the gas spring (1000 N, Industrial Gas Spring Inc., PA)

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Figure 13

SMA design diagram for Actuator 1 (force-displacement space)

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