&lt;title&gt;DARPA/ARFL/NASA Smart Wing second wind tunnel test results&lt;/title&gt;

Scherer, Lewis B.; Martin, Chris; West, Mark N.; Florance, James R.; Wieseman, Carol D.; Burner, A. W.; Fleming, Gary A.

doi:10.1117/12.351563

Cited by 13 publications

(14 citation statements)

References 4 publications

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“…This is comparable to the lift increases seen by other researchers. Scherer, et al [17], for instance, achieved a Dc l that ranged from 0.03 to 0.09, based on SMA-actuated trailing edge deflections. However, the achieved Dc l is considerably less than the Dc l predicted by the numerical models.…”

Section: Discussionmentioning

confidence: 99%

<title>Fabrication and testing of a shape memory alloy actuated reconfigurable wing</title>

Strelec

Lagoudas

2002

SPIE Proceedings

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The unique thermal and mechanical properties exhibited by shape memory alloys (SMAs) present exciting design possibilities in the field of aerospace engineering. When properly trained, SMA wires act as linear actuators by contracting when heated and returning to their original shape when cooled. These SMA wire actuators can be attached to points on the inside of an airfoil, and can be activated to alter the shape of the airfoil. This shape-change can effectively increase the efficiency of a wing in flight at several different flow regimes. Design optimization has previously been conducted to determine the placement of actuators within the reconfigurable airfoil. A wind tunnel model reconfigurable wing was fabricated based on the design optimization to verify the predicted structural and aerodynamic response. Wind tunnel tests indicated an increase in lift for a given flow velocity and angle of attack by activating the SMA wire actuators. The pressure data taken during the wind tunnel tests followed the trends expected from the numerical pressure results.

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Section: Discussionmentioning

confidence: 99%

<title>Fabrication and testing of a shape memory alloy actuated reconfigurable wing</title>

Strelec

Lagoudas

2002

SPIE Proceedings

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“…Phase I of the program produced a 16 percent scale F18-E/F planform Smart Wing with embedded SMAs to actuate seamless trailing edge control surfaces 6 and generate wing twist 7 . The Smart Wing underwent two series of wind tunnel tests in the NASA Langley (LaRC) Transonic Dynamics Tunnel; the first in May, 1996 8 , and the second in July, 1998 9 . Accurate, in-situ measurement of the Smart Wing shape and deformation during these developmental wind tunnel tests was critical in understanding relationships between control surface actuation and aerodynamic reaction.…”

Section: Introductionmentioning

confidence: 99%

“…The external measurement techniques, however, proved to be more accurate and reliable. 9 A LaRC-developed optical Video Model Deformation (VMD) system based on single camera / single view photogrammetry was used as the primary Smart Wing deformation measurement tool during both wind tunnel entries. A single component Projection Moiré Interferometry (PMI) system with full field measurement capability was also used during the second wind tunnel entry to complement the more accurate VMD system.…”

Section: Introductionmentioning

confidence: 99%

<title>Deformation measurements of smart aerodynamic surfaces</title>

Fleming

Burner

1999

Optical Diagnostics for Fluids/Heat/Combustion and Photomechanics for Solids

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Video Model Deformation (VMD) and Projection Moiré Interferometry (PMI) were used to acquire wind tunnel model deformation measurements of the Northrop Grumman-built Smart Wing tested in the NASA Langley Transonic Dynamics Tunnel. The F18-E/F planform Smart Wing was outfitted with embedded shape memory alloys to actuate a seamless trailing edge aileron and flap, and an embedded torque tube to generate wing twist. The VMD system was used to obtain highly accurate deformation measurements at three spanwise locations along the main body of the wing, and at spanwise locations on the flap and aileron. The PMI system was used to obtain full-field wing shape and deformation measurements over the entire wing lower surface. Although less accurate than the VMD system, the PMI system revealed deformations occurring between VMD target rows indistinguishable by VMD. This paper presents the VMD and PMI techniques and discusses their application in the Smart Wing test.

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“…As such, more effective placement strategies along the leading edge were investigated to provide robust control. Similar to this approach are techniques using smart materials to create large scale deflections that would replace control surfaces [12], [20], [6].…”

Section: Modelling and Control Of Morphing Wingmentioning

confidence: 99%

“…These aeroelastic deformations then are used to decrease drag, reduce maneuver loads, and reduce weight of the aircraft. The AAW project has been applied to a F-18 testbed and has demonstrated that it is able to show improvements in performance and aeroelastic deformation with minimal control effort (when compared to a method such as [12], [20], [6]). However, in this instance the objective is not flight control but performance improvement.…”

Section: Modelling and Control Of Morphing Wingmentioning

confidence: 99%

Modeling and control of a morphing airfoil structure

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<title>DARPA/ARFL/NASA Smart Wing second wind tunnel test results</title>

Cited by 13 publications

References 4 publications

<title>Fabrication and testing of a shape memory alloy actuated reconfigurable wing</title>

<title>Fabrication and testing of a shape memory alloy actuated reconfigurable wing</title>

<title>Deformation measurements of smart aerodynamic surfaces</title>

Modeling and control of a morphing airfoil structure

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