&lt;title&gt;Controlled aeroelastic response and airfoil shaping using adaptive materials and integrated systems&lt;/title&gt;

Jennifer, L Pinkerton; Anna-Maria, R McGowan; Robert, W Moses; Robert, Carl; Heeg, Jennifer

doi:10.1117/12.239019

Cited by 13 publications

(8 citation statements)

References 11 publications

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“…Different approaches span the range of mechanical actuation techniques. [12][13][14][15][16][17][18][19][20][21][22][23][24][25][26] Since we are interested in µAVs which are small and light, a natural choice for our wings is the use of piezoelectric actuation. There have been several other attempts to influence flow over surfaces using piezoelectric devices.…”

Section: Adaptive Wingsmentioning

confidence: 99%

Active control of separation on a wing with conformal camber

Munday

Jacob

2001

39th Aerospace Sciences Meeting and Exhibit

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A preliminary investigation of a wing with a conformal camber is discussed. The wing uses an adaptive actuator mounted internally to alter the shape of the suction surface which results in a change in the effective camber by increasing the maximum thickness and moving the location of maximum thickness aft. Since the actuator motion can be altered continuously, this allows the wing shape to be either static or dynamic. For the static mode, effects of profile perturbations are tested in a wind tunnel and tow tank to determine the change in wing efficiency due to variations in the camber at low Reynolds number. Various actuator locations and frequencies are tested from Re = 2.5 · 10 4 to Re = 2 · 10 5 at varying angles of attack. Preliminary comparisons are made with numerical predictions to demonstrate the effect of adaptive wing shaping on flight performance and the difficulty of predicting separated flow at low Re. For the dynamic mode, a wing with 5 modular span-wise sections each with a separately controlled internal actuator was constructed. The dynamic effects are currently being examined.

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Section: Adaptive Wingsmentioning

confidence: 99%

Active control of separation on a wing with conformal camber

Munday

Jacob

2001

39th Aerospace Sciences Meeting and Exhibit

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“…Thus began the active control era [8]. However, as demonstrated in [9], there are many drawbacks when using primary flight controls for auxiliary purposes.…”

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confidence: 99%

Flight Envelope Expansion Via Piezoelectric Actuation Receptance Method and Time-delayed Feedback Control

Enciu¹,

Informatics²

2019

IJMO

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In aerodynamics, the phenomenon of flutter suppression represents a great challenge. Since it is a complex and difficult process, it requires an innovative approach. In this paper, a V-shaped piezoelectric actuator whose role is to widen the aircraft flight envelope by raising the speed limit at which flutter occurs is presented. The demonstrator is in fact an intelligent model of wing, which is itself a control system, with sensors, piezo actuator and an implemented control law. The control law is obtained through the receptance method of eigenvalues assignment using the measured transfer function. The content of the paper refers to technical solutions for wing model design and to experimental results in subsonic wind tunnel. Another contribution of the paper concern the consideration of a time-delayed feedback control.

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“…These shapes produce different performance characteristics as well as require specially built mechanisms so that the pieces can be used at their optimum mode. The curvature of the THUNDER™ devices has advantages in some applications such as the matching of wing or antenna contours 8,9 . Details concerning the modeling of the final actuator shape as a function of manufacturing conditions is summarized in reference 10.…”

Section: Typical Thunder™ Configurationsmentioning

confidence: 99%

Evaluation criteria for THUNDER actuators

et al. 1999

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THUNDER™ (thin-layer composite unimorph ferroelectric driver and sensor) represents a new class of piezoceramicbased actuators capable of generating significant displacements and forces in response to input voltages. The performance capabilities of THUNDER™ actuators are due to the component materials and process used in their construction. A typical THUNDER™ actuator is composed of metallic backing materials (e.g., aluminum or stainless steel), a piezoceramic wafer, and adhesive in spray or film form. The materials are bonded under high pressures and temperatures and then cooled to room temperature after the adhesive has solidified. Due to the prestresses which result from the differing thermal properties of the component materials under cooling, the actuator is highly durable with respect to mechanical impacts and voltage levels. As a result of this construction, voltages in excess of 800 V can be applied to new actuator models without causing damage. This provides the actuators with significant displacement and force capabilities. In this paper, we discuss the development of evaluation criteria which are suitable for characterizing the actuator capabilities and provide a legitimate methodology for comparing THUNDER™ properties with those of other smart material actuators. For example, the concept of blocked force is often used to quantify the force capabilities of an actuator. However, due to the inherent curvature and mode of operation, standard techniques for measuring blocked forces are inappropriate for THUNDER™ actuators. Furthermore, changing operating conditions, frequency, etc., often make blocked force measurements ambiguous. We will discuss techniques for evaluating THUNDER™ properties in a manner which limits such ambiguities when comparing with other smart materials. We note that the evaluation issues discussed here are germane to a variety of high performance smart material transducers.

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<title>Controlled aeroelastic response and airfoil shaping using adaptive materials and integrated systems</title>

Cited by 13 publications

References 11 publications

Active control of separation on a wing with conformal camber

Active control of separation on a wing with conformal camber

Flight Envelope Expansion Via Piezoelectric Actuation Receptance Method and Time-delayed Feedback Control

Evaluation criteria for THUNDER actuators

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