&lt;title&gt;Development of high-rate large-deflection hingeless trailing-edge control surface for the Smart Wing wind tunnel model&lt;/title&gt;

Wang, Donny P.; Bartley-Cho, Jonathan D.; Martin, Christopher; Hallam, Brian J.

doi:10.1117/12.429682

Cited by 30 publications

(20 citation statements)

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“…Wang et al 22 , in the Smart Wing 2 program of DARPA, developed a high-rate, large deflection, hinge less trailing edge control surface for the smart wing model. The model consisted of distributed piezoelectric stack actuators with and without hydraulic amplifiers and pumps, as well as aggressive tendon actuation, and "eccentuation".…”

Section: Introductionmentioning

confidence: 99%

Control validation of a morphing wing in an open loop architecture

Kammegne

Nguyen

Botez

et al. 2015

AIAA Modeling and Simulation Technologies Conference

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Aircraft wings are generally designed and optimized to give the best possible performance for cruise flight conditions. Using conventional control surfaces such as flaps, ailerons, variable wing sweep and spoilers, the structure of aircraft wings is changed for other flight conditions. With the introduction of wing morphing, the flow over an aircraft's wings can be modified locally to improve the overall wing and aircraft performance during the different flight steps. The goal of this research work is to develop an actuation control principle using a grid consisting of four similar miniature electromechanical actuators for a new morphing wing mechanism. The actuators modify the flexible upper surface of the wing so that the upper flow is modified and consequently the transition point from laminar to turbulence is delayed. The flexible upper wing surface is closed to the wing tip, while the skin is made of composite materials. The first actuation line is located at 32% and the second actuation line is at 48% of the chord. The actuators are fixed on the wing ribs and the top is attached to the flexible skin with screws. A database that relates the actuator displacements and the optimized skin is tailored for different flight conditions. A smart controller based fuzzy logic is designed to control the position of the actuator in real time so that the desired optimized skin corresponding to the desired displacements is obtained and maintained during the flight tests. The feasibility and the effectiveness of the control method are demonstrated experimentally. Nomenclature M = Mach number AoA = Angle of attack β = Deflection angle

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Section: Introductionmentioning

confidence: 99%

Control validation of a morphing wing in an open loop architecture

Kammegne

Nguyen

Botez

et al. 2015

AIAA Modeling and Simulation Technologies Conference

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“…An alternative to this approach is represented by the use of piezoelectric active fibers as embedded actuator layers in the composite layup (Wilkie et al, 1999;Cesnik and Shin, 2001;Ghiringhelli et al, 2001). The use of piezoelectric motors to drive the deflection of a flexible, hingeless control surface using an embedded mechanism has also been analyzed (Wang et al, 2001). While this approach is capable of generating large deflections and does not require continuous application of control voltage to maintain the given deflection, it is however characterized by low bandwidth and complexity.…”

Section: Introductionmentioning

confidence: 99%

Modeling and Analysis of Active Flap Using Coiled Bender Piezoelectric Actuators

Vasilescu

Dancila

2004

Journal of Intelligent Material Systems and Structures

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The applicability and effectiveness of three novel piezoelectric coiled bender actuators to deflect a plain trailing edge flap on a straight wing in the presence of incompressible flow airloads is investigated in this paper through analytical modeling. This work builds upon previous research in which the three actuator configurations, the linear spiral type, the helicoidal type, and the hybrid type, have been proposed and analytically modeled, and the first two configurations have been experimentally validated. A simple analytical model for the piezoelectrically actuated flap is developed and used for this investigation. Results show that the use of coiled piezoelectric actuators for flap deflection is an effective approach. The variation of flap deflection angles with applied actuation voltage and wing angle of attack is also shown, together with performance envelopes.

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“…The ACS can be used as active truss members, struts in Stewart and modified Stewart platforms [42,43], etc. The ACP can be incorporated as active members within space and aerospace structures such as micro-aerial-vehicles, MAV, [44], airplane wings [45][46][47], smart tails [48], helicopter blades, active panels [49][50][51], and strut housing [19,20,52]. These active members may have a dual role with both active vibration suppression and precision positioning capabilities.…”

Section: Problem Statementmentioning

confidence: 99%

Finite Element Method for Active Vibration Suppression of Smart Composite Structures using Piezoelectric Materials

Ghasemi‐Nejhad

Pourjalali²,

Uyema³

et al. 2006

Journal of Thermoplastic Composite Materials

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Adaptive or intelligent structures which have the capability for sensing and responding to their environment promise a novel approach to satisfy the stringent performance requirements of future space missions. Analytical, numerical, and experimental results are employed to verify the performance of piezoelectric stacks and patches as well as to determine the natural frequencies of typical strut and panel structures. A strut model with a piezoelectric stack actuator for axial vibration suppression and a composite beam with surface-mounted piezoelectric patch actuator for lateral vibration suppression are considered to model an active composite strut (ACS) and an active composite panel (ACP), respectively. These ACS and ACP are employed to develop an actuator optimum voltage (OV) for active vibration suppression using modal, harmonic, and transient finite element analyses for a range of frequency encompassing a natural frequency. The ACP model demonstrates that the actuator vibration suppression capability depends on the modal shape and location of the actuator. The OV, in this work, is determined by increasing the level of actuator voltage gradually and generating a vibration with same frequencies as the external vibration but 180 out-of-phase, and observing the increasing level of active vibration suppression until an optimum/threshold actuator voltage is reached. agreements. This work also presents a systematic guideline for the use of piezoelectric stack and monolithic patch smart materials in intelligent structures using the finite element method.KEY WORDS: active vibration suppression, smart composite structures, piezoelectric stacks and patches, finite element analysis, actuator optimum voltage, active composite struts and panels, axial and lateral vibration, actuator location effects.

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<title>Development of high-rate large-deflection hingeless trailing-edge control surface for the Smart Wing wind tunnel model</title>

Cited by 30 publications

References 0 publications

Control validation of a morphing wing in an open loop architecture

Control validation of a morphing wing in an open loop architecture

Modeling and Analysis of Active Flap Using Coiled Bender Piezoelectric Actuators

Finite Element Method for Active Vibration Suppression of Smart Composite Structures using Piezoelectric Materials

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