A model based feedback controller for wing-twist via piezoceramic actuation

Ray, Cody W.; Batten, Belinda A.; Singler, John R.

doi:10.1109/acc.2011.5991258

Cited by 3 publications

(1 citation statement)

References 24 publications

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“…Lim et al 24 described their design in which the trailing edges of the wing sections are controlled by lightweight piezo-composite actuators (LIPCA), while Yudi et al 25 realized the design and demonstration of a small expandable morphing wing based on two actuators to modify its camber. Incorporating a bioinspired flexible wing, Ray et al utilized a model with piezoceramic actuators 26 . Using these piezoceramic actuators, they showed the effectiveness of model-based feedback control in obtaining a desired wing tip position.…”

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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Sensor placement for flexible wing shape control

Ray

Batten

2012

2012 American Control Conference (ACC)

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In a series of recent papers, shape control of a flexible plate through piezoceramic actuation has been presented. In that work, full-state feedback was assumed. In this paper, we move to sensor placement for design of an observer. Piezoceramic actuators and sensors for strain and velocity will be used. We will compare the performance of three systems: one with a distribution of sensors based on predictions of high strain regions based on elasticity theory; another with sensors placed manually based on bending gain features; and a third with sensors placed using the centroidal Voronoi tesselation with functional gains as placement weights. We compare the effectiveness of the systems in achieving a desired tip position in the presence of disturbances.

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