Piezoelectric Transducer Actuated Leading Edge De-Icing with Simultaneous Shear and Impulse Forces

Venna, Suresh V.; Lin, Yueh‐Jaw; Botura, Galdemir

doi:10.2514/1.23996

Cited by 81 publications

(43 citation statements)

References 11 publications

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“…In this context, systems for aircraft ice protection using piezoelectric actuators represent a practical solution that do not require large currents with long rise times. [16][17][18] However, the piezoelectric systems developed for deicing to date are either unable to reliably deice the affected surface for atmospheric icing conditions at very low temperatures, 17 or have to face the problem of ineffective removal of continuous ice accretions around the leading edge that are held against the leading edge by aerodynamic forces even though the ice has already been mechanically separated from the surface. 16…”

Section: B Low-power Consuming Piezoelectric Deicing Systemsmentioning

confidence: 99%

Feasibility Study of a Hybrid Ice Protection System

Strobl

Storm

Thompson

et al. 2014

6th AIAA Atmospheric and Space Environments Conference

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A key design factor impacting the utilization of electrical power to drive aircraft systems and subsystems is energy efficiency. With the design of an all-electric, hybrid ice protection system, energy consumption can be reduced to a large extent. The hybridization is achieved through an intentional partitioning of the ice at the stagnation line by melting via surface heating and ice shedding in the unheated regions of the airfoil surface via an electromechanical deicing system based on piezoelectric multilayer actuators. In addition, to reduce energy consumption, the adhesion forces between the ice and the airfoil surface can be reduced using an ultrasmooth, nanostructured surface with water and ice repellent properties that encourages ice shedding. Experimental investigations, performed in a laboratory-scale icing wind tunnel for a small-scale system configuration, reveal that the hybrid approach for ice protection reliably sheds the ice accreted on the airfoil surface. Compared to conventional state-of-the-art systems for ice protection, the hybrid approach is able to reduce power consumption up to 95 %. Beyond the laboratory tests, numerical simulations of the hybrid strategy analogous to the one used for the experiments are performed. The time history of the residual ice shapes aft of the heated region are simulated using the ice accretion prediction software LEWICE2D for a wet-running anti-icing subsystem. Finite element analyses of the effects of the piezoelectric actuators are then performed using Abaqus to investigate the ice shedding capability in the unheated regions of airfoil surface. It is shown that the variation in the thickness of the different ice shapes affects the stiffness of the model, and the ice shedding capability, respectively. Simulation results correlate well with experimental results obtained with the icing wind tunnel. It can be concluded that reliable operation of the hybrid system for ice shedding can be guaranteed when using a harmonic sweep excitation able to excite the structure at its resonance. NomenclatureA = surface area α = mass proportional Rayleigh damping coefficient β = stiffness proportional Rayleigh damping coefficient C3D8E = 8-node three-dimensional linear piezoelectric brick elements C3D8R = 8-node three-dimensional linear brick elements EDM = electro-discharge machining f = frequency FEA = finite element analysis 2 IPS = ice protection system LWC = liquid water content MVD = median volume diameter NACA = National Advisory Committee for Aeronautics p d = power density q = heater density Q m = mechanical quality factor R a = arithmetic mean value of surface roughness SEM = scanning electron microscope T = air temperature  = shear stress V air = velocity of the airstream Subscripts exp = experimental FEA = finite element analysis heater = carbon fiber cord heater int = interface n = natural piezo = piezoelectric st = static condition surf_ice = surface of the ice tot = total condition

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Section: B Low-power Consuming Piezoelectric Deicing Systemsmentioning

confidence: 99%

Feasibility Study of a Hybrid Ice Protection System

Strobl

Storm

Thompson

et al. 2014

6th AIAA Atmospheric and Space Environments Conference

View full text Add to dashboard Cite

show abstract

“…Therefore they have the potential for removing ice accumulated on different surfaces. For example, Venna et al [7] applied ultrasonic waves of 1 kHz frequency on an aluminium airfoil structure which matched its resonance frequency and de-iced the airfoil. They could manage to shed off the ice 130 s after excitation of piezoelectric excitation patches.…”

Section: Introductionmentioning

confidence: 98%

A dual de-icing system for wind turbine blades combining high-power ultrasonic guided waves and low-frequency forced vibrations

et al. 2015

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a b s t r a c tWind turbines mounted on cold climate sites are subject to icing which could significantly influence the performance of the turbine blades for harvesting wind energy. In this study, an innovative dual de-icing system under development is described. This either prevents ice accumulation (anti-icing) or removes any ice layer present on the surface of the blade material (de-icing). A modelling study on ultrasonic guided waves propagating in composite blades was used to determine the optimal frequency and location of the transducers for ensuring wave propagation, causing the required level of energy concentration and resulting shear stress across the leading edge of the turbine's blade. In parallel, the effects of low frequency vibrations have been investigated through modal and harmonic analyses. This allowed specification and optimisation of the positioning of shaker(s), together with the magnitude and direction of harmonic forces required to induce sufficient acceleration to the blade surface for ice removal. An appropriate survey was also carried out to evaluate the potential for fatigue failure of the blade due to harmonic forces induced by shakers. The proposed technique configures and presents an active solution for the icing problem, allowing safe and reliable operation of wind turbines in adverse weather conditions.

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“…Smart materials, such as macro-fiber composites (MFCs), piezoceramics, and shape memory alloys (SMAs), have been employed for a diverse array of applications including vibration and shape control [1], energy harvesting [2], aircraft deicing [3], and flight control [4 -9]. Macro-fiber composites [10], pictured in Figure 1.1, are manufactured as thin sheets composed of piezoceramic fibers and polyimide electrodes held together in an epoxy matrix.…”

Section: Introductionmentioning

confidence: 99%

Design, characterization, and testing of macro-fiber composite actuators for integration on a fixed-wing UAV

Prazenica¹,

Kim²,

Moncayo³

et al. 2014

SPIE Proceedings

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Smart materials offer several potential advantages for UAV flight control applications compared to traditional servo actuators. One important benefit is that smart materials are lightweight and can be embedded directly into the structure of a wing or control surface. Therefore, they can reduce the overall weight of the vehicle and eliminate the need for mechanical appendages that may compromise the form factor of the wing, benefits that become more significant as the size of the vehicle decreases. In addition, smart materials can be used to realize continuous camber change of aerodynamic surfaces. Such designs offer improved aerodynamic efficiency compared to the discontinuous deflections of traditional hinged control surfaces driven by servo actuators. In the research discussed in this paper, macro-fiber composite (MFC) aileron actuators are designed for implementation on a medium-scale, fixed-wing UAV in order to achieve roll control. Macro-fiber composites, which consist of piezoceramic fibers and electrodes embedded in an epoxy matrix, are an attractive choice for UAV actuation because they are manufactured as lightweight, thin sheets and, when implemented as bending actuators, can provide both large structural deflections and high bandwidth. In this study, several MFC aileron actuator designs were evaluated through a combination of theoretical and experimental analysis. The current design consists of glass fiber composite ailerons with two unimorph MFC actuators embedded in each aileron to produce upward deflection. Wind tunnel test results are presented to assess the changes in lift and drag coefficients for different levels of MFC aileron actuation. Preparations for open-loop flight testing using a Skywalker UAV with MFC ailerons are also discussed. In addition, the development of a closed-loop, autonomous flight control system for the Skywalker is overviewed in preparation for conducting simulations and flight testing of an autonomous Skywalker with MFC aileron actuators.

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Piezoelectric Transducer Actuated Leading Edge De-Icing with Simultaneous Shear and Impulse Forces

Cited by 81 publications

References 11 publications

Feasibility Study of a Hybrid Ice Protection System

Feasibility Study of a Hybrid Ice Protection System

A dual de-icing system for wind turbine blades combining high-power ultrasonic guided waves and low-frequency forced vibrations

Design, characterization, and testing of macro-fiber composite actuators for integration on a fixed-wing UAV

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