Simulation of the Electroimpulse De-Icing Process of Aircraft Wings

In this work we propose to model ice shedding by an innovative paradigm that is based on cartesian grids, penalization and level sets. The use of cartesian grids bypass the meshing issue in complex geometries and moreover allows extensions to higher order accuracy in a natural and simple way. Penalization is an efficient alternative to explicitly impose boundary conditions so that the body fitted meshes can be avoided, making multi fluid/multi physics flows easy to set up and simulate. Level sets describe the geometry in a non-parametric way so that geometrical and topological changes due to physics and in particular ice-shedding are straight forward to follow.

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“…One possible model is the failure criterion proposed by Labeas et al 13 The model is based on both normal σ and shear τ interface stresses:…”

Section: Ice Shedding Lawmentioning

confidence: 99%

Simulation of Ice Shedding Around an Airfoil

Beaugendre

Morency

Gallizio³

2010

AIAA Atmospheric and Space Environments Conference

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“…However this modeling approach, restricted by early computer systems, cannot calculate exact stresses, which results in deviation to measured results. Labeas et al 12 have published an advanced methodology for numerical simulations of the de-icing process. Normal and shear interface stresses of ice and leading edge skin can be determined more precisely by three-dimensional elements and a debonding criterion is used for simulations of a nonlinear de-icing process.…”

Section: Introductionmentioning

confidence: 99%

Coupled Magnetic and Structural Numerical Simulation and Experimental Validation of the Electro Impulse De-Icing

Moehle

Haupt

Horst

2013

54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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The Electro Impulse De-Icing system is an alternative process of deicing wing slat structures made of carbon fiber reinforced plastics or aluminum. It is especially qualified for no-bleed systems that are used in modern and future aircraft. Due to the time dependent interactions between the induced magnetic field and the structural deformation it can be necessary to couple these physical fields in analyses. This paper presents a threedimensional simulation as well as experiments of flat plates. The simulation is characterized by electrical and structural finite element calculations, which are two-way coupled in each time step. The current progress is based on real tests which are executed at a special test rig. A coil, which is connected to an impulse generator, is used to induce magnetic forces. Flat plates of aluminum or carbon reinforced plastics (with an additional aluminum doubler) were tested at room temperature and deformation results were used to validate numerical simulations. Further research deals with the simulation of the deicing process itself with a stress criterion for ice adhesion. Therefore, the test rig is mounted in a cooling chamber. The ice layer is produced by spraying cooled water through a nozzle with a droplet size of supercooled large droplets (SLD). The deformation progress with and without ice is analyzed at different impulse forces and ice thicknesses. The coupled finite element analysis gives the opportunity to simulate the process of de-icing in-situ to the time dependent loading of the plate by magnetic forces. Furthermore the complex dynamic behavior of the structure can be simulated with excellent agreement to real tests.

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“…Electro-mechanical protection systems are able to flex the thin outer skin of the wing to remove the ice build-up. This can be achieved by the generation of (i) small high frequency vibrations using ultrasonic exciters 4 or (ii) larger low frequency deformations initiated by electro-magnets positioned under the wing skin 3,5 . Other methods of actuation such as piezoelectric transducers have also been demonstrated 6 .…”

Section: Introductionmentioning

confidence: 99%

Actuation of Bistable Laminates by Conductive Polymer Nanocomposites for use in Thermal-Mechanical Aerosurface De-icing Systems

Brampton¹,

Bowen

Buschhorn

et al. 2014

55th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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This paper considers a novel electro-thermal system combining aligned carbon nanotubes (A-CNT) as a resistive heater and bistable laminates. The use of A-CNT heaters to actuate bistable laminates is characterized in terms of steady-state shape as a function of applied voltage to the heating element and the transient response of the laminate to heating. Snap-through from one stable state to another was successfully achieved with a linear relationshiop between laminate curvature and applied voltage up to the snap-through event. Thermal actuation of a bistable wing skin has the potential for an efficient multifunctional thermo-mechanical ice protection system (IPS); using heat to address anti-and de-icing, and secondly using thermal actuation of the bistable laminate to deform or mechanically disturb the skin to initiate debond of the ice-skin interface. Nomenclature V= applied voltage I = current P = power T = temperature

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Simulation of the Electroimpulse De-Icing Process of Aircraft Wings

Cited by 46 publications

References 5 publications

Simulation of Ice Shedding Around an Airfoil

Simulation of Ice Shedding Around an Airfoil

Coupled Magnetic and Structural Numerical Simulation and Experimental Validation of the Electro Impulse De-Icing

Actuation of Bistable Laminates by Conductive Polymer Nanocomposites for use in Thermal-Mechanical Aerosurface De-icing Systems

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