The Experts below are selected from a list of 282 Experts worldwide ranked by ideXlab platform
Lokman Bennani - One of the best experts on this subject based on the ideXlab platform.
-
Electromechanical resonant Ice Protection systems: numerical investigation through a phase-field mixed adhesive/brittle fracture model
Engineering Fracture Mechanics, 2020Co-Authors: Alexis Marbœuf, Lokman Bennani, Marc Budinger, Valérie Pommier-budingerAbstract:Abstract Electromechanical resonant de-icing systems provide a low-energy solution against Ice accumulation on aircraft. Recent researches show a growing interest towards these systems in the context of more electrical aircraft. Electromechanical de-icing systems consists in electric actuators producing stress within the Ice, through micro-vibrations of the surface to be protected, leading to bulk or adhesive failure and, ultimately, Ice shedding. The understanding of the mechanisms at play is of prime importance in order to design efficient Ice Protection systems. Despite a large number of studies in the literature, there is still a lack when dealing with fracture propagation phenomena in this context. In this work the authors propose a model based on the well established phase-field variational approach to fracture. The approach is applied to the study of crack propagation and debonding of Ice under the effect of an electromechanical resonant de-icing system. Numerical experiments are performed in order to assess possible Ice shedding mechanisms.
-
a survey of Icephobic coatings and their potential use in a hybrid coating active Ice Protection system for aerospace applications
Progress in Aerospace Sciences, 2019Co-Authors: Xiao Huang, Marc Budinger, Philippe Villedieu, Nick Tepylo, Valerie Pommierbudinger, Elmar Bonaccurso, Lokman BennaniAbstract:Icephobic coatings for aircraft and other surfaces subjected to Ice accretion have generated great interest in the past two decades, due to the advancement of nanomaterials, coating fabrication methods, biomimetics, and a more in-depth understanding of Ice nucleation and Ice adhesion. Icephobic coatings have demonstrated the ability to repel water droplets, delay Ice nucleation and significantly reduce Ice adhesion. Despite these ongoing research activities and promising results, the findings reported hereafter suggest that coatings alone cannot be used for aircraft anti-icing and de-icing operations; rather, they should be considered as a complementary option to either thermal or mechanical Ice Protection methods, for reducing power consumption and the ecological footprint of these active systems and for expediting ground de-icing operations. This paper will first review the state-of-the-art of Icephobic coatings for various applications, including their performance and existing deficiencies. The second part of this paper focuses on aerospace anti-icing and de-icing requirements and the need for hybrid systems to provide a complete Ice Protection solution. Lastly, several urgent issues facing further development in the field are discussed.
-
A survey of Icephobic coatings and their potential use in a hybrid coating/active Ice Protection system for aerospace applications
Progress in Aerospace Sciences, 2019Co-Authors: Xiao Huang, Valérie Pommier-budinger, Marc Budinger, Philippe Villedieu, Nick Tepylo, Elmar Bonaccurso, Lokman BennaniAbstract:Icephobic coatings for aircraft and other surfaces subjected to Ice accretion have generated great interest in the past two decades, due to the advancement of nanomaterials, coating fabrication methods, biomimetics, and a more in-depth understanding of Ice nucleation and Ice adhesion. Icephobic coatings have demonstrated the ability to repel water droplets, delay Ice nucleation and significantly reduce Ice adhesion. Despite these ongoing research activities and promising results, the findings reported hereafter suggest that coatings alone cannot be used for aircraft anti-icing and de-icing operations; rather, they should be considered as a complementary option to either thermal or mechanical Ice Protection methods, for reducing power consumption and the ecological footprint of these active systems and for expediting ground de-icing operations. This paper will first review the state-of-the-art of Icephobic coatings for various applications, including their performance and existing deficiencies. The second part of this paper focuses on aerospace anti-icing and de-icing requirements and the need for hybrid systems to provide a complete Ice Protection solution. Lastly, several urgent issues facing further development in the field are discussed.
-
Electromechanical Resonant Ice Protection Systems: Analysis of Fracture Propagation Mechanisms
AIAA Journal, 2018Co-Authors: Marc Budinger, Valérie Pommier-budinger, Lokman Bennani, Elmar Bonaccurso, Pierrick Rouset, Fabien DezitterAbstract:Recent research is showing growing interest in low-power electromechanical de-icing systems and, in particular, de-icing systems based on piezoelectric actuators. These systems use the vibrations generated by piezoelectric actuators at resonance frequencies to produce shear stress at the interface between the Ice and the support or to produce tensile stress in the Ice. This paper provides analytical and numerical models enabling a better understanding of the main de-icing mechanisms of resonant actuation systems. Different possible Ice shedding mechanisms involving cohesive and adhesive fractures are analyzed with an approach combining modal, stress and crack propagation analyses. Simple analytical models are proposed to better understand the effects on Ice shedding of the type of mode, Ice thickness, or frequency with respect to cohesive and adhesive fractures.
-
a robust coupling algorithm applied to thermal Ice Protection system unsteady modeling
6th AIAA Atmospheric and Space Environments Conference - AVIATION 2014, 2014Co-Authors: Remi Chauvin, Philippe Villedieu, Pierre Trontin, Lokman BennaniAbstract:The aim of the present paper is to propose a general methodology for the numerical modelling of both anti and de-icing systems. A lubrication model is used for dealing with the dynamics of the runback water film. As regards thermal effects, in order to take into account heat conduction and unsteadiness, a parabolic temperature profile is assumed with respect to the normal coordinate for the Ice layer. Heat transfers in the airfoil solid structure are described using a dedicated solver based on the unsteady heat conduction equation. The most original contribution of this work is the new technique (herein referred to as the "improved Schwarz method") which is proposed for coupling in a robust way the accretion-runback model and the solid heat conduction model. This new coupling algorithm allows to ensure fast convergence of both temperature and heat flux at the coupling interface (airfoil outer surface) and can be used either for steady state computations (anti-icing mode) or unsteady computations (de-icing mode). Numerical test cases which have been performed so far are very promising and show the relevance of this new approach for real applications and 3D extension.
Wagdi G Habashi - One of the best experts on this subject based on the ideXlab platform.
-
aero thermal optimization of in flight electro thermal Ice Protection systems in transient de icing mode
International Journal of Heat and Fluid Flow, 2015Co-Authors: Mahdi Pourbagian, Wagdi G HabashiAbstract:Abstract Even if electro-thermal Ice Protection systems (IPS) consume less energy when operating in de-icing mode than in anti-icing mode, they still need to be optimized for energy usage. The optimization, however, should also take into account the effect of the de-icing system on the aerodynamic performance. The present work offers an optimization framework in which both thermal and aerodynamic viewpoints are taken into account in formulating various objective and constraint functions by considering the energy consumption, the thickness, the volume, the shape and the location of the accreted Ice on the surface as the key parameters affecting the energy usage and the aerodynamic performance. The design variables include the power density and the activation time of the electric heating blankets. A derivative-free technique, called the mesh adaptive direct search (MADS) method, is used to carry out the optimization process, which would normally need a large number of unsteady conjugate heat transfer (CHT) calculations for the IPS simulation. To avoid such prohibitive computations, reduced-order modeling (ROM) is used to construct simplified low-dimensional CHT models. The approach is illustrated through several test cases, in which different combinations of objective and constraint functions, design variables and cycling sequence patterns are examined. In these test cases, the energy consumption is significantly reduced compared to the experiments by improving the spatial and temporal distribution of the thermal energy usage. The results show the benefits of the approach in bringing energy, safety and aerodynamic considerations together in designing de-icing systems.
-
Surrogate-Based Optimization of Electrothermal Wing Anti-Icing Systems
Journal of Aircraft, 2013Co-Authors: Pourbagian, Wagdi G HabashiAbstract:The optimization of electrothermal in-flight anti-icing systems is presented by introducing a general methodology. The optimization goal was to achieve an Ice-free area over the protected zone by using the lowest energy possible. The power and/or length of the electric pads are considered as design variables. The optimization procedure is performed via a derivative-free method that typically needs many objective-function evaluations. This would be impractical as aero-icing flow simulation remains computationally intensive when coupled with conjugate heat-transfer calculations, as in the case of Ice-Protection systems. The cost is even more prohibitive for an optimization process, as a large number of simulations are needed. To make it practical, this work presents a surrogate-based optimization approach using proper orthogonal decomposition, in conjunction with kriging. The results obtained show that the methodology is efficient and reliable in optimizing electrothermal Ice-Protection systems in particula...
-
On Optimal Design of Electro-Thermal In-Flight Ice Protection Systems
5th AIAA Atmospheric and Space Environments Conference, 2013Co-Authors: Pourbagian, Wagdi G HabashiAbstract:In-flight icing remains an aviation safety concern, with Ice Protection systems (IPS) being developed through experimental, empirical and numerical methods. Electro-thermal IPS have been receiving more attention in recent years in the context of the “more electric aircraft”. Experimental and numerical efforts are ongoing to understand the characteristics of these systems under different conditions. In the present study, based on computational fluid dynamics, an analysis of the energy requirements of IPS is first performed to achieve an insight into the operational characteristics of these systems through quantitative and qualitative assessments. The paper then presents various approaches for IPS optimization. The approaches are concerned with both defining suitable cost functions/constraints and applying proper optimization methods, including a pattern search method and an evolutionary algorithm.
-
cfd based optimization of electro thermal wing Ice Protection systems in de icing mode
51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, 2013Co-Authors: Mahdi Pourbagian, Wagdi G HabashiAbstract:Even if electro-thermal Ice Protection systems consume less energy operating in de-icing mode than in anti-icing mode, they still need to be optimized for energy usage. This paper defines suitable design variables, objective functions and constraints for such optimization. A derivative-free technique is used to carry out the optimization process, which normally needs a large number of unsteady conjugate heat transfer simulations. To avoid such prohibitive computations, reduced-order modeling (ROM) is used to construct a simplified low-dimensional model at each time step of the simulation. The approach is illustrated through test cases, showing its benefits in bringing energy and safety considerations together in designing de-icing systems.
-
Power and Design Optimization of Electro-Thermal Anti-Icing Systems via FENSAP-Ice
4th AIAA Atmospheric and Space Environments Conference, 2012Co-Authors: Pourbagian, Wagdi G Habashi, Bombardier-bell Helicopter-caeAbstract:A general methodology for the power and design optimization of electro-thermal in-flight anti-icing systems is presented. The optimization goal is to achieve an Ice-free area over the protected zone by using the lowest energy possible. The power and/or length of the electric pads are considered as design variables. The optimization procedure is performed via a derivative-free method that typically needs many objective function evaluations. This would be impractical as aero-icing flow simulation remains computationally intensive when coupled with conjugate heat transfer calculations, as in the case of Ice Protection systems. The cost is even more prohibitive for an optimization process, as a large number of simulations are needed. To make it practical, this work presents a surrogate-based optimization approach using proper orthogonal decomposition (POD), in conjunction with Kriging. The numerical results obtained for some optimization cases show the benefits of the methodology in substantially reducing the cost of high-fidelity optimization of electrothermal anti-icing systems, in particular, and other types of thermal-based Ice Protection systems, in general.
Tobias Strobl - One of the best experts on this subject based on the ideXlab platform.
-
Chapter 26 – Synergic Effects of Passive and Active Ice Protection Systems
Morphing Wing Technologies, 2018Co-Authors: Tobias Strobl, Stefan Storm, Salvatore AmeduriAbstract:Abstract Ice accretion on aerodynamic surfaces can catastrophically impact the safety of an aircraft; it leads to a sudden lift drop and a relevant drag rise, compromising the aircrafts flight capability. Typical Ice Protection systems (IPS) are either concurrently or alternately hampering the Ice accretion (anti-icing) or removing the Ice itself before it achieves a dangerous consistency (deicing). Thermoelectric-resistance, pneumatic, and mechanic-hydraulic IPSs are among the most common devIces currently implemented on aircraft. Those IPSs require a consistent amount of power and need sufficient room inside the leading edge, the critical wing zone for Ice Protection. For this reason, more and more research departments, aerospace industries and airline companies are devoting efforts worldwide to the study of Ice generation and growth phenomena, with the goal of developing safer, simpler, and cheaper IPSs. The work at hand focuses on three different IPS solutions and how they can be combined for energy-efficient Ice Protection. The first was a passive technique, implementing a nanostructured surface that reduces the actual wetted surface, thus limiting droplet adhesion. The other two were based on a forced heat transfer to hinder Ice formation on the leading edge at the stagnation line, and a mechanical devIce using piezoelectric actuators to induce Ice fragmentation aft of the heated zone. Combined, these devIces may need only limited electrical power. The design process used computational fluid dynamics (CFD) numerical tools to describe the Ice development and its interaction with the aerodynamic flow. In particular, the Ice melting due to thermoelectrical system action was modeled with its downstream motion, illustrating how the melting particles give rise to Ice reformation once they move far from the heated zone. The aerodynamic action necessary to ultimately produce Ice detachment in this region was then estimated; this information is used to size the piezoelectric actuator system, in terms of actuator thickness, extension, location, and excitation conditions. The Icephobic surface characteristics were defined to minimize the wet surface and facilitate the removal action of the aerodynamic and mechanical forces. Laboratory tests were carried out on a scaled airfoil model to estimate the adhesion strength of both rime and glazed Ice on both a conventional surface and on a nanostructured Icephobic surface. This parameter was used to set the numerical tools. Experiments were then conducted in a wind tunnel environment. There, the Ices behavior was observed from formation and throughout its evolution: from its melting at the stagnation point, the downstream movement of the resulting particles, and its reassembly, until its final removal via flow action. The results were compared with the theoretical predictions, appreciating and quantifying the combined action of the three elements of the energy-efficient IPS.
-
feasibility study of a hybrid Ice Protection system
Journal of Aircraft, 2015Co-Authors: Tobias Strobl, Stefan Storm, David Thompson, Mirko Hornung, Frank ThieleckeAbstract:A key design factor impacting the use 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. To further 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 configuration, reveal that the hybrid approach for Ice Protection reliably sheds the Ice accreted on the airfoil surface. Compared with an all-thermoelectric system for Ice p...
-
A Hybrid System for Ice Protection and Detection
2015Co-Authors: Tobias Strobl, Robert Adam, Ricardo EntzAbstract:A Hybrid System for Ice Protection and Detection Tobias Strobl (1), Robert Adam (2), Ricardo Entz (3) 1 : Airbus Group Innovations, Munich, 81663, Germany, Tobias.Strobl@airbus.com 2 : Airbus Group Innovations, Robert.Adam@airbus.com, 3 : Airbus Group Innovations, Ricardo.Entz@airbus.com Abstract Aircraft icing is considered a serious weather hazard during flight. Against the background of a more- electric aircraft, electro-thermal and -mechanical systems for Ice Protection are well-suited to remove in-flight Ice accretions from aircraft components. This effort intends to investigate the performance of a hybrid Ice Protection system for a small-scale configuration in a laboratory-size icing wind tunnel. The hybrid Ice Protection system is composed of a slender thermo-electric heating wire at the stagnation line, piezoelectric actuators in the unheated aft regions and a superhydrophobic surface with low Ice adhesion properties, which is applied in the leading edge area of the airfoil. The hybrid system is analyzed regarding its efficacy for shedding minimum thicknesses in Ice using a laser-scanning system. In addition, the extent to which the system is able to detect whether Ice is
-
feasibility study of a hybrid Ice Protection system based on passive removal of residual Ice
53rd AIAA Aerospace Sciences Meeting, 2015Co-Authors: Tobias Strobl, David Thompson, Mirko HornungAbstract:Aircraft icing is considered a serious weather hazard during flight. Against the background of a more-electric aircraft, electro-thermal systems for Ice Protection are wellsuited to remove in-flight Ice accretions from aircraft components. This effort intends to investigate the performance of a wet-running electro-thermal Ice Protection system and the extent to which surface coatings with low Ice adhesion properties enable passive, aerodynamically-induced Ice shedding. A heater systematically partitions the Ice accreted around the leading edge into an upper and a lower part by melting the Ice in the region near the stagnation line. The region of the airfoil aft of the heated region is treated to reduce the adhesion of the Ice to the surface and facilitate aerodynamically-induced Ice shedding. To demonstrate the feasibility of this approach, a prototype system is tested in a laboratoryscale icing wind tunnel. A numerical model of a NACA 0012 airfoil with a slender thermoelectric heater at the stagnation line is also studied. The aerodynamic forces acting on the residual Ice shapes are predicted using a computational fluid dynamics simulation. The resulting loads acting on the Ice shape are incorporated into a finite element analysis to determine if the stresses in the Ice shape produce delamination from the airfoil surface. The aerodynamic forces required to shed the Ice in the unheated area are numerically analyzed and compared to experimental data obtained in a laboratory-scale icing wind tunnel. It can be concluded from both the numerical simulations and the experimental investigations that, except for the warm and mushy glaze Ice cases, passive Ice shedding due to the aerodynamic forces of the airstream is obtained once the Ice layer is thick enough.
Marc Budinger - One of the best experts on this subject based on the ideXlab platform.
-
Electromechanical resonant Ice Protection systems: numerical investigation through a phase-field mixed adhesive/brittle fracture model
Engineering Fracture Mechanics, 2020Co-Authors: Alexis Marbœuf, Lokman Bennani, Marc Budinger, Valérie Pommier-budingerAbstract:Abstract Electromechanical resonant de-icing systems provide a low-energy solution against Ice accumulation on aircraft. Recent researches show a growing interest towards these systems in the context of more electrical aircraft. Electromechanical de-icing systems consists in electric actuators producing stress within the Ice, through micro-vibrations of the surface to be protected, leading to bulk or adhesive failure and, ultimately, Ice shedding. The understanding of the mechanisms at play is of prime importance in order to design efficient Ice Protection systems. Despite a large number of studies in the literature, there is still a lack when dealing with fracture propagation phenomena in this context. In this work the authors propose a model based on the well established phase-field variational approach to fracture. The approach is applied to the study of crack propagation and debonding of Ice under the effect of an electromechanical resonant de-icing system. Numerical experiments are performed in order to assess possible Ice shedding mechanisms.
-
a survey of Icephobic coatings and their potential use in a hybrid coating active Ice Protection system for aerospace applications
Progress in Aerospace Sciences, 2019Co-Authors: Xiao Huang, Marc Budinger, Philippe Villedieu, Nick Tepylo, Valerie Pommierbudinger, Elmar Bonaccurso, Lokman BennaniAbstract:Icephobic coatings for aircraft and other surfaces subjected to Ice accretion have generated great interest in the past two decades, due to the advancement of nanomaterials, coating fabrication methods, biomimetics, and a more in-depth understanding of Ice nucleation and Ice adhesion. Icephobic coatings have demonstrated the ability to repel water droplets, delay Ice nucleation and significantly reduce Ice adhesion. Despite these ongoing research activities and promising results, the findings reported hereafter suggest that coatings alone cannot be used for aircraft anti-icing and de-icing operations; rather, they should be considered as a complementary option to either thermal or mechanical Ice Protection methods, for reducing power consumption and the ecological footprint of these active systems and for expediting ground de-icing operations. This paper will first review the state-of-the-art of Icephobic coatings for various applications, including their performance and existing deficiencies. The second part of this paper focuses on aerospace anti-icing and de-icing requirements and the need for hybrid systems to provide a complete Ice Protection solution. Lastly, several urgent issues facing further development in the field are discussed.
-
A survey of Icephobic coatings and their potential use in a hybrid coating/active Ice Protection system for aerospace applications
Progress in Aerospace Sciences, 2019Co-Authors: Xiao Huang, Valérie Pommier-budinger, Marc Budinger, Philippe Villedieu, Nick Tepylo, Elmar Bonaccurso, Lokman BennaniAbstract:Icephobic coatings for aircraft and other surfaces subjected to Ice accretion have generated great interest in the past two decades, due to the advancement of nanomaterials, coating fabrication methods, biomimetics, and a more in-depth understanding of Ice nucleation and Ice adhesion. Icephobic coatings have demonstrated the ability to repel water droplets, delay Ice nucleation and significantly reduce Ice adhesion. Despite these ongoing research activities and promising results, the findings reported hereafter suggest that coatings alone cannot be used for aircraft anti-icing and de-icing operations; rather, they should be considered as a complementary option to either thermal or mechanical Ice Protection methods, for reducing power consumption and the ecological footprint of these active systems and for expediting ground de-icing operations. This paper will first review the state-of-the-art of Icephobic coatings for various applications, including their performance and existing deficiencies. The second part of this paper focuses on aerospace anti-icing and de-icing requirements and the need for hybrid systems to provide a complete Ice Protection solution. Lastly, several urgent issues facing further development in the field are discussed.
-
electro mechanical resonant Ice Protection systems initiation of fractures with piezoelectric actuators
AIAA Journal, 2018Co-Authors: Valerie Pommierbudinger, Marc Budinger, Pierrick Rouset, Fabien Dezitter, Florent Huet, Marc Wetterwald, Elmar BonaccursoAbstract:Recent research is showing growing interest in low-power electromechanical de-icing systems and, in particular, de-icing systems based on piezoelectric actuators. These systems use the vibrations generated by piezoelectric actuators at resonance frequencies to produce shear stress at the interface between the Ice and the support or to produce tensile stress in the Ice. Many configurations of de-icing systems using piezoelectric actuators have been tested and showed that piezoelectric actuation may be a viable Ice removal system. If the many experimental studies already achieved have the advantage to present tests in different configurations, they often lack analysis of the phenomena, which limits the optimization opportunities. This paper proposes a computational method for estimating voltages and currents of a piezoelectric de-icing system to initiate cohesive fractures in the Ice or adhesive fractures at the Ice/support interface. The computational method is validated by comparing numerical results with experimental results. Other contributions of this paper are the study of the types of mode (extensional or flexural) and of the frequency range with respect to de-icing performances and the proposal of some general rules for designing such systems while limiting their electric power consumption.
-
Electromechanical Resonant Ice Protection Systems: Analysis of Fracture Propagation Mechanisms
AIAA Journal, 2018Co-Authors: Marc Budinger, Valérie Pommier-budinger, Lokman Bennani, Elmar Bonaccurso, Pierrick Rouset, Fabien DezitterAbstract:Recent research is showing growing interest in low-power electromechanical de-icing systems and, in particular, de-icing systems based on piezoelectric actuators. These systems use the vibrations generated by piezoelectric actuators at resonance frequencies to produce shear stress at the interface between the Ice and the support or to produce tensile stress in the Ice. This paper provides analytical and numerical models enabling a better understanding of the main de-icing mechanisms of resonant actuation systems. Different possible Ice shedding mechanisms involving cohesive and adhesive fractures are analyzed with an approach combining modal, stress and crack propagation analyses. Simple analytical models are proposed to better understand the effects on Ice shedding of the type of mode, Ice thickness, or frequency with respect to cohesive and adhesive fractures.
Philippe Villedieu - One of the best experts on this subject based on the ideXlab platform.
-
A survey of Icephobic coatings and their potential use in a hybrid coating/active Ice Protection system for aerospace applications
Progress in Aerospace Sciences, 2019Co-Authors: Xiao Huang, Valérie Pommier-budinger, Marc Budinger, Philippe Villedieu, Nick Tepylo, Elmar Bonaccurso, Lokman BennaniAbstract:Icephobic coatings for aircraft and other surfaces subjected to Ice accretion have generated great interest in the past two decades, due to the advancement of nanomaterials, coating fabrication methods, biomimetics, and a more in-depth understanding of Ice nucleation and Ice adhesion. Icephobic coatings have demonstrated the ability to repel water droplets, delay Ice nucleation and significantly reduce Ice adhesion. Despite these ongoing research activities and promising results, the findings reported hereafter suggest that coatings alone cannot be used for aircraft anti-icing and de-icing operations; rather, they should be considered as a complementary option to either thermal or mechanical Ice Protection methods, for reducing power consumption and the ecological footprint of these active systems and for expediting ground de-icing operations. This paper will first review the state-of-the-art of Icephobic coatings for various applications, including their performance and existing deficiencies. The second part of this paper focuses on aerospace anti-icing and de-icing requirements and the need for hybrid systems to provide a complete Ice Protection solution. Lastly, several urgent issues facing further development in the field are discussed.
-
a survey of Icephobic coatings and their potential use in a hybrid coating active Ice Protection system for aerospace applications
Progress in Aerospace Sciences, 2019Co-Authors: Xiao Huang, Marc Budinger, Philippe Villedieu, Nick Tepylo, Valerie Pommierbudinger, Elmar Bonaccurso, Lokman BennaniAbstract:Icephobic coatings for aircraft and other surfaces subjected to Ice accretion have generated great interest in the past two decades, due to the advancement of nanomaterials, coating fabrication methods, biomimetics, and a more in-depth understanding of Ice nucleation and Ice adhesion. Icephobic coatings have demonstrated the ability to repel water droplets, delay Ice nucleation and significantly reduce Ice adhesion. Despite these ongoing research activities and promising results, the findings reported hereafter suggest that coatings alone cannot be used for aircraft anti-icing and de-icing operations; rather, they should be considered as a complementary option to either thermal or mechanical Ice Protection methods, for reducing power consumption and the ecological footprint of these active systems and for expediting ground de-icing operations. This paper will first review the state-of-the-art of Icephobic coatings for various applications, including their performance and existing deficiencies. The second part of this paper focuses on aerospace anti-icing and de-icing requirements and the need for hybrid systems to provide a complete Ice Protection solution. Lastly, several urgent issues facing further development in the field are discussed.
-
a robust coupling algorithm applied to thermal Ice Protection system unsteady modeling
6th AIAA Atmospheric and Space Environments Conference - AVIATION 2014, 2014Co-Authors: Remi Chauvin, Philippe Villedieu, Pierre Trontin, Lokman BennaniAbstract:The aim of the present paper is to propose a general methodology for the numerical modelling of both anti and de-icing systems. A lubrication model is used for dealing with the dynamics of the runback water film. As regards thermal effects, in order to take into account heat conduction and unsteadiness, a parabolic temperature profile is assumed with respect to the normal coordinate for the Ice layer. Heat transfers in the airfoil solid structure are described using a dedicated solver based on the unsteady heat conduction equation. The most original contribution of this work is the new technique (herein referred to as the "improved Schwarz method") which is proposed for coupling in a robust way the accretion-runback model and the solid heat conduction model. This new coupling algorithm allows to ensure fast convergence of both temperature and heat flux at the coupling interface (airfoil outer surface) and can be used either for steady state computations (anti-icing mode) or unsteady computations (de-icing mode). Numerical test cases which have been performed so far are very promising and show the relevance of this new approach for real applications and 3D extension.
-
two dimensional model of an electro thermal Ice Protection system
5th AIAA Atmospheric and Space Environments Conference, 2013Co-Authors: Lokman Bennani, Philippe Villedieu, Michel SalaunAbstract:In this communication we shall focus on the main governing equations and building blocks of the M.A.D (Anti-icing Deicing Modelling) numerical tool, which is now renamed as INUIT (Integrated NUmerical model of Ice Protection sysTems) and part of the new generation of ONERA icing codes. The code simulates the functioning of an electro-thermal de-icing system. We shall also discuss the various improvements and new features we have added, especially a mechanical model of the Ice block in order to improve the Ice-shedding criterion.
