subject:(in flight icing)

1. Andersson, Daniel. The performance of an iced aircraft wing.

Degree: Engineering Science, 2011, University West

URL: http://urn.kb.se/resolve?urn=urn:nbn:se:hv:diva-4098

► The goal of this thesis work has been to develop and manufacture an ice layer which was to be mounted on the tip of… (more)

Subjects/Keywords: Airfoil; ice layer; in-flight icing; wind tunnel; rapid prototyping; lift force

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APA (6^th Edition):

Andersson, D. (2011). The performance of an iced aircraft wing. (Thesis). University West. Retrieved from http://urn.kb.se/resolve?urn=urn:nbn:se:hv:diva-4098

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Andersson, Daniel. “The performance of an iced aircraft wing.” 2011. Thesis, University West. Accessed February 25, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:hv:diva-4098.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Andersson, Daniel. “The performance of an iced aircraft wing.” 2011. Web. 25 Feb 2021.

Vancouver:

Andersson D. The performance of an iced aircraft wing. [Internet] [Thesis]. University West; 2011. [cited 2021 Feb 25]. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:hv:diva-4098.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Andersson D. The performance of an iced aircraft wing. [Thesis]. University West; 2011. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:hv:diva-4098

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

2. Droz, Christophe. Guidage des ondes d'ordre élevé dans les composites : application au dégivrage en vol des pales d'hélicoptères : High-order wave propagation in composite waveguides : application to in-flight de-icing of helicopter rotor blades.

Degree: Docteur es, Dynamique des structures, 2015, Ecully, Ecole centrale de Lyon

URL: http://www.theses.fr/2015ECDL0026

►

Lorsqu’un hélicoptère opère dans des conditions givrantes extrêmes, l’accumulation de glace sur les pales peut considérablement impacter les performances de l’appareil. De nombreuses recherches portant… (more)

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Lorsqu’un hélicoptère opère dans des conditions givrantes extrêmes, l’accumulation de glace sur les pales peut considérablement impacter les performances de l’appareil. De nombreuses recherches portant sur le développement d’un système de dégivrage à faible consommation et moindre coût ont été initiées ces dernières années. Dans cette thèse, une technique ondulatoire de protection contre la formation de glace sur les surfaces des pales d’hélicoptères est étudiée. La stratégie proposée repose sur l’utilisation d’ondes guidées d’ordre élevé spécifiques pour créer des cisaillements dépassant la force d’adhésion surfacique d’un profil de glace. Des essais ont d’abord été menés pour réaliser le modèle E.F. d’un tronçon de pale, puis une stratégie de réduction de modèle est développée pour la Méthode des Éléments Finis Ondulatoires. Cette formulation s’appuie sur la projection des vecteurs d’état sur une base réduite, constituée des formes d’ondes progressives. Elle permet de réaliser des analyses ondulatoires large-bande dans les structures complexes, 1D ou 2D périodiques. Les ondes guidées sont d’abord examinées dans la pale d’hélicoptère, puis les effets de localisation et de conversion des ondes sont interprétés dans divers guides d’ondes 1D et 2D. Les interactions de ces ondes d’ordre élevé avec les profils d’accrétion de glace, ainsi qu’avec plusieurs types de singularités structurelles, sont analysées au moyen d’une Méthode des Matrices de Diffusion. Une formulation ondulatoire temporelle est ensuite proposée pour l’analyse rapide de la propagation d’un train d’ondes dans les guides d’ondes couplés. Enfin, un réseau d’actionneurs est conçu pour la génération de trains d’ondes d’ordre élevé, et des validations temporelles sont réalisées dans une plaque composite ainsi que dans une pale de Super Puma.

When helicopters fly through extreme conditions, ice can aggregate on their blades and seriously affect the aircraft performances. Recently, an increasing research effort was devoted to the development of affordable low power de-icing solutions. In this thesis, a wave-based approach is adopted to prevent and/or remove ice aggregates from the surfaces of helicopter rotor blades. The de-icing strategy uses specific high-order guided waves to exceed the shear adhesion strength of ice accretion profiles. Experiments are conducted in order to update the FE model of a realistic rotor blade, then a Model Order Reduction strategy is developed for the Wave Finite Element Method. It involves a projection of the state vectors on a reduced basis of propagating waves shapes, and enables broadband wave analysis in structurally advanced 1D and 2D periodic structures. Guided wave propagation is studied within a helicopter rotor blade, and wave localization and conversion effects are discussed in various 1D and 2D composite waveguides. The interactions of high-order waves with ice aggregates and other types of structural singularities are also examined by means of a Diffusion Matrix Method. Then, time-domain propagation in coupled…

Advisors/Committee Members: Ichchou, Mohamed (thesis director).

Subjects/Keywords: Pales d'hélicoptères; Dégivrage en vol; Helicopter rotor; In-flight de-icing

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Droz, C. (2015). Guidage des ondes d'ordre élevé dans les composites : application au dégivrage en vol des pales d'hélicoptères : High-order wave propagation in composite waveguides : application to in-flight de-icing of helicopter rotor blades. (Doctoral Dissertation). Ecully, Ecole centrale de Lyon. Retrieved from http://www.theses.fr/2015ECDL0026

Chicago Manual of Style (16^th Edition):

Droz, Christophe. “Guidage des ondes d'ordre élevé dans les composites : application au dégivrage en vol des pales d'hélicoptères : High-order wave propagation in composite waveguides : application to in-flight de-icing of helicopter rotor blades.” 2015. Doctoral Dissertation, Ecully, Ecole centrale de Lyon. Accessed February 25, 2021. http://www.theses.fr/2015ECDL0026.

MLA Handbook (7^th Edition):

Droz, Christophe. “Guidage des ondes d'ordre élevé dans les composites : application au dégivrage en vol des pales d'hélicoptères : High-order wave propagation in composite waveguides : application to in-flight de-icing of helicopter rotor blades.” 2015. Web. 25 Feb 2021.

Vancouver:

Droz C. Guidage des ondes d'ordre élevé dans les composites : application au dégivrage en vol des pales d'hélicoptères : High-order wave propagation in composite waveguides : application to in-flight de-icing of helicopter rotor blades. [Internet] [Doctoral dissertation]. Ecully, Ecole centrale de Lyon; 2015. [cited 2021 Feb 25]. Available from: http://www.theses.fr/2015ECDL0026.

Council of Science Editors:

Droz C. Guidage des ondes d'ordre élevé dans les composites : application au dégivrage en vol des pales d'hélicoptères : High-order wave propagation in composite waveguides : application to in-flight de-icing of helicopter rotor blades. [Doctoral Dissertation]. Ecully, Ecole centrale de Lyon; 2015. Available from: http://www.theses.fr/2015ECDL0026

University of Waterloo

3. Geiger, Paul. Simulation of In-Flight Rime Icing Using a Non-Body-Fitted Mesh.

Degree: 2020, University of Waterloo

URL: http://hdl.handle.net/10012/15810

► In-flight rime icing occurs when supercooled droplets strike the surface of an aircraft and instantly freeze. This often occurs in the high moisture, cold environments… (more)

▼ In-flight rime icing occurs when supercooled droplets strike the surface of an aircraft and instantly freeze. This often occurs in the high moisture, cold environments of clouds and is of major concern to aircraft manufacturers and pilots due to safety issues, as the icing degrades the aerodynamic performance of the plane. Rime icing models are important in their own right and as a step towards more complex glaze ice/mixed ice models. Most current commercially available software use boundary-fitted approaches to the air and droplet phases along with a node-displacement method for the boundary. This can cause issues as the node-displacement approach to the boundary can cause tangles in the boundary which are unphysical, and the boundary-fitted methodologies require remeshing after each ice accretion step which can degrade mesh quality and cause crashes. The goal of this thesis is to create a non-boundary-fitted approach towards rime icing simulations. Level set methodologies, which are unsusceptible to tangles, are used to handle the evolution of the boundaries. Static meshes which are Cartesian in the vicinity of the boundary are used, and high Reynolds wall functions are incorporated into the methodology so that the meshes can be made coarser and solutions can be reached faster. This proposed model is implemented via modifications of the OpenFOAM® 5.0 open-source environment. Where possible, results are compared to experimental results and to the commercially available FENSAP-ICE software by ANSYS, Inc. Immersed boundary and cut-cell methodologies are explored for the droplets near the boundary. It was found that the developed cut-cell methodology is about twice as accurate as the immersed boundary method developed and that this is one of the dominant discretization errors in many tests. It was shown that as droplet size goes down, particularly below 10 μm, differences in-between the FENSAP-ICE and the proposed model start increasing, with the total collection efficiency going from 0.2% different in-between the models for droplets of size 35.52 μm up to as much as 300% for 4.96 μm, and it is suggested that modifications to the model and discretization be made before tests for sub-10 μm mean-value droplet diameter (MVD) are run, although these tend to be rarely encountered in nature as most droplets tend to range from 10-50 μm. For simulation using a MVD of 16 μm and a 7-bin Langmuir-D distribution, it was found that the model differed in total collection predictions from FENSAP-ICE by 0.8%, and by 2.9% using just the MVD, as the smallest droplets contribute very little to the net collection. Using a pseudo-steady-state, multistep icing procedure, it was found that over a NACA23012 airfoil at a 2⁰ angle of attack, the total accreted ice for a 1-step ice accretion differed by 0.21% from FENSAP-ICE results, and for a 4-step test, it differed by 0.11% with similar resultant ice shapes when a developed model for the ending time-step which increases the global conservation was used, and by 17% for a 1-step…

Subjects/Keywords: in-flight icing; rime icing; immersed boundary method; cut-cell method; finite volume method; level set method; non-body-fitted mesh

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APA (6^th Edition):

Geiger, P. (2020). Simulation of In-Flight Rime Icing Using a Non-Body-Fitted Mesh. (Thesis). University of Waterloo. Retrieved from http://hdl.handle.net/10012/15810

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Geiger, Paul. “Simulation of In-Flight Rime Icing Using a Non-Body-Fitted Mesh.” 2020. Thesis, University of Waterloo. Accessed February 25, 2021. http://hdl.handle.net/10012/15810.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Geiger, Paul. “Simulation of In-Flight Rime Icing Using a Non-Body-Fitted Mesh.” 2020. Web. 25 Feb 2021.

Vancouver:

Geiger P. Simulation of In-Flight Rime Icing Using a Non-Body-Fitted Mesh. [Internet] [Thesis]. University of Waterloo; 2020. [cited 2021 Feb 25]. Available from: http://hdl.handle.net/10012/15810.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Geiger P. Simulation of In-Flight Rime Icing Using a Non-Body-Fitted Mesh. [Thesis]. University of Waterloo; 2020. Available from: http://hdl.handle.net/10012/15810

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Iowa State University

4. Li, Haixing. Experimental studies on the dynamics of in-flight and impacting water droplets pertinent to aircraft icing phenomena.

Degree: 2017, Iowa State University

URL: https://lib.dr.iastate.edu/etd/15564

► Aircraft icing is widely recognized as a significant hazard to aircraft operations in cold weather. When an aircraft or rotorcraft fly in a cold climate,… (more)

▼ Aircraft icing is widely recognized as a significant hazard to aircraft operations in cold weather. When an aircraft or rotorcraft fly in a cold climate, some of the super-cooled water droplets would impact and freeze on the exposed aircraft surfaces to form ice shapes, which can degrade the aerodynamic performance of an airplane significantly by decreasing lift while increasing drag, and even lead to the aircraft crash. In the present study, a series of experimental investigations were conducted to investigate dynamics and thermodynamics of in-flight and impinging water droplets in order to elucidate the underlying physics of the important microphysical process pertinent to aircraft icing phenomena. A novel lifetime-based molecular tagging thermometry technique (MTT) is developed to achieve simultaneous measurements of droplet size, flying velocity and transient temperature of in-flight water droplets to characterize the dynamic and thermodynamic behaviors of the micro-sized in-flight droplets pertinent to aircraft icing phenomena. By using high-speed imaging and infrared thermal imaging techniques, a comprehensive experimental study was conducted to quantify the unsteady heat transfer and phase changing processes as water droplets impinging onto frozen cold surfaces under different test conditions (i.e., with different Weber numbers, Reynolds numbers, and impact angles of the impinging droplets, different temperature, hydrophobicity and roughness of the test plates) to simulate the scenario of super-cooled water droplets impinging onto the frozen cold wing surfaces. A novel digital image projector (DIP) technique was also developed to achieve time-resolved film thickness measurements to quantify the dynamic impinging process of water droplets (i.e., droplet impact, rebounding, splashing and freezing process). An impact droplet maximum spreading diameter model and a damped harmonic oscillator model was proposed based on precise measurement of the impact droplet 3D shape. A better understanding of the important micro physical processes pertinent to aircraft icing phenomena would lead to better ice accretion models for more accurate prediction of ice formation and accretion on aircraft wings as well as develop more effective and robust anti-/de-icing strategies for safer and more efficient operation of aircraft in cold weather.

Subjects/Keywords: 3-D shape reconstruction of impact droplet; Aircraft icing; Droplet impact dynamics; Droplet impact on super-hydrophobic surface; In-flight droplets temperature measurement; Aerospace Engineering

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APA (6^th Edition):

Li, H. (2017). Experimental studies on the dynamics of in-flight and impacting water droplets pertinent to aircraft icing phenomena. (Thesis). Iowa State University. Retrieved from https://lib.dr.iastate.edu/etd/15564

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Li, Haixing. “Experimental studies on the dynamics of in-flight and impacting water droplets pertinent to aircraft icing phenomena.” 2017. Thesis, Iowa State University. Accessed February 25, 2021. https://lib.dr.iastate.edu/etd/15564.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Li, Haixing. “Experimental studies on the dynamics of in-flight and impacting water droplets pertinent to aircraft icing phenomena.” 2017. Web. 25 Feb 2021.

Vancouver:

Li H. Experimental studies on the dynamics of in-flight and impacting water droplets pertinent to aircraft icing phenomena. [Internet] [Thesis]. Iowa State University; 2017. [cited 2021 Feb 25]. Available from: https://lib.dr.iastate.edu/etd/15564.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Li H. Experimental studies on the dynamics of in-flight and impacting water droplets pertinent to aircraft icing phenomena. [Thesis]. Iowa State University; 2017. Available from: https://lib.dr.iastate.edu/etd/15564

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

5. Pena, Dorian. Développement d'un code de givrage tridimensionnel avec méthode Level-Set : Development of a three-dimensional icing code using level-set method.

Degree: Docteur es, Mécanique des fluides, 2016, Strasbourg; Ecole polytechnique (Montréal, Canada)

URL: http://www.theses.fr/2016STRAD014

►

Le travail réalisé dans cette thèse introduit le concept de l'utilisation de la méthode Level-Set pour simuler l'interface Glace/Air au cours du temps lors du… (more)

▼

Le travail réalisé dans cette thèse introduit le concept de l'utilisation de la méthode Level-Set pour simuler l'interface Glace/Air au cours du temps lors du processus de givrage en vol des aéronefs. Pour cela, un code de givrage tri-dimensionnel multi-blocs et parallélisé a été implémenté au sein du solveur NSMB (Navier-Stokes-Multi-Blocks). Il comprend notamment un module de calcul des trajectoires des gouttelettes par une approche Eulérienne compatible avec l'utilisation de grilles chimères et un module thermodynamique pour le calcul des masses de glace incluant deux modèles différents : un modèle algébrique itératif et un modèle à dérivées partielles. Une attention particulière a été portée sur la vérification du code de givrage implémenté en comparant systématiquement, si possible, les résultats obtenus avec les données expérimentales et numériques existantes dans la littérature. Pour cette raison, le module de déformation de maillage existant dans NSMB a été intégré au code implémenté afin de pouvoir simuler le givrage par une méthode traditionnelle. Enfin, un nouveau principe pour le suivi de l'interface glace/air est introduit via l'utilisation d'une méthode Level-Set. Puisque dans ce travail de thèse nous nous intéressons particulièrement au concept, la méthode Level-Set développée est d'ordre un et est résolue implicitement. On montrera cependant que des résultats valides sont obtenus avec une telle approximation.

This thesis introduces the concept of the Level-Set method for simulating the evolution through time of the ice/air interface during the process of in-flight aircraft icing. For that purpose, a three-dimensionnal multi-block and parallelized icing code have been implemented in the NSMB flow solver (Navier-Stokes-Multi-Blocks). It includes a module for calculating the droplet trajectories by an Eulerian approach compatible with the use of chimera grids and a thermodynamic module to calculate the ice masses including two different models : an iterative algebraic model and a PDE model. Particular attention was paid to the validation of the icing code irnplemented by comparing results with existing experimental and numerical data in the literature. For this reason, the existing mesh deformation algorithm in NSMB was integrated into the code to simulate icing by a traditional method. Finally a new principle to track the ice/air interface is introduced using the Level-Set method. Since we are particularly interested in the concept, the Level-Set method developped is first order and solved implicitly. However it will be shown that valid results are obtained with such an approximation.

Advisors/Committee Members: Hoarau, Yannick (thesis director), Laurendeau, Eric (thesis director).

Subjects/Keywords: Givrage; Méthode Eulérienne de transport de particules; Thermodynamique du givrage; Méthode Level-Set; Méthode chimère; Icing; Eulerian approach; Process of in-flight aircraft icing; Level-Set method; Chimeria method; Navier-Stokes-Multi-Blocks; 629.1; 532.5

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Pena, D. (2016). Développement d'un code de givrage tridimensionnel avec méthode Level-Set : Development of a three-dimensional icing code using level-set method. (Doctoral Dissertation). Strasbourg; Ecole polytechnique (Montréal, Canada). Retrieved from http://www.theses.fr/2016STRAD014

Chicago Manual of Style (16^th Edition):

Pena, Dorian. “Développement d'un code de givrage tridimensionnel avec méthode Level-Set : Development of a three-dimensional icing code using level-set method.” 2016. Doctoral Dissertation, Strasbourg; Ecole polytechnique (Montréal, Canada). Accessed February 25, 2021. http://www.theses.fr/2016STRAD014.

MLA Handbook (7^th Edition):

Pena, Dorian. “Développement d'un code de givrage tridimensionnel avec méthode Level-Set : Development of a three-dimensional icing code using level-set method.” 2016. Web. 25 Feb 2021.

Vancouver:

Pena D. Développement d'un code de givrage tridimensionnel avec méthode Level-Set : Development of a three-dimensional icing code using level-set method. [Internet] [Doctoral dissertation]. Strasbourg; Ecole polytechnique (Montréal, Canada); 2016. [cited 2021 Feb 25]. Available from: http://www.theses.fr/2016STRAD014.

Council of Science Editors:

Pena D. Développement d'un code de givrage tridimensionnel avec méthode Level-Set : Development of a three-dimensional icing code using level-set method. [Doctoral Dissertation]. Strasbourg; Ecole polytechnique (Montréal, Canada); 2016. Available from: http://www.theses.fr/2016STRAD014

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