subject:(Process of in flight aircraft icing)

1. 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

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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)

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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 (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 March 07, 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. 07 Mar 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 Mar 07]. 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

Iowa State University

2. 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 March 07, 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. 07 Mar 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 Mar 07]. 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

Brno University of Technology

3. Čížková, Markéta. Využití GPS pro měření za letu: Use GPS for in flight measurement.

Degree: 2019, Brno University of Technology

URL: http://hdl.handle.net/11012/176617

► Bachelor thesis Use GPS for In-Flight Measurement addresses the applicability of Global Positioning System as a tool for aircraft certification. The theoretical part of thesis… (more)

Subjects/Keywords: GPS; letadla; letové zkoušky; metody zkoušení letadel; zkoušení za letu; Aircraft; flight test; GPS; In-Flight Measurement; methods of aircraft testing

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APA (6^th Edition):

Čížková, M. (2019). Využití GPS pro měření za letu: Use GPS for in flight measurement. (Thesis). Brno University of Technology. Retrieved from http://hdl.handle.net/11012/176617

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):

Čížková, Markéta. “Využití GPS pro měření za letu: Use GPS for in flight measurement.” 2019. Thesis, Brno University of Technology. Accessed March 07, 2021. http://hdl.handle.net/11012/176617.

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

MLA Handbook (7^th Edition):

Čížková, Markéta. “Využití GPS pro měření za letu: Use GPS for in flight measurement.” 2019. Web. 07 Mar 2021.

Vancouver:

Čížková M. Využití GPS pro měření za letu: Use GPS for in flight measurement. [Internet] [Thesis]. Brno University of Technology; 2019. [cited 2021 Mar 07]. Available from: http://hdl.handle.net/11012/176617.

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

Council of Science Editors:

Čížková M. Využití GPS pro měření za letu: Use GPS for in flight measurement. [Thesis]. Brno University of Technology; 2019. Available from: http://hdl.handle.net/11012/176617

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

Tampere University

4. Maly, Yahya. Cold Sprayed SLIPS Coatings: A pathway towards process optimization and icephobicity .

Degree: 2020, Tampere University

URL: https://trepo.tuni.fi/handle/10024/122358

► Ice accretion is a major problem that causes economic loss, damages structure, impedes transports, and potentially leads to human injury and death. There is a… (more)

▼ Ice accretion is a major problem that causes economic loss, damages structure, impedes transports, and potentially leads to human injury and death. There is a strong demand for a reliable passive anti-icing system to reduce and prevent ice adhesion, especially in aircraft applications where ice accretion can change the aerodynamic behaviour and lead to loss of control. Although de-icing and active anti-icing methods exist, passive anti-icing systems are desired because they do not rely on complicated infrastructure and do not require externally supplied energy. It has been established that SLIPS, short for Slippery Liquid-Infused Porous Surfaces, inhibit high water resistance properties, however the connection between the wetting properties (hydrophobicity) and icephobic behavior is under debate. During this study, the feasibility of producing SLIPS via cold spray is studied through multiple randomized experiments aimed at evaluating different spraying parameters and techniques for process development. The study is conducted using various polymer powders and different spraying material. The purpose of these experiments is to produce a functional porous coating that it capable of a lubricant liquid infusion. The process used to produce the polymer-based cold sprayed SLIPS was detailed in this paper. In total, 34 substrates were cold sprayed with polymer-based powders using low-pressure and high-pressure cold spray guns. Eight samples were selected to undergo lubricant infusion and further testing. The coating structures were visually analysed with a microscope. The wettability was estimated by measuring water contact angle. Roughness data and surface topographies were obtained via a profilometer. Lubricant stability of the oil-infused structures was evaluated via centrifuge testing. The results showed that the production of polymer-based cold sprayed SLIPS is feasible. Furthermore, the cold spraying process aids with the production of SLIPS due to partial melting of the polymer particles upon impact with the substrate, resulting in a porous structure. The result further showed that cold sprayed SLIPS have excellent oil stability and do not require complicated surface preparation, which is advantageous over other SLIPS design methods. This thesis work focused on the development of coatings for potential use as icephobic products (i.e. passive anti-icing systems). A deeper investigation into icephobics found that since 1930’s, the development of icephobic products has been hindered by the lack of understanding of ice accretion, unknown meaningful testing methods for new products, debated connection to hydrophobicity, unreliability of icing wind tunnel testing and lack of a standardized method, large scatters of ice adhesion data, discrepancies in literature and different conclusions on the affecting mechanisms, experimental biases, and a general lack of understanding for properties. Although there exist a few icephobic products on the market, their effectiveness is in question by research. The results…

Subjects/Keywords: Icephobicity ; Aircraft icing ; Ice wind tunnel ; Anti-icing ; De-icing ; Passive anti-ice systems ; Icephobic coatings ; Sprayed coatings ; Hydrophobicity ; superhydrophobicity ; Nature-inspired technology ; Lotus Effect ; SLIPS ; Slippery Liquid Infused Porous Surfaces ; Thermal spraying technology ; Cold spraying of polymers ; Flame spraying ; Process development

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APA (6^th Edition):

Maly, Y. (2020). Cold Sprayed SLIPS Coatings: A pathway towards process optimization and icephobicity . (Masters Thesis). Tampere University. Retrieved from https://trepo.tuni.fi/handle/10024/122358

Chicago Manual of Style (16^th Edition):

Maly, Yahya. “Cold Sprayed SLIPS Coatings: A pathway towards process optimization and icephobicity .” 2020. Masters Thesis, Tampere University. Accessed March 07, 2021. https://trepo.tuni.fi/handle/10024/122358.

MLA Handbook (7^th Edition):

Maly, Yahya. “Cold Sprayed SLIPS Coatings: A pathway towards process optimization and icephobicity .” 2020. Web. 07 Mar 2021.

Vancouver:

Maly Y. Cold Sprayed SLIPS Coatings: A pathway towards process optimization and icephobicity . [Internet] [Masters thesis]. Tampere University; 2020. [cited 2021 Mar 07]. Available from: https://trepo.tuni.fi/handle/10024/122358.

Council of Science Editors:

Maly Y. Cold Sprayed SLIPS Coatings: A pathway towards process optimization and icephobicity . [Masters Thesis]. Tampere University; 2020. Available from: https://trepo.tuni.fi/handle/10024/122358

5. 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

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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… (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 (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 March 07, 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. 07 Mar 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 Mar 07]. 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

6. 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 March 07, 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. 07 Mar 2021.

Vancouver:

Geiger P. Simulation of In-Flight Rime Icing Using a Non-Body-Fitted Mesh. [Internet] [Thesis]. University of Waterloo; 2020. [cited 2021 Mar 07]. 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

Baylor University

7. Shannon, Timothy Andrew, 1991-. Convection from realistic ice roughness on a simulated NACA 0012 airfoil.

Degree: M.S.M.E., Baylor University. School of Engineering., 2015, Baylor University

URL: http://hdl.handle.net/2104/9534

► Ice roughness properties are critically important to the development of ice accretions on aircraft surfaces. Ice accretions degrade aircraft performance by increasing the skin friction… (more)

Subjects/Keywords: Aircraft icing. Ice roughness.

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

APA (6^th Edition):

Shannon, Timothy Andrew, 1. (2015). Convection from realistic ice roughness on a simulated NACA 0012 airfoil. (Masters Thesis). Baylor University. Retrieved from http://hdl.handle.net/2104/9534

Chicago Manual of Style (16^th Edition):

Shannon, Timothy Andrew, 1991-. “Convection from realistic ice roughness on a simulated NACA 0012 airfoil.” 2015. Masters Thesis, Baylor University. Accessed March 07, 2021. http://hdl.handle.net/2104/9534.

MLA Handbook (7^th Edition):

Shannon, Timothy Andrew, 1991-. “Convection from realistic ice roughness on a simulated NACA 0012 airfoil.” 2015. Web. 07 Mar 2021.

Vancouver:

Shannon, Timothy Andrew 1. Convection from realistic ice roughness on a simulated NACA 0012 airfoil. [Internet] [Masters thesis]. Baylor University; 2015. [cited 2021 Mar 07]. Available from: http://hdl.handle.net/2104/9534.

Council of Science Editors:

Shannon, Timothy Andrew 1. Convection from realistic ice roughness on a simulated NACA 0012 airfoil. [Masters Thesis]. Baylor University; 2015. Available from: http://hdl.handle.net/2104/9534

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

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 March 07, 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. 07 Mar 2021.

Vancouver:

Andersson D. The performance of an iced aircraft wing. [Internet] [Thesis]. University West; 2011. [cited 2021 Mar 07]. 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

Brno University of Technology

9. Fazekaš, Slavomír. Odmrazovací soustavy letadel: Aircraft de-icing systems.

Degree: 2018, Brno University of Technology

URL: http://hdl.handle.net/11012/27286

► The aim of my bachelor thesis is to make the acquaintance of the danger of ice coating on airplanes, it s creation and the way… (more)

Subjects/Keywords: Lietadlo; námraza; lietadlové systémy; protinámrazový systém; odmrazovanie; Aircraft; icing; aircraft systems; anti-icing; de-icing

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APA (6^th Edition):

Fazekaš, S. (2018). Odmrazovací soustavy letadel: Aircraft de-icing systems. (Thesis). Brno University of Technology. Retrieved from http://hdl.handle.net/11012/27286

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):

Fazekaš, Slavomír. “Odmrazovací soustavy letadel: Aircraft de-icing systems.” 2018. Thesis, Brno University of Technology. Accessed March 07, 2021. http://hdl.handle.net/11012/27286.

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

MLA Handbook (7^th Edition):

Fazekaš, Slavomír. “Odmrazovací soustavy letadel: Aircraft de-icing systems.” 2018. Web. 07 Mar 2021.

Vancouver:

Fazekaš S. Odmrazovací soustavy letadel: Aircraft de-icing systems. [Internet] [Thesis]. Brno University of Technology; 2018. [cited 2021 Mar 07]. Available from: http://hdl.handle.net/11012/27286.

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

Council of Science Editors:

Fazekaš S. Odmrazovací soustavy letadel: Aircraft de-icing systems. [Thesis]. Brno University of Technology; 2018. Available from: http://hdl.handle.net/11012/27286

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

University of Ottawa

10. Nicklin, Sean. Hopping the Pond: The Normalization of North Atlantic Civil Aviation from its Origins to the Rise of the Jumbo Jet, 1919-1970 .

Degree: 2016, University of Ottawa

URL: http://hdl.handle.net/10393/35298

► Flight across the North Atlantic is a routine process now, with thousands of flights carrying millions of passengers between Europe and North America every year… (more)

Subjects/Keywords: civil aviation; commercial flight; North Atlantic; transatlantic; aircraft; infrastructure; history of technology; history of flight

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APA (6^th Edition):

Nicklin, S. (2016). Hopping the Pond: The Normalization of North Atlantic Civil Aviation from its Origins to the Rise of the Jumbo Jet, 1919-1970 . (Thesis). University of Ottawa. Retrieved from http://hdl.handle.net/10393/35298

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):

Nicklin, Sean. “Hopping the Pond: The Normalization of North Atlantic Civil Aviation from its Origins to the Rise of the Jumbo Jet, 1919-1970 .” 2016. Thesis, University of Ottawa. Accessed March 07, 2021. http://hdl.handle.net/10393/35298.

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

MLA Handbook (7^th Edition):

Nicklin, Sean. “Hopping the Pond: The Normalization of North Atlantic Civil Aviation from its Origins to the Rise of the Jumbo Jet, 1919-1970 .” 2016. Web. 07 Mar 2021.

Vancouver:

Nicklin S. Hopping the Pond: The Normalization of North Atlantic Civil Aviation from its Origins to the Rise of the Jumbo Jet, 1919-1970 . [Internet] [Thesis]. University of Ottawa; 2016. [cited 2021 Mar 07]. Available from: http://hdl.handle.net/10393/35298.

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

Council of Science Editors:

Nicklin S. Hopping the Pond: The Normalization of North Atlantic Civil Aviation from its Origins to the Rise of the Jumbo Jet, 1919-1970 . [Thesis]. University of Ottawa; 2016. Available from: http://hdl.handle.net/10393/35298

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

Penn State University

11. Soltis, Jared T. Design and Testing of an Erosion Resistant Ultrasonic De-icing System for Rotorcraft Blades.

Degree: 2013, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/19062

► The goal of this research was to design a helicopter rotor blade lead edge that had high sand erosion resistance and was conducive to ultrasonic… (more)

▼ The goal of this research was to design a helicopter rotor blade lead edge that had high sand erosion resistance and was conducive to ultrasonic ice protection systems (IPSs). The first section of research tried to tailor the leading edge to promote ice interfacial transverse shear stress created by the ultrasonic vibration of piezoelectric actuators. Previous work done to tailor leading edges removed material from the inside of the cap. However, there were concerns about structural integrity and erosion wear when material was removed. A new system of adding material to the inside of the leading edge instead of removing material to create stress concentrations was researched for this thesis. Finite element analysis was used to determine the optimal locations for the discontinuities for the ultrasonic IPS. The discontinuities located in the optimal location are called Tailored Stress Concentrators (TSCs). Using the finite element results, it was determined that the best location for the TSCs were in regions of normally low stress in the baseline model before the addition of the TSCs. The addition of the TSCs creates stress concentrations as well as increased the original local maximum stresses. Initial models showed increases in average interfacial shear stress of 20%. Since the first FEM was not practical to construct as a bench top experiment, a second model was developed. Next, a bench top experiment and matching finite element model were built to validate the finite element analysis. The finite element model predicted a decrease of 9% in interfacial shear stress when TSCs were added to the bench top model. The bench top experiments confirmed the ineffectiveness of TSCs. There was no reduction in power required to de-ice when the TSCs were added to the bench top model. The next part of the research focused on the material used for the leading edge erosion cap. Coating systems based on titanium nitride (TiN) applied via cathodic arc physical vapor deposition (CA-PVD) were developed for rotorcraft erosion caps to protect against sand and rain erosion. Erosion resistant materials must also be compatible with ice protection systems. The ice adhesion strength of titanium nitride and titanium aluminum nitride (TiAlN) were evaluated experimentally and compared to the ice adhesion strength of uncoated metallic materials currently used on rotor blade leading edge caps: stainless steel 430, Inconel 625, and titanium grade 2. Experimental studies presented in this paper investigated which environmental and material parameters are most influential on impact ice adhesion strength. The effects of median volumetric diameter, liquid water content, ambient temperature, surface roughness, and material grain direction were tested on stainless steel 430. Tests revealed that surface roughness and temperature have the greatest effect on ice adhesion strength. There was an increase in adhesion strength of 670% from -8°C to -16°C and 250% increase from 24 Ra µin to 105 Ra µin. An increase in water droplet size from 20 µm to 40 µm… Advisors/Committee Members: Jose Palacios, Thesis Advisor/Co-Advisor, Douglas Edward Wolfe, Thesis Advisor/Co-Advisor.

Subjects/Keywords: aircraft icing; de-icing systems; ice adhesion strength; ultrasonic de-icing; erosion resistant materials

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APA (6^th Edition):

Soltis, J. T. (2013). Design and Testing of an Erosion Resistant Ultrasonic De-icing System for Rotorcraft Blades. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/19062

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):

Soltis, Jared T. “Design and Testing of an Erosion Resistant Ultrasonic De-icing System for Rotorcraft Blades.” 2013. Thesis, Penn State University. Accessed March 07, 2021. https://submit-etda.libraries.psu.edu/catalog/19062.

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

MLA Handbook (7^th Edition):

Soltis, Jared T. “Design and Testing of an Erosion Resistant Ultrasonic De-icing System for Rotorcraft Blades.” 2013. Web. 07 Mar 2021.

Vancouver:

Soltis JT. Design and Testing of an Erosion Resistant Ultrasonic De-icing System for Rotorcraft Blades. [Internet] [Thesis]. Penn State University; 2013. [cited 2021 Mar 07]. Available from: https://submit-etda.libraries.psu.edu/catalog/19062.

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

Council of Science Editors:

Soltis JT. Design and Testing of an Erosion Resistant Ultrasonic De-icing System for Rotorcraft Blades. [Thesis]. Penn State University; 2013. Available from: https://submit-etda.libraries.psu.edu/catalog/19062

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

Brno University of Technology

12. Smékal, Aleš. Odmrazovací soustavy letadel: Aircraft de-icing systems.

Degree: 2019, Brno University of Technology

URL: http://hdl.handle.net/11012/33535

► The bachelor´s thesis is familiarization of me with icing on aircrafts. It includes the distribution systems for anti-icing and de-icing, energy intensity and efficiency are… (more)

Subjects/Keywords: Námraza; protinámrazový; letadlové systémy; led; odmrazování; Icing; anti-icing; aircraft systems; ice; de-icing

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APA (6^th Edition):

Smékal, A. (2019). Odmrazovací soustavy letadel: Aircraft de-icing systems. (Thesis). Brno University of Technology. Retrieved from http://hdl.handle.net/11012/33535

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):

Smékal, Aleš. “Odmrazovací soustavy letadel: Aircraft de-icing systems.” 2019. Thesis, Brno University of Technology. Accessed March 07, 2021. http://hdl.handle.net/11012/33535.

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

MLA Handbook (7^th Edition):

Smékal, Aleš. “Odmrazovací soustavy letadel: Aircraft de-icing systems.” 2019. Web. 07 Mar 2021.

Vancouver:

Smékal A. Odmrazovací soustavy letadel: Aircraft de-icing systems. [Internet] [Thesis]. Brno University of Technology; 2019. [cited 2021 Mar 07]. Available from: http://hdl.handle.net/11012/33535.

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

Council of Science Editors:

Smékal A. Odmrazovací soustavy letadel: Aircraft de-icing systems. [Thesis]. Brno University of Technology; 2019. Available from: http://hdl.handle.net/11012/33535

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

University of Missouri – Kansas City

13. Alabsi, Mohammed. In-Flight Learning Based Flight Control of an Unmanned Aircraft System.

Degree: 2018, University of Missouri – Kansas City

URL: http://hdl.handle.net/10355/68835

► Unmanned Aerial Vehicles (UAVs) popularity has increased substantially in the last few years. UAVs capabilities continue to improve as a result of advances in battery… (more)

▼ Unmanned Aerial Vehicles (UAVs) popularity has increased substantially in the last few years. UAVs capabilities continue to improve as a result of advances in battery technology, communication, navigation systems and electronics. Increased popularity has driven researchers to improve UAVs reliability and safety which is reﬂected by the number of publications and accelerating educational programs interest. UAVs are suited for a wide range of civilian and military applications; however, UAVs currently can not integrate with civilian airspace because of stringent safety requirements. Hence, it is necessary to push the envelope for UAVs design and control so that they can learn from nature and have more self-aware capabilities to improve safety and reliability. This dissertation addresses some challenges involved with ﬂight controller learning based on real-time modeling of UAV. Plenty of UAV applications require different operational capabilities within a composite mission. These capabilities include landing and taking off using short runways, while being able to perform missions that require a high cruise speed i.e. tracking applications. A composite mission also requires the aircraft to be able to hover or operate with low cruise speeds for applications involving stationary moments. All of these different operational modes require a hybrid aircraft design that combines ﬁxed wing aircraft capabilities and Vertical Take-Off and Landing (VTOL) aircraft capabilities. However, extensive resources required for hybrid aircraft design prohibited the discovery of different revolutionary designs. The work presented in this dissertation describes the development of a rapid modeling, prototyping and controller design platform of an unmanned quadrotor aircraft. Three main objectives are investigated: intelligent excitation input design, real-time parameter estimation, and learning control. Real-time estimation of dynamic model parameters is important for control adaptation. However, the aircraft model estimation performance can be severely degraded by an active control system and highly collinear model terms such as those found on a quadrotor unmanned aircraft. Recursive Fourier Transform Regression was applied to estimate parameters of different model forms/structures and using different excitation levels. The generated models are utilized to reconﬁgure a Nonlinear Dynamic Inversion (NDI) controller considering different testing conditions: normal, failure, and learning ﬂights. Finally,an intelligent input design technique is proposed which enables autonomous identiﬁcation of the vehicle’s response modal frequencies and emphasizes excitation power accordingly. Advisors/Committee Members: Fields, Travis (advisor).

Subjects/Keywords: Drone aircraft; Flight control; Dissertation – University of Missouri – Kansas City – Engineering

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

APA (6^th Edition):

Alabsi, M. (2018). In-Flight Learning Based Flight Control of an Unmanned Aircraft System. (Thesis). University of Missouri – Kansas City. Retrieved from http://hdl.handle.net/10355/68835

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):

Alabsi, Mohammed. “In-Flight Learning Based Flight Control of an Unmanned Aircraft System.” 2018. Thesis, University of Missouri – Kansas City. Accessed March 07, 2021. http://hdl.handle.net/10355/68835.

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

MLA Handbook (7^th Edition):

Alabsi, Mohammed. “In-Flight Learning Based Flight Control of an Unmanned Aircraft System.” 2018. Web. 07 Mar 2021.

Vancouver:

Alabsi M. In-Flight Learning Based Flight Control of an Unmanned Aircraft System. [Internet] [Thesis]. University of Missouri – Kansas City; 2018. [cited 2021 Mar 07]. Available from: http://hdl.handle.net/10355/68835.

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

Council of Science Editors:

Alabsi M. In-Flight Learning Based Flight Control of an Unmanned Aircraft System. [Thesis]. University of Missouri – Kansas City; 2018. Available from: http://hdl.handle.net/10355/68835

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

Rochester Institute of Technology

14. Komendat, Andrew. Center-of-gravity estimation of an aircraft solely using traditional aircraft measurement sensors.

Degree: Mechanical Engineering, 2012, Rochester Institute of Technology

URL: https://scholarworks.rit.edu/theses/195

► In this work, a novel algorithm for estimating aircraft center-of-gravity location based solely on traditional aircraft measurements is investigated. The algorithm uses known physics-based kinematic… (more)

Subjects/Keywords: Aircraft; Center of gravity; Estimation; Flight dynamics; Optimization; Simulation

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

APA (6^th Edition):

Komendat, A. (2012). Center-of-gravity estimation of an aircraft solely using traditional aircraft measurement sensors. (Thesis). Rochester Institute of Technology. Retrieved from https://scholarworks.rit.edu/theses/195

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):

Komendat, Andrew. “Center-of-gravity estimation of an aircraft solely using traditional aircraft measurement sensors.” 2012. Thesis, Rochester Institute of Technology. Accessed March 07, 2021. https://scholarworks.rit.edu/theses/195.

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

MLA Handbook (7^th Edition):

Komendat, Andrew. “Center-of-gravity estimation of an aircraft solely using traditional aircraft measurement sensors.” 2012. Web. 07 Mar 2021.

Vancouver:

Komendat A. Center-of-gravity estimation of an aircraft solely using traditional aircraft measurement sensors. [Internet] [Thesis]. Rochester Institute of Technology; 2012. [cited 2021 Mar 07]. Available from: https://scholarworks.rit.edu/theses/195.

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

Council of Science Editors:

Komendat A. Center-of-gravity estimation of an aircraft solely using traditional aircraft measurement sensors. [Thesis]. Rochester Institute of Technology; 2012. Available from: https://scholarworks.rit.edu/theses/195

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

California State University – Sacramento

15. Watt, Christian. Basic interchangeability of flight test methodology between remote controlled aircraft & full - scale aircraft.

Degree: MS, Mechanical Engineering, 2020, California State University – Sacramento

URL: http://hdl.handle.net/10211.3/217323

► Flight test methodology is often discussed regarding full-scale aircraft, leaving out the flight testing of model aircraft. Information on how to comprehensively conduct and analyze… (more)

Subjects/Keywords: Telemetry; Flight test; RC aircraft; Sawtooth climb; Determination of airspeeds

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APA (6^th Edition):

Watt, C. (2020). Basic interchangeability of flight test methodology between remote controlled aircraft & full - scale aircraft. (Masters Thesis). California State University – Sacramento. Retrieved from http://hdl.handle.net/10211.3/217323

Chicago Manual of Style (16^th Edition):

Watt, Christian. “Basic interchangeability of flight test methodology between remote controlled aircraft & full - scale aircraft.” 2020. Masters Thesis, California State University – Sacramento. Accessed March 07, 2021. http://hdl.handle.net/10211.3/217323.

MLA Handbook (7^th Edition):

Watt, Christian. “Basic interchangeability of flight test methodology between remote controlled aircraft & full - scale aircraft.” 2020. Web. 07 Mar 2021.

Vancouver:

Watt C. Basic interchangeability of flight test methodology between remote controlled aircraft & full - scale aircraft. [Internet] [Masters thesis]. California State University – Sacramento; 2020. [cited 2021 Mar 07]. Available from: http://hdl.handle.net/10211.3/217323.

Council of Science Editors:

Watt C. Basic interchangeability of flight test methodology between remote controlled aircraft & full - scale aircraft. [Masters Thesis]. California State University – Sacramento; 2020. Available from: http://hdl.handle.net/10211.3/217323

Cranfield University

16. Charpin, Jean P. F. Water flow on accreting ice surfaces.

Degree: PhD, 2002, Cranfield University

URL: http://dspace.lib.cranfield.ac.uk/handle/1826/10742 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.273526

► Ice growth may rapidly degrade the aerodynamic performance of an aircraft. It can also severely damage structures such as communication towers or power lines. Subsequently,… (more)

Subjects/Keywords: 629; Aircraft icing

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APA (6^th Edition):

Charpin, J. P. F. (2002). Water flow on accreting ice surfaces. (Doctoral Dissertation). Cranfield University. Retrieved from http://dspace.lib.cranfield.ac.uk/handle/1826/10742 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.273526

Chicago Manual of Style (16^th Edition):

Charpin, Jean P F. “Water flow on accreting ice surfaces.” 2002. Doctoral Dissertation, Cranfield University. Accessed March 07, 2021. http://dspace.lib.cranfield.ac.uk/handle/1826/10742 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.273526.

MLA Handbook (7^th Edition):

Charpin, Jean P F. “Water flow on accreting ice surfaces.” 2002. Web. 07 Mar 2021.

Vancouver:

Charpin JPF. Water flow on accreting ice surfaces. [Internet] [Doctoral dissertation]. Cranfield University; 2002. [cited 2021 Mar 07]. Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/10742 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.273526.

Council of Science Editors:

Charpin JPF. Water flow on accreting ice surfaces. [Doctoral Dissertation]. Cranfield University; 2002. Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/10742 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.273526

17. Ma, Liqun. Experimental investigations on bio-inspired surface coatings for aircraft icing mitigation.

Degree: 2019, Iowa State University

URL: https://lib.dr.iastate.edu/etd/17053

► Aircraft icing is widely recognized as a significant hazard to aircraft operations in cold weathers. Bio-inspired water- and ice-phobic coatings are currently being investigated for… (more)

▼ Aircraft icing is widely recognized as a significant hazard to aircraft operations in cold weathers. Bio-inspired water- and ice-phobic coatings are currently being investigated for use as viable strategies for aircraft in-flight icing mitigation. The objective of this study is to evaluate the anti-/de-icing performance of a number of bioinspired hydro-/ice-phobic coatings and explore their potentials for aircraft in-flight icing mitigation. In the present study, the bioinspired hydro-/ice-phobic coatings examined include the lotus-leaf-inspired super-hydrophobic surface (SHS), the pitcher-plant-inspired slippery liquid-infused porous surface (SLIPS) and the goose-feather-inspired textured surface. Firstly, a comprehensive experimental study was conducted to investigate the dynamics of impacting water droplets onto the test plates with SHS, SLIPS and goose feather surface, in comparison with that of over a conventional hydrophilic aluminum surface. A novel wind tunnel was built to accelerate the droplets to the Weber number up to 3,000, in the range relevant to aircraft in-flight icing phenomena. A high-speed, high-resolution system was used to reveal the droplet impact dynamics at the high Weber number regimes. Secondly, a new anti-/de-icing strategy with icephobic soft materials (e.g., made from PDMS gels) was also explored for aircraft anti-icing applications. The effects of surface stiffness on the dynamics of droplet impingement at high Weber numbers were investigated in great details. The soft surface was also applied to an airfoil/wing model to demonstrate its effectiveness for in-flight icing mitigation in the unique icing research tunnel of Iowa State University (i.e., ISU-IRT). Thirdly, the durability of various surface coatings due to spray erosion pertinent to aircraft icing mitigation scenario was also experimentally investigated and compared for the bio-inspired hydro-/ice-phobic surface coatings. Surface morphology, wettability, and ice adhesion strength were compared quantitatively after different spray erosion testing durations. A theoretic wettability-based lifetime model was developed following the Cumulative-Fatigue-Damage theory to predict the spray erosion characteristics of the bio-inspired hydro-/ice-phobic surface coatings. Fourthly, Particle Image Velocimetry (PIV) technique was used to measure the flow fields around wind-driven droplets on surfaces with various wettabilities. A theoretical model based on force balance analysis was developed to predict the critical wind speed which dislodges the droplet from the solid surface. Finally, wind-driven droplet motion on SLIPS was provided with more details by measuring the flow field inside and outside of the droplet simultaneously using the PIV technique. It showed that wind-driven droplet internal circulation is related to the droplet viscosity and it will influence the prediction of the droplet moving speed. The findings derived from this study could be very helpful to explore/optimize design paradigms for the development of innovative,…

Subjects/Keywords: Aircraft icing; Icephobic coatings; Aerospace Engineering

10 more images…

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APA (6^th Edition):

Ma, L. (2019). Experimental investigations on bio-inspired surface coatings for aircraft icing mitigation. (Thesis). Iowa State University. Retrieved from https://lib.dr.iastate.edu/etd/17053

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):

Ma, Liqun. “Experimental investigations on bio-inspired surface coatings for aircraft icing mitigation.” 2019. Thesis, Iowa State University. Accessed March 07, 2021. https://lib.dr.iastate.edu/etd/17053.

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

MLA Handbook (7^th Edition):

Ma, Liqun. “Experimental investigations on bio-inspired surface coatings for aircraft icing mitigation.” 2019. Web. 07 Mar 2021.

Vancouver:

Ma L. Experimental investigations on bio-inspired surface coatings for aircraft icing mitigation. [Internet] [Thesis]. Iowa State University; 2019. [cited 2021 Mar 07]. Available from: https://lib.dr.iastate.edu/etd/17053.

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

Council of Science Editors:

Ma L. Experimental investigations on bio-inspired surface coatings for aircraft icing mitigation. [Thesis]. Iowa State University; 2019. Available from: https://lib.dr.iastate.edu/etd/17053

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

Oklahoma State University

18. Avery, Alyssa Shearon. Ice Accretion on Small Unmanned Aircraft.

Degree: Mechanical and Aerospace Engineering, 2019, Oklahoma State University

URL: http://hdl.handle.net/11244/323357

► Aircraft icing is an important and complex problem. Small unmanned aerial systems are becoming increasingly common in high quality operations. The hazards of icing on… (more)

Subjects/Keywords: aircraft icing; heat transfer; unmanned systems

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APA (6^th Edition):

Avery, A. S. (2019). Ice Accretion on Small Unmanned Aircraft. (Thesis). Oklahoma State University. Retrieved from http://hdl.handle.net/11244/323357

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):

Avery, Alyssa Shearon. “Ice Accretion on Small Unmanned Aircraft.” 2019. Thesis, Oklahoma State University. Accessed March 07, 2021. http://hdl.handle.net/11244/323357.

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

MLA Handbook (7^th Edition):

Avery, Alyssa Shearon. “Ice Accretion on Small Unmanned Aircraft.” 2019. Web. 07 Mar 2021.

Vancouver:

Avery AS. Ice Accretion on Small Unmanned Aircraft. [Internet] [Thesis]. Oklahoma State University; 2019. [cited 2021 Mar 07]. Available from: http://hdl.handle.net/11244/323357.

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

Council of Science Editors:

Avery AS. Ice Accretion on Small Unmanned Aircraft. [Thesis]. Oklahoma State University; 2019. Available from: http://hdl.handle.net/11244/323357

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

University of Canterbury

19. Dey, Karla. Aviation human error modelled as a production process.

Degree: Mechanical Engineering, 2015, University of Canterbury

URL: http://hdl.handle.net/10092/10216

► As technology systems have become more complex, so it is increasingly difficult for human operators to comprehend how the system is behaving. There is a… (more)

Subjects/Keywords: aircraft pilot; production process; safety; sociotechnical interaction; systems engineering; Field of Research::09 - Engineering::0901 - Aerospace Engineering::090104 - Aircraft Performance and Flight Control Systems; Field of Research::17 - Psychology and Cognitive Sciences::1702 - Cognitive Science::170202 - Decision Making

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APA (6^th Edition):

Dey, K. (2015). Aviation human error modelled as a production process. (Thesis). University of Canterbury. Retrieved from http://hdl.handle.net/10092/10216

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):

Dey, Karla. “Aviation human error modelled as a production process.” 2015. Thesis, University of Canterbury. Accessed March 07, 2021. http://hdl.handle.net/10092/10216.

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

MLA Handbook (7^th Edition):

Dey, Karla. “Aviation human error modelled as a production process.” 2015. Web. 07 Mar 2021.

Vancouver:

Dey K. Aviation human error modelled as a production process. [Internet] [Thesis]. University of Canterbury; 2015. [cited 2021 Mar 07]. Available from: http://hdl.handle.net/10092/10216.

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

Council of Science Editors:

Dey K. Aviation human error modelled as a production process. [Thesis]. University of Canterbury; 2015. Available from: http://hdl.handle.net/10092/10216

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

University of Canterbury

20. Babu, Dinesh Kumar. Numerical Studies on Thrust Vectoring Using Shock- Induced Self Impinging Secondary Jets.

Degree: 2015, University of Canterbury

URL: http://hdl.handle.net/10092/101482

► Numerical studies have been carried out using a validated two-dimensional standard k-omega turbulence model for the design optimization of a thrust vector control system using… (more)

Subjects/Keywords: Fluidic thrust vectoring; rocket steering; self-impinging secondary supersonic jet; TVC in aerospace vehicles; Fields of Research::40 - Engineering::4001 - Aerospace engineering::400103 - Aircraft performance and flight control systems

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APA (6^th Edition):

Babu, D. K. (2015). Numerical Studies on Thrust Vectoring Using Shock- Induced Self Impinging Secondary Jets. (Thesis). University of Canterbury. Retrieved from http://hdl.handle.net/10092/101482

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):

Babu, Dinesh Kumar. “Numerical Studies on Thrust Vectoring Using Shock- Induced Self Impinging Secondary Jets.” 2015. Thesis, University of Canterbury. Accessed March 07, 2021. http://hdl.handle.net/10092/101482.

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

MLA Handbook (7^th Edition):

Babu, Dinesh Kumar. “Numerical Studies on Thrust Vectoring Using Shock- Induced Self Impinging Secondary Jets.” 2015. Web. 07 Mar 2021.

Vancouver:

Babu DK. Numerical Studies on Thrust Vectoring Using Shock- Induced Self Impinging Secondary Jets. [Internet] [Thesis]. University of Canterbury; 2015. [cited 2021 Mar 07]. Available from: http://hdl.handle.net/10092/101482.

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

Council of Science Editors:

Babu DK. Numerical Studies on Thrust Vectoring Using Shock- Induced Self Impinging Secondary Jets. [Thesis]. University of Canterbury; 2015. Available from: http://hdl.handle.net/10092/101482

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

Linköping University

21. Martinez, Anna. Design and manufacturing of a thrust measurement system for a micro jet engine : Enabling in-flight drag estimation for subscale aircraft testing.

Degree: Fluid and Mechatronic Systems, 2018, Linköping University

URL: http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-149288

► Good estimation of aerodynamic coefficients is of fundamental importance in the design and development process of an aircraft. Generally, these parameters are obtained using… (more)

Subjects/Keywords: thrust measurement; drag estimation; subscale aircraft; in-flight measurements; Engineering and Technology; Teknik och teknologier

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APA (6^th Edition):

Martinez, A. (2018). Design and manufacturing of a thrust measurement system for a micro jet engine : Enabling in-flight drag estimation for subscale aircraft testing. (Thesis). Linköping University. Retrieved from http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-149288

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):

Martinez, Anna. “Design and manufacturing of a thrust measurement system for a micro jet engine : Enabling in-flight drag estimation for subscale aircraft testing.” 2018. Thesis, Linköping University. Accessed March 07, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-149288.

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

MLA Handbook (7^th Edition):

Martinez, Anna. “Design and manufacturing of a thrust measurement system for a micro jet engine : Enabling in-flight drag estimation for subscale aircraft testing.” 2018. Web. 07 Mar 2021.

Vancouver:

Martinez A. Design and manufacturing of a thrust measurement system for a micro jet engine : Enabling in-flight drag estimation for subscale aircraft testing. [Internet] [Thesis]. Linköping University; 2018. [cited 2021 Mar 07]. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-149288.

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

Council of Science Editors:

Martinez A. Design and manufacturing of a thrust measurement system for a micro jet engine : Enabling in-flight drag estimation for subscale aircraft testing. [Thesis]. Linköping University; 2018. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-149288

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

University of Minnesota

22. Gupta, Abhineet. Flight Dynamics Model of A Small Flexible Aircraft.

Degree: PhD, Aerospace Engineering and Mechanics, 2019, University of Minnesota

URL: http://hdl.handle.net/11299/211757

► The presence of aeroservoelastic effects in the flight dynamics of flexible aircraft presents significant challenges in terms of performance degradation and instability. In order to… (more)

▼ The presence of aeroservoelastic effects in the flight dynamics of flexible aircraft presents significant challenges in terms of performance degradation and instability. In order to develop control system for such aircraft, an accurate flight dynamics model is needed. Developing such a model is an multi-disciplinary effort and re- quires theoretical and experimental knowledge and research. This thesis describes the development of the flight dynamics model of a small, flexible aircraft. Each step of the multi-stage process of the development of the flight dynamics model is described. The steps include designing and conducting vibration experiments on the aircraft for system identification of the structural dynamics and the devel- opment of a finite element model based structural model based on the acquired data. Aerodynamic models are developed and implemented using modifications of standard vortex and doublet lattice methods. The purpose of the modifications is to capture the geometric nonlinearity. The effects of these complex phenomena on the flight dynamics and instability (flutter) are analyzed. Mean axes based flight dynamics equations are utilized. These subcomponents are implemented in the simulation software SIMULINK to obtain the flight dynamics model. Flight tests are conducted to obtain data which is used to update the flight dynamics model by updating the aerodynamics model of the aircraft. A correction matrices based approach is used for this purpose. The resulting model has low computational cost but is capable of capturing complex behavior like geometric nonlinearities and un- steady aerodynamics. The low computational cost and modularity of the flight dynamics model makes it ideal for analysis of the effect of various kinds of aero- dynamics and structural phenomena. For example, the significant effects of the capturing the geometrically nonlinear aerodynamics on flutter characteristics of the aircraft are easily evaluated by this model without long, tedious and resource intensive computations. The model is also suitable for Monte-Carlo analysis to estimate the effect of various kinds of open-loop and closed-loop uncertainties.

Subjects/Keywords: Aeroelasticity; Flexible Aircraft; Flight Dynamics

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APA (6^th Edition):

Gupta, A. (2019). Flight Dynamics Model of A Small Flexible Aircraft. (Doctoral Dissertation). University of Minnesota. Retrieved from http://hdl.handle.net/11299/211757

Chicago Manual of Style (16^th Edition):

Gupta, Abhineet. “Flight Dynamics Model of A Small Flexible Aircraft.” 2019. Doctoral Dissertation, University of Minnesota. Accessed March 07, 2021. http://hdl.handle.net/11299/211757.

MLA Handbook (7^th Edition):

Gupta, Abhineet. “Flight Dynamics Model of A Small Flexible Aircraft.” 2019. Web. 07 Mar 2021.

Vancouver:

Gupta A. Flight Dynamics Model of A Small Flexible Aircraft. [Internet] [Doctoral dissertation]. University of Minnesota; 2019. [cited 2021 Mar 07]. Available from: http://hdl.handle.net/11299/211757.

Council of Science Editors:

Gupta A. Flight Dynamics Model of A Small Flexible Aircraft. [Doctoral Dissertation]. University of Minnesota; 2019. Available from: http://hdl.handle.net/11299/211757

Penn State University

23. Borigo, Cody J. A Novel Actuator Phasing Method for Ultrasonic De-icing of Aircraft Structures.

Degree: 2014, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/23379

► Aircraft icing is a critical concern for commercial and military rotorcraft and fixed-wing aircraft. In-flight icing can lead to dramatic decreases in lift and increases… (more)

▼ Aircraft icing is a critical concern for commercial and military rotorcraft and fixed-wing aircraft. In-flight icing can lead to dramatic decreases in lift and increases in drag that have caused more than a thousand deaths and hundreds of accidents over the past three decades alone. Current ice protection technologies have substantial drawbacks due to weight, power consumption, environmental concerns, or incompatibility with certain structures. In this research, an actuator phasing method for ultrasonic de-icing of aircraft structures was developed and tested using a series of finite element models, 3D scanning laser Doppler vibrometer measurements, and experimental de-icing tests on metallic and composite structures including plates and airfoils. An independent actuator analysis method was developed to allow for practical evaluation of many actuator phasing scenarios using a limited number of finite element models by properly calculating the phased stress fields and electromechanical impedance curves using a complex coupled impedance model. A genetic algorithm was utilized in conjunction with a series of finite element models to demonstrate that phase inversion, in which only in-phase and anti-phase signal components are applied to actuators, can be utilized with a small number of phasing combinations to achieve substantial improvements in de-icing system coverage. Finite element models of a 48”-long airfoil predicted that phase inversion with frequency sweeping can provide an improvement in the shear stress coverage levels of up to 90% compared to frequency sweeping alone. Experimental evaluation of the phasing approach on an icing grid showed a 189% improvement in de-icing coverage compared to frequency sweeping alone at comparable power levels. 3D scanning laser Doppler vibrometer measurements confirmed the increased variation in the surface vibration field induced by actuator phasing compared to unphased frequency sweeping. Additional contributions were made to facilitate actuator phasing and to advance the state-of-the-art in ultrasonic de-icing technology. These contributions include the development of improved frequency optimization, reduction in the size of the system hardware, and improvements in actuator bonding techniques. It was demonstrated that a dynamic frequency selection method is critical to effectively implementing the actuator phasing method. A miniaturized relay system was also designed and implemented to facilitate actuator phasing in conjunction with a phase splitter circuit and a single amplifier. An improved frequency tuning method was adopted and implemented in the de-icing system to eliminate the need for an impedance analyzer and to provide more accurate frequency selection by directly measuring the forward and reflected power between the amplifier and the de-icing actuators. Overall, it was demonstrated that this novel method can greatly improve the efficiency and effectiveness of the ultrasonic de-icing system by effectively redistributing the shear stress fields at the ice-structure… Advisors/Committee Members: Joseph Lawrence Rose, Dissertation Advisor/Co-Advisor, Joseph Lawrence Rose, Committee Chair/Co-Chair, Clifford Jesse Lissenden Iii, Committee Member, Bernhard R Tittmann, Committee Member, Edward C Smith, Committee Member.

Subjects/Keywords: de-icing; aircraft; ultrasound; ultrasonic; vibration; ice protection; anti-icing; phasing; piezoelectric

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APA (6^th Edition):

Borigo, C. J. (2014). A Novel Actuator Phasing Method for Ultrasonic De-icing of Aircraft Structures. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/23379

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):

Borigo, Cody J. “A Novel Actuator Phasing Method for Ultrasonic De-icing of Aircraft Structures.” 2014. Thesis, Penn State University. Accessed March 07, 2021. https://submit-etda.libraries.psu.edu/catalog/23379.

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

MLA Handbook (7^th Edition):

Borigo, Cody J. “A Novel Actuator Phasing Method for Ultrasonic De-icing of Aircraft Structures.” 2014. Web. 07 Mar 2021.

Vancouver:

Borigo CJ. A Novel Actuator Phasing Method for Ultrasonic De-icing of Aircraft Structures. [Internet] [Thesis]. Penn State University; 2014. [cited 2021 Mar 07]. Available from: https://submit-etda.libraries.psu.edu/catalog/23379.

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

Council of Science Editors:

Borigo CJ. A Novel Actuator Phasing Method for Ultrasonic De-icing of Aircraft Structures. [Thesis]. Penn State University; 2014. Available from: https://submit-etda.libraries.psu.edu/catalog/23379

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

Iowa State University

24. Kolbakir, Cem. Experimental investigations on thermodynamic characteristics of DBD plasma and applications for aircraft icing mitigation.

Degree: 2019, Iowa State University

URL: https://lib.dr.iastate.edu/etd/17721

► Aircraft icing is widely recognized as a significant hazard to aircraft operations. When an airplane flies in a cold climate, some of the super-cooled droplets… (more)

Subjects/Keywords: Aircraft Icing; Anti-Icing; DBD; Dielectric Barrier Discharge; Plasma Actuator; Aerospace Engineering

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APA (6^th Edition):

Kolbakir, C. (2019). Experimental investigations on thermodynamic characteristics of DBD plasma and applications for aircraft icing mitigation. (Thesis). Iowa State University. Retrieved from https://lib.dr.iastate.edu/etd/17721

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):

Kolbakir, Cem. “Experimental investigations on thermodynamic characteristics of DBD plasma and applications for aircraft icing mitigation.” 2019. Thesis, Iowa State University. Accessed March 07, 2021. https://lib.dr.iastate.edu/etd/17721.

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

MLA Handbook (7^th Edition):

Kolbakir, Cem. “Experimental investigations on thermodynamic characteristics of DBD plasma and applications for aircraft icing mitigation.” 2019. Web. 07 Mar 2021.

Vancouver:

Kolbakir C. Experimental investigations on thermodynamic characteristics of DBD plasma and applications for aircraft icing mitigation. [Internet] [Thesis]. Iowa State University; 2019. [cited 2021 Mar 07]. Available from: https://lib.dr.iastate.edu/etd/17721.

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

Council of Science Editors:

Kolbakir C. Experimental investigations on thermodynamic characteristics of DBD plasma and applications for aircraft icing mitigation. [Thesis]. Iowa State University; 2019. Available from: https://lib.dr.iastate.edu/etd/17721

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

University of Missouri – Kansas City

25. Tiemann, Christopher A. Viability and Validation of Near-Passive Descent Control for Quadrotor Systems.

Degree: 2020, University of Missouri – Kansas City

URL: http://hdl.handle.net/10355/74346

► A quadrotor unmanned aerial vehicle capable of lifting small payloads can be used to deliver small payloads from high altitudes rapidly and with high accuracy.… (more)

Subjects/Keywords: Drone aircraft; Guidance systems (Flight); Predictive control; Thesis – University of Missouri – Kansas City – Engineering

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APA (6^th Edition):

Tiemann, C. A. (2020). Viability and Validation of Near-Passive Descent Control for Quadrotor Systems. (Thesis). University of Missouri – Kansas City. Retrieved from http://hdl.handle.net/10355/74346

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):

Tiemann, Christopher A. “Viability and Validation of Near-Passive Descent Control for Quadrotor Systems.” 2020. Thesis, University of Missouri – Kansas City. Accessed March 07, 2021. http://hdl.handle.net/10355/74346.

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

MLA Handbook (7^th Edition):

Tiemann, Christopher A. “Viability and Validation of Near-Passive Descent Control for Quadrotor Systems.” 2020. Web. 07 Mar 2021.

Vancouver:

Tiemann CA. Viability and Validation of Near-Passive Descent Control for Quadrotor Systems. [Internet] [Thesis]. University of Missouri – Kansas City; 2020. [cited 2021 Mar 07]. Available from: http://hdl.handle.net/10355/74346.

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

Council of Science Editors:

Tiemann CA. Viability and Validation of Near-Passive Descent Control for Quadrotor Systems. [Thesis]. University of Missouri – Kansas City; 2020. Available from: http://hdl.handle.net/10355/74346

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

North Carolina State University

26. Burke, David Alexander. System Level Airworthiness Tool: A Comprehensive Approach to Small Unmanned Aircraft System Airworthiness.

Degree: PhD, Aerospace Engineering, 2010, North Carolina State University

URL: http://www.lib.ncsu.edu/resolver/1840.16/6267

► One of the pillars of aviation safety is assuring sound engineering practices through airworthiness certification. As Unmanned Aircraft Systems (UAS) grow in popularity, the need… (more)

Subjects/Keywords: Safety Engineering; System Engineering; Point Based Tool; Unmanned Aircraft Systems; Airworthiness; Safety of Flight

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APA (6^th Edition):

Burke, D. A. (2010). System Level Airworthiness Tool: A Comprehensive Approach to Small Unmanned Aircraft System Airworthiness. (Doctoral Dissertation). North Carolina State University. Retrieved from http://www.lib.ncsu.edu/resolver/1840.16/6267

Chicago Manual of Style (16^th Edition):

Burke, David Alexander. “System Level Airworthiness Tool: A Comprehensive Approach to Small Unmanned Aircraft System Airworthiness.” 2010. Doctoral Dissertation, North Carolina State University. Accessed March 07, 2021. http://www.lib.ncsu.edu/resolver/1840.16/6267.

MLA Handbook (7^th Edition):

Burke, David Alexander. “System Level Airworthiness Tool: A Comprehensive Approach to Small Unmanned Aircraft System Airworthiness.” 2010. Web. 07 Mar 2021.

Vancouver:

Burke DA. System Level Airworthiness Tool: A Comprehensive Approach to Small Unmanned Aircraft System Airworthiness. [Internet] [Doctoral dissertation]. North Carolina State University; 2010. [cited 2021 Mar 07]. Available from: http://www.lib.ncsu.edu/resolver/1840.16/6267.

Council of Science Editors:

Burke DA. System Level Airworthiness Tool: A Comprehensive Approach to Small Unmanned Aircraft System Airworthiness. [Doctoral Dissertation]. North Carolina State University; 2010. Available from: http://www.lib.ncsu.edu/resolver/1840.16/6267

27. Balogh, Shelby. Use Of FOQA Data To Estimate The Probability Of Vehicle Upset Or Loss Of Control In-Flight.

Degree: MS, Aviation, 2017, University of North Dakota

URL: https://commons.und.edu/theses/2099

► The leading cause of fatal aviation accidents worldwide remains loss of control in-flight, whereby control of the aircraft is lost or the aircraft enters… (more)

Subjects/Keywords: Aviation Safety; Loss of Control In-flight

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APA (6^th Edition):

Balogh, S. (2017). Use Of FOQA Data To Estimate The Probability Of Vehicle Upset Or Loss Of Control In-Flight. (Masters Thesis). University of North Dakota. Retrieved from https://commons.und.edu/theses/2099

Chicago Manual of Style (16^th Edition):

Balogh, Shelby. “Use Of FOQA Data To Estimate The Probability Of Vehicle Upset Or Loss Of Control In-Flight.” 2017. Masters Thesis, University of North Dakota. Accessed March 07, 2021. https://commons.und.edu/theses/2099.

MLA Handbook (7^th Edition):

Balogh, Shelby. “Use Of FOQA Data To Estimate The Probability Of Vehicle Upset Or Loss Of Control In-Flight.” 2017. Web. 07 Mar 2021.

Vancouver:

Balogh S. Use Of FOQA Data To Estimate The Probability Of Vehicle Upset Or Loss Of Control In-Flight. [Internet] [Masters thesis]. University of North Dakota; 2017. [cited 2021 Mar 07]. Available from: https://commons.und.edu/theses/2099.

Council of Science Editors:

Balogh S. Use Of FOQA Data To Estimate The Probability Of Vehicle Upset Or Loss Of Control In-Flight. [Masters Thesis]. University of North Dakota; 2017. Available from: https://commons.und.edu/theses/2099

Brno University of Technology

28. Rydlo, Tomáš. Druhy a metody zkoušení letadel: Technics and Methods of Aircraft Testing.

Degree: 2019, Brno University of Technology

URL: http://hdl.handle.net/11012/10580

► This bachelor´s thesis deals with processing of technics and methods of aircraft testing. Even the name shows that this theme is very demanding and extensive.… (more)

Subjects/Keywords: letadla; zkoušky letadel; metody zkoušení letadel; statické zkoušky; únavové zkoušky; letové zkoušky; aircraft; aircraft test; methods of aircraft testing; static test; fatigue test; flight test

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APA (6^th Edition):

Rydlo, T. (2019). Druhy a metody zkoušení letadel: Technics and Methods of Aircraft Testing. (Thesis). Brno University of Technology. Retrieved from http://hdl.handle.net/11012/10580

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):

Rydlo, Tomáš. “Druhy a metody zkoušení letadel: Technics and Methods of Aircraft Testing.” 2019. Thesis, Brno University of Technology. Accessed March 07, 2021. http://hdl.handle.net/11012/10580.

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

MLA Handbook (7^th Edition):

Rydlo, Tomáš. “Druhy a metody zkoušení letadel: Technics and Methods of Aircraft Testing.” 2019. Web. 07 Mar 2021.

Vancouver:

Rydlo T. Druhy a metody zkoušení letadel: Technics and Methods of Aircraft Testing. [Internet] [Thesis]. Brno University of Technology; 2019. [cited 2021 Mar 07]. Available from: http://hdl.handle.net/11012/10580.

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

Council of Science Editors:

Rydlo T. Druhy a metody zkoušení letadel: Technics and Methods of Aircraft Testing. [Thesis]. Brno University of Technology; 2019. Available from: http://hdl.handle.net/11012/10580

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

Baylor University

29. Tecson, Joshua Logan. Convective heat transfer from realistic ice roughness distributions.

Degree: M.S.M.E., Mechanical Engineering., 2013, Baylor University

URL: http://hdl.handle.net/2104/8757

► As supercooled water droplets impinge the surfaces of in-flight aircraft, a layer of accreted ice will form. In the initial stages of the accretion process,… (more)

Subjects/Keywords: Convective heat transfer.; Aircraft icing.; Ice roughness.; Surface roughness.

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APA (6^th Edition):

Tecson, J. L. (2013). Convective heat transfer from realistic ice roughness distributions. (Masters Thesis). Baylor University. Retrieved from http://hdl.handle.net/2104/8757

Chicago Manual of Style (16^th Edition):

Tecson, Joshua Logan. “Convective heat transfer from realistic ice roughness distributions.” 2013. Masters Thesis, Baylor University. Accessed March 07, 2021. http://hdl.handle.net/2104/8757.

MLA Handbook (7^th Edition):

Tecson, Joshua Logan. “Convective heat transfer from realistic ice roughness distributions.” 2013. Web. 07 Mar 2021.

Vancouver:

Tecson JL. Convective heat transfer from realistic ice roughness distributions. [Internet] [Masters thesis]. Baylor University; 2013. [cited 2021 Mar 07]. Available from: http://hdl.handle.net/2104/8757.

Council of Science Editors:

Tecson JL. Convective heat transfer from realistic ice roughness distributions. [Masters Thesis]. Baylor University; 2013. Available from: http://hdl.handle.net/2104/8757

30. Triphahn, Christopher. Lagrangian Parcel Volume method applied to icing surfaces to predict impact efficiency.

Degree: MS, 4048, 2012, University of Illinois – Urbana-Champaign

URL: http://hdl.handle.net/2142/42376

► When trying to predict how and where ice will accrete on an aircraft, engineers first need to be able to track the path and concentration… (more)

▼ When trying to predict how and where ice will accrete on an aircraft, engineers first need to be able to track the path and concentration of water particles; this will allow for a better representation of water impingement and ice accretion. This tracking can be accomplished by using either a Lagrangian computational method, which tracks particle paths with no diffusion, or an Eulerian computational method, which uses a partial differential equation to calculate concentrations with high efficiency. The current study expands upon previous work which developed a new Lagrangian computational method, called the Lagrangian Parcel Volume (LPV) method. The LPV method uses Lagrangian particle trajectories which define a parcel’s volume to compute particle concentration. The change in particle concentration (particle volume per mixed-fluid volume) can be determined directly by comparing the final volume of a parcel to its initial value. Previous investigations with the LPV method found that it provides accurate and efficient results when compared with other computational techniques. A two-dimensional (2-D) unsteady potential cylinder flow was used for most predictions. In chapter I of this study, different aspects of the LPV method’s computational makeup were investigated for impact efficiency predictions. These studies included parcel shape definition, varying the number of parcels released in a given simulation, using a non-linear drag model for particle trajectory calculations, and also, varying the timestep used in simulations. Futher studies performed investigated the effects on impact efficiency due to unsteady flow oscillations and polydisperse particle distributions. LPV impact efficiency predictions on the clean two-dimensional four inch cylinder were found to agree well with experimental data. iii In chapter II of this study, the LPV method was further expanded by implementing a new type of flowfield into the code: Large Eddy Simulations (LES). LES flowfields are needed to describe upstream unsteadiness and flow separation for complex geometries. Two geometries were studied in these LES simulations: a clean four inch diameter cylinder and a large glaze ice model (mounted on a two inch diameter cylinder). Impact efficiency predictions for both geometries were found to agree well with experimental data. This research demonstrates the LPV method can be used for both potential and LES flowfields while displaying high accuracy and efficiency. Advisors/Committee Members: Loth, Eric (advisor).

Subjects/Keywords: Impact Efficiency; Aircraft Icing

…Aircraft icing is a major concern during the development of new aircraft components such as… …cause severe decreases in the performance, stability, and controllability of the aircraft. The… …on the surface. To better understand icing phenomena, representations of spatial and… …phase of the development process are, however, computationally intensive. Prediction… …interaction effects, such as particle collisions, coalescence, and breakup. In addition, use of the…

10 more images…

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APA (6^th Edition):

Triphahn, C. (2012). Lagrangian Parcel Volume method applied to icing surfaces to predict impact efficiency. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/42376

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):

Triphahn, Christopher. “Lagrangian Parcel Volume method applied to icing surfaces to predict impact efficiency.” 2012. Thesis, University of Illinois – Urbana-Champaign. Accessed March 07, 2021. http://hdl.handle.net/2142/42376.

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

MLA Handbook (7^th Edition):

Triphahn, Christopher. “Lagrangian Parcel Volume method applied to icing surfaces to predict impact efficiency.” 2012. Web. 07 Mar 2021.

Vancouver:

Triphahn C. Lagrangian Parcel Volume method applied to icing surfaces to predict impact efficiency. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2012. [cited 2021 Mar 07]. Available from: http://hdl.handle.net/2142/42376.

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

Council of Science Editors:

Triphahn C. Lagrangian Parcel Volume method applied to icing surfaces to predict impact efficiency. [Thesis]. University of Illinois – Urbana-Champaign; 2012. Available from: http://hdl.handle.net/2142/42376

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

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Open Access Theses and Dissertations