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Dissertations / Theses on the topic 'Aircraft icing'

Author: Grafiati

Published: 4 June 2021

Last updated: 26 July 2025

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1

Ma, Qinglin. "Aircraft icing and thermo-mechanical expulsion de-icing technology." Thesis, Cranfield University, 2010. http://dspace.lib.cranfield.ac.uk/handle/1826/12478.

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The topic of this thesis is Aircraft Icing and Aircraft Icing and Thermo-Mechanical Expulsion De-icing Technology. The main objectives are to investigate aircraft icing meteorology and effects on aircraft, ice protection systems and thermo-mechanical expulsion de-icing technology. Initially, the research project focuses on aircraft icing meteorology, ice accumulation and icing effects on flight safety. A basic understanding of aircraft icing is explained, including icing conditions and parameters, ice detection, ice accretion shapes, and icing effects in terms of different airframe surfaces. I

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2

Wang, Yuchen. "Development of improved aircraft de-icing fluids." Thesis, University of Strathclyde, 2013. http://oleg.lib.strath.ac.uk:80/R/?func=dbin-jump-full&object_id=25541.

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3

Turcotte, François A. "A method for aircraft icing diagnosis in precipitation /." Thesis, McGill University, 1994. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=55400.

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A study of feasibility is performed for the development of a nowcasting method of aircraft icing conditions. The supercooled cloud water content is a key parameter for the determination of hazardous regions. The production of supercooled water in clouds is possible only where sufficiently strong updraft produces supersaturation with respect to water. However, to maintain the presence of supercooled droplets, the generation of moisture excess during the air uplift must exceed the rate of vapor deposition on snow and the rate of snow riming. The "storm of the century" (March 13-14, 1993) has bee

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4

Matheis, Brian Daniel. "Numerical investigation of roughness effects in aircraft icing calculations." [Ames, Iowa : Iowa State University], 2008.

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5

Leese, Graeme Neil. "On the accretion of ice on aircraft." Thesis, University of Cambridge, 2011. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.609639.

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6

Charpin, Jean P. F. "Water flow on accreting ice surfaces." Thesis, Cranfield University, 2002. http://dspace.lib.cranfield.ac.uk/handle/1826/10742.

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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, de-icing and anti-icing systems have been developed and a number of codes designed to predict ice shapes. When ice accretion starts, two different types of ice can appear, depending on the temperature and conditions. All of the incoming fluid may freeze almost instantaneously and turn into rime ice. Alternatively, a fraction of the incoming fluid may freeze and turn into glaze ice while the other part remains liquid and may

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7

Zeppetelli, Danial. "Computational fluid dynamics icing analysis: a predictive approach to in-flight icing risk management and aircraft certification." Thesis, McGill University, 2011. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=104598.

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In-flight icing is a hazard that continues to afflict the aviation industry, despite all the research and efforts to mitigate the risks. The recurrence of these types of accidents has given renewed impetus to the development of advanced analytical predictive tools to study both the accretion of ice on aircraft components in flight, and the aerodynamic consequences of such ice accumulations. In this work, an in-depth analysis of the occurrence of in-flight icing accidents and incidents was conducted to identify high-risk flight conditions. To investigate these conditions more thoroughly, a comp

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8

Erdogan, Baris. "Production And Development Of De/anti Icing Fluids For Aircraft." Master's thesis, METU, 2008. http://etd.lib.metu.edu.tr/upload/3/12609926/index.pdf.

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Aircraft are not allowed to take off prior to cleaning of snow and ice deposits that form on their surfaces under winter conditions to refrain from compromising flight safety. Water based solutions containing mainly ethylene or propylene glycol, or both, are employed either to remove the snow/ice layers or to provide protection against deposition of these layers. The first group of solutions, i.e. de-icing fluids, are Newtonian and have generally low viscosity so that right after their application they fall off the aircraft surfaces, providing little or no further protection against precipitat

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9

Pellissier, Mathieu. "Optimization via CFD of aircraft hot-air anti-icing systems." Thesis, McGill University, 2010. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=95154.

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In-flight icing is a major concern in aircraft safety and a non-negligible source of incidents and accidents, and is still a serious hazard today. It remains consequently a design and certification challenge for aircraft manufacturers. The aerodynamic performance of an aircraft can indeed degrade rapidly when flying in icing conditions, leading to incidents or accidents. In-flight icing occurs when an aircraft passes through clouds containing supercooled water droplets at or below freezing temperature. Droplets impinge on its exposed surfaces and freeze, causing roughness and shape changes tha

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10

Anderson, Harry. "Stability effects of heat and mass transfer on thin liquid films." Thesis, Cranfield University, 2002. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.250500.

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11

Jimenez, Andrew Enrique. "Design and Analysis of a Novel Deformed Skin Adhesion for Aircraft Icing." Case Western Reserve University School of Graduate Studies / OhioLINK, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=case1619781381968283.

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12

Gates, Melinda M. "The Effect of Icing on the Dispatch Reliability of Small Aircraft." Thesis, Virginia Tech, 2004. http://hdl.handle.net/10919/35946.

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In 2000, the National Aeronautics and Space Administration (NASA) initiated a program to promote the use of small aircraft as an additional option for national public transportation. The Small Aircraft Transportation System (SATS) asserted the idea of everyday individuals piloting themselves on trips, within a specified distance range, using a small (4 person), piston powered, un-pressurized aircraft and small airports in close proximity to their origin and destination. <p>This thesis investigates how one weather phenomenon, in-flight icing, affects the dispatch reliability of this transport

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13

Korpe, Durmus Sinan. "Development Of De-icing And Anti-icing Solutions For Aircraft On Ground And Analysis Of Their Flow Instability Characteristics." Master's thesis, METU, 2008. http://etd.lib.metu.edu.tr/upload/3/12609968/index.pdf.

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In this thesis, development process of de-icing and anti-icing solutions and their flow instability characteristics are presented. In the beginning, the chemical additives in the solutions and their effects on the most critical physical properties of the solutions were investigated. Firstly, chemical additives were added to glycol and water mixtures at different weight ratios one by one in order to see their individual effects. Then, the changes in physical properties were observed when the chemicals were added to water-glycol mixture together. After that, study was focused on effect of polyme

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14

Wang, Hong Zhi 1971. "3D conjugate heat transfer simulation of aircraft hot-air anti-icing systems." Thesis, McGill University, 2005. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=83942.

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When an aircraft flies through clouds under icy conditions, supercooled water droplets at temperatures below the freezing point may impact on its surfaces and result in ice accretion. The design of efficient devices to protect aircraft against in-flight icing continues to be a challenging task in the aerospace industry. Advanced numerical tools to simulate complex conjugate heat transfer phenomena associated with hot-air anti-icing are needed. In this work, a 3D conjugate heat transfer procedure based on a loose-coupling method has been developed to solve the following four domains: the

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15

Alexander, Jeremy Brandon. "Enhancement of the daytime GOES-based aircraft icing potential algorithm using MODIS." Thesis, Monterey California. Naval Postgraduate School, 2005. http://hdl.handle.net/10945/2326.

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Approved for public release, distribution is unlimited<br>In this thesis, a fuzzy logic algorithm is developed for the detection of potential aircraft icing conditions using the Moderate-Resolution Imaging Spectroradiometer (MODIS). The fuzzy MODIS algorithm is developed in a manner similar to the cloud mask currently used to process MODIS imagery. The MODIS icing potential detection algorithm uses thresholds for 8 channels in a series of 12 tests to determine the probability of icing conditions being present within a cloud. The MODIS algorithm results were compared to results of the GOES icin

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Alexander, Jeremy B. "Enhancement of the daytime goes-based aircraft icing potential algorithm using MODIS /." Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2005. http://library.nps.navy.mil/uhtbin/hyperion/05Mar%5FAlexander.pdf.

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17

Riley, S. J. "Investigations relating to factors influencing the effectiveness of an aero-engine intake thermal anti-icing system." Thesis, Loughborough University, 1991. https://dspace.lboro.ac.uk/2134/7201.

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Thermal anti-icing systems are commonly used to protect aircraft leading edges from a potentially hazardous build-up of ice. Such systems have proven reliable in service and are relatively cheap and efficient. Typically, hot air is tapped from the engine compressor and ducted (via a regulation and control system) to the surface to be protected. Ideally an optimisation process should be employed at the design stage in order to ensure adequate anti-icing capability with minimal use of engine bleed air, since the latter represents a performance penalty. Following submission by the author of an MS

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18

Antonini, C. "Superhydrophobicity as a strategy against icing. Analysis of the water/surface dynamic interaction for icing mitigation." Doctoral thesis, Università degli Studi di Bergamo, 2011. http://hdl.handle.net/10281/222265.

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The thesis illustrates the efforts made to proof how water repellent surfaces can help reducing ice accretion in icing conditions: tests performed in an icing wind tunnel showed that application of superhydrophobic coatings allow considerable savings in supplied heating power, necessary to keep an aerodynamic wing clean from ice, and reduce runback ice, which often forms in unprotected areas. The present thesis is the result of a three year research study, aimed at understanding the potential of superhydrophobicity for combating icing accretion on aircrafts. The project was performed in the f

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19

Andersson, Daniel. "The performance of an iced aircraft wing." Thesis, Högskolan Väst, Institutionen för ingenjörsvetenskap, 2011. http://urn.kb.se/resolve?urn=urn:nbn:se:hv:diva-4098.

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The goal of this thesis work has been to develop and manufacture an ice layer which was to be mounted on the tip of a scaled down wing model. The iced wing should be tested in a wind tunnel and aerodynamic comparisons should be made to the same wing without ice.The development of the ice was carried out as a modified product development process. The main differences are that there is no costumer and that the actual shape and functions of the product are more or less predetermined. The challenge was to find the best way to create the ice layer and how to mount it to the wing without damaging it

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20

Cooper, Michael J. "Enhancement of the daytime MODIS based aircraft icing potential algorithm using mesoscale model data." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2006. http://library.nps.navy.mil/uhtbin/hyperion/06Mar%5FCooper.pdf.

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Thesis (M.S. in Physical Oceanography and Meteorology)--Naval Postgraduate School, March 2006.<br>Thesis Advisor(s): Philip Durkee, Carlyle Wash. "March 2006." Includes bibliographical references (p. 49-51). Also available online.

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ANTONINI, Carlo. "Superhydrophobicity as a strategy against icing. Analysis of the water/surface dynamic interaction for icing mitigation." Doctoral thesis, Università degli studi di Bergamo, 2011. http://hdl.handle.net/10446/881.

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The thesis illustrates the efforts made to proof how water repellent surfaces can help reducing ice accretion in icing conditions: tests performed in an icing wind tunnel showed that application of superhydrophobic coatings allow considerable savings in supplied heating power, necessary to keep an aerodynamic wing clean from ice, and reduce runback ice, which often forms in unprotected areas. The present thesis is the result of a three year research study, aimed at understanding the potential of superhydrophobicity for combating icing accretion on aircrafts. The project was performed in the f

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ANTONINI, Carlo. "Superhydrophobicity as a strategy against icing. Analysis of the water/surface dynamic interaction for icing mitigation." Doctoral thesis, Università degli studi di Bergamo, 2011. http://hdl.handle.net/10446/222126.

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The thesis illustrates the efforts made to proof how water repellent surfaces can help reducing ice accretion in icing conditions: tests performed in an icing wind tunnel showed that application of superhydrophobic coatings allow considerable savings in supplied heating power, necessary to keep an aerodynamic wing clean from ice, and reduce runback ice, which often forms in unprotected areas. The present thesis is the result of a three year research study, aimed at understanding the potential of superhydrophobicity for combating icing accretion on aircrafts. The project was performed in the fr

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23

Schroll, Susanne. "Experimental investigation of contamination and adhesion failure of type II aircraft ground de-icing fluids." Thesis, Massachusetts Institute of Technology, 1995. http://hdl.handle.net/1721.1/47389.

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24

Shinkafi, A. "Development of a method to study aircraft trajectory optimisation in the presence of icing conditions." Thesis, Cranfield University, 2015. http://dspace.lib.cranfield.ac.uk/handle/1826/10154.

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There is a growing demand for new technologies and ight procedures that will enable aircraft operators to burn less fuel and reduce the impacts of aviation on the environment. Conventional approaches to trajectory optimisation do not include aircraft systems in the optimisation set-up. However, the fuel penalty due to aircraft systems operation is signi cant. Thus, applying optimised trajectories which do not account for systems o -takes in real aircraft Flight Management System (FMS) will likely fail to achieve a true optimum. This is more important in real scenarios where the ambient condit

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25

Anagnostakis, Ioannis. "Experimental investigations of physical factors which influence runoff and failure behavior of aircraft de-icing fluids." Thesis, Massachusetts Institute of Technology, 1994. http://hdl.handle.net/1721.1/49934.

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26

Insana, Eric J. "Low Reynolds Number Experimental Aerodynamic Verification of Scaled and LEWICE Simulated Ice Accretions in SLD Conditions." University of Dayton / OhioLINK, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1597082782224451.

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27

Alzaili, Jafar S. L. "Semi-empirical approach to characterize thin water film behaviour in relation to droplet splashing in modelling aircraft icing." Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/7849.

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Modelling the ice accretion in glaze regime for the supercooled large droplets is one of the most challenging problems in the aircraft icing field. The difficulties are related to the presence of the liquid water film on the surface in the glaze regime and also the phenomena associated with SLD conditions, specifically the splashing and re-impingement. The steady improvement of simulation methods and the increasing demand for highly optimised aircraft performance, make it worthwhile to try to get beyond the current level of modelling accuracy. A semi-empirical method has been presented to char

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28

Zima, Martin. "CFD analýza tvorby námrazy na letounu kategorie commuter." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2019. http://www.nusl.cz/ntk/nusl-400828.

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The Diploma Thesis concerns investigation of icing effects at L 410 NG aircraft. The aircraft is certified under FAR/CS/AP-23 Commuter category. An analysis was performed for existing Pneumatic De-icing Boots System at the wing area according to three flight configurations and icing conditions referring to document Part 25 Appendix C and O. The analysis was done by CFD solver FENSAP-ICE for various runs with respect to the icing envelope. Cases were assigned as two 2D cross-sections situated at the aircraft’s wing aileron part. Cross-sectional Reynold’s number oscillate between 4.5–8.5×106. Au

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29

Marklund, Lars. "Flygplansavisningens miljöpåverkan vid svenska flygplatser." Thesis, Uppsala University, Department of Earth Sciences, 2004. http://urn.kb.se/resolve?urn=urn:nbn:se:uu:diva-88865.

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<p>The aim of this thesis was to answer a number of questions about the environmental consequences of aircraft de-icing. A further aim was to suggest how the environmental consequences due to the release of de-icing fluids can be measured and reduced.</p><p>The main impact of the aircraft de-icing on the environment is due to the large oxygen demand for the degradation of glycol based de-icing fluids which are released in the environment. The effect of the increase in oxygen demand depends on where the degradation occurs in the ecosystem. In a sensitive ecosystem, the large demand of oxygen co

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Luxford, Geoffrey. "Experimental and modelling investigation of the deformation, drag and break-up of drizzle droplets subjected to strong aerodynamics forces in relation to SLD aircraft icing." Thesis, Cranfield University, 2005. http://hdl.handle.net/1826/945.

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The distortion, drag and break-up of drizzle droplets subjected to strong aerodynamic forces was investigated to understand the pre-impact behaviour of droplets in aircraft icing from supercooled freezing drizzle. The objective was to obtain a formulation and data for the drag properties of droplets distorted by the aerodynamic forces, which were beyond the scope of available experimental and modelling methods. A practical and efficient semi-empirical computer model was developed for small water droplets in air, 100Î¼m < D < 500Î¼m, at moderate Reynolds numbers, 350 < Re < 1500, and high Weber

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31

Pena, Dorian. "Développement d'un code de givrage tridimensionnel avec méthode Level-Set." Thesis, Strasbourg, 2016. http://www.theses.fr/2016STRAD014/document.

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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 : u

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32

Silva, Guilherme Araújo Lima da. "Transferência de calor e massa no escoamento bifásico em torno de aerofólios equipados com sistemas de antigelo aeronáuticos." Universidade de São Paulo, 2009. http://www.teses.usp.br/teses/disponiveis/3/3150/tde-27032009-082825/.

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Há a necessidade de prevenir formação de gelo nas asas e nos estabilizadores de aeronaves, pois as formas de gelo podem causar a degradação do desempenho aerodinâmico, o aumento de peso, bem como dificuldades de controle e manobra que, em casos críticos, leva a uma diminuição da margem de segurança operacional. Quando as aeronaves atravessam nuvens com gotículas de água sub-resfriadas, ou seja, em equilíbrio metaestável, o crescimento de gelo ocorre nas superfícies não protegidas. Usualmente, os sistemas antigelo térmicos de aerofólios são projetados, desenvolvidos e certificados com o auxílio

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33

Silva, Guilherme Araújo Lima da. "Modelagem e simulação da operação de sistema antigelo eletrotérmico de um aerofólio." Universidade de São Paulo, 2002. http://www.teses.usp.br/teses/disponiveis/3/3132/tde-19092007-000212/.

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No presente trabalho foi implementado um modelo matemático para simular o sistema antigelo eletrotérmico de um aerofólio. Por meio do programa ONERA2D simulou-se o escoamento potencial completo com velocidade 44,7 m/s (100 mph) e 89,4 m/s (200 mph) em torno de um aerofólio perfil NACA0012 de corda 0,914 m (3 pés) com ângulo de ataque de 0°, e calculou-se a eficiência de coleta local de gotículas de água com diâmetro mediano volumétrico de 20 μm. Foram simuladas quatro condições de teste com diferentes distribuições de fluxo de calor nos aquecedores elétricos do sistema antigelo. O modelo

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34

Шмирьов, Володимир Федорович, та Volodymyr Fedorovych Shmyrov. "Наукові основи проектування та створення енергозалежних систем літаків транспортної категорії". Thesis, Національний авіаційний університет, 2020. https://er.nau.edu.ua/handle/NAU/44724.

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Дисертаційну роботу присвячено розробці наукових основ проектування та створення енергозалежних систем та комплексів сучасних літаків транспортної категорії з оптимізацією за еквівалентною масою, включаючи повітрозбірники. Закладено наукові основи проектування систем протиобмерзання літаків, починаючи від визначення зон захисту, потрібних енергетичних витрат і закінчуючи проектуванням протиобмерзачів і повітряних трубопроводів для всього експлуатаційного діапазону застосування літака. Наведено приклади використання розроблених наукових основ проектування при виконанні структурного аналізу мод

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35

Wang, Hsuan-Wei, and 王璿瑋. "The Simulation and Diagnosis of Aircraft Icing." Thesis, 2010. http://ndltd.ncl.edu.tw/handle/94668089339392499825.

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碩士<br>國立臺灣大學<br>大氣科學研究所<br>98<br>Icing plays a significant role in the issue of fight safety, and it’s also an important issue of microphysical observation and model simulation in meteorology. In the literatures, the current icing forecasting and warning system only use temperature and relative humidity parameters. But the over-prediction of the spatial extent of aircraft icing has reduced the reference for flight path planning. Some research found Icing intensity can deduce from estimation of liquid water content (LWC), and the U.S. NOAA/NWS icing forecasting production for United States Rout

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Smith-Cunningham, Sandra L. "Aircraft de-icing/anti-icing fluid (ADAF)-laden wastewater evaluation and recommendations for its treatment and regulation /." 2008. http://proquest.umi.com/pqdweb?did=1537011201&sid=1&Fmt=2&clientId=39334&RQT=309&VName=PQD.

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Thesis (M.S.)--State University of New York at Buffalo, 2008.<br>Title from PDF title page (viewed on Dec. 1, 2008) Available through UMI ProQuest Digital Dissertations. Thesis adviser: Jensen, James N. Includes bibliographical references.

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37

De, Rosa Francesco. "Electrically heated composite leading edges for aircraft anti-icing applications." Tesi di dottorato, 2010. http://www.fedoa.unina.it/8354/1/DE_ROSA_FRANCESCO_23.pdf.

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An investigation was conducted in the Aerospace Engineering Department (DIAS) at Federico II University of Naples aiming to evaluate the feasibility and the performance of an electrically heated composite leading edge for anti-icing and de-icing applications. A 283 [mm] chord NACA0012 airfoil prototype was designed, manufactured and equipped with an High Temperature composite leading edge with embedded Ni-Cr heating element. The heating element was fed by a DC power supply unit and the average power densities supplied to the leading edge were ranging 1.0 to 30.0 [kW m-2]. The present investiga

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