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Journal articles on the topic 'Engine icing'

Author: Grafiati

Published: 4 June 2021

Last updated: 1 February 2022

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1

Bartlett, C. S. "Turbine Engine Icing Spray Bar Design Issues." Journal of Engineering for Gas Turbines and Power 117, no. 3 (1995): 406–12. http://dx.doi.org/10.1115/1.2814110.

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Techniques have been developed at the Engine Test Facility (ETF) of the Arnold Engineering Development Center (AEDC) to simulate flight through atmospheric icing conditions of supercooled liquid water droplets. Ice formed on aircraft and propulsion system surfaces during flight through icing conditions can, even in small amounts, be extremely hazardous. The effects of ice are dependent on many variables and are still unpredictable. Often, experiments are conducted to determine the characteristics of the aircraft and its propulsion system in an icing environment. Facilities at the ETF provide t

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2

Yamazaki, Masafumi, Aleksandar Jemcov, and Hirotaka Sakaue. "A Review on the Current Status of Icing Physics and Mitigation in Aviation." Aerospace 8, no. 7 (2021): 188. http://dx.doi.org/10.3390/aerospace8070188.

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Icing on an aircraft is the cause of numerous adverse effects on aerodynamic performance. Although the issue was recognized in the 1920s, the icing problem is still an area of ongoing research due to the complexity of the icing phenomena. This review article aims to summarize current research on aircraft icing in two fundamental topics: icing physics and icing mitigation techniques. The icing physics focuses on fixed wings, rotors, and engines severely impacted by icing. The study of engine icing has recently become focused on ice-crystal icing. Icing mitigation techniques reviewed are based o

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3

MA, HUI, WEIJIAN CHEN, and DALIN ZHANG. "NUMERICAL INVESTIGATION OF ENGINE INLET VANE HOT–AIR ANTI–ICING SYSTEM WITH SURFACE AIR FILM." International Journal of Modern Physics: Conference Series 19 (January 2012): 331–40. http://dx.doi.org/10.1142/s2010194512008926.

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The inlet vane of aircraft engine needs to be equipped with anti-icing system to prevent ice accretion on the leading edge due to flight safety requirements, and the engine bleed hot-air is mostly used to heat the vane surface in anti-icing system. In order to save the energy consumption, a new anti-icing structure was developed and investigated with numerical simulation. Besides the use of small tunnels to enhance the heat transfer characteristics, a narrow gap was opened and assigned on the vane surface at the end of the anti-icing tunnels, and the exhaust hot-air was released from the gap t

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4

Dong, W., J. Zhu, M. Zheng, G. L. Lei, and Z. X. Zhou. "Experimental Study on Icing and Anti-Icing Characteristics of Engine Inlet Guide Vanes." Journal of Propulsion and Power 31, no. 5 (2015): 1330–37. http://dx.doi.org/10.2514/1.b35679.

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5

Gębura, Andrzej, Kazimierz Janusiak, and Michał Poradowski. "An Icing Of Aircraft – Reasons, Consequences, Counteraction." Journal of KONBiN 32, no. 1 (2014): 57–70. http://dx.doi.org/10.2478/jok-2014-0031.

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Abstract The article presents reasons of an helicopter’s ising as well as an aircraft’s ising. The maion attention is addressed a conteraction of an ising. Autors divide the problem an two groups: an ising of an airframe – mostly lifting surfaces, an ising of engines. According to authors reasons, an extension (first of all) consequences of airframe’s ising considerably differ from seemingly similar events in an engine. The considerable attention is concentrated on a connteraction of consequences of an ising during the flight. The most complicated ising referes to helicopters, considering thei

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6

Jérôme, Emilie, Franck Hervy, and Séverine Maguis. "Icing test capabilities at DGA Aero-engine Testing." International Journal of Engineering Systems Modelling and Simulation 8, no. 2 (2016): 77. http://dx.doi.org/10.1504/ijesms.2016.075562.

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7

Al-Khalil, Kamel M., Theo G. Keith, Kenneth J. DeWitt, James K. Nathman, and Donald A. Dietrich. "Thermal analysis of engine inlet anti-icing systems." Journal of Propulsion and Power 6, no. 5 (1990): 628–34. http://dx.doi.org/10.2514/3.23264.

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8

HAYASHI, Ryosuke, and Makoto YAMAMOTO. "Modelling of ice shedding phenomenon for engine fan icing." Transactions of the JSME (in Japanese) 80, no. 815 (2014): CM0209. http://dx.doi.org/10.1299/transjsme.2014cm0209.

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9

Haggerty, Julie, Eric Defer, Adrianus De Laat, et al. "Detecting Clouds Associated with Jet Engine Ice Crystal Icing." Bulletin of the American Meteorological Society 100, no. 1 (2019): 31–40. http://dx.doi.org/10.1175/bams-d-17-0252.1.

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AbstractIn the past two decades, more than 150 jet engine power-loss and damage events have been attributed to a phenomenon known as ice crystal icing (ICI). Ingestion of large numbers of ice particles into the engine core are thought to be responsible for these events, which typically occur at high altitudes near large convective systems in tropical air masses. In recent years, scientists, engineers, aviation regulators, and airlines from around the world have collaborated to better understand the relevant meteorological processes associated with ICI events, solve critical engineering problem

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10

Simpson, M. P., and P. M. Render. "Investigation of the certification and operational procedures for turboprop aircraft in icing." Aeronautical Journal 103, no. 1028 (1999): 449–54. http://dx.doi.org/10.1017/s0001924000064393.

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Abstract A study was conducted to identify possible improvements to the current certification and operational procedures for turboprop powered aircraft operating in icing conditions. Information was gathered through a series of interviews with airframe and engine manufacturers and also, operators and aircrews in Europe and Canada. The significant issues raised during the interviews are discussed, and a number of recommendations are made for future research and development activities in die area of aircraft icing. These recommendations identify the need for improved ice protection methods, enha

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11

Zhang, Fei, Lifen Zhang, Yundan Li, Zhenxia Liu, and Pengfei Zhu. "Experimental investigation of the icing scaling test method for a rotating cone." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 9 (2018): 3368–80. http://dx.doi.org/10.1177/0954410018796037.

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One of the reliable methods of studying engine icing is to carry out testing in an icing wind tunnel. Due to the operational limitations of test facility, model-size scaling is adopted. An icing scaling test method for the rotating cone is established based on the dimensional analysis coupled with similarity theory and evaluated by considering the rotating effect. Similarity parameters are determined in the following five aspects: flow field similarity, droplet trajectory similarity, water catch similarity, heat balance similarity, and rotating characteristics similarity. Experimental icing te

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12

TAN, Yan, and Wuguo WEI. "Numerical Study of Super-cooled droplet impingement on Aeroengine." Mechanics 26, no. 1 (2020): 25–30. http://dx.doi.org/10.5755/j01.mech.26.1.23107.

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In this work, a large bypass ratio engine was taken as the research object. The impingement property of droplets with various diameters including SLD (Super-cooled Large Droplet) was obtained by Euler method based on Mundo model. The grid models of nose cone, fan, guild vanes in bypass duct and core duct were established in segments firstly. The mixed boundary was used to realize the data exchange between different flow fields. Then the Spalart-Allmaras turbulence model was applied to calculate the three dimensional engine flow field. Based on the flow field result, the droplet trajectory was

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13

Raghunathan, S., E. Benard, J. K. Watterson, et al. "Key aerodynamic technologies for aircraft engine nacelles." Aeronautical Journal 110, no. 1107 (2006): 265–88. http://dx.doi.org/10.1017/s0001924000013154.

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AbstractCustomer requirements and vision in aerospace dictate that the next generation of civil transport aircraft should have a strong emphasis on increased safety, reduced environmental impact and reduced cost without sacrificing performance. In this context, the School of Mechanical and Aerospace Engineering at the Queen’s University of Belfast and Bombardier have, in recent years, been conducting research into some of the key aerodynamic technologies for the next generation of aircraft engine nacelles. Investigations have been performed into anti-icing technology, efficient thrust reversal

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14

Al-Khalil, Kamel M., Theo G. Keith, and Kenneth J. De Witt. "Icing Calculations on a Typical Commercial Jet Engine Inlet Nacelle." Journal of Aircraft 34, no. 1 (1997): 87–93. http://dx.doi.org/10.2514/2.2139.

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15

Hayashi, Ryosuke, and Makoto Yamamoto. "Numerical Investigation of Ice Shedding Phenomenon in Engine Fan Icing." Proceedings of The Computational Mechanics Conference 2014.27 (2014): 733–35. http://dx.doi.org/10.1299/jsmecmd.2014.27.733.

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16

Dong, W., M. Zheng, J. Zhu, G. Lei, and Q. Zhao. "Experimental Investigation on Anti-Icing Performance of an Engine Inlet Strut." Journal of Propulsion and Power 33, no. 2 (2017): 379–86. http://dx.doi.org/10.2514/1.b36067.

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17

XUAN, YiMin, and WenLei LIAN. "A new anti-icing method for an aero-engine nose cone." Chinese Science Bulletin 61, no. 25 (2016): 2843–50. http://dx.doi.org/10.1360/n972016-00445.

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18

Beroun, Stanislav, Pavel Brabec, Aleš Dittrich, Ondřej Dráb, and Tuan Nguyen Thanh. "Computational Modeling of the Liquid LPG Injection into the Suction Manifold of an SI Vehicle Engine." Applied Mechanics and Materials 390 (August 2013): 355–59. http://dx.doi.org/10.4028/www.scientific.net/amm.390.355.

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LPG is a very first-rate alternative fuel for a vehicle SI engine. By mixture formation using the injection of the gaseous LPG into suction manifold of the naturally aspirated SI engine the engine power is reduced to the original petrol engine power. This advantage is corrected by mixture formation using the liquid LPG injection into the intake air to the suction manifold. The paper deals with the computational modelling of the process on the liquid LPG injection, especially of the history LPG pressure and the LPG temperature before outlet nozzle. The calibration of the computational model has

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19

Lian, Wenlei, and Yimin Xuan. "Experimental investigation on a novel aero-engine nose cone anti-icing system." Applied Thermal Engineering 121 (July 2017): 1011–21. http://dx.doi.org/10.1016/j.applthermaleng.2017.04.160.

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20

Milyaev, Kirill, Sergey Semenov, and Alexander Balakirev. "WAYS OF FIGHT AGAINST FROSTING IN THE AVIATION ENGINE METHODS OF COUNTERING WITH ICING IN THE AIRCRAFT ENGINE." Perm National Research Polytechnic University Aerospace Engineering Bulletin, no. 59 (2019): 5–19. http://dx.doi.org/10.15593/2224-9982/2019.59.01.

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21

Jin, W., R. R. Taghav, and S. Farokhi. "Flow distortion in an S-duct inlet with simulated icing effect and heat transfer." Aeronautical Journal 116, no. 1177 (2012): 251–70. http://dx.doi.org/10.1017/s0001924000006825.

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Abstract A diffusing S-duct aircraft intake system is computationally studied for the effects of inlet icing and wall heat transfer on engine face distortion. A Reynolds-Averaged Navier-Stokes (RANS) code with k -ω SST turbulence model is used to simulate the compressible viscous flow in the duct. The glaze ice accretion on the inlet lip is simulated as a fixed protrusion from NASA LEWICE3D code. The shape and size of the ice on the inlet lip are assumed to remain constant even in the case of the heated wall. The case of zero external heat transfer is modeled by the adiabatic wall boundary con

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22

Danilkin, S. Yu, and V. A. Teleshev. "Investigation of the vibration behavior of a gas turbine engine in icing conditions." VESTNIK of the Samara State Aerospace University, no. 5-3(47) (July 10, 2015): 55. http://dx.doi.org/10.18287/1998-6629-2014-0-5-3(47)-55-59.

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23

Bartkus, Tadas P., Peter Struk, and Jen-Ching Tsao. "Development of a Coupled Air and Particle Thermal Model for Engine Icing Test Facilities." SAE International Journal of Aerospace 8, no. 1 (2015): 15–32. http://dx.doi.org/10.4271/2015-01-2155.

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24

Ahn, Gook-Bin, Ki-Young Jung, Sung-Ki Jung, Hun-Bum Shin, and Rho-Shin Myong. "Investigation of the Performance of Anti-Icing System of a Rotorcraft Engine Air Intake." Journal of the Korean Society for Aeronautical & Space Sciences 41, no. 4 (2013): 253–60. http://dx.doi.org/10.5139/jksas.2013.41.4.253.

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25

Shen, Xiaobin, Yundan Tan, Rendong Yu, et al. "Effects of Upstream Component and Air Injection on Water Droplet Impingement Characteristics for Downstream Surfaces." International Journal of Aerospace Engineering 2021 (June 23, 2021): 1–12. http://dx.doi.org/10.1155/2021/2698028.

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Water droplet changes its movement direction and velocity when it bypasses an aircraft component with the surrounding airflow or gets blown by air injection from the inner part. When the deflected droplet impacts on the downstream surface, its impingement characteristics would be different from those without the frontal effects. In this article, a Lagrangian method was developed to include those upstream effects on the droplet collection efficiency. Validation cases were carried out for a cylinder and an MS (1)-0317 airfoil, whereas a multielement airfoil and an engine cone with a hot air film

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26

Shen, Xiao Bin, Zuo Dong Mu, Gui Ping Lin, and Yue Zhou. "Prediction of Ice Shape for Three-Dimensional Engine Inlet Based on the Proper Orthogonal Decomposition Method." Advanced Materials Research 1008-1009 (August 2014): 1011–15. http://dx.doi.org/10.4028/www.scientific.net/amr.1008-1009.1011.

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To increase the prediction speed of ice accretion on the 3D engine inlet, the Proper Orthogonal Decomposition (POD) method was introduced. Taking the ice shapes from CFD numerical calculation results as samples, in view of the change of icing temperature, the procedures of predicting the ice shapes by POD method were introduced, which used ice shapes’ coordinates and ice accretion height as compute parameters, respectively. The POD and CFD ice shapes were found coincident, which indicates that the POD method can fast and accurately calculate the 3D engine inlet ice shapes. The results from the

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27

Isobe, Keisuke, Masaya Suzuki, and Makoto Yamamoto. "Numerical investigation on super-cooled large droplet icing of fan rotor blade in jet engine." Journal of Thermal Science 23, no. 5 (2014): 432–37. http://dx.doi.org/10.1007/s11630-014-0726-2.

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28

Mikhailovskiy, K. V., and S. V. Baranovski. "Accounting for Icing in the Design Analysis of Polymer Composite Wings." Proceedings of Higher Educational Institutions. Маchine Building, no. 3 (708) (March 12, 2019): 61–70. http://dx.doi.org/10.18698/0536-1044-2019-3-61-70.

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The aircraft aerodynamic characteristics are directly dependent on their geometry, in particular, on the wing airfoil. The airfoil can change significantly in-flight due to the growth of ice, which can impact effectiveness of the airfoil. Accounting for this phenomenon is a multidisciplinary task that requires an appropriate solution, making it relevant for design calculations. The process of obtaining an ice-covered surface of the aircraft using the performed calculation of the external aerodynamics problem is described in this paper. The shape and geometry, as well as the ice effect on the a

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29

Beroun, Stanislav, Pavel Brabec, and Aleš Dittrich. "Vehicle SI Engine with MPI of Liquid State LPG." Journal of Middle European Construction and Design of Cars 14, no. 1 (2016): 41–47. http://dx.doi.org/10.1515/mecdc-2016-0004.

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Abstract The first part of the article reviews the possible methods for LPG and air mixture forming (injection of gaseous or liquid state LPG) and their influence on the operating properties of an SI engine. The next chapter explains the processes that take place when liquid state LPG is injected into the air flow of an internal combustion engine intake manifold. A simplified calculation is used to show that the injection of liquid state LPG is associated with extreme low temperature of the LPG injected into intake manifold and with ice formation on the outlet nozzle. The article sets out the

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30

Лось, Александр Васильевич. "ОСОБЛИВОСТІ ОЦІНКИ ПАЛИВНОЇ ЕФЕКТИВНОСТІ МОДИФІКАЦІЙ ЛІТАКІВ З БАГАТОДВИГУНОВИМИ СИЛОВИМИ УСТАНОВКАМИ". Open Information and Computer Integrated Technologies, № 86 (14 лютого 2020): 117–26. http://dx.doi.org/10.32620/oikit.2019.86.08.

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When creating modifications of transport category airplanes, fuel efficiency appears in the structure of their parameters.This indicator is very important, since operating costs largely depend on the amount of fuel consumed per unit of work.The problem of evaluating the fuel efficiency of modifications of transport aircraft with multi-engine power plants is considered. It is noted that multi-engine power plants, used mainly on medium and heavy aircraft, contribute to solving a number of problematic issues:– expanding the ability to operate in hot climates and highlands;– improving operational

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31

Hervy, Franck, Severine Maguis, François Virion, Biagio Esposito, and Hugo Pervier. "Improvement of an Altitude Test Facility Capability in Glaciated Icing Conditions at DGA Aero-engine Testing." SAE International Journal of Aerospace 8, no. 1 (2015): 9–14. http://dx.doi.org/10.4271/2015-01-2154.

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32

Oliver, Michael. "Ice Crystal Icing Engine Testing in the NASA Glenn Research Center's Propulsion Systems Laboratory: Altitude Investigation." SAE International Journal of Aerospace 8, no. 1 (2015): 33–37. http://dx.doi.org/10.4271/2015-01-2156.

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33

Yezeguelian, Axel, and Askin T. Isikveren. "Methods to improve UAV performance using hybrid-electric architectures." Aircraft Engineering and Aerospace Technology 92, no. 5 (2020): 685–700. http://dx.doi.org/10.1108/aeat-11-2019-0227.

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Purpose When comparing and contrasting different types of fixed-wing military aircraft on the basis of an energetic efficiency figure-of-merit, unmanned aerial vehicles (UAVs) dedicated to tactical medium-altitude long-endurance (MALE) operations appear to have significant potential when hybrid-electric propulsion and power systems (HEPPS) are implemented. Beginning with a baseline Eulair drone, this paper aims to examine the feasibility of retro-fitting with an Autarkic-Parallel-HEPPS architecture to enhance performance of the original single diesel engine. Design/methodology/approach In view

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34

Ayan, E., and S. Özgen. "In-flight ice accretion simulation in mixed-phase conditions." Aeronautical Journal 122, no. 1249 (2017): 409–41. http://dx.doi.org/10.1017/aer.2017.127.

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ABSTRACTIcing in conditions where clouds contain both liquid and solid phase particles has attracted considerable interest in recent years due to numerous in-flight incidents including engine rollbacks in the vicinity of deep convective clouds in tropical regions. These incidents have prompted certification authorities to investigate and extend the icing conditions to include solid and mixed-phase clouds for airworthiness certification. These efforts have resulted in the amendments issued by the Federal Aviation Administration (FAA) and European Aviation Safety Agency (EASA) to the certificati

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35

Kim, Yung-Jin, Ki-Bum Kim, and Ki-Hyung Lee. "EXPERIMENTAL STUDY ON LIQUID PHASE LPG SPRAY AND ICING PHENOMENON FOR A MIDDLE CLASS DIESEL ENGINE APPLICATION." Atomization and Sprays 21, no. 7 (2011): 611–24. http://dx.doi.org/10.1615/atomizspr.2012004106.

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36

Jung, SungKi, L. Prince Raj, A. Rahimi, H. Jeong, and R. S. Myong. "Performance evaluation of electrothermal anti-icing systems for a rotorcraft engine air intake using a meta model." Aerospace Science and Technology 106 (November 2020): 106174. http://dx.doi.org/10.1016/j.ast.2020.106174.

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37

Li, Linkai, Yang Liu, Linchuan Tian, et al. "An experimental study on a hot-air-based anti-/de-icing system for aero-engine inlet guide vanes." Applied Thermal Engineering 167 (February 2020): 114778. http://dx.doi.org/10.1016/j.applthermaleng.2019.114778.

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38

Chen, L. W. A., J. G. Watson, J. C. Chow, M. C. Green, D. Inouye, and K. Dick. "Wintertime particulate pollution episodes in an urban valley of the Western US: a case study." Atmospheric Chemistry and Physics Discussions 12, no. 6 (2012): 15801–36. http://dx.doi.org/10.5194/acpd-12-15801-2012.

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Abstract. This study investigates the causes of elevated PM2.5 concentrations and potential exceedences of the US National Ambient Air Quality Standards (NAAQS) in Truckee Meadows, Nevada, an urban valley of the Western US, during winter 2009/2010. Continuous PM2.5 mass and time-integrated chemical speciation data were acquired from a central valley monitoring site with meteorological measurements from nearby sites. All nine days with PM2.5>35 μg m−3 experienced 24-h average temperature inversion of 1.5–4.5 °C and snow cover of 8–18 cm. A stagnant atmospheric condition inhibited wind ventil

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39

Chen, L. W. A., J. G. Watson, J. C. Chow, M. C. Green, D. Inouye, and K. Dick. "Wintertime particulate pollution episodes in an urban valley of the Western US: a case study." Atmospheric Chemistry and Physics 12, no. 21 (2012): 10051–64. http://dx.doi.org/10.5194/acp-12-10051-2012.

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Abstract. This study investigates the causes of elevated PM2.5 episodes and potential exceedences of the US National Ambient Air Quality Standards (NAAQS) in Truckee Meadows, Nevada, an urban valley of the Western US, during winter 2009/2010, an unusually cold and snowy winter. Continuous PM2.5 mass and time-integrated chemical speciation data were acquired from a central valley monitoring site, along with meteorological measurements from nearby sites. All nine days with PM2.5 > 35 μg m−3 showed 24-h average temperature inversion of 1.5–4.5 °C and snow cover of 8–18 cm. Stagnant atmospheric

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40

Boyarshinov, M. G., and N. I. Kuznetsov. "Thermal Regime of Automobile Exhaust System at Low Temperature." World of Transport and Transportation 17, no. 4 (2020): 48–67. http://dx.doi.org/10.30932/1992-3252-2019-17-48-67.

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Currently operation of cars in large cities in winter is the most unfavorable from the point of view of the risk of blocking the exhaust system by condensate accumulated in it. Frequent starts during relatively short period of time, or the cycle of start-up – short run – and subsequent long-term parking at low temperatures are dangerous because the exhaust system does not have time to warm up and remove the accumulated condensate. Daily operation in such modes contributes to rapid accumulation of condensate, and subsequent long-term parking at ambient temperatures below 0˚C are equally dangero

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41

Leishman, B. A., N. A. Cumpsty, and J. D. Denton. "Effects of Bleed Rate and Endwall Location on the Aerodynamic Behavior of a Circular Hole Bleed Off-Take." Journal of Turbomachinery 129, no. 4 (2006): 645–58. http://dx.doi.org/10.1115/1.2752191.

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In a jet engine bleed off-takes on the hub and casing endwalls, part way through the compressor, supply high-pressure air for cooling, sealing, de-icing, and aircraft cabin air applications; bleed also assists compressor operation at part-speed conditions. Two separate issues are of interest: the bleed off-take air pressure and the interaction of the bleed off-take with the primary flow through the blade passage. In this paper, the aerodynamic behavior is presented for a circular-hole bleed off-take at three endwall locations within a stationary cascade blade passage: at midpassage; near the b

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42

Leusden, Christoph Pels, Christoph Sorgenfrey, and Lutz Du¨mmel. "Performance Benefits Using Siemens Advanced Compressor Cleaning System." Journal of Engineering for Gas Turbines and Power 126, no. 4 (2004): 763–69. http://dx.doi.org/10.1115/1.1787512.

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Extensive operational performance data from the Siemens Power Generation V64.3 unit in Obernburg, Germany (operated by Kraftwerk Obernburg GmbH) is evaluated. The unit was commissioned in 1996 and has been running continuously in base load operation with fuel gas to supply heat and power to a nearby chemical plant. In rare cases, fuel oil is used as a backup fuel. During the first major outage after approximately 25,000 equivalent operating hours (EOH), the Siemens PG Advanced Compressor Cleaning System (ACCS) was implemented at Obernburg. ACCS features separate nozzle systems for online and o

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43

Veillard, X., W. G. Habashi, and G. S. Baruzzi. "Icing Simulation in Multistage Jet Engines." Journal of Propulsion and Power 27, no. 6 (2011): 1231–37. http://dx.doi.org/10.2514/1.b34060.

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44

Bin, Yang, and Zhou Yanpei. "Icing Certification of Civil Aircraft Engines." Procedia Engineering 17 (2011): 603–15. http://dx.doi.org/10.1016/j.proeng.2011.10.076.

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45

Baranovsky, Vladimir, Tatiana Korotkova, and Mikhail Konovalov. "A novel anti-icing system solution for gas turbine engines at combined gas and steam plants." Energy Safety and Energy Economy 4 (August 2018): 36–40. http://dx.doi.org/10.18635/2071-2219-2018-4-36-40.

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46

de Boer, Gijs, Scott Palo, Brian Argrow, et al. "The Pilatus unmanned aircraft system for lower atmospheric research." Atmospheric Measurement Techniques 9, no. 4 (2016): 1845–57. http://dx.doi.org/10.5194/amt-9-1845-2016.

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Abstract. This paper presents details of the University of Colorado (CU) “Pilatus” unmanned research aircraft, assembled to provide measurements of aerosols, radiation and thermodynamics in the lower troposphere. This aircraft has a wingspan of 3.2 m and a maximum take-off weight of 25 kg, and it is powered by an electric motor to reduce engine exhaust and concerns about carburetor icing. It carries instrumentation to make measurements of broadband up- and downwelling shortwave and longwave radiation, aerosol particle size distribution, atmospheric temperature, relative humidity and pressure a

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47

de Boer, G., S. Palo, B. Argrow, et al. "The pilatus unmanned aircraft system for lower atmospheric research." Atmospheric Measurement Techniques Discussions 8, no. 11 (2015): 11987–2023. http://dx.doi.org/10.5194/amtd-8-11987-2015.

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Abstract. This paper presents details of the University of Colorado (CU) Pilatus unmanned research aircraft, assembled to provide measurements of aerosols, radiation and thermodynamics in the lower troposphere. This aircraft has a wingspan of 3.2 m and a maximum take off weight of 25 kg and is powered by an electric motor to reduce engine exhaust and concerns about carburetor icing. It carries instrumentation to make measurements of broadband up- and downwelling shortwave and longwave radiation, aerosol particle size distribution, atmospheric temperature, relative humidity and pressure and to

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Musci, Maria Angela, Luigi Mazzara, and Andrea Maria Lingua. "Ice Detection on Aircraft Surface Using Machine Learning Approaches Based on Hyperspectral and Multispectral Images." Drones 4, no. 3 (2020): 45. http://dx.doi.org/10.3390/drones4030045.

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Aircraft ground de-icing operations play a critical role in flight safety. However, to handle the aircraft de-icing, a considerable quantity of de-icing fluids is commonly employed. Moreover, some pre-flight inspections are carried out with engines running; thus, a large amount of fuel is wasted, and CO2 is emitted. This implies substantial economic and environmental impacts. In this context, the European project (reference call: MANUNET III 2018, project code: MNET18/ICT-3438) called SEI (Spectral Evidence of Ice) aims to provide innovative tools to identify the ice on aircraft and improve th

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Shakina, N. P., I. A. Gorlach, E. N. Skriptunova, and N. I. Komas’ko. "Icing of aircraft engines in ice crystal clouds: A case study." Russian Meteorology and Hydrology 39, no. 2 (2014): 121–25. http://dx.doi.org/10.3103/s1068373914020083.

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Vercillo, Vittorio, Norbert Karpen, Alexandre Laroche, et al. "Analysis and modelling of icing of air intake protection grids of aircraft engines." Cold Regions Science and Technology 160 (April 2019): 265–72. http://dx.doi.org/10.1016/j.coldregions.2019.01.012.

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