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Dissertations / Theses on the topic 'Trailing edge flaps'

Author: Grafiati

Published: 4 June 2021

Last updated: 6 September 2023

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1

Frederick, Mark. "Load reduction using rapidly deployed trailing-edge flaps." Thesis, Imperial College London, 2009. http://hdl.handle.net/10044/1/4647.

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This thesis details investigations into the aerodynamic properties of a small, rapidlyactuated, actively controlled trailing-edge ap and the potential of such a device to alleviate the unsteady loading experienced by wind turbine blades due to atmospheric turbulence and the atmospheric boundary layer, although such a device would have potential applications in other elds such as rotorcraft. The main goals of this work were to investigate whether aerodynamic loadings could in fact be alleviated by the use of a small trailing-edge ap using only measurements of the unsteady lift on the wing as a

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2

Yu, Jie. "Novel swing arm mechanism design for trailing edge flaps on commercial airliner." Thesis, Cranfield University, 2008. http://dspace.lib.cranfield.ac.uk/handle/1826/9586.

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This thesis will describe the works had been done by the author in the Flying Crane aircraft group design project and the new design of a novel swing arm mechanism which can be applied in the trailing edge high lift devices for this aircraft concept. Flying Crane aircraft is a new generation commercial airliner concept as the result of group design project conducted by China Aviation Industry Corporation I (AVIC I) and Cranfield University. At the end of the group design project, parameters such as take-off and landing distance, trailing edge flap type and deflection in take-off and landing co

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3

Couch, Mark A. "A three-dimensional flutter theory for rotor blades with trailing-edge flaps." Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2003. http://library.nps.navy.mil/uhtbin/hyperion-image/03Jun%5fCouch%5FPhD.pdf.

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Thesis (Ph. D. in Aeronautical and Astronautical Engineering)--Naval Postgraduate School, June 2003.<br>Dissertation supervisor and advisor: E. Roberts Wood. Includes bibliographical references (p. 205-210). Also available online.

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4

Gagliardi, Adriano. "CFD analysis and design of a low-twist, hovering rotor equipped with trailing-edge flaps." Thesis, Connect to e-thesis, 2008. http://theses.gla.ac.uk/350/.

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Thesis (Ph.D.) - University of Glasgow, 2007.<br>Ph.D. thesis submitted to the Department of Aerospace Engineering, Faculty of Engineering, University of Glasgow, 2007. Includes bibliographical references. Print version also available.

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5

Schwarz, Eva [Verfasser]. "CFD-based studies of active wind turbine load control by means of trailing edge flaps / Eva Schwarz." München : Verlag Dr. Hut, 2021. http://d-nb.info/1238423051/34.

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6

Li, Wei-En. "Enhancement of roll maneuverability using post-reversal design." Diss., Atlanta, Ga. : Georgia Institute of Technology, 2009. http://hdl.handle.net/1853/29602.

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Thesis (Ph.D)--Aerospace Engineering, Georgia Institute of Technology, 2009.<br>Committee Chair: Hodges, Dewey; Committee Member: Bauchau, Olivier; Committee Member: Goldsman, David; Committee Member: Prasad, J.V.R.; Committee Member: Smith, Marilyn. Part of the SMARTech Electronic Thesis and Dissertation Collection.

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7

Schoensleben, Sven. "Integrated trailing edge flap track mechanism for commercial aircraft." Zürich : ETH, Eidgenössische Technische Hochschule Zürich, Center of Structure Technologies, 2006. http://e-collection.ethbib.ethz.ch/show?type=dipl&nr=228.

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8

Martins, Pires Rui Miguel. "Design methodology for wing trailing edge device mechanisms." Thesis, Cranfield University, 2007. http://hdl.handle.net/1826/3393.

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Over the last few decades the design of high lift devices has become a very important part of the total aircraft design process. Reviews of the design process are performed on a regular basis, with the intent to improve and optimize the design process. This thesis describes a new and innovative methodology for the design and evaluation of mechanisms for Trailing Edge High-Lift devices. The initial research reviewed existing High-Lift device design methodologies and current flap systems used on existing commercial transport aircraft. This revealed the need for a design methodology that could im

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9

Adair, Desmond. "Turbulent flow in the vicinity of the trailing-edge of an aerofoil flap." Thesis, Imperial College London, 1986. http://hdl.handle.net/10044/1/37915.

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10

Herdic, Scott Lucas. "Developement of Piezo-Hydraulic Actuation Systems Technology for use on a Helicopter Trailing Edge Flap." Thesis, Georgia Institute of Technology, 2005. http://hdl.handle.net/1853/7556.

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The purpose of this study was to create a proof-of-concept piezoelectric actuator system capable of meeting the performance requirements necessary for actuation of a trailing edge flap for a helicopter main rotor blade. Due to extremely small displacements produced by piezoelectric actuators, their output is amplified several times in order to produce the required displacement for this device. The amplification is accomplished in two stages. The first stage, mechanical amplification, uses differential length lever arms to increase the piezoelectric actuator output. The second stage, hydrau

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11

Shen, Jinwei. "Comprehensive aeroelastic analysis of helicopter rotor with trailing-edge flap for primary control and vibration control." College Park, Md. : University of Maryland, 2003. http://hdl.handle.net/1903/122.

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Thesis (Ph. D.) -- University of Maryland, College Park, 2003.<br>Thesis research directed by: Aerospace Engineering. Title from t.p. of PDF. Includes bibliographical references. Published by UMI Dissertation Services, Ann Arbor, Mich. Also available in paper.

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12

Tsiachris, Fotios K. "Retreating blade stall control on a NACA 0015 aerofoil by means of a trailing edge flap." Thesis, University of Glasgow, 2005. http://theses.gla.ac.uk/5109/.

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Trailing edge flaps may provide a mechanism for alleviating retreating blade stall. In the present investigation numerical simulations were conducted involving a NACA 0015 aerofoil section fitted with a plain trailing edge (TE) flap. All simulations were conducted using DIVEX, a tool being developed at the University of Glasgow, Department of Aerospace Engineering. In summary, the code uses a surface shedding discrete vortex method (DVM) for the simulation of 2-D incompressible flows around pitching aerofoils. The aero-foil is oscillating in pitch about its quarter chord axis and the clap unde

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13

Walker, Jessica Nicole. "Numerical Studies of Jet-Wing Distributed Propulsion and a Simplified Noise Metric Method." Thesis, Virginia Tech, 2004. http://hdl.handle.net/10919/34752.

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<P> In recent years, the aircraft industry has begun to focus its research capabilities on reducing emissions and noise produced by aircraft. Modern aircraft use two to four engines arranged on the wing or behind to produce thrust that is concentrated directly behind the engine. Kuchemann suggested a way to improve the propulsive efficiency by changing the normal configuration of engine and aircraft. This concept is the jet-wing distributed propulsion idea, which redistributes the thrust across the span of the wings. Distributed propulsion is accomplished by using many smaller engines spre

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14

Cantoni, Lorenzo. "Load Control Aerodynamics in Offshore Wind Turbines." Thesis, KTH, Kraft- och värmeteknologi, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-291417.

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Due to the increase of rotor size in horizontal axis wind turbine (HAWT) during the past 25 years in order to achieve higher power output, all wind turbine components and blades in particular, have to withstand higher structural loads. This upscalingproblem could be solved by applying technologies capable of reducing aerodynamic loads the rotor has to withstand, either with passive or active control solutions. These control devices and techniques can reduce the fatigue load upon the blades up to 40% and therefore less maintenance is needed, resulting in an important money savings for the wind

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15

Segawa, Hidehiro. "Optimum flap angles for roll control on wings with multiple trailing-edge flaps." 2007. http://www.lib.ncsu.edu/theses/available/etd-11062007-170923/unrestricted/etd.pdf.

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16

Montanye, Pamela L. Smith Edward C. Rahn Christopher D. Conlon Stephen C. "Shipboard helicopter gust response alleviation using active trailing edge flaps /." 2008. http://etda.libraries.psu.edu/theses/approved/WorldWideIndex/ETD-3173/index.html.

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17

Duling, Christopher T. Gandhi Farhan S. "Further investigations on primary helicopter control using trailing edge flaps." 2009. http://etda.libraries.psu.edu/theses/approved/WorldWideIndex/ETD-3960/index.html.

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18

Viswamurthy, S. R. "Piezoceramic Dynamic Hysteresis Effects On Helicopter Vibration Control Using Multiple Trailing-Edge Flaps." Thesis, 2007. http://hdl.handle.net/2005/561.

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Helicopters suffer from severe vibration levels compared to fixed-wing aircraft. The main source of vibration in a helicopter is the main rotor which operates in a highly unsteady aerodynamic environment. Active vibration control methods are effective in helicopter vibration suppression since they can adapt to various flight conditions and often involve low weight penalty. One such method is the actively controlled flap (ACF) approach. In the ACF approach, a trailing-edge flap (TEF) located in each rotor blade is deflected at higher harmonics of rotor frequency to reduce vibratory loads at the

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19

Kim, Jun-Sik. "Design and analysis of rotor systems with multiple trailing edge flaps and resonant actuators." 2005. http://www.etda.libraries.psu.edu/theses/approved/WorldWideIndex/ETD-1067/index.html.

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20

Leon, Olivier Gandhi Farhan S. "Reducing helicopter main rotor power requirements using multiple trailing edge flaps and extendable chord sections." 2009. http://etda.libraries.psu.edu/theses/approved/WorldWideIndex/ETD-4433/index.html.

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21

Mallick, Rajnish. "Design and Development of Piezoelectric Stack Actuated Trailing Edge Flap for Helicopter Vibration Reduction." Thesis, 2014. http://etd.iisc.ernet.in/handle/2005/2990.

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This research investigates on-blade partial span active plain trailing edge flaps (TEFs)with an aim to alleviate the helicopter vibrations. Among all the available smart materials, piezoelectric stack actuator(PEA)has shown its strong candidature for full scale rotor systems. Although, PEAs are quite robust in operation, however, they exhibit rate dependent hysteresis phenomenon and can generate only very small displacements. Dynamic hysteresis is a complex phenomenon which, if not modeled, can lead to drift in the vibration predictions. In this research, a comprehensive experimental analysis

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22

Lin, Hung-Yi, and 林宏益. "The Analysis of Composite Trailing Edge Elevon Flap." Thesis, 2004. http://ndltd.ncl.edu.tw/handle/37609902068411055105.

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23

Chang, Ying-Hsun, and 張穎巽. "On the Trailing Edge Flap Effects of the Nonlinear Composite Rotor Blade." Thesis, 2005. http://ndltd.ncl.edu.tw/handle/78734036097977955979.

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碩士<br>淡江大學<br>航空太空工程學系碩士班<br>93<br>The dynamic behavior of a long slender beam is of interest in connection with helicopter rotor blades, wind-turbine blades, and other systems that perform large and/or complex motions. When the vibration amplitude is large, various nonlinear effects come into play. Owing to the participation of these nonlinear characteristics, many nonlinear phenomena deserve detailed exam. For the past years, the concept of trailing edge flap (TEF) has been applied on the helicopter rotor blade system. Although experimental analyses have made a successfully progress, the

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24

Wu, Guan-Heng, and 吳冠亨. "Experimental Study of Wake Structure Behind Delta Wing with Trailing Edge Flap." Thesis, 1999. http://ndltd.ncl.edu.tw/handle/79152415988916961392.

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碩士<br>國立中興大學<br>機械工程學系<br>87<br>The purpose of this study is to understand the flow structure and characteristic frequency downstream of a delta wing with trailing-edge flap. The flow visualization is first employed to visualize the qualitative flow structure. Secondly, the quantitative results are performed by way of non-intrusive LDV system. Both the mean and spectrum of the fluctuating velocity field are analyzed to reveal the complex flow structure downstream of the delta wing. The Reynolds number, based on the root chord (20.2cm) and the free stream velocity (8.1cm/s), is around 1.9×104.

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25

Shinde, Sachin Yashavant. "Hydrodynamics Of An Oscillating Foil With A Long Flexible Trailing Edge." Thesis, 2007. http://hdl.handle.net/2005/884.

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In nature, many swimming and flying creatures use the principle of oscillatory lift-based propulsion. Often the flapping element is flexible, totally or partially. The flow dynamics because of a flexible flap is thus of considerable interest. We are interested especially in lunate fish propulsion. The present work investigates the effect of trailing edge flexibility on the flow field created by an oscillating airfoil in an attempt to mimic the flow around the flexible tails often found in fish. A flexible flap with negligible mass and stiffness is attached at the trailing edge of NACA0015 air

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26

Chiu, Chien-Chih, and 邱建智. "The Effects of Wake Dynamics and Trailing Edge Flap on Wind Turbine Blade." Thesis, 2014. http://ndltd.ncl.edu.tw/handle/90725284968901945384.

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碩士<br>淡江大學<br>航空太空工程學系碩士班<br>102<br>Wind power devices are now used to produce electricity, and commonly termed wind turbines. Load and performance calculations of wind turbines are usually performed by the Blade-Element/Momentum (BEM) method. However, the wake effects and the wake-blade structure interactions are less considered in most wind turbine analysis. This research studied a dynamic wake and blade interacted wind turbine. The Peters dynamic wake theory was applied. The effects of the wake and the configuration of the modern trailing-edge-flap (TEF) on the wind turbine blade were

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27

Bluman, James Edward. "Reducing trailing edge flap deflection requirements in primary control through a moveable horizontal tail." 2008. http://etda.libraries.psu.edu/theses/approved/WorldWideIndex/ETD-2706/index.html.

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28

Abdelrahman, Ahmed. "Development of a Wind Turbine Test Rig and Rotor for Trailing Edge Flap Investigation." Thesis, 2014. http://hdl.handle.net/10012/8454.

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Alleviating loads on a wind turbine blades would allow a reduction in weight, and potentially increase the size and lifespan of rotors. Trailing edge flaps are one technology proposed for changing the aerodynamic characteristics of a blade in order to limit the transformation of freestream wind fluctuations into load fluctuations within the blade structure. An instrumented wind turbine test rig and rotor were developed to enable a wide-range of experimental set-ups for such investigations. The capability of the developed system was demonstrated through a study of the effect of stationary trail

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29

Cormier, Christopher P. Mockensturm Eric M. "Design of a centrifuge and aerodynamic testing apparatus for evaluating the performance of a novel trailing-edge flap actuator." 2008. http://etda.libraries.psu.edu/theses/approved/WorldWideIndex/ETD-3409/index.html.

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30

Aquino, Bryce B. "New Generator Control Algorithms for Smart-Bladed Wind Turbines to Improve Power Capture in Below Rated Conditions." 2014. https://scholarworks.umass.edu/masters_theses_2/66.

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With wind turbines growing in size, operation and maintenance has become a more important area of research with the goal of making wind energy more profitable. Wind turbine blades are subjected to intense fluctuating loads that can cause significant damage over time. The need for advanced methods of alleviating blade loads to extend the lifespan of wind turbines has become more important as worldwide initiatives have called for a push in renewable energy. An area of research whose goal is to reduce the fatigue damage is smart rotor control. Smart bladed wind turbines have the ability to sense

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