Relevant bibliographies by topics / Flutter Prediction / Dissertations / Theses
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Dissertations / Theses on the topic 'Flutter Prediction'

Author: Grafiati
Published: 6 September 2023

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1

Perrocheau, Mathilde. "Flutter Prediction in Transonic Regime." Thesis, KTH, Flygdynamik, 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-234840.

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The flutter is a dangerous aeroelastic instability that can cause dramatic failures. It is important to evaluate in which conditions it can occur to ensure the safety of the pilots and the passengers. As flight tests are very expensive and hazardous, the need for efficient and trustworthy numerical tools becomes essential. This report focuses on two methods to predict the flutter conditions in the transonic domain. To evaluate the accuracy of these tools, their results are compared to experimental data gathered during a wind-tunnel test. The influence of the Mach number and the angle of attack
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2

Turevskiy, Arkadiy 1974. "Flutter boundary prediction using experimental data." Thesis, Massachusetts Institute of Technology, 1998. http://hdl.handle.net/1721.1/50327.

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3

Yildiz, Erdinc Nuri. "Aeroelastic Stability Prediction Using Flutter Flight Test Data." Phd thesis, METU, 2007. http://etd.lib.metu.edu.tr/upload/12608623/index.pdf.

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Flutter analyses and tests are the major items in flight certification efforts required when a new air vehicle is developed or when a new external store is developed for an existing aircraft. The flight envelope of a new aircraft as well as the influence of aircraft modifications on an existing flight envelope can be safely determined only by flutter tests. In such tests, the aircraft is instrumented by accelerometers and exciters. Vibrations of the aircraft at specific dynamic pressures are measured and transmitted to a ground station via telemetry systems during flutter tests. These vibratio
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4

Shieh, Teng-Hua. "Prediction and analysis of wing flutter at transonic speeds." Diss., The University of Arizona, 1991. http://hdl.handle.net/10150/185694.

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This dissertation deals with the instability, known as flutter, of the lifting and control surfaces of aircraft of advanced design at high altitudes and speeds. A simple model is used to represent the aerodynamics for flutter analysis of a two-degree-of-freedom airfoil system. Flutter solutions of this airfoil system are shown to be algebraically homomorphic in that solutions about different elastic axes can be found by mapping them to those about the mid-chord. Algebraic expressions for the flutter speed and frequency are thus obtained. For the prediction of flutter of a wing at transonic spe
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5

Sun, Tianrui. "Improved Flutter Prediction for Turbomachinery Blades with Tip Clearance Flows." Licentiate thesis, KTH, Energiteknik, 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-233770.

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Recent design trends in steam turbines strive for high aerodynamic loading and high aspect ratio to meet the demand of higher efficiency. These design trends together with the low structural frequency in last stage steam turbines increase the susceptibility of the turbine blades to flutter. Flutter is the self-excited and self-sustained aeroelastic instability phenomenon, which can result in rapid growth of blade vibration amplitude and eventually blade failure in a short period of time unless adequately damped. To prevent the occurrences of flutter before the operation of new steam turbines,
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6

Opgenoord, Max Maria Jacques. "Transonic flutter prediction and aeroelastic tailoring for next-generation transport aircraft." Thesis, Massachusetts Institute of Technology, 2018. http://hdl.handle.net/1721.1/120380.

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Thesis: Ph. D., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2018.<br>This electronic version was submitted by the student author. The certified thesis is available in the Institute Archives and Special Collections.<br>Cataloged from student-submitted PDF version of thesis.<br>Includes bibliographical references (pages 121-141) and index.<br>Novel commercial transport aircraft concepts feature large wing spans to increase their fuel efficiency; these wings are more flexible, leading to more potential aeroelastic problems. Furthermore, these aircraft fly i
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7

Erives, Anchondo Ruben. "Validation of non-linear time marching and time-linearised CFD solvers used for flutter prediction." Thesis, KTH, Kraft- och värmeteknologi, 2015. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-175542.

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The turbomachinery related industry relies heavily on numerical tools for the design and development of modern turbomachines. In order to be competitive turbomachines ought to be highly efficient and robust. This has lead engineers to develop more aggressive designs, which often leads to lower margins of structural reliability.  One of the strongest threats to turbomachines are high cycle fatigue problems which arise from aeroelastic phenomena such as flutter. According to Kielb R. (2013) many of such problems are detected at developing testing stage. This implies that the prediction capabilit
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8

Delamore-Sutcliffe, David William. "Modelling of unsteady stall aerodynamics and prediction of stall flutter boundaries for wings and propellers." Thesis, University of Bristol, 2007. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.440048.

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9

Kassem, H. I. "Flutter prediction of metallic and composite wings using coupled DSM-CFD models in transonic flow." Thesis, City, University of London, 2017. http://openaccess.city.ac.uk/20404/.

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Although flutter analysis is a relatively old problem in aviation, it is still challenging, particularly with the advent of composite materials and requirements for high-speed light airframes. The main challenge for this problem is at the transonic flow region. The transonic flow, being non-linear, poses a great challenge over traditional linear theories which fail to predict the aerodynamic properties accurately. Aerospace has been one of the primary areas of applications to take advantage of composite materials with the aim to reduce the total mass and improve control effectiveness. This wor
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10

Perry, Brendan. "Predictions of flutter at transonic speeds." Thesis, University of Manchester, 2009. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.498853.

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11

Lee, Sung-yeoul. "Viscous effects in predicting transonic flutter boundary." Thesis, Cranfield University, 2001. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.393619.

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12

Moyroud, François. "Fluid-structure integrated computational methods for turbomachinery blade flutter and forced response predictions /." Stockholm : Tekniska högsk, 1998. http://www.lib.kth.se/abs98/moyr1214.pdf.

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13

Moyroud, François. "Fluid-structure integrated computational methods for turbomachinery blade flutter and forced response predictions." Lyon, INSA, 1998. http://www.theses.fr/1998ISAL0101.

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Les ensembles disque-aubes des turbomachines modernes sont amenés à satisfaire des critères stricts en termes de stabilité aéroélastique et de réponse forcée. L'objectif de cette thèse est d'utiliser et de développer des techniques de modélisation, capables de prédire le phénomène de flottement et de quantifier les amplitudes de résonance des aubages de turbomachine. Pour le flottement, deux méthodes d'analyse aéroélastique sont considérées: la méthode énergétique (approche fluidestructure non-couplée) et le schéma de couplage modal (approche fluide-structure couplée). Ces modèles ont été inst
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14

Lee, Yun-Chou, and 李韻舟. "Identification and prediction of flutter derivatives using artificial neural network." Thesis, 2004. http://ndltd.ncl.edu.tw/handle/wz367b.

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碩士<br>中原大學<br>土木工程研究所<br>92<br>This investigation develops an artificial neural <a href="http://www.ntsearch.com/search.php?q=network&v=56">network</a> (ANN) algorithm to identify aeroelastic parameters of cable-supported bridge section models in smooth flow and turbulent flow in a wind tunnel <a href="http://www.ntsearch.com/search.php?q=test&v=56">test</a>. The ANN approach method uses observed dynamic responses to train a back-propagation (BP) neural <a href="http://www.ntsearch.com/search.php?q=network&v=56">network</a> frame. The characteristic parameters of the section model for various
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15

Kumar, Brijesh. "Flutter Susceptibility Assessment of Airplanes in Sub-critical Regime using Ameliorated Flutter Margin and Neural Network Based Methods." Thesis, 2014. http://hdl.handle.net/2005/3124.

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As flight flutter testing on an airplane progresses to high dynamic pressures and high Mach number region, it becomes very difficult for engineers to predict the level of the remaining stability in a flutter-prone mode and flutter-prone mechanism when response data is infested with uncertainty. Uncertainty and ensuing scatter in modal data trends always leads to diminished confidence amidst the possibility of sudden decrease in modal damping of a flutter-prone mode. Since the safety of the instrumented prototype and the crew cannot be compromised, a large number of test-points are planned, whi
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16

Boersma, Pieter. "A NUMERICAL FLUTTER PREDICTOR FOR 3D AIRFOILS USING THE ONERA DYNAMIC STALL MODEL." 2018. https://scholarworks.umass.edu/masters_theses_2/692.

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To be able to harness more power from the wind, wind turbine blades are getting longer. As they get longer, they get more flexible. This creates issues that have until recently not been of concern. Long flexible wind turbine blades can lose their stability to flow induced instabilities such as coupled-mode flutter. This type of flutter occurs when increasing wind speed causes a coupling of a bending and a torsional mode, which create limit cycle oscillations that can lead to blade failure. To be able to make the design of larger blades possible, it is important to be able to predict the critic
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17

PAIFELMAN, ELENA. "Optimal control of systems with memory." Doctoral thesis, 2019. http://hdl.handle.net/11573/1229231.

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The “Optimal Control of Systems with memory” is a PhD project that is borne from the collaboration between the Department of Mechanical and Aerospace Engineering of Sapienza University of Rome and CNR-INM the Institute for Marine Engineering of the National Research Council of Italy (ex INSEAN). This project is part of a larger EDA (European Defence Agency) project called ETLAT: Evaluation of State of the Art Thin Line Array Technology. ETLAT is aimed at improving the scientific and technical knowledge of potential performance of current Thin Line Towed Array (TLA) technologies (element
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