Tesis sobre el tema "Flutter Prediction"
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Perrocheau, Mathilde. "Flutter Prediction in Transonic Regime". Thesis, KTH, Flygdynamik, 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-234840.
Texto completoTurevskiy, Arkadiy 1974. "Flutter boundary prediction using experimental data". Thesis, Massachusetts Institute of Technology, 1998. http://hdl.handle.net/1721.1/50327.
Texto completoYildiz, Erdinc Nuri. "Aeroelastic Stability Prediction Using Flutter Flight Test Data". Phd thesis, METU, 2007. http://etd.lib.metu.edu.tr/upload/12608623/index.pdf.
Texto completoShieh, Teng-Hua. "Prediction and analysis of wing flutter at transonic speeds". Diss., The University of Arizona, 1991. http://hdl.handle.net/10150/185694.
Texto completoSun, 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.
Texto completoOpgenoord, 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.
Texto completoThis electronic version was submitted by the student author. The certified thesis is available in the Institute Archives and Special Collections.
Cataloged from student-submitted PDF version of thesis.
Includes bibliographical references (pages 121-141) and index.
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 in the transonic flow regime, where utter prediction is difficult. The goals for this thesis are to devise a method to reduce the computational burden of including transonic utter constraints in conceptual design tools, and to offer a potential solution for mitigating utter problems through the use of additive manufacturing techniques, specically focusing on a design methodology for lattice structures. To reduce the computational expense of considering transonic utter in conceptual aircraft design, a physics-based low-order method for transonic utter prediction is developed, which is based on small unsteady disturbances about a known steady flow solution. The states of the model are the circulation and doublet perturbations, and their evolution equation coefficients are calibrated using off-line unsteady two-dimensional flow simulations. The model is formulated for swept high-aspect ratio wings through strip theory and 3D corrections. The resulting low-order unsteady flow model is coupled to a typical-section structural model (for airfoils) or a beam model (for wings) to accurately predict utter of airfoils and wings. The method is fast enough to permit incorporation of transonic utter constraints in conceptual aircraft design calculations, as it only involves solving for the eigenvalues of small state-space systems. This model is used to describe the influence of transonic utter on next generation aircraft configurations, where it was found that transonic utter constraints can limit the eciency gains seen by better material technology. As a potential approach for mitigating utter, additively manufactured lattice structures are aeroelastically tailored to increase the flutter margin of wings. Adaptive meshing techniques are used to design the topology of the lattice to align with the load direction while adhering to manufacturing constraints, and the lattice is optimized to minimize the structural weight and to improve the flutter margin. The internal structure of a wing is aeroelastically tailored using this design strategy to increase the flutter margin, which only adds minimal weight to the structure due to the large design freedom the lattice structure offers.
by Max Maria Jacques Opgenoord.
Ph. D.
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.
Texto completoDelamore-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.
Texto completoKassem, 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/.
Texto completoPerry, Brendan. "Predictions of flutter at transonic speeds". Thesis, University of Manchester, 2009. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.498853.
Texto completoLee, Sung-yeoul. "Viscous effects in predicting transonic flutter boundary". Thesis, Cranfield University, 2001. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.393619.
Texto completoMoyroud, 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.
Texto completoMoyroud, François. "Fluid-structure integrated computational methods for turbomachinery blade flutter and forced response predictions". Lyon, INSA, 1998. http://www.theses.fr/1998ISAL0101.
Texto completoThe lightweight, high performance bladed-disks used in today's aeroengines must meet strict standards in terms of aeroelastic stability and resonant response characteristics. The research presented in this thesis is directed toward improved prediction and understanding of blade flutters and forced response problems in turbomachines. To address the blade flutter problem, two aeroelastic analysis methods are considered: the energy method (fluid-structure uncoupled approach) and the modal aeroelastic coupling scheme (fluid-structure coupled approach). The two methods have been implemented in the STRUFLO master code which is designed to provide fluid-structure interfaces for a library of structural and flow solvers. Especially tailored methods are used to couple or interface a wide range of structural and aerodynamic analyses. First, the modal aeroelastic coupling scheme is extended to deal with single blade, cyclic symmetric and full assembly modal analyses as weil as single and multiple blade passage unsteady aerodynamic analyses. Second, an interfacing grid technique is proposed to circumvent problems due to the presence of non-conforming fluid and structural grids at the interface. Finally, a grid-to-grid interpolation/extrapolation scheme is used to transfer blade mode shapes and blade surface unsteady pressures from the structural grid to the aerodynamic grid and vice versa. One structural characteristic of bladed-disks that can significantly impact bath on the aeroelastic stability and the resonant response is that of structural mistuning. With this respect, two reduction methods have been developed to perform full assembly modal analyses and forced response analyses. Various numerical applications are proposed to illustrate the applicability of the above mentioned methods including structural dynamic, aerodynamic and aeroelastic analyses of the NASA Rotor 67 unshrouded transonic fan, a shrouded transonic fan and a subsonic wide chard fan
Lee, Yun-Chou y 李韻舟. "Identification and prediction of flutter derivatives using artificial neural network". Thesis, 2004. http://ndltd.ncl.edu.tw/handle/wz367b.
Texto completo中原大學
土木工程研究所
92
This investigation develops an artificial neural network (ANN) algorithm to identify aeroelastic parameters of cable-supported bridge section models in smooth flow and turbulent flow in a wind tunnel test. The ANN approach method uses observed dynamic responses to train a back-propagation (BP) neural network frame. The characteristic parameters of the section model for various wind velocities are estimated using weight matrices in the neural network. The eight flutter derivatives can then be determined precisely. The procedure can be applied to process experimental data obtained from wind tunnel tests involving flat plate section models given various width/depth (B/D) ratios. Finally, the flutter characteristics of various bluff bodies are examined, as they are very sensitive to geometry and structural dynamics.
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.
Texto completoBoersma, Pieter. "A NUMERICAL FLUTTER PREDICTOR FOR 3D AIRFOILS USING THE ONERA DYNAMIC STALL MODEL". 2018. https://scholarworks.umass.edu/masters_theses_2/692.
Texto completoPAIFELMAN, ELENA. "Optimal control of systems with memory". Doctoral thesis, 2019. http://hdl.handle.net/11573/1229231.
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