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Academic literature on the topic 'Flutter Margin'

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Published: 6 September 2023

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Journal articles on the topic "Flutter Margin"

1

Abbasi, A. A., and J. E. Cooper. "Statistical evaluation of flutter boundaries from flight flutter test data." Aeronautical Journal 113, no. 1139 (January 2009): 41–51. http://dx.doi.org/10.1017/s0001924000002761.

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AbstractA methodology is described that determines the statistical confidence bounds on the results from flight flutter tests: modal parameter estimates, flutter margin values and flutter speed estimates, without the need for Monte-Carlo simulation. The approach is based on least squares statistics and eigenvalue perturbation theory applied to the various stages of the analysis process, starting with frequency and damping estimation through to the flutter margin calculations. The technique is demonstrated upon a number of data sets from aeroelastic simulations of flight flutter tests.
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2

Zafari, E., MM Jalili, and A. Mazidi. "Analytical nonlinear flutter and sensitivity analysis of aircraft wings subjected to a transverse follower force." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 4 (February 1, 2018): 1503–15. http://dx.doi.org/10.1177/0954410017754171.

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In the present study, the nonlinear aeroelastic and sensitivity analysis of high aspect ratio wings subjected to a transverse follower force are discussed. A nonlinear structural model of wings is extracted and coupled with an incompressible unsteady aerodynamic model. The governing equations of motions are obtained via Hamilton’s principle and Galerkin method. Utilizing the method of multiple-scales, analytical approximate flutter response of the system is obtained. For validation, the analytical solution is compared with numerical solution and good agreement is observed. The time history of the tip displacement and tip twist solution are plotted for different airspeeds. Effects of follower force and its spanwise location and also the wing geometric characteristics on the flutter margin are discussed. Moreover, flutter margin sensitivity to different design parameters is analyzed. Results indicate that increasing the wing chord makes the system unstable. Furthermore, according to the analytical solution, effects of the wing chord and mass per unit length on the flutter margins are more important than the other system parameters.
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3

Niblett, LL T. "The fundamentals of body-freedom flutter." Aeronautical Journal 90, no. 899 (November 1986): 373–77. http://dx.doi.org/10.1017/s0001924000015979.

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SummaryThe object of this paper is to uncover the nature of the destabilising coupling that is the major cause of body-freedom flutter and to see whether a simple cure for the flutter can be found. To do this frequency-coalesence theory is applied to a simple aircraft. It is shown that the aircraft is liable to flutter if it has a sweptforward wing and a positive ‘tail-off’ cg margin or a sweptback wing and a negative cg margin but a simple cure for the flutter does not appear to exist.
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4

Sudha, U. P. V., G. S. Deodhare, and K. Venkatraman. "A comparative assessment of flutter prediction techniques." Aeronautical Journal 124, no. 1282 (October 27, 2020): 1945–78. http://dx.doi.org/10.1017/aer.2020.84.

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ABSTRACTTo establish flutter onset boundaries on the flight envelope, it is required to determine the flutter onset dynamic pressure. Proper selection of a flight flutter prediction technique is vital to flutter onset speed prediction. Several methods are available in literature, starting with those based on velocity damping, envelope functions, flutter margin, discrete-time Autoregressive Moving Average (ARMA) modelling, flutterometer and the Houbolt–Rainey algorithm. Each approach has its capabilities and limitations. To choose a robust and efficient flutter prediction technique from among the velocity damping, envelope function, Houbolt–Rainey, flutter margin and auto-regressive techniques, an example problem is chosen for their evaluation. Hence, in this paper, a three-degree-of-freedom model representing the aerodynamics, stiffness and inertia of a typical wing section is used(1). The aerodynamic, stiffness and inertia properties in the example problem are kept the same when each of the above techniques is used to predict the flutter speed of this aeroelastic system. This three-degree-of-freedom model is used to generate data at speeds before initiation of flutter, during flutter and after occurrence of flutter. Using these data, the above-mentioned flutter prediction methods are evaluated and the results are presented.
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5

Yang, Zhi Chun, and Ying Song Gu. "Robust Flutter Analysis of an Airfoil with Flap Freeplay Uncertainty." Advanced Materials Research 33-37 (March 2008): 1247–52. http://dx.doi.org/10.4028/www.scientific.net/amr.33-37.1247.

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Modern robust flutter method is an advanced technique for flutter margin estimation. It always gives the worst-case flutter speed with respect to potential modeling errors. Most literatures are focused on linear parameter uncertainty in mass, stiffness and damping parameters, etc. But the uncertainties of some structural nonlinear parameters, the freeplay in control surface for example, have not been taken into account. A robust flutter analysis approach in μ-framework with uncertain nonlinear operator is proposed in this study. Using describing function method the equivalent stiffness formulation is derived for a two dimensional wing model with freeplay nonlinearity in its flap rotating stiffness. The robust flutter margin is calculated for the two dimensional wing with flap freeplay uncertainty and the results are compared with that obtained with nominal parameter values. It is found that by considering the perturbation of freeplay parameter more conservative flutter boundary can be obtained, and the proposed method in μ-framework can be applied in flutter analysis with other types of concentrated nonlinearities.
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6

Torii, Hiroshi, and Yuji Matsuzaki. "Flutter Margin Evaluation for Discrete-Time Systems." Journal of Aircraft 38, no. 1 (January 2001): 42–47. http://dx.doi.org/10.2514/2.2732.

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7

MATSUDAIRA, Yasuaki, Hiroyuki NAKAGAWA, Hikaru YOSHIDA, and Hiromichi OBARA. "Supercavitation Hydrofoil Performance and Torsional Flutter Margin." Transactions of the Japan Society of Mechanical Engineers Series B 66, no. 648 (2000): 2079–86. http://dx.doi.org/10.1299/kikaib.66.648_2079.

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8

Corpas, J. L. Casado, and J. López Díez. "Flutter margin with non-linearities: Real-time prediction of flutter onset speed." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 222, no. 6 (June 2008): 921–29. http://dx.doi.org/10.1243/09544100jaero251.

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9

Saputra, Angga Dwi, and R. Wibawa Purabaya. "Prediction of Flutter Boundary Using Flutter Margin for The Discrete-Time System." Journal of Physics: Conference Series 1005 (April 2018): 012019. http://dx.doi.org/10.1088/1742-6596/1005/1/012019.

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10

Price, S. J., and B. H. K. Lee. "Evaluation and Extension of the Flutter-Margin Method for Flight Flutter Prediction." Journal of Aircraft 30, no. 3 (May 1993): 395–402. http://dx.doi.org/10.2514/3.56887.

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Dissertations / Theses on the topic "Flutter Margin"

1

Luce, Brian. "Light From Behind the Iron Curtain: Anti-Collectivist Style in Edison Denisov's Quatre Pièces pour flûte et piano, With Three Recitals of Selected Works by Bach, Beaser, Carter, Fauré, Martin, Ibert, Liebermann, and Others." Thesis, University of North Texas, 2000. https://digital.library.unt.edu/ark:/67531/metadc2564/.

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An examination of the compositional style illustrative of the anti-collectivist ideology as found in Edison Denisov's Quatre Pièces pour flûte et piano. Includes a short history of Denisov's formal training, history of the Soviet musical environment, an overview of his creative output, and discussion of the anti-collectivist characteristics in his works. Defines the anti-collectivist doctrine as individual reaction to the totalitarian collective of the Soviet communist state of the twentieth century. Identification of eclectic compositional techniques, and how they represent individual expression under a totalitarian regime. Listing of Denisov's works with the flute in a primary role, interviews with Aurèle Nicolet and Ekaterina Denisov, correspondence from Denisov to Nicolet, and the manuscript score to Quatre Pièces pour flûte et piano follow as appendices.
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2

Kumar, Brijesh. "Flutter Susceptibility Assessment of Airplanes in Sub-critical Regime using Ameliorated Flutter Margin and Neural Network Based Methods." Thesis, 2014. http://etd.iisc.ac.in/handle/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, which eventually results in increased development time and associated costs. There has been a constant demand from the flight test community to improve understanding of the con-ventional methods and develop new methods that could enable ground-station engineers to make better decision with regard to flutter susceptibility of structural components on the airframe. An extensive literature survey has been done for many years to take due cognizance of the ground realities, historical developments, and the state of the art. Besides, discussion on the results of a survey carried on occurrences of flutter among general aviation airplanes has been provided at the very outset. Data for research comprises results of Computational Aero elasticity Analysis (CAA) and limited Flight Flutter Tests (FFTs) on two slightly different structural designs of the airframe of a supersonic fixed-wing airplane. Detail discussion has been provided with regard to the nature of the data, the certification requirements for an airplane to be flutter-free in the flight-envelope, and the adopted process of flight flutter testing. Four flutter-prone modes - with two modes forming a symmetric bending-pitching flutter mechanism and the other two forming an anti-symmetric bending-pitching mechanism have been identified based on the analysis of computational data. CAA and FFT raw data of these low frequency flutter modes have been provided followed by discussion on its quality and flutter susceptibility of the critical mechanisms. Certain flight-conditions, at constant altitude line and constant Mach number lines, have been chosen on the basis of availability of FFT data near the same flight conditions. Modal damping is often a highly non-linear function of airspeed and scatter in such trends of modal damping can be very misleading. Flutter margin (FM) parameter, a measure of the remaining stability in a binary flutter mechanism, exhibits smooth and gradual variation with dynamic pressure. First, this thesis brings out the established knowledge of the flutter margin method and marks the continuing knowledge-gaps, especially about the applicable form of the flutter margin prediction equation in transonic region. Further theoretical developments revealed that the coefficients of this equation are flight condition depended to a large extent and the equation should be only used in small ‘windows’ of the flight-envelope by making the real-time flutter susceptibility assessment ‘progressive’ in nature. Firstly, it is brought out that lift curve slope should not be treated as a constant while using the prediction equation at constant altitudes on an airplane capable of transonic flight. Secondly, it was realized that the effect of shift in aerodynamic canter must be considered as it causes a ‘transonic-hump’. Since the quadratic form of flutter margin prediction equation developed 47 years ago, does not provide a valid explanation in that region, a general equation has been derived. Furthermore, flight test data from only supersonic region must be used for making acceptable predictions in supersonic region. The ‘ameliorated’ flutter margin prediction equation too provides bad predictions in transonic region. This has been attributed to the non-validity of quasi-steady approximation of aerodynamic loads and other additional non-linear effects. Although the equation with effect of changing lift curve slope provides inconsistent predictions inside and near the region of transonic-hump, the errors have been acceptable in most cases. No consistent congruency was discovered to some earlier reports that FM trend is mostly parabolic in subsonic region and linear in supersonic region. It was also found that the large scatter in modal frequencies of the constituent modes can lead to scatter in flutter margin values which can render flutter margin method as ineffective as the polynomial fitting of modal damping ratios. If the modal parameters at a repeated test-point exhibit Gaussian spread, the distribution in FM is non-Gaussian but close to gamma-type. Fifteen uncertainty factors that cause scatter in modal data during FFT and factor that cause modelling error in a computational model have been enumerated. Since scatter in modal data is ineluctable, it was realized that a new predictive tool is needed in which the probable uncertainty can be incorporated proactively. Given the recent shortcomings of NASA’s flutter meter, the neural network based approach was recognized as the most suitable one. MLP neural network have been used successfully in such scenarios for function approximation through input-output mapping provided the domains of the two are remain finite. A neural network requires ample data for good learning and some relevant testing data for the evaluation of its performance. It was established that additional data can be generated by perturbing modal mass matrix in the computational model within a symmetric bound. Since FFT is essentially an experimental process, it was realized that such bound should be obtained from experimental data only, as the full effects of uncertainty factors manifest only during flight tests. The ‘validation FFT program’, a flight test procedure for establishing such bound from repeated tests at five diverse test-points in safe region has been devised after careful evaluation of guide-lines and international practice. A simple statistical methodology has been devised to calculate the bound-of-uncertainty when modal parameters from repeated tests show Gaussian distribution. Since no repeated tests were conducted on the applicable airframe, a hypothetical example with compatible data was considered to explain the procedure. Some key assumptions have been made and discussion regarding their plausibility has been provided. Since no updated computational model was made available, the next best option of causing random variation in nominal values of CAA data was exercised to generate additional data for arriving at the final form of neural network architecture and making predictions of damping ratios and FM values. The problem of progressive flutter susceptibility assessment was formulated such that the CAA data from four previous test-points were considered as input vectors and CAA data from the next test-point was the corresponding output. General heuristics for an optimal learning performance has been developed. Although, obtaining an optimal set of network parameters has been relatively easy, there was no single set of network parameters that would lead to consistently good predictions. Therefore some fine-tuning, of network parameters about the optimal set was often needed to achieve good generalization. It was found that data from the four already flown test-points tend to dominate network prediction and the availability of flight-test data from these previous test-points within the bound about nominal is absolutely important for good predictions. The performance improves when all the five test-points are closer. If above requirements were met, the predictive performance of neural network has been much more consistent in flutter margin values than in modal damping ratios. A new algorithm for training MLP network, called Particle Swarm Optimization (PSO) has also been tested. It was found that the gradient descent based algorithm is much more suitable than PSO in terms of training time, predictive performance, and real-time applicability. In summary, the main intellectual contributions of this thesis are as follows: • Realization of that the fact that secondary causes lead incidences of flutter on airplanes than primary causes. • Completion of theoretical understanding of data-based flutter margin method and flutter margin prediction equation for all ranges of flight Mach number, including the transonic region. • Vindication of the fact that including lift-curve slope in the flutter margin pre-diction equation leads to improved predictions of flutter margins in subsonic and supersonic regions and progressive flutter susceptibility assessment is the best way of reaping benefits of data-based methods. • Explanation of a plausible recommended process for evaluation of uncertainty in modal damping and flutter margin parameter. • Realization of the fact that a MLP neural network, which treats a flutter mechanism as a stochastic non-linear system, is a indeed a promising approach for real-time flutter susceptibility assessment.
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3

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.

Full text
Abstract:
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, which eventually results in increased development time and associated costs. There has been a constant demand from the flight test community to improve understanding of the con-ventional methods and develop new methods that could enable ground-station engineers to make better decision with regard to flutter susceptibility of structural components on the airframe. An extensive literature survey has been done for many years to take due cognizance of the ground realities, historical developments, and the state of the art. Besides, discussion on the results of a survey carried on occurrences of flutter among general aviation airplanes has been provided at the very outset. Data for research comprises results of Computational Aero elasticity Analysis (CAA) and limited Flight Flutter Tests (FFTs) on two slightly different structural designs of the airframe of a supersonic fixed-wing airplane. Detail discussion has been provided with regard to the nature of the data, the certification requirements for an airplane to be flutter-free in the flight-envelope, and the adopted process of flight flutter testing. Four flutter-prone modes - with two modes forming a symmetric bending-pitching flutter mechanism and the other two forming an anti-symmetric bending-pitching mechanism have been identified based on the analysis of computational data. CAA and FFT raw data of these low frequency flutter modes have been provided followed by discussion on its quality and flutter susceptibility of the critical mechanisms. Certain flight-conditions, at constant altitude line and constant Mach number lines, have been chosen on the basis of availability of FFT data near the same flight conditions. Modal damping is often a highly non-linear function of airspeed and scatter in such trends of modal damping can be very misleading. Flutter margin (FM) parameter, a measure of the remaining stability in a binary flutter mechanism, exhibits smooth and gradual variation with dynamic pressure. First, this thesis brings out the established knowledge of the flutter margin method and marks the continuing knowledge-gaps, especially about the applicable form of the flutter margin prediction equation in transonic region. Further theoretical developments revealed that the coefficients of this equation are flight condition depended to a large extent and the equation should be only used in small ‘windows’ of the flight-envelope by making the real-time flutter susceptibility assessment ‘progressive’ in nature. Firstly, it is brought out that lift curve slope should not be treated as a constant while using the prediction equation at constant altitudes on an airplane capable of transonic flight. Secondly, it was realized that the effect of shift in aerodynamic canter must be considered as it causes a ‘transonic-hump’. Since the quadratic form of flutter margin prediction equation developed 47 years ago, does not provide a valid explanation in that region, a general equation has been derived. Furthermore, flight test data from only supersonic region must be used for making acceptable predictions in supersonic region. The ‘ameliorated’ flutter margin prediction equation too provides bad predictions in transonic region. This has been attributed to the non-validity of quasi-steady approximation of aerodynamic loads and other additional non-linear effects. Although the equation with effect of changing lift curve slope provides inconsistent predictions inside and near the region of transonic-hump, the errors have been acceptable in most cases. No consistent congruency was discovered to some earlier reports that FM trend is mostly parabolic in subsonic region and linear in supersonic region. It was also found that the large scatter in modal frequencies of the constituent modes can lead to scatter in flutter margin values which can render flutter margin method as ineffective as the polynomial fitting of modal damping ratios. If the modal parameters at a repeated test-point exhibit Gaussian spread, the distribution in FM is non-Gaussian but close to gamma-type. Fifteen uncertainty factors that cause scatter in modal data during FFT and factor that cause modelling error in a computational model have been enumerated. Since scatter in modal data is ineluctable, it was realized that a new predictive tool is needed in which the probable uncertainty can be incorporated proactively. Given the recent shortcomings of NASA’s flutter meter, the neural network based approach was recognized as the most suitable one. MLP neural network have been used successfully in such scenarios for function approximation through input-output mapping provided the domains of the two are remain finite. A neural network requires ample data for good learning and some relevant testing data for the evaluation of its performance. It was established that additional data can be generated by perturbing modal mass matrix in the computational model within a symmetric bound. Since FFT is essentially an experimental process, it was realized that such bound should be obtained from experimental data only, as the full effects of uncertainty factors manifest only during flight tests. The ‘validation FFT program’, a flight test procedure for establishing such bound from repeated tests at five diverse test-points in safe region has been devised after careful evaluation of guide-lines and international practice. A simple statistical methodology has been devised to calculate the bound-of-uncertainty when modal parameters from repeated tests show Gaussian distribution. Since no repeated tests were conducted on the applicable airframe, a hypothetical example with compatible data was considered to explain the procedure. Some key assumptions have been made and discussion regarding their plausibility has been provided. Since no updated computational model was made available, the next best option of causing random variation in nominal values of CAA data was exercised to generate additional data for arriving at the final form of neural network architecture and making predictions of damping ratios and FM values. The problem of progressive flutter susceptibility assessment was formulated such that the CAA data from four previous test-points were considered as input vectors and CAA data from the next test-point was the corresponding output. General heuristics for an optimal learning performance has been developed. Although, obtaining an optimal set of network parameters has been relatively easy, there was no single set of network parameters that would lead to consistently good predictions. Therefore some fine-tuning, of network parameters about the optimal set was often needed to achieve good generalization. It was found that data from the four already flown test-points tend to dominate network prediction and the availability of flight-test data from these previous test-points within the bound about nominal is absolutely important for good predictions. The performance improves when all the five test-points are closer. If above requirements were met, the predictive performance of neural network has been much more consistent in flutter margin values than in modal damping ratios. A new algorithm for training MLP network, called Particle Swarm Optimization (PSO) has also been tested. It was found that the gradient descent based algorithm is much more suitable than PSO in terms of training time, predictive performance, and real-time applicability. In summary, the main intellectual contributions of this thesis are as follows: • Realization of that the fact that secondary causes lead incidences of flutter on airplanes than primary causes. • Completion of theoretical understanding of data-based flutter margin method and flutter margin prediction equation for all ranges of flight Mach number, including the transonic region. • Vindication of the fact that including lift-curve slope in the flutter margin pre-diction equation leads to improved predictions of flutter margins in subsonic and supersonic regions and progressive flutter susceptibility assessment is the best way of reaping benefits of data-based methods. • Explanation of a plausible recommended process for evaluation of uncertainty in modal damping and flutter margin parameter. • Realization of the fact that a MLP neural network, which treats a flutter mechanism as a stochastic non-linear system, is a indeed a promising approach for real-time flutter susceptibility assessment.
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4

Sudha, U. P. V. "Flutter Identification and Aeroelastic Stability during Wake Penetration." Thesis, 2015. https://etd.iisc.ac.in/handle/2005/4799.

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Demonstration of utter stability over the design envelope and identi fication of safe ight envelope is a prerequisite for operational clearance of any new aircraft design. An important step involved in flight flutter testing is the proper use of flutter prediction techniques to accurately predict flutter. This study focuses on flutter estimation techniques given flight test data. We review various flutter prediction techniques by simulating them on a three-degree-of-freedom aeroelastic system. We show that flutter margin and an auto-regressive model based approach are robust and reasonably accurate in predicting flutter onset. Using these two techniques, flutter margins are computed at flight test points obtained from flight test data of flexible aircraft. Throughout, we have predicted flutter dynamic pressure at constant Mach number. One of the contributions of this work is in predicting flutter dynamic pressure at transonic Mach numbers. A critical issue in flutter prediction is the lack of information on the flutter instability mode and thereby the number of modes to include in a model. In a novel application of tools from statistical signal processing, we determine the optimum model order to construct an auto-regressive model using the flight flutter test time response data. From this auto-regressive model the frequency and damping values are estimated which in turn is used to estimate aeroelastic stability parameters. High resolution property of auto-regressive technique even with short data records is demonstrated in this thesis. This will provide a quick evaluation of spectral estimate and stability parameter using the same auto-regressive model, facilitating a quick envelope expansion. Aeroelastic stability during wake penetration is an essential part of operational clearance of new aircraft. In this thesis, and perhaps one of the first such study, wake flight test response data is used to assess the stability of the aircraft during wake penetration by modeling the wake response data in an auto-regressive framework. We have compared analytical predictions of incremental load factor based on simulations with flight tests on wake interactions. Estimates for safe wake encounter distance that do not exceed structural limit load factors have been determined.
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5

Ming, Huang Chun, and 黃俊銘. "The Analysis and Interpretation of Frank Martin Ballade for Flute and Piano." Thesis, 2010. http://ndltd.ncl.edu.tw/handle/64762280811386874714.

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碩士
輔仁大學
音樂研究所
99
Martin (Frank Martin, 1890-1974) was an important composer in the 20th century. Besides composing, simultaneously he was also a pianist and a harpsichordist. Although he was Swiss, Martin also set his foot in France, Holland and Germany. Such experience presented diversified and integrable creation techniques in Martin's works. Ballade for Flute and Piano is the work which is quite popular in the flute concert programs. Although he utilized the brief musical forms, the rhythmic motives and the speed changes, the entire piece presents the dramatic tensity. This piece has two kinds of different accompaniment editions. One was completed in 1939- the flute and piano's edition, another edition was arranged for string orchestra and piano's in 1947. This research was based on the former edition, discussed its music analysis and the performance interpretation. The music in the 20th century broke free of shackles of the tonality and the musical form, the author made an integrable research by referring to the specialized books- the 20th century music theory and voice materials, and collected the information of the growth background and history of the composer etc. At the end, the author summed up and analyzed the results of the music analysis and the performance interpretation.
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6

Jelle, Lisa A. "The flute and piccolo music of Martin Amlin: An introduction, discussion, and analyses of the Sonata for Flute and Piano; "Trio Sonatina" for flute, clarinet, and piano; and Sonata for Piccolo and Piano." Thesis, 2000. http://hdl.handle.net/1911/19514.

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The compositional style of music for flute and piccolo by Martin Amlin is examined through formal and harmonic analyses and through interviews with the composer and the musicians most closely associated with the works, flutist Leone Buyse and piccoloist Zart Dombourian-Eby. Amlin's compositional style as represented in these pieces may be described as combining characteristic twentieth-century American driving rhythms and perpetual motion, symmetry on multiple levels, and a unique blend of French use of color and phrasing. Complex rhythms and constantly-shifting meters and timbres give the music a kaleidoscopic effect. The composer's fascination with symmetry is reflected both formally and harmonically, in both the often-used arch form and the frequent use of serialism based on symmetrical tone rows. Symmetrical division of meter often produces jazz rhythms, and major and minor 7th chords are featured due to their symmetrical sound. Amlin's style of serialism appeals to many because of its unusual, almost-tonal sound. This effect is due to the structure of the rows, in which half of the intervals are perfect 4ths; many major and minor 7th chords are produced internally. This is intentional on the part of the composer, who is not so much intent on abandoning all tonality as on producing music that finds favor with both the ear and the mind. All three pieces exhibit use of the full range of the instruments, a quality that both Buyse and Dombourian-Eby mentioned as appealing to them. Yet, as in the style of the best sonatas of the repertoire, the parts are balanced; lines interweave, rise, and fall in a balanced whole. As more flutists become aware of the quality of these works, they will become a strong and vibrant staple of the body of flute and piccolo literature.
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7

廖怡貞. "The Analysis and Interpretation of Baroque Flute Suite Jacques-Martin Hotteterre’s Troisiéme Suite in G Major, Op. 2." Thesis, 2013. http://ndltd.ncl.edu.tw/handle/52341293509414974637.

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碩士
國立嘉義大學
音樂學系
101
In Baroque era, instrumental music grown up and creative works increased, during the splendid time, many compositions began to show fantastic techniques. In order to meet the requirement of compositions, instrumental fabrication of winds was improved, especially for woodwind. The one-keyed flute was born under the fabrication of Hotteterre family who were famous for instrumental fabrication in France. Jacques-Martin Hotteterre ( 1674-1763 ), a member of Hotteterre family, delivered Principes de la Flûte Traversière in 1707, the treatise was the first of its kind and remained an important source of information on tonguing and ornamentation. His publication of suites for flute in 1708 further contributed to the elucidation of flute performance. During the Baroque period, unique composition methods and musical styles of genres were developed, and the suite was at the top of its form among them. Due to the differences in style between movements, the transformation interpretation became important. Nowadays, the Baroque music has its own interpretation of performance, more and more instrumentation are examined and recorded. Some musicians even use ancient instrument and methods to reproduce the contemporary music. Owing to the importance of the Baroque music and the characteristics of suites, and the impact from Hotteterre on flute performance instruction and construction evolution, this study applies documentary analysis to investigate not only Hotteterre’s entire life and his works, but also the evolution of dance music and suites. On the other hand, the music style and performance interpretation of movements in Jacques-Martin Hotteterre’s Troisiéme Suite in G Major, Op. 2 is understood by musical form analysis. In this study, reference documents about Hotteterre are recorded, and it helps performers to interpret the Baroque and Hotteterre’s works. Keywords: Hotteterre, Flute, Baroque, Suite, Dance music
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Books on the topic "Flutter Margin"

1

J, Brenner Martin, and NASA Dryden Flight Research Center., eds. Robust flutter margin analysis that incorporates flight data. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1998.

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2

Lind, Rick. Robust flutter margin analysis that incorporates flight data. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1998.

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3

NASA Dryden Flight Research Center., ed. A presentation on robust flutter margin analysis and a flutterometer. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1997.

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United States. National Aeronautics and Space Administration., ed. WORST-CASE FLUTTER MARGINS FROM F/A-18 AIRCRAFT AEROELASTIC DATA ... NASA/TM-97-207564... MAY 5, 1998. [S.l: s.n., 1999.

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United States. National Aeronautics and Space Administration., ed. WORST-CASE FLUTTER MARGINS FROM F/A-18 AIRCRAFT AEROELASTIC DATA ... NASA/TM-97-207564... MAY 5, 1998. [S.l: s.n., 1999.

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National Aeronautics and Space Administration (NASA) Staff. Rotor Design Options for Improving XV-15 Whirl-Flutter Stability Margins. Independently Published, 2018.

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Martin, Frank. Frank Martin: Ballade Pour Flute Et Piano (Paula Robison Masterclass). Universal Edition, 2003.

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Book chapters on the topic "Flutter Margin"

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Lind, Rick, and Marty Brenner. "Robust Flutter Margins of the F/A-18 SRA." In Robust Aeroservoelastic Stability Analysis, 153–71. London: Springer London, 1999. http://dx.doi.org/10.1007/978-1-4471-0849-8_11.

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Solheim, Anders, and Anders Elverhøi. "Submarine Glacial Flutes and DeGeer Moraines." In Glaciated Continental Margins, 56–57. Dordrecht: Springer Netherlands, 1997. http://dx.doi.org/10.1007/978-94-011-5820-6_17.

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Pudsey, Carol J., Peter F. Barker, and Robert D. Larter. "Glacial Flutes and Iceberg Furrows, Antarctic Peninsula." In Glaciated Continental Margins, 58–59. Dordrecht: Springer Netherlands, 1997. http://dx.doi.org/10.1007/978-94-011-5820-6_18.

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Clark, Kate, and Amanda Markwick. "The Hexachord." In The Renaissance Flute, 160–73. Oxford University Press, 2020. http://dx.doi.org/10.1093/oso/9780190913335.003.0012.

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In Chapter 12, we present the three primary hexachords used in the Renaissance, plus basic advice on how to apply them to the music. We also consider Martin Agricola’s suggestion that the six different hexachord syllables had distinctive intrinsic qualities, which could open up new expressive possibilities for the more advanced musician approaching renaissance music.
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Conference papers on the topic "Flutter Margin"

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Fucun, Qu. "Determination of Flutter Boundary by Robust Flutter Margin Method." In 2012 International Conference on Industrial Control and Electronics Engineering (ICICEE). IEEE, 2012. http://dx.doi.org/10.1109/icicee.2012.280.

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Wu, Zhigang, and Jonathan E. Cooper. "Active Flutter Suppression Combining the Receptance Method and Flutter Margin." In 57th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-1227.

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Tamayama, Masato, Hitoshi Arizono, Kenichi Saitoh, and Norio Yoshimoto. "Development of flutter margin prediction program." In 9TH INTERNATIONAL CONFERENCE ON MATHEMATICAL PROBLEMS IN ENGINEERING, AEROSPACE AND SCIENCES: ICNPAA 2012. AIP, 2012. http://dx.doi.org/10.1063/1.4765614.

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Torri, Hiroshi, and Yuji Matsuzaki. "Flutter margin evaluation in discrete-time system." In 39th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-1724.

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Heidersbach, Ross, Dhuree Seth, Matthew McCrink, and Moti Karpel. "Safe Flutter Flight Testing of an Unmanned Aerial Vehicle Utilizing Parametric Flutter Margin." In AIAA SCITECH 2023 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2023. http://dx.doi.org/10.2514/6.2023-2071.

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Roizner, Federico, Moti Karpel, Robert Carrese, Nishit Joseph, and Pier Marzocca. "Parametric Flutter Margin Analysis with CFD-Based Aerodynamics." In 2018 AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-0704.

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Khalil, Mohammad, Abhijit Sarkar, and Dominique Poirel. "Application of Bayesian Inference to the Flutter Margin Method: New Developments." In ASME 2010 3rd Joint US-European Fluids Engineering Summer Meeting collocated with 8th International Conference on Nanochannels, Microchannels, and Minichannels. ASMEDC, 2010. http://dx.doi.org/10.1115/fedsm-icnmm2010-30041.

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Zimmerman and Weissenburger flutter margin method is extended to account for modal parameter uncertainties by applying a Bayesian estimation technique to obtain the probability distribution function of the flutter speed. In previous work, a least-squares estimation technique was applied to obtain the posterior pdf of the flutter speed. The limitation of this technique is the assumption that the flutter margin at each airspeed is strictly Gaussian. In this paper, the joint distribution of the modal parameters (and consequently the flutter margin) is obtained from preflutter measured system responses using a full Bayesian analysis utilizing Markov Chain Monte Carlo sampling technique. The flutter margin pdfs are then utilized to obtain the posterior probability density function of the flutter speed. Results are presented for a two-degrees-of-freedom numerical model, for which the true flutter speed is known.
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Stapelfeldt, Sina, and Mehdi Vahdati. "Improving the Flutter Margin of an Unstable Fan Blade." In ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/gt2018-76889.

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The aim of this paper is to introduce design modifications which can be made to improve the flutter stability of a fan blade. A rig fan blade, which suffered from flutter in the part-speed range and for which good quality measured data in terms of steady flow and flutter boundary is available, is used for this purpose. The work is carried out numerically using the aeroelasticity code AU3D. Two different approaches are explored; aerodynamic modifications and aero-acoustic modifications. In the first approach, the blade is stabilized by altering the radial distribution of the stagger angle based on the steady flow on the blade. The re-staggering patterns used in this work are therefore particular to the fan blade under investigation. Moreover, the modifications made to the blade are very simple and crude and more sophisticated methods and/or an optimization approach could be used to achieve the above objectives with a more viable final design. This paper, however, clearly demonstrates how modifying the steady blade aerodynamics can prevent flutter. In the second approach, flutter is removed by drawing bleed air from the casing above the tip of the blade. Only a small amount of bleed (0.2% of the total inlet flow) is extracted such that the effect on the operating point of the fan is small. The purpose of the bleed is merely to attenuate the pressure wave which propagates from the trailing edge to the leading edge of the blade. The results show that extracting bleed over the tip of the fan blade can improve the flutter margin of the fan significantly.
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Torii, Hiroshi, and Yuji Matsuzaki. "Flutter Margin Evaluation for Three-Mode Discrete-Time Systems." In 52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-2144.

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Pitt, Dale, Darin Haudrich, Michael Thomas, and Kenneth Griffin. "Probabilistic Aeroelastic Analysis and Its Implications on Flutter Margin Requirements." In 49th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
16th AIAA/ASME/AHS Adaptive Structures Conference
10t. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-2198.

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Reports on the topic "Flutter Margin"

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Kerr, D. E. Reconnaissance surficial geology, Mara River, Nunavut, 76-K. Natural Resources Canada/CMSS/Information Management, 2022. http://dx.doi.org/10.4095/329667.

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The Mara River map area consists of extensive glacially and meltwater scoured bedrock, deposits of hummocky till, fluted till blanket, and till veneer throughout the map area, glaciofluvial sediments within major river valleys, and postglacial marine sediments in coastal lowlands. The boundaries of many till deposits were eroded to bedrock by proglacial and subglacial meltwater, and locally northwest-trending corridors are defined by eskers. Glacially dammed lakes, associated with deltas between 450 m and 230 m elevation, occupied some river valleys where retreating or stagnant ice impeded drainage to the east and north. Striations and streamlined landforms indicate a north-northwestward regional ice flow in the eastern and northern regions, diverging to a west-southwestward flow in the western regions. A series of glaciomarine and marine deltas, and fine-grained sediments record the marine incursion up to 200 m elevation. Isostatic rebound caused marine regression, forming deltas between 200 m and 60 m, and raised beaches from 150 m elevation to current sea level.
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Kerr, D. E. Reconnaissance surficial geology, Bloody River, Northwest Territories-Nunavut, NTS 96-P. Natural Resources Canada/CMSS/Information Management, 2022. http://dx.doi.org/10.4095/329457.

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Preliminary surficial geology, based on airphoto interpretation and limited legacy field data of Bloody River map area, records a dynamic Late Wisconsin glacial landscape. Streamlined till and bedrock landforms, relating to Laurentide ice originating east of the map region, indicate regional westward flow diverged northwestward and southwestward at the eastern end of two topographic highs. Ice then converged between and south of these two highs, then diverged at the western end of these highlands. During deglaciation, ice stagnated in northwestern and central highland regions, forming extensive hummocky moraine, large kames, recessional moraines, and kame moraines. In other parts of the map area, hummocky till, small moraines, and undifferentiated till ridges, were deposited over fluted till. Outwash plains, eskers, and meltwater corridors record northwestward to southwestward meltwater flow. Glaciolacustrine sediments associated with glacial Lake McConnell occur in the southeast, up to 280 m elevation. Other unrelated, isolated glaciolacustrine deltas indicate small ice-marginal lakes between 400 and 460 m elevation.
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