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Articles de revues sur le sujet « Flutter Margin »

Auteur : Grafiati

Publié le 6 septembre 2023

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1

Abbasi, A. A., and J. E. Cooper. "Statistical evaluation of flutter boundaries from flight flutter test data." Aeronautical Journal 113, no. 1139 (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 (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

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3

Niblett, LL T. "The fundamentals of body-freedom flutter." Aeronautical Journal 90, no. 899 (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 (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 t

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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 formula

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6

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

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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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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 (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 (1993): 395–402. http://dx.doi.org/10.2514/3.56887.

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11

Casado Corpas, JL, A. Sanz-Lobera, I. González-Requena, and L. Sevilla. "A revision of the flutter margin method to predict in real-time the limit cycle oscillations onset speed with structural freeplay present in the plunge axis." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 1 (2016): 124–42. http://dx.doi.org/10.1177/0954410016638867.

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Computational fluid dynamic and order reducing methods have been extensively applied to predict the flutter onset speed of several types of aircrafts. However, the accuracy required by certification standards still ascribes flight testing as the only method available that safely validates the flight envelope of an aircraft. In particular, free-flutter conditions must be demonstrated in the target flight envelope, and several methods have been developed to determine the flutter onset speed in real-time when expanding the envelope during flight testing. Among the methods, the damping versus velo

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12

Poirel, Dominique, Shane Dunn, and Jay Porter. "Flutter-Margin Method Accounting for Modal Parameters Uncertainties." Journal of Aircraft 42, no. 5 (2005): 1236–43. http://dx.doi.org/10.2514/1.7778.

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Roizner, Federico, and Moti Karpel. "Parametric Flutter Margin Method for Aeroservoelastic Stability Analysis." AIAA Journal 56, no. 3 (2018): 1011–22. http://dx.doi.org/10.2514/1.j056514.

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14

Baldelli, Dario H., Hirobumi Ohta, Hiroshi Matsushita, Masataka Hashidate, and Kenichi Saitoh. "Flutter margin augmentation synthesis using normalized coprime factors approach." Journal of Guidance, Control, and Dynamics 18, no. 4 (1995): 802–11. http://dx.doi.org/10.2514/3.21462.

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15

Khalil, Mohammad, Dominique Poirel, and Abhijit Sarkar. "Bayesian analysis of the flutter margin method in aeroelasticity." Journal of Sound and Vibration 384 (December 2016): 56–74. http://dx.doi.org/10.1016/j.jsv.2016.07.016.

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16

Lu, P. J., and S. K. Chen. "Evaluation of Acoustic Flutter Suppression for Cascade in Transonic Flow." Journal of Engineering for Gas Turbines and Power 124, no. 1 (2000): 209–19. http://dx.doi.org/10.1115/1.1365933.

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Flutter suppression via actively excited acoustic waves is a new idea proposed recently. The high flutter frequency (typically 50–500 Hz for a fan blade) and stringent space constraint make conventional mechanical type flutter suppression devices difficult to implement for turbomachines. Acoustic means arises as a new alternative which avoids the difficulties associated with the mechanical methods. The objective of this work is to evaluate numerically the transonic flutter suppression concept based on the application of sound waves to two-dimensional cascade configuration. This is performed us

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17

MATSUDAIRA, Yasuaki, and Naoto OKAZAKI. "Fluid Force and Flutter Margin of a Pitching Hydrofoil in Subcavitation Region." Transactions of the Japan Society of Mechanical Engineers Series B 63, no. 613 (1997): 2938–44. http://dx.doi.org/10.1299/kikaib.63.2938.

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18

Schildkamp, Roderick, Jing Chang, Jurij Sodja, Roeland De Breuker, and Xuerui Wang. "Incremental Nonlinear Control for Aeroelastic Wing Load Alleviation and Flutter Suppression." Actuators 12, no. 7 (2023): 280. http://dx.doi.org/10.3390/act12070280.

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This paper proposes an incremental nonlinear control method for an aeroelastic system’s gust load alleviation and active flutter suppression. These two control objectives can be achieved without modifying the control architecture or the control parameters. The proposed method has guaranteed stability in the Lyapunov sense and also has robustness against external disturbances and model mismatches. The effectiveness of this control method is validated by wind tunnel tests of an active aeroelastic parametric wing apparatus, which is a typical wing section containing heave, pitch, flap, and spoile

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19

Pizzoli, Marco, Francesco Saltari, and Franco Mastroddi. "Linear and Nonlinear Reduced Order Models for Sloshing for Aeroelastic Stability and Response Predictions." Applied Sciences 12, no. 17 (2022): 8762. http://dx.doi.org/10.3390/app12178762.

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This paper makes use of sloshing reduced-order models to investigate the effects of sloshing dynamics on aeroelastic stability and response of flying wing structure. More specifically, a linear frequency-domain operator derived by an equivalent mechanical model is used to model lateral (linear) sloshing dynamics whereas data-driven neural-networks are used to model the vertical (nonlinear) sloshing dynamics. These models are integrated into a formulation that accounts for both the rigid and flexible behavior of aircraft. A time domain representation of the unsteady aerodynamics is achieved by

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20

Ueda, Takeo. "AEROELASTIC ANALYSIS CONSIDERING STRUCTURAL UNCERTAINTY." Aviation 9, no. 1 (2005): 3–7. http://dx.doi.org/10.3846/16487788.2005.9635889.

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Uncertainties in aero elastic analysis are investigated. In aero elastic analysis, we usually find divergence speed or flutter speed by using deterministic equations of motion for elastic wings of aircraft. If any parameter in these equations is sensitive to the critical speed, we should treat it carefully since inaccuracy is inevitable in the production process. Tragic failure may occur if the margin is small. Therefore, it is important to know in the analysis the effects of uncertainties of the critical values when they play a critical role in the design. The sensitivity of parameters in aer

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21

Rahme, Marc M., Elise Jalil, Martin Laflamme, and Teresa Kus. "Effect of autonomic neurotransmitters on excitable gap composition in canine atrial flutter." Canadian Journal of Physiology and Pharmacology 79, no. 1 (2001): 13–17. http://dx.doi.org/10.1139/y00-109.

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Atrial arrhythmias are believed to be influenced by autonomic nervous system tone. We evaluated the effects of sympathetic and parasympathetic activation on atrial flutter (AFl) by determining the effects of norepinephrine (NE) and acetylcholine (ACh) on the composition of the excitable gap. A model of reentry around the tricuspid valve was produced in 17 chloralose anesthetized dogs using a Y-shaped lesion in the intercaval area that extended to the right atrial appendage. Excitable gap characteristics were determined during AFl by scanning diastole with a single premature extrastimulus at pr

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22

Piche´, R. "On the Symmetrizability of Structural Control Systems With Noncolocated Sensors and Actuators." Journal of Dynamic Systems, Measurement, and Control 112, no. 2 (1990): 249–52. http://dx.doi.org/10.1115/1.2896132.

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In problems of active vibration control of elastic structures, it is known that systems with symmetric feedback matrices (realized using colocated dual sensor/actuator pairs) possess many desirable properties, including real eigenvalues, infinite gain margin, no flutter instability, and the lower-bound character of Rayleigh estimation formulas. In this paper, we consider systems with nonsymmetric feedback matrices which may be transformed, via a similarity transformation, into symmetric systems. We propose constructive conditions to recognize a-priori which systems are symmetrizable. It is sho

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23

Parafes’, S. G. "About revising the computational dynamic scheme of an unmanned aerial vehicle based on the results of ground-based modal test operations in the aeroelasticity problems." Civil Aviation High Technologies 25, no. 3 (2022): 73–85. http://dx.doi.org/10.26467/2079-0619-2022-25-3-73-85.

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The problem of revising the computational dynamic scheme of an unmanned aerial vehicle (UAV), based on the results of ground-based modal test operations, in order to study the UAV flutter and to assess the aeroelastic stability of an UAV with an automatic control system (ACS), is considered. It is noted that at the design stage, when there is no UAV prototype or its units yet, the determination of modal characteristics, specifically natural frequencies, modes and generalized masses, is carried out using the computational dynamic scheme developed according to the design documentation. However,

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24

Xie, Chang Chuan, Jia Zhen Leng, and Chao Yang. "Geometrical Nonlinear Aeroelastic Stability Analysis of a Composite High-Aspect-Ratio Wing." Shock and Vibration 15, no. 3-4 (2008): 325–33. http://dx.doi.org/10.1155/2008/957561.

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A composite high-aspect-ratio wing of a high-altitude long-endurance (HALE) aircraft was modeled with FEM by MSC/NASTRAN, and the nonlinear static equilibrium state is calculated under design load with follower force effect, but without load redistribution. Assuming the little vibration amplitude of the wing around the static equilibrium state, the system is linearized and the natural frequencies and mode shapes of the deformed structure are obtained. Planar doublet lattice method is used to calculate unsteady aerodynamics in frequency domain ignoring the bending effect of the deflected wing.

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25

Iannelli, Andrea, Mark Lowenberg, and Andrés Marcos. "On the effect of model uncertainty on the Hopf bifurcation of aeroelastic systems." Nonlinear Dynamics 103, no. 2 (2021): 1453–73. http://dx.doi.org/10.1007/s11071-020-06169-2.

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AbstractThis paper investigates the effect of model uncertainty on the nonlinear dynamics of a generic aeroelastic system. Among the most dangerous phenomena to which these systems are prone, Limit Cycle Oscillations are periodic isolated responses triggered by the nonlinear interactions among elastic deformations, inertial forces, and aerodynamic actions. In a dynamical systems setting, these responses typically emanate from Hopf bifurcation points, and thus a recently proposed framework, which address the problem of robustness from a nonlinear dynamics viewpoint, is employed. Briefly, the no

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26

Roizner, Federico, Daniella E. Raveh, and Moti Karpel. "Safe Flutter Tests Using Parametric Flutter Margins." Journal of Aircraft 56, no. 1 (2019): 228–38. http://dx.doi.org/10.2514/1.c035045.

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27

Li, H. D., and L. He. "Toward Intra-Row Gap Optimization for One and Half Stage Transonic Compressor." Journal of Turbomachinery 127, no. 3 (2005): 589–98. http://dx.doi.org/10.1115/1.1928934.

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Multistage effects on both aerodynamics and aeromechanics have been identified as significant. Thus, design optimizations for both aerodynamic performance and aeromechanical stability should be done in the unsteady multistage environment. The key issue preventing such a procedure to be carried out is the enormous computing time cost of multistage unsteady simulations. In this paper, a methodology based on the single-passage shape-correction method integrated with an interface disturbance truncation technique has been developed. The capability, efficiency, and accuracy of the developed methodol

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Travaglini, Lorenzo, Sergio Ricci, and Giampiero Bindolino. "PyPAD: a multidisciplinary framework for preliminary airframe design." Aircraft Engineering and Aerospace Technology 88, no. 5 (2016): 649–64. http://dx.doi.org/10.1108/aeat-02-2015-0061.

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Purpose The purpose of this paper is to describe the development of an integrated framework suitable for preliminary airframe design, called PyPAD (Python module for Preliminary Aircraft Design), providing the capability to define models to compute loads and to perform the structural sizing. Design/methodology/approach The modules developed until now allow for the definition of multi-fidelity aero-structural models starting from a Common Parametric Aircraft Configuration Schema (CPACS) input file and to compute static loads (trim) and flutter margin with minimum user effort. PyPAD take advanta

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Cipolla, Vittorio, Andri Dine, Andrea Viti, and Vincenzo Binante. "MDAO and Aeroelastic Analyses of Small Solar-Powered UAVs with Box-Wing and Tandem-Wing Architectures." Aerospace 10, no. 2 (2023): 105. http://dx.doi.org/10.3390/aerospace10020105.

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The market of solar-powered Unmanned Aerial Vehicles (UAVs) for defence purposes and drone services is expected to grow by a factor of more than 2 in the next decade. From an aircraft design perspective, the main challenge is the scalability of the proposed architectures, which is needed to increase the payload capabilities. Beside some successful examples of wing-tail UAVs, some newcomers are developing prototypes with tandem-wing architectures, hence enlarging the possible design. The present paper aims to introduce a further step in this direction, taking also the box-wing architecture into

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Lind, Rick. "Flutter Margins for Multimode Unstable Couplings with Associated Flutter Confidence." Journal of Aircraft 46, no. 5 (2009): 1563–68. http://dx.doi.org/10.2514/1.40328.

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Roizner, Federico, and Moti Karpel. "Sensitivity of Aeroservoelastic Stability Characteristics Using Parametric Flutter Margins." Journal of Aircraft 56, no. 4 (2019): 1387–97. http://dx.doi.org/10.2514/1.c035286.

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Acree, C. W., R. J. Peyran, and Wayne Johnson. "Rotor Design Options for Improving Tiltrotor Whirl-Flutter Stability Margins." Journal of the American Helicopter Society 46, no. 2 (2001): 87–95. http://dx.doi.org/10.4050/jahs.46.87.

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Lind, Rick, and Marty Brenner. "Flutterometer: An On-Line Tool to Predict Robust Flutter Margins." Journal of Aircraft 37, no. 6 (2000): 1105–12. http://dx.doi.org/10.2514/2.2719.

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Karpel, M. "Sensitivity derivatives of flutter characteristics and stability margins for aeroservoelastic design." Journal of Aircraft 27, no. 4 (1990): 368–75. http://dx.doi.org/10.2514/3.25281.

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Lind, Rick, and Marty Brenner. "Robust Flutter Margins of an F/A-18 Aircraft from Aeroelastic Flight Data." Journal of Guidance, Control, and Dynamics 20, no. 3 (1997): 597–604. http://dx.doi.org/10.2514/2.4082.

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36

Lewy, Zeev. "The function of the ammonite fluted septal margins." Journal of Paleontology 76, no. 1 (2002): 63–69. http://dx.doi.org/10.1017/s0022336000017352.

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The fluted margins of ammonite septa were thought to resist the hydrostatic pressure upon the phragmocone while the ammonoid dived. However, ammonoids probably did not dive deeper than the extant nautilids, whose conchs, with the simple septa, sustain pressure correlative to depth of about 800 m. The backward and forward stretching lobes and saddles actually provide resistance to pressure perpendicular to the septum. Ammonoids lived for about three to five years, and septa were precipitated in intervals of nearly two weeks to two days, which explain the small dimensions of the scars of the add

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LEWY, ZEEV. "THE FUNCTION OF THE AMMONITE FLUTED SEPTAL MARGINS." Journal of Paleontology 76, no. 1 (2002): 63–69. http://dx.doi.org/10.1666/0022-3360(2002)076<0063:tfotaf>2.0.co;2.

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Iannelli, Andrea, Mark Lowenberg, and Andrés Marcos. "An extension of the structured singular value to nonlinear systems with application to robust flutter analysis." CEAS Aeronautical Journal 11, no. 4 (2020): 1057–69. http://dx.doi.org/10.1007/s13272-020-00469-4.

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Abstract The paper discusses an extension of $$\mu$$ μ (or structured singular value), a well-established technique from robust control for the study of linear systems subject to structured uncertainty, to nonlinear polynomial problems. Robustness is a multifaceted concept in the nonlinear context, and in this work the point of view of bifurcation theory is assumed. The latter is concerned with the study of qualitative changes of the steady-state solutions of a nonlinear system, so-called bifurcations. The practical goal motivating the work is to assess the effect of modeling uncertainties on

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Taylor, N. V., C. B. Allen, A. Gaitonde, and D. P. Jones. "A structure-coupled CFD method for time-marching flutter analysis." Aeronautical Journal 108, no. 1086 (2004): 389–401. http://dx.doi.org/10.1017/s0001924000000208.

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AbstractAeroelastic analysis is a critical area of the aircraft design process, as a good understanding of the dynamic behaviour of the wing structure is essential to safe operation of the vehicle. The inevitable inaccuracies present in the modelling of such phenomena impose mass penalties, as large safety margins are necessitated, which in turn lead to overly stiff designs. In an effort to reduce the uncertainty in analysis methods, fully coupled CFD and structural models are under widespread development. This paper describes the results produced by such a system for a series of test cases ba

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Clark, Jathan, Mark Murray-Flutter, and Tyler Berger. "Book Reviews." Armax: The Journal of Contemporary Arms VIII, no. 2 (2023): 103–8. http://dx.doi.org/10.52357/armax98640.

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Kunstoffe: A Collector’s Guide to German World War II Plastics and Their Markings Reviewed by: Jathan Clark W. Darrin Weaver. Atglen: Schiffer Military, 2008. ISBN 978-0-7643-2923-4. 176 pp., numerous col. & b. & w. illus. $40. Sniping Rifles in World War I Reviewed by: Mark Murray-Flutter Martin Pegler. Oxford: Osprey Publishing, 2022. ISBN 978-1-4728-5076-8. 80 pp., numerous col. and b. & w. illus. £14.99 (paperback). Gun Barons: The Weapons That Transformed America and the Men Who Invented Them Reviewed by: Tyler Berger John Bainbridge, Jr. New York: St. Martin’s Press, 2022. IS

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Prabhu, L., and J. Srinivas. "Modeling of flutter stability margins in an aerofoil cantilever wing with multiple engines mounts under inherent structural nonlinearities." Engineering Science and Technology, an International Journal 21, no. 5 (2018): 1034–46. http://dx.doi.org/10.1016/j.jestch.2018.07.001.

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Le Heron, D. P., P. Dietrich, M. E. Busfield, C. Kettler, S. Bermanschläger, and B. Grasemann. "Scratching the surface: Footprint of a late Carboniferous ice sheet." Geology 47, no. 11 (2019): 1034–38. http://dx.doi.org/10.1130/g46590.1.

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Abstract Field observations in conjunction with aerial images from an unmanned aerial vehicle were used to create the first map of a glacial unconformity underlying the late Carboniferous Dwyka Group of South Africa. Crosscutting relationships reveal that the glacial unconformity at Oorlogskloof, in which flutes, grooves, and striae were ploughed into unconsolidated sand, formed in a three-phased process charting a periodic shift in the locus of subglacial erosion. The unconformity formed by a periodically decoupled ice sheet in a probable tidewater setting. This model contrasts with earlier v

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Polyak, Leonid, Dennis A. Darby, Jens F. Bischof, and Martin Jakobsson. "Stratigraphic constraints on late Pleistocene glacial erosion and deglaciation of the Chukchi margin, Arctic Ocean." Quaternary Research 67, no. 2 (2007): 234–45. http://dx.doi.org/10.1016/j.yqres.2006.08.001.

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AbstractAt least two episodes of glacial erosion of the Chukchi margin at water depths to ∼ 450 m and 750 m have been indicated by geophysical seafloor data. We examine sediment stratigraphy in these areas to verify the inferred erosion and to understand its nature and timing. Our data within the eroded areas show the presence of glaciogenic diamictons composed mostly of reworked local bedrock. The diamictons are estimated to form during the last glacial maximum (LGM) and an earlier glacial event, possibly between OIS 4 to 5d. Both erosional events were presumably caused by the grounding of ic

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Le Heron, Daniel Paul, Christoph Kettler, Bethan J. Davies, et al. "Rapid geomorphological and sedimentological changes at a modern Alpine ice margin: lessons from the Gepatsch Glacier, Tirol, Austria." Journal of the Geological Society 179, no. 3 (2021): jgs2021–052. http://dx.doi.org/10.1144/jgs2021-052.

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The Gepatsch Glacier in Tirol (Austria) is a rapidly retreating valley glacier whose host valley and forefield reveal subglacial, proglacial, and reworked sediment–landform assemblages. Structures include roches moutonées develop on gneiss, compound bedrock-sediment bedforms (crag and tail structures), flutes, and small diamicton ridges. The glacial sediments and landforms are undergoing incision and terrace development by meltwater streams. Glacial geomorphological and surface geological maps, in concert with elevation models of difference between July 2019 and July 2020 highlight considerabl

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COBOS-VILLAGRÁN, AURORA, TANIA RAYMUNDO, ROSA PAULINA CALVILLO-MEDINA, and RICARDO VALENZUELA. "Rhytidhysteron mexicanum sp. nov. (Dothideomycetes, Ascomycota) from the Sierra of Guadalupe, Trans Mexican Volcanic Belt." Phytotaxa 479, no. 3 (2021): 275–86. http://dx.doi.org/10.11646/phytotaxa.479.3.4.

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A novel dothideomycete species, Rhytidhysteron mexicanum, is described and illustrated supported by morphological and cultural characters and a phylogenetic analysis (rDNA nucleotide data set). The new species is characterized when immature by boat-shaped hysterothecia (2–4 mm long × 1.5–2.5 mm wide). In mature stage, 2.5–4 mm apothecia with fluted margins remain the same when dry. The epithecium is yellowish green to pistachio green, becoming ocher in the presence of 10% KOH. Ascospores are 34–40(–44) × 10–12(–15) µm, and reddish brown. The morphology of R. mexicanum is compared with other Rh

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Hu, Zhengwen, Baoqiang Zhang, and Jing Yang. "A Two-Phase Monte Carlo Simulation/Non-Intrusive Polynomial Chaos (MSC/NIPC) Method for Quantification of Margins and Mixed Uncertainties (QMMU) in Flutter Analysis." IEEE Access 8 (2020): 118773–86. http://dx.doi.org/10.1109/access.2020.3005289.

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Sutherland, James, and Anubhav Datta. "Fabrication, Testing, and 3D Comprehensive Analysis of Swept-Tip Tiltrotor Blades." Journal of the American Helicopter Society 68, no. 1 (2023): 1–17. http://dx.doi.org/10.4050/jahs.68.012002.

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This paper covers the design, fabrication, testing, and modeling of a family of Froude-scale tiltrotor blades. They are designed with the objective of gaining a fundamental understanding of the impact of a swept tip on tiltrotor whirl flutter. The goal of this paper is to describe the development of the blades needed for this purpose. The rotor is three bladed with a diameter of 4.75 ft. The blades have a VR-7 profile, chord of 3.15 inches, and linear twist of –37° per span. The swept-tip blades have a sweep of 20° starting at 80% R. The blade properties are loosely based on the XV-15 design.

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Marques, Fernando Araújo dos Santos, Carlos Antônio Ferreira, Eliana Tiba Gomes Grande, Maria Gláucia Dourado Furquim, and José Carlos de Sousa Júnior. "Desenvolvimento de um aplicativo multilateral de gerenciamento de negócios para microempreendedores individuais do setor de estética." Research, Society and Development 11, no. 16 (2022): e453111636898. http://dx.doi.org/10.33448/rsd-v11i16.36898.

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O marketing é uma ferramenta primordial nas relações de troca e venda do meio comercial. Para um melhor relacionamento com o público-alvo é necessário conhecer suas necessidades e trazer uma melhor experiência nos serviços e produtos que são adquiridos pelo consumidor final. A proposta deste artigo é fundamentar e propor um aplicativo de serviços de estética que em conjunto com o composto dos 4 P's estratégicos do marketing auxiliará microempreendedores individuais do ramo de estética a gerenciar os pedidos de agendamento, a abrangência da marca e o relacionamento com o público-alvo. Nesse sen

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Laws, Catherine. "Beckett in New Musical Composition." Journal of Beckett Studies 23, no. 1 (2014): 54–72. http://dx.doi.org/10.3366/jobs.2014.0086.

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The musical legacy of Samuel Beckett is evident in the large number of compositions inspired by his work. Moreover, Beckett's influence has endured beyond the associations with musical modernism from the 1960s onwards. How, then, do the approaches of younger composers relate to and differ from those working during Beckett's lifetime, and what are the implications for performance? This article explores these questions in relation to two recent compositions: Damien Harron's what is the word (2011) for flute, percussion, piano and electronics, and Martin Iddon's head down among the stems and bell

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Ebbestad, Jan Ove R., and Juan Carlos Gutiérrez-Marco. "Phragmolites (Gastropoda) from the Late Ordovician of the Peruvian Altiplano." Journal of Paleontology 94, no. 2 (2019): 255–65. http://dx.doi.org/10.1017/jpa.2019.79.

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AbstractPhragmolites lissoni new species is described from 11 specimens found in the Sandbian Calapuja Formation near Calapuja in Peru. The deposits are part of the Central Andean Basin. This is the hitherto only systematically described Ordovician gastropod from Peru. The species is from a brachiopod-dominated siliciclastic sequence and is associated with bryozoans. Most specimens are preserved as external molds, but latex casts yield excellent details of shell ornamentation and are used as a basis for evaluating this feature in the genus. The characteristic ornamentation of Phragmolites shou

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