Typical Wing Research Articles

The presence of quill mites (Gabucinia bicaudata) and lice (Struthiolipeurus struthionis) in ostrich wing feathers

Quill mites (Gabucinia bicaudata) and lice (Struthiolipeurus struthionis) may infest ostrich feathers, resulting in skin damage, pruritus and excessive feather preening and loss. Four different feather types (prime white, femina extra wide, femina class 1, and femina short; n = 10) were collected. The quill mites and lice were removed with fine forceps, studied using a photographic optical microscope and counted microscopically at x 100 magnification following collection by sedimentation. They were placed in separate Petri dishes containing lactophenol solution and examined (x40 magnification). Anatomical features are described. The density of quill mites in all feather types of both wings was higher than that of the lice. There was no significant difference between the counts of both arthropods on the left wing and the right wing, respectively, except for the femina class 1 quill mites (P = 0.01). The femina extra wide feathers were a preferred habitat in both wings. Large standard deviations (quill mites left wing: 73 +/- 8; quill mites right wing: 69 +/- 7) suggested variations in the degree of migration between feather shafts or as a response to escape preening. It is recommended that ostriches be treated with an oral preparation of Ivermectin administered per os at a dosage rate of 0.2 mg/kg at 30-day intervals for quill mites, and with a 1-5 % Malathion dust at 14-day intervals for lice.

Crystal Structure of the Human FOXK1a-DNA Complex and Its Implications on the Diverse Binding Specificity of Winged Helix/Forkhead Proteins

Interleukin enhancer binding factor (ILF) is a human transcription factor and a new member of the winged helix/forkhead family. ILF can bind to purine-rich regulatory motifs such as the human T-cell leukemia virus-long terminal region and the interleukin-2 promoter. Here we report the 2.4 A crystal structure of two DNA binding domains of ILF (FOXK1a) binding to a 16-bp DNA duplex containing a promoter sequence. Electrophoretic mobility shift assay studies demonstrate that two ILF-DNA binding domain molecules cooperatively bind to DNA. In addition to the recognition helix recognizing the core sequences through the major groove, the structure shows that wing 1 interacts with the minor groove of DNA, and the H2-H3 loop region makes ionic bonds to the phosphate group, which permits the recognition of DNA. The structure also reveals that the presence of the C-terminal alpha-helix in place of a typical wing 2 in a member of this family alters the orientation of the C-terminal basic residues (RKRRPR) when binding to DNA outside the core sequence. These results provide a new insight into how the DNA binding specificities of winged helix/forkhead proteins may be regulated by their less conserved regions.

Achene Wall Anatomy and Surface Sculpturing of Lactuca L. and Related Genera (Compositae: Lactuceae) with Notes on Their Systematic Significance

AbstractThe achene wall anatomy and surface sculpturing of 14 species representing Lactuca L. and related genera were investigated to evaluate inter‐ and intrageneric relationships. The achene wall anatomy of the studied species can be divided into two types: winged and ribbed. The winged type is present in Lactuca L., Pterocypsela Shih, Cicerbita Wallr., Chaetoseris Shih and Stenoseris Shih, and is characterized by protruding wings and costae in transverse section. Winged type achene mesocarps are composed of parenchymatous cells and fiber cells, and the distinct fibrous strands are confined to the costae or wings of the achenes. The ribbed type is present in Notoseris Shih and Paraprenanthes Chang ex Shih, and is characterized by only having costae in transverse section. Fiber cells are continuous in the costae and intercostae. In surface sculpturing, the ornamentation and the shape of epidermal cells are different among these genera. The results indicate that L. altaica and L. serriola should be conspecific, and that L. dolichophylla is probably an intermediate taxon between Lactuca and Chaetoseris. The results also support the separation of Pterocypsela, Paraprenanthes, Notoseris, Chaetoseris and Stenoseris from Lactuca and Cicerbita as independent entities. Close affinities between Pterocypsela and Lactuca, Paraprenanthes and Notoseris, and Chaetoseris and Stenoseris are also proposed.(Managing editor: Wei Wang)

A low‐order model for analysing effects of blade fatigue load control

AbstractA new low‐order mathematical model is introduced to analyse blade dynamics and blade load‐reducing control strategies for wind turbines. The model consists of a typical wing section model combined with a rotor speed model, leading to four structural degrees of freedom (flapwise, edgewise and torsional blade oscillations and rotor speed). The aerodynamics is described by an unsteady aerodynamic model. The equations of motion are derived in non‐linear and linear form. The linear equations of motion are used for stability analysis and control design. The non‐linear equations of motion are used for time simulations to evaluate control performance. The stability analysis shows that the model is capable of predicting classical flutter and stall‐induced vibrations. The results from the stability analysis are compared with known results, showing good agreement. The model is used to compare the performance of one proportional–integral–derivative controller and two full‐state feedback controllers. Copyright © 2006 John Wiley & Sons, Ltd.

Structural Design, Manufacturing, and Wind Tunnel Test of a Small Expandable Wing

This paper describes design, manufacturing, and wind tunnel test of a motor-driven small-scale expandable wing for MAV class vehicles. The bird-like expandable wing has been developed for investigating the influence of aspect ratio change on the lift and drag of the wing. As a typical bird wing, the wing is separated into inner and outer wings. The wing model consists of the linkage system made of carbon composite strip/rod and the remaining part covered with carbon composite sheet and multiple LIPCAs (Lightweight Piezo-Composite Actuators) mimicking wing feathers. The LIPCA actuator was used to control wing camber, which created additional lift. Wind tunnel tests were conducted to investigate the changes in lift and drag during wing folding and expansion, and to observe the influence of LIPCA actuation on the wing. In the tests, effects of the wing fold/expansion and actuation of LIPCA on changes in lift and drag were quantitatively identified.

Effects of Leading Edge Separation Vortex of Flexible Structure Delta Wing on Its Aerodynamic Characteristics

The aerodynamic forces and moments of a flexible delta wing in pitching motion were experimentally studied in a low-speed wind tunnel. Three types of flexible delta wing were investigated, the flexible parts of which were 44, 70 and 99% of the delta wing. Aerodynamic characteristics were different among the three types of flexible and completely hard delta wing, and it was found that the winding-up of the leading edge of the delta wing is the key factor for determining the leading edge vortex on the upper side of the wing and the pressure distribution on the windward side. Lift, drag, and pitching moment formed a hysteresis loop with an angle of attack in pitching motion, particularly in a region with a large attack angle, accompanied by leading edge vortex breakdown. The flow visualization of leading edge vortices was also carried out to explain the dynamic characteristics of the delta wings.

509 円柱ブレードを用いた風車(2)(OS5-2 風力発電,OS5 風力発電,オーガナイズドセッション)

This report introduces an attempt for wind turbine using blades with circular cross section, although many wind turbines now has blades with wing section. The blades with circular cross section become profitable with strength, stiffness and manufacturing cost in comparison with wing type blades. They are not pure circular cylinders, but have grooves on their surface in long distance direction. A groove forces boundary layer transition on the flow, and that causes asymmetry flow around circular section. The blade with circular cross section produces lift. We performed some wind tunnel test for the blade with circular cross section. Wind tunnel test shows that maximum lift coefficient is 0.6〜0.8 at Reynolds number 1.509×10^5〜2.515×10^5, and suggests that the wind turbine using blades with circular cross section is low speed high torque type.

Evaluation of Biological Deployable Systems

The paper presents a survey of deployable structural systems found in some biological organisms. Four biological systems are presented and analysed in terms of their morphology, kinematics and structural characteristics. This presentation is followed by an evaluation of the similarity of the biological systems with existing deployable structures and of potential applications. The four biological systems surveyed are two types of insect wings – Coleoptera (beetles) and locust; locomotion of the earthworm; and the jaw of the egg eater snake ( Dasypeltis). These systems represent a diversity of deployable mechanisms. The paper concludes by associating the surveyed and other biological systems with known deployable structural systems such as: folded plates, tensioned membrane, pneumatic tubes ( pneus) and structures composed of articulated rigid members.

Dynamic Response of a High Aspect Ratio Wing Equipped with PZT Patches – A Theoretical and Experimental Study

The present study is aimed at demonstrating both the capability and the relevant restrictions of piezoceramic elements (patches) to provide enough authority to control the dynamic behavior of a full size wing type structure (supposedly more rigid). Therefore, a 3000-mm long composite wing, that represents a typical high aspect ratio (AR 1/4 16.7) wing was designed and fabricated. The theoretical dynamic behavior of the wing box was calculated using the MSC/NASTRAN finite element code. The wing was excited using bonded piezoelectric patches at its first five natural frequencies. The experimental results proved the capability to excite real type structures using piezoelectric patches. The present composite wing will be used as a test-bed to evaluate the performances of piezoelectric materials in vibration control and flutter suppression of flexible wings.

A Study on Transient Performance Characteristics of the Canard Rotor Wing Type Unmanned Aerial Vehicle Propulsion System During Flight Mode Transition

A propulsion system of the CRW (Canard rotor wing) type UAV (unmanned aerial vehicle) was composed of the turbojet engine, exhaust nozzles (including some tip jet nozzles and a main nozzle), and the duct system (including straight ducts, curved ducts, and master valve). The CRW-type UAV has three different flight modes, such as the rotary wing mode for takeoff and landing, the high-speed forward flight mode with the fixed wing, and the transition flight mode between the previously mentioned two flight modes. In order to evaluate transient performance characteristics of the CRW-type UAV propulsion system during flight mode transition, the propulsion system was modeled using SIMULINK®, which is a user-friendly graphical-user-interface-(GUI) type dynamic analysis tool provided by MATLAB, in this study. The transition flight mode between the rotary wing mode and the fixed wing mode was simulated by considering area variation of the master valve and the main exhaust nozzle. In order to verify acceptability of the main turbojet engine model, performance simulation results using SIMULINK were compared to results using the commercial program GSP. Through this simulation, proper operation of the master valve and the variable area main nozzle can be found for safe flight transition. Therefore, performance characteristics were investigated depending on various angle positions of the master valve.

Liriomyza spp.

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AEROELASTIC ANALYSIS CONSIDERING STRUCTURAL UNCERTAINTY

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 aero elastic analysis is not simple even in linear analysis. It is not always possible to have an analytic form of the sensitivity of uncertainty. In order to evaluate the structural sensitivity of aero elastic phenomena, we have to resort to numerical calculations with uncertain parameters having some random deviations, i.e. the so‐called Monte Carlo simulation. In the present study, the divergence speed and flutter speed of a typical wing section with structural uncertainties are discussed, and some results of calculations with scattering parameters in Gaussian distribution will be presented.

Reduced-Order-Model Approach for Aeroelastic Analysis Involving Aerodynamic and Structural Nonlinearities

Ar educed-order model (ROM) for solving an aeroelasticity problem including structural and aerodynamic nonlinearities is introduced. The aerodynamic system is identified using a Volterra-based ROM. The appropriate procedures needed for the identification of the aerodynamic linearized kernel are presented, and a procedure to identify the first- and second-order Volterra kernels and a linearized ROM kernel from aerodynamic step response is detailed. A coupled framework for addressing the nonlinear aeroelasticity problem using a typical wing section model is introduced for the validation of the procedure. Nonlinear unsteady aerodynamic forces in both subsonic and transonic regimes are evaluated using a conventional approach using the CFL3D (version 6.1) code capable of integrating Navier‐Stokes and the structural equations. The computational-fluid-dynamics (CFD) solver is used to compute the aerodynamic response to step or impulse inputs. Aerodynamic responses to arbitrary inputs are predicted using ROM kernels. The Gaussian pulse response obtained using ROM was validated by comparison with the response obtained from CFD solver. Aeroelastic analysis was conducted using the ROM with aerodynamic and structural nonlinearities. The results show that the reduced-order model can estimate accurately flutter speed as well as the limit-cycle oscillations (LCO). Also the ROM approach is found to be computationally efficient.

パラグライダー・キャノピー・セル（インフレータブル翼）の翼形成に関する実験的研究

This study focuses on the formation mechanism of para-foil canopy. Three types of model wing, which represent each cell of para-foil canopy (a rigid wing with air intake, an inflatable wing and a cassette model) were prepared to explore the effects of air intake on inflatable wing formation in wind tunnel experiments. The flow fields both outside and inside of the wings were investigated, together with the process that the flexible wing inflates to form a wing. It was found that the robust nature of canopy is derived from the concaving deformation of the leading edge at small angles of attack, and the enhanced outward suction pressure acting on the leading edge, which are caused by the flexibility of the wing as well as the pressure of air intake in sacrifice of increased drag coefficient.

病院建築におけるブロックプラン計画の系譜 : 日本の病院建築の計画史に関する研究1(建築計画)

More than a half century has passed after the W.W.II, hospital architecture have been developed in not only quantitative phase but also qualitative. The purpose of this study is to analyze the policy of planning of the hospital architecture from the point ot genealogical point. This paper tries to classify the block plan of hospital. At first "The pavilion type" has been developed as a typical block plan. "The symmetrical and integrated type" appeared for urban situation. "The matchbox on the muffin type" has been developed for reserving spreading space for diagnostic and treatment departments and saving site area. "The independent ward type" aimed discretion of planning of D & T dept. besides the restriction of ward structure. "The multi wing type" and "the modern ward independent type" has kept the right of growth and change in hospital architecture.

Control of a Nonlinear Wing Section Using Leading- and Trailing-Edge Surfaces

The control of nonlinear aeroelastic response of a wing section with a continuous stiffening-type structural nonlinearity is examined through analytical and experimental studies. Motivated by the limited effectiveness of using a single, trailing-edge control surface for the suppression of limit-cycle oscillations of a typical wing section, improvements in the control of limit-cycle oscillations are investigated through the use of multiple control surfaces, namely, an additional leading-edge control surface. The control methodology consists of a feedback linearization approach that transforms the system equations of motion via Lie algebraic methods and a model reference adaptive control strategy that augments the closed-loop system to account for inexact cancellation of nonlinear terms due to modeling uncertainty. Specifically, uncertainty in the nonlinear pitch stiffness is examined. It is shown through simulations and experiments that globally stabilizing control may be achieved by using two control surfaces.

On Accuracy of Prediction of Flutter Boundaries on Unstructured Grids

The accuracies of unstructured grid methods for flutter analysis were investigated. Time accurate flow simulations with moving boundary were carried out on three types of unstructured grids. The results are compared with a recent report obtained by a structured, parallel flow solver. Semi-structured triangular grids and isotropic fine grids show similar results and agree well with the data. Poor grid resolution can result in wrong responses of the wing motion near the flutter boundary even when the same grid distribution is used on the wing. Typical wing responses for the lower- and higher-frequency modes are elaborated.

Local Heat Transfer Characteristics in Simulated Electronic Modules

When heat is released by forced convection from electronic modules in a narrow printed circuit board channel, complex flow phenomena—such as stagnation and acceleration on the front surface, separation and reattachment on the top surface, wake or cavity flow near the rear surface—affect the heat transfer characteristics. The purpose of this study is to investigate how these flow conditions influence the local heat transfer from electronic modules. Experiments are performed on a three-dimensional array of hexahedral elements as well as on a two-dimensional array of rectangular elements. Naphthalene sublimation technique is employed to measure three-dimensional local mass transfer, and the mass transfer data are converted to their counterparts of the heat transfer process using the analogy equation between heat and mass transfer. Module location and streamwise module spacing are varied, and the effect of vortex generators on heat transfer enhancement is also examined. Dramatic change of local heat transfer coefficients is found on each surface of the module, and three-dimensional modules have a little higher heat transfer value than two-dimensional modules because of bypass flow. Longitudinal vortices formed by vortex generator enhance the mixing of fluids and thereby heat transfer, and the rectangular wing type vortex generator is found to be more effective than the delta wing type vortex generator.

Evolution of the dynamic susceptibility of simple glass formers in the stronglysupercooled regime

We discuss dielectric and light scattering susceptibility spectra ofsimple glass formers at temperatures above as well as below thecritical temperature of the mode coupling theory (MCT). Close toTgthe systems are characterized by the presence of a pronounced excess wing(type A glass formers). The data are analysed within a phenomenologicalapproach, on the one hand, and within MCT, on the other. Among other workwe present a complete interpolation of the dielectric data for glycerol(Lunkenheimer et al2000 Contemp. Phys. 41 15). The crossover temperatureTx,defined by the emergence of the excess wing upon cooling, is extracted from thephenomenological analysis and found to agree well with the critical temperatureTc,extracted from the MCT analysis at high temperatures. BelowTxthe evolution of the susceptibility is characterized by a universal appearanceof the excess wing. No difference is observed for the non-fragile systemwith respect to fragile glass formers provided that the wing parametersare studied as a function of the correlation time τα.Finally, a generalized scaling for the susceptibility minimum is proposed which is aphenomenological extension of that of MCT but now also includes the data belowTc.

Allometric prediction of locomotor performance: an example from Southeast Asian flying lizards.

Allometric scaling analysis is the standard paradigm for studies attempting to unravel the consequences of evolutionary size change (Huxley 1932; Gould 1966; SchmidtNielsen 1984). Although the value of this approach is clear, prediction of the allometry of performance is often hamstrung by the complexity of biological systems. This complexity derives from the heterogeneous interaction of physiological and morphological variables that together determine maximal performance. Despite this complication, allometric analysis is widely employed primarily because understanding the consequences of size evolution is so important to our field. Not only does size influence virtually every aspect of an organism’s biology (Calder 1984; Schmidt-Nielsen 1984), but it is also remarkably variable, even among closely related species. There is little consensus in the literature regarding the expected relationship between morphology and locomotor performance over a range of sizes. Despite a diversity of alternative models attempting to predict the allometry of performance (Thompson 1917; Hill 1950; Alexander 1968; McMahon 1973, 1975, 1984; Gunther 1975; Bennet-Clark 1977; Rubin and Lanyon 1984; Marsh 1988, 1994; Wakeling et al. 1999), empirical data often fail to conform to any extant model (e.g., Emerson 1978; Garland 1983, 1985; Chappell 1989; Katz and Gosline 1993; Bennett 2000; Wil-