Thematische Bibliographien / Wing construction

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Auswahl der wissenschaftlichen Literatur zum Thema „Wing construction“

Autor: Grafiati

Veröffentlicht am 28. Juni 2021

Zuletzt aktualisiert am 15. Februar 2022

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Zeitschriftenartikel zum Thema "Wing construction"

Tarnowski, Andrzej. „Morphing wing with skin discontinuity – kinematic concept“. Aircraft Engineering and Aerospace Technology 89, Nr. 4 (03.07.2017): 535–46. http://dx.doi.org/10.1108/aeat-11-2016-0208.

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Purpose This paper aims to describe the concept of morphing tailless aircraft with discontinuous skin and its preliminary kinematic solution. Project assumptions, next steps and expected results are briefly presented. Design/methodology/approach Multidisciplinary numerical optimization will be used to determine control allocation for wing segments rotation. Wing demonstrator will be fabricated and tested in wind tunnel. Results will be used in construction of flying model and design of its control system. Flight data of morphing demonstrator and reference aircraft will result in comparative analysis of both technologies. Findings Proposed design combines advantages of wing morphing without complications of wing’s structure elastic deformation. Better performance, stability and maneuverability is expected due to wing’s construction which is entirely composed of unconnected wing segments. Independent control of each segment allows for free modeling of spanwise lift force distribution. Originality/value Nonlinear multipoint distribution of wing twist as the only mechanism for control and flight performance optimization has never been studied or constructed. Planned wind tunnel investigation of such complex aerodynamic structure has not been previously published and will be an original contribution to the development of aviation and in particular to the aerodynamics of wing with discontinuous skin.

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Richter, Charles, und Hod Lipson. „Untethered Hovering Flapping Flight of a 3D-Printed Mechanical Insect“. Artificial Life 17, Nr. 2 (April 2011): 73–86. http://dx.doi.org/10.1162/artl_a_00020.

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This project focuses on developing a flapping-wing hovering insect using 3D-printed wings and mechanical parts. The use of 3D printing technology has greatly expanded the possibilities for wing design, allowing wing shapes to replicate those of real insects or virtually any other shape. It has also reduced the time of a wing design cycle to a matter of minutes. An ornithopter with a mass of 3.89 g has been constructed using the 3D printing technique and has demonstrated an 85-s passively stable untethered hovering flight. This flight exhibits the functional utility of printed materials for flapping-wing experimentation and ornithopter construction and for understanding the mechanical principles underlying insect flight and control.

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Irwin, A. J., und P. M. Render. „The influence of simulated missile warhead fragment damage on the aerodynamic characteristics of two-dimensional wings“. Aeronautical Journal 117, Nr. 1194 (August 2013): 823–37. http://dx.doi.org/10.1017/s0001924000008472.

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AbstractThe paper describes a method of representing damage on a wing due to multiple warhead fragments, and investigates two of the key variables: fragment impact density and hole diameter. The aerodynamic effects of the damage were quantified by wind-tunnel tests on a two-dimensional wing at a Reynolds number of 5 × 105. The wing was of hollow construction with leading and trailing-edge spars. In all of the cases tested, simulated fragment damage resulted in significant lift losses, drag increases and pitching moment changes. Increasing fragment density or hole size resulted in greater effects. To a first order approximation, both lift and drag increments at a given incidence were related to the percentage wing area removed. Surface flow visualisation showed that low fragment densities and small damage sizes resulted in a complex flow structure on the surface of the wing. This was made up of boundary-layer growth between the damage holes, attached wakes from the forward damage holes and separated surface flow over the rear of the wing. For these cases, individual hole patterns showed similar flow mechanisms to those seen for larger scale gunfire damage cases. Increased fragment density and hole size resulted in upper surface flow separation at the first row of holes. Behind this separation, the flow was attached and consisted of the combined wakes from the forward damage holes. Investigations into the influence of internal model structure indicated that trends in coefficient changes were similar for both hollow and solid wings. However, the magnitudes of the effects were found to be smaller for hollow wings than for solid wings.

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Newman, D. J. S., und R. J. Wootton. „An Approach to the Mechanics of Pleating in Dragonfly Wings“. Journal of Experimental Biology 125, Nr. 1 (01.09.1986): 361–72. http://dx.doi.org/10.1242/jeb.125.1.361.

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A structural engineering approach to the pleated wings of Odonata has been developed during a functional study of wing morphology in the group. The wing can be regarded as a folded plate structure within which each pleat-side acts as a deep plate-girder. Small cross-veins act as stiffeners within the girders, allowing the membrane to carry web shearing forces as pure tension, through a stressed-skin effect. Bending experiments confirm that the membrane significantly increases the rigidity of wing components. The properties of the membrane are unknown. It lacks birefringence, is very thin, and may be pure epicuticle. The advantages of stressedskin construction are discussed, and possible modes of structural failure considered. The wing seems adapted to yield reversibly to unpredictable heavy loads.

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Breen, John E., Michael E. Kreger, Christopher D. White und Gordon C. Clark. „Field evaluation and model test of a composite wing-girder bridge“. Canadian Journal of Civil Engineering 14, Nr. 6 (01.12.1987): 753–62. http://dx.doi.org/10.1139/l87-113.

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This paper presents the key observations and conclusions from the evaluation of an innovative "loose-fit" composite, post-tensioned concrete wing-girder bridge proposed for an elevated interstate highway expansion in an urban environment. The evaluation program included both testing to destruction of a 1/2-scale model of a partial span as well as construction monitoring and field testing at service load levels of a full-scale prototype two-span bridge. Results of both construction measurements and loading tests were compared with analytical predictions. Laboratory tests showed the composite behavior of the wing-girder joint to be fully effective and a high level of load transfer between wings to be present. Recommendations for modification of the prototype design are made to improve constructibility, durability, structural performance, and economy. Key words: box girder, bridge, post-tensioned, prestressed concrete, reinforcement, stresses, temperature, tendons.

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YOSHIZU, Toshihiro. „DEVELOPMENT OF SCREW STEEL PIPE PILE WITH TOE WING HAVING AN INNER WING“. AIJ Journal of Technology and Design 20, Nr. 45 (2014): 467–70. http://dx.doi.org/10.3130/aijt.20.467.

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Жданов, Дмитро, und Дмитро Зінченко. „Aerodynamic design of adaptive airplane wing of hybrid construction“. MECHANICS OF GYROSCOPIC SYSTEMS, Nr. 29 (10.07.2015): 84. http://dx.doi.org/10.20535/0203-377129201560714.

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WIELOCH, GRZEGORZ. „Low noise with wood milling "Airface" constructions“. Annals of WULS, Forestry and Wood Technology 106 (15.01.2019): 49–56. http://dx.doi.org/10.5604/01.3001.0013.7736.

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Low noise with wood milling"airface" constructions. The noise surrounds us everywhere, constituting a disruptive component of our lives. In the wood industry it is more than in other industries due to the specificity of wood processing carried out by high-speed tools. GUS data say that in 2012 as many as 53% of employees worked in noise. Hence the necessity of constant search for new methods of noise reduction. One of them is the use of a grooved surface patterned on the plumage of owls in the construction of milling heads. Their characteristic construction makes the flight of owls almost silent. this is possible due to the special construction of ailerons, which form the bearing surface of the wing. The "owl's wing" smoothes the air flow with a serrated edge and scatters the noise. This allows for almost silent flight characteristics without adversely affecting aerodynamics. Leuco has used this concept of learning from nature to make the milling tools even more aerodynamic, and to get further noise reduction effects! Leuco has submitted a patent for this aerodynamic head design called "airface".

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Arokiasami, Willson Amalraj, Prahlad Vadakkepat und Abdullah Al Mamun. „Wingbeat Generation for a 15 DOF Flexible-Wing Aerial Vehicle Using Cosine Wave Functions“. Unmanned Systems 05, Nr. 02 (April 2017): 115–27. http://dx.doi.org/10.1142/s230138501750008x.

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Birds and conventional airplanes control their flight in a different manner. Conventional airplanes maneuver themselves by means of moving surfaces, while birds can bend, twist and deform their wings and adapt to unforeseen conditions such as wind gusts. However, if planes can do exactly as the birds do they can gain agility, more lift, less drag while consuming less fuel. This work aims to address this issue. Therefore, approaches of wingbeat generation for a 15 DOF flexible-wing aerial vehicle are developed in this paper. A computationally cost-effective cosine wave function-based algorithm that computes a set of wingbeats enabling the aerial vehicle to follow a desired trajectory in a realistic manner is discussed. The flexible-wing aerial vehicle is modeled similar to a seagull with an articulated skeleton. Motion of the aerial vehicle is simulated by applying joint torques and aerodynamic forces over a period of time in forward dynamics simulation. Wing and tail feather motions generate lift in the aerial vehicle, which makes it possible for the aerial vehicle to trace predefined paths. The solidworks mechanical design is used as input into Matlab SimMechanics for visualization. The results are promising for the construction of bird-like aerial vehicles.

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Horden, R. „The Wing Tower (Der "Wing Tower")“. Stahlbau 69, Nr. 6 (Juni 2000): 466–68. http://dx.doi.org/10.1002/stab.200001490.

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Dissertationen zum Thema "Wing construction"

Rahman, Selma, und Anujan Ranganathan. „Conceptual design and construction of a UAV wing structure“. Thesis, KTH, Skolan för teknikvetenskap (SCI), 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-276681.

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This report presents the design of the wing structure for a UAV called Skywalker X8. A model of the UAV was given and analyzed to design a wing box structure that is twice the size of the current model, with "greener" technology and lightweight materials. The loads that act upon the UAV were simulated and thereafter analyzed with the help of the CFD program called Star CCM+. Modifications on the CAD model and the FEM simulations were performed in Siemens NX. Eight different combinations were tested from the following five materials: CFRP (carbon fiber reinforced polymer), LDPE (low density polyethylene), polyethylene, polypropylene, and balsa wood. The results that best fit the requirements given was the combination of polypropylene as the wing skin and balsa as the honeycomb structure. This design weighed 3.576 kg and had the following stresses: 0.671 MPa, 0.340 MPa, 1 MPa, and 4 MPa for the angle of attacks at 1,2,3, and 6 degrees respectively. A modification of the trailing edge, which was the implementation of a Gurney flap, was made to see if it improved the lift-to-drag ratio, but unfortunately it did not so it was not developed further.
Denna rapport kommer att presentera en design och konstruktion av höger vinge på en drönar-modell (UAV), X8 Skywalker. CAD modellen var given och användes vid de aerodynamiska och hållfasthets simuleringarna. Syftet med projektet var att konstruera vingen utifrån dessa perspektiv för vingen i fördubblad storlek, med "grönare" teknik i åtanke. Belastningarna som verkar på drönaren beräknades med hjälp av ett program, Star CCM+, som behandlar CFD-simuleringar. Redigering av CAD modellen och FEM-analyserna utfördes med hjälp av Siemens NX. Åtta olika kombinationer av 5 olika material testades, vilket är de följande: CFRP (carbon fibre reinforced polymer), LDPE (low density polyethylene), polyeten, polypropylen och balsa. Resultaten som uppfyller kraven bäst var polypropylen som vingens ytterhölje och balsa som honeycomb-strukturen. Denna konstruktion vägde totalt 3.576 kg och hade följande von Mises spänningar: 0.671 MPa, 0.340 MPa, 1 MPa och 4 MPa för angreppsvinklarna 1, 2, 3 respektive 6 grader. En modifiering av trailing edge gjordes för att se om det gav en förbättring av lift-to-drag ratio. Då den inte gav en önskad förändring så utvecklades den inte vidare.

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Skelton, Ian R. „Innovation in construction techniques for tall buildings“. Thesis, Loughborough University, 2015. https://dspace.lboro.ac.uk/2134/19637.

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The skyline of many 'world cities' are defined and punctuated by tall buildings. The drivers for such dominant skylines range from land scarcity and social needs; high real estate values; commercial opportunity and corporate demand, through to metropolitan signposting. This fascination with tall buildings started with the patrician families who created the 11th Century skyline of San Gimignano by building seventy tower-houses (some up to 50m tall) as symbols of their wealth and power. This was most famously followed in the late 19th Century with the Manhattan skyline, then Dubai building the world's highest building, then China building some eighty tall buildings completed in the last 5 years, then UK building Europe's highest tower, the Shard and finally back to Dubai, planning a kilometre tall tower, potentially realising Ludwig Mies van der Rohe's 'Impossible Dream' of the 1920's and Frank Lloyd Wright's 1956 'Mile High Illinois'. This ambition to build higher and higher continues to challenge the Architects, Engineers and Builders of tall buildings and is expected to continue into the future. The tall building format is clearly here to stay.

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Chabada, Martin. „Návrh křídla letounu UAV v kategorii do 600 kg“. Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2021. http://www.nusl.cz/ntk/nusl-442849.

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The main aim of the this diploma thesis is the wing design of the UAV aircraft, including the appropriate material choice, calculation of the wing load and also strength analysis. Other goals include the design of the location and volume of fuel tanks, as well as the design of wingspan reduction after landing.

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Kao, Pi-Jen. „Efficient methods for integrated structural-aerodynamic wing optimum design“. Diss., Virginia Polytechnic Institute and State University, 1989. http://hdl.handle.net/10919/54211.

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The dissertation is focused on the large computational costs of integrated multidisciplinary design. Efficient techniques are developed to reduce the computational costs associated with integrated structural-aerodynamic design. First efficient methods for the calculations of the derivatives of the flexibility matrix and the aerodynamic influence coefficient matrix are developed. An adjoint method is used for the flexibility sensitivity, and a perturbation method is used for the aerodynamic sensitivity. Second a sequential optimization algorithm that employs approximate analysis methods is implemented. Finally, a modular sensitivity analysis, corresponding to the abstraction of a system as an assembly of interacting black boxes, is applied. This method was developed for calculating system sensitivity without modifying disciplinary black-box software packages. The modular approach permits the calculation of aeroelastic sensitivities without the expensive calculation of the derivatives of the flexibility matrix and the aerodynamic influence coefficient matrix.
Ph. D.

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Strauch, Gregory J. „Integrated multi-disciplinary design of a sailplane wing“. Thesis, Virginia Tech, 1985. http://hdl.handle.net/10919/45660.

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The objective of this research is to investigate the techniques and payoffs of integrated aircraft design. Lifting line theory and beam theory are used for the analysis of the aerodynamics and the structures of a composite sailplane wing. The wing is described by 33 - 34 design variables which involve the planform geometry, the twist distribution, and thicknesses of the spar caps, spar webs, and the skin at various stations along the wing. The wing design must satisfy 30 â 31 aeroelastic, structural, aerodynamic, and performance constraints.

Two design procedures are investigated. The first, referred to as the iterative, sequential procedure, involves optimizing the aerodynamic design for maximum average cross-country speed at E1 constant structural weight, and then optimizing the the structural design of the resulting wing geometry for minimum weight. This value is then used in another aerodynamic optimization, and the process continues iteratively until the weight converges. The other procedure, the integrated one, simultaneously optimizes the aerodynamic and the structural design variables for either maximum average cross-country speed or minimum weight.

The integrated procedure was able to improve the value of the objective function obtained by the iterative procedure in all cases. This shows The objective of this research is to investigate the techniques and payoffs of integrated aircraft design. Lifting line theory and beam theory are used for the analysis of the aerodynamics and the structures of a composite sailplane wing. The wing is described by 33 - 34 design variables which involve the planform geometry, the twist distribution, and thicknesses of the spar caps, spar webs, and the skin at various stations along the wing. The wing design must satisfy 30 â 31 aeroelastic, structural, aerodynamic, and performance constraints. Two design procedures are investigated. The first, referred to as the iterative, sequential procedure, involves optimizing the aerodynamic design for maximum average cross-country speed at E1 constant structural weight, and then optimizing the the structural design of the resulting wing geometry for minimum weight. This value is then used in another aerodynamic optimization, and the process continues iteratively until the weight converges. The other procedure, the integrated one, simultaneously optimizes the aerodynamic and the structural design variables for either maximum average cross-country speed or minimum weight.

The integrated procedure was able to improve the value of the objective function obtained by the iterative procedure in all cases. This shows that definite benefits can be gained from taking advantage of aerodynamic/structural interactions during the design process.

Master of Science

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Polen, David M. „Integrated aerodynamic-structural design of a subsonic, forward- swept transport wing“. Thesis, Virginia Tech, 1989. http://hdl.handle.net/10919/46059.

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The introduction of composite materials and the ability to tailor these materials to improve aerodynamic and structural performance is having a distinct effect upon aircraft design. In order to optimize the efficiency of the design procedure, a design process which is more integrated than the traditional approach is required. Currently the utilization of such design procedures produces enormous computational costs. An ongoing effort to reduce these costs is the development of efficient methods for cross-disciplinary sensitivities and approximate optimization techniques.

The present research concentrates on investigating the integrated design optimization of a subsonic, forward-swept transport wing. A modular sensitivity approach for calculating the cross-sensitivity derivatives is employed. These derivatives are then used to guide the optimization process. The optimization process employed is an approximate technique due to the complexity of the analysis procedures. These optimization results are presented and the impact of the modular technique is discussed.

Master of Science

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Dewitz, Michael B. „The effect of a fillet on a wing/body junction flow“. Thesis, Virginia Tech, 1988. http://hdl.handle.net/10919/43843.

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Brooks, W. G. „The design, construction and test of a postbuckled, carbon fibre reinforced plastic wing box“. Thesis, Cranfield University, 1987. http://hdl.handle.net/1826/3292.

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A postbuckled, carbon fibre reinforced plastic (CFRP) wing box has been designed, manufactured and tested for an aerobatic light aircraft, the Cranfield Al. Methods of analysis have been evaluated including: i) Non-linear finite element analysis for the prediction o-f panel postbuckling. ii) A simpler technique based on an effective width method. This forms the core of a design program, 'oPTIMIST'. It predicts buckling loads, postbuckled reduced stiffness and overall column failure of co-cured hat stiffened panels. It then optimises the con-Figuration of a box beam for minimum weight. iii) The use of the effective width method allied to a large scale, linear finite element analysis. The work includes the development of a new method o-F construction for composite box structures. The wing skin sti-Ffeners and rib flanges are co-cured together. Integral slotted Joint features are formed in each part. The structure is then adhesively bonded together. A full description of the manufacture o-F the wing box is included. The structure was also tested in a specially designed rig. It was tested to ultimate design loads in: i) Positive bending to 13.33. ii) Negative bending to -96. iii) Pure torsion resulting from full aileron load. iv) Torsion with 96 bending. The compression panels were seen to postbuckle and recover in each load case. Results are compared with theory, and with the original aluminium Al wing. The structure is 257. lighter than its aluminium counterpart. Finally, suggestions are made for possible areas of further research.

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Unger, Eric Robert. „Computational aspects of the integrated multi-disciplinary design of a transport wing“. Thesis, Virginia Tech, 1990. http://hdl.handle.net/10919/42125.

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Past research at this university has proven the feasibility of the multi-disciplinary design of a complex system involving the complete interaction of aerodynamics and structural mechanics. Critical to this design process, is the ability to accurately and efficiently calculate the sensitivities of the involved quantities (such as drag and dynamic pressure) with respect to the design variables. These calculations had been addressed in past research, but it was felt that insufficient accuracy had been obtained. The focus of this research was to improve the accuracy of these sensitivity calculations with a thorough investigation of the computational aspects of the problem. These studies led to a more complete understanding of the source of the errors that plagued previous results and provided substantially improved sensitivity calculations. Additional research led to an improvement in the aerodynamic-structural interface which aided in the accuracy of the sensitivity computations. Furthermore, this new interface removed discontinuities in the calculation of the drag which the previous model tended to yield. These improvements were made possible with the application of shape functions in surface deflection analysis, instead of the previous ‘zonal’ approach. Other factors which led to accuracy improvements were changes to the aerodynamic model and the paneling scheme. Final studies with the optimization process demonstrated the ability of the improved sensitivities to accurately approximate the design problem and provided useful results. Additional studies on the optimization process itself provided information on move limit restrictions and various constraint problems.
Master of Science

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Rohl, Peter Jurgen. „A multilevel decomposition procedure for the preliminary wing design of a high-speed civil transport aircraft“. Diss., Georgia Institute of Technology, 1995. http://hdl.handle.net/1853/11827.

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Bücher zum Thema "Wing construction"

Selberg, Bruce P. Aerodynamic-structural study of canard wing, dual wing and conventional wing systems for general aviation applications. Hampton, Virginia: NASA Langley Research Center, 1985.

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Fighter wing: A guided tour of an Airforce Combat wing. New York: Berkley Books, 1995.

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Wood, Richard M. The natural flow wing-design concept. Hampton, Va: Langley Research Center, 1992.

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Clancy, Tom. Fighter wing: A guided tour of an Air Force combat wing. New York: Berkley Books, 1995.

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Clancy, Tom. Fighter wing: A guided tour of an Air Force combat wing. New York: Berkley Books, 2004.

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Fighter wing: A guided tour of an Air Force combat wing. London: HarperCollins, 1995.

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Valasek, John. Morphing aerospace vehicles and structures. Chichester, West Sussex: John Wiley & Sons, 2012.

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American Institute of Aeronautics and Astronautics, Hrsg. Morphing aerospace vehicles and structures. Chichester, West Sussex: John Wiley & Sons, 2012.

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Wrong and dangerous: Ten right-wing myths about the constitution. Lanham, Md: Rowman & Littlefield, 2012.

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Merlin, Peter W. A New twist in flight research: The F-18 active aeroelastic wing project. Washington, DC: National Aeronautics and Space Administration, Aeronautics Research Mission Directorate, 2013.

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Buchteile zum Thema "Wing construction"

Moss, David. „The Construction of Judicial Accounts“. In The Politics of Left-Wing Violence in Italy, 1969–85, 165–209. London: Palgrave Macmillan UK, 1989. http://dx.doi.org/10.1007/978-1-349-20249-2_5.

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Brooks, W. G. „The Construction of a Postbuckled Carbon Fibre Wing Box“. In Composite Structures 4, 178–90. Dordrecht: Springer Netherlands, 1987. http://dx.doi.org/10.1007/978-94-009-3455-9_13.

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Siim, Birte, und Susi Meret. „Right-wing Populism in Denmark: People, Nation and Welfare in the Construction of the ‘Other’“. In The Rise of the Far Right in Europe, 109–36. London: Palgrave Macmillan UK, 2016. http://dx.doi.org/10.1057/978-1-137-55679-0_5.

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Berend, Ivan T. „Is the European Union a neoliberal construction that deserves to be destroyed? A debate with left-wing attacks“. In Against European Integration, 111–21. Abingdon, Oxon; New York, NY: Routledge, 2019. | Series: Economics in the real world: Routledge, 2019. http://dx.doi.org/10.4324/9780429200458-10.

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Gill, Clare. „Reading the ‘Religion of Socialism’: Olive Schreiner, the Labour Church and the Construction of Left-wing Reading Communities in the 1890s“. In The History of Reading, Volume 2, 48–63. London: Palgrave Macmillan UK, 2011. http://dx.doi.org/10.1057/9780230316799_4.

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Qu, Yingying, und Sai On Cheung. „Logrolling “Win–Win” Settlement in Construction Dispute Mediation“. In Construction Dispute Research, 383–410. Cham: Springer International Publishing, 2014. http://dx.doi.org/10.1007/978-3-319-04429-3_20.

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Hau, Erich, Jens Langenbrinck und Wolfgang Palz. „The WEGA Wind Turbines — Design and Construction“. In WEGA Large Wind Turbines, 41–91. Berlin, Heidelberg: Springer Berlin Heidelberg, 1993. http://dx.doi.org/10.1007/978-3-642-52129-4_3.

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Bahadori, Mehdi N., Alireza Dehghani-sanij und Ali Sayigh. „Designing, Constructing, and Testing Conventional Baudgeers and New Designs“. In Wind Towers, 163–77. Cham: Springer International Publishing, 2014. http://dx.doi.org/10.1007/978-3-319-05876-4_7.

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Wisser, A., und W. Nachtigall. „Biomechanical Aspects of the Wing Joints in Flies, Especially in Calliphora erythrocephala“. In Constructional Morphology and Evolution, 193–207. Berlin, Heidelberg: Springer Berlin Heidelberg, 1991. http://dx.doi.org/10.1007/978-3-642-76156-0_14.

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Borri, Claudio, Paolo Biagini und Enzo Marino. „Large wind turbines in earthquake areas: structural analyses, design/construction & in-situ testing“. In Environmental Wind Engineering and Design of Wind Energy Structures, 295–350. Vienna: Springer Vienna, 2011. http://dx.doi.org/10.1007/978-3-7091-0953-3_7.

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Konferenzberichte zum Thema "Wing construction"

Thompson, Daniel, Joshuo Feys, Michael Filewich, Sharif Abdel-Magid, Dennis Dalli und Fumitaka Goto. „The Design and Construction of a Blended Wing Body UAV“. In 49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-841.

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Manzo, Justin E., Emily A. Leylek und Ephrahim Garcia. „Drawing Insight From Nature: A Bat Wing for Morphing Aircraft“. In ASME 2008 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. ASMEDC, 2008. http://dx.doi.org/10.1115/smasis2008-613.

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Being the only flying mammal, bats have evolved unique flight devices affording them high maneuverability and efficiency despite their low flight speeds. By selecting bats of three different ecological niches — a highly efficient fishing bat, a nimble insectivorous forager, and a large soaring bat of the ‘flying fox’ family — passive wing shapes can be demonstrated as capable of attaining very different aerodynamic performance characteristics. The aerodynamics of man-made equivalents to these wing shapes, using thin airfoils rather than skeleton and membrane construction, are studied both computationally through a lifting-line approach and experimentally with quasistatic wind tunnel data of ‘morphed’ and ‘unmorphed’ wing shapes. Results confirm that shape inspired by the larger soaring bat has higher lift-to-drag ratios, while that of the foraging bat maintains lift at higher angles of attack than the other wings. The advantages are more pronounced by morphing, increasing both lift coefficient and lift-to-drag ratios by up to 50% for certain wings. This is validated both numerically and in the Cornell University 4′×4′ wind tunnel. Analysis of these shapes provides the first phase of wing design for use on a morphing aircraft vehicle. In order to take greater advantage of vehicle morphing, wing shapes with camber and twist distributions unique from those found in nature will evolve to suit a man-made structure. In this way, a wing shape intended for cruise may extend its practicality into highly maneuverable operations through the use of wing morphing. Starting from the bat planform shapes, a series of optimizations determines the best camber and twist distributions for effective morphing. Given a fixed degree of shape change at any point along an airfoil based on mechanism constraints, improved morphing performance can be found compared to initial assumptions of the natural shape change. Heuristic optimization employing simulated annealing determines the required morphing shapes for increased performance, broadening the abilities of each wing shape by increasing parameters such as lift, rolling moment, and endurance.

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Onishi, Ryoichi, Toshiya Kimura, Zhihong Guo und Toshiyuki Iwamiya. „Computational aero-structural dynamics for wing with skin-spar-rib construction“. In 18th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-4225.

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Andaste, Yosua Sepri, Muhammad Aldo Aditiya Nugroho, R. S. Brian Benyamin, Bambang Riyanto Trilaksono und Agoes Moelyadi. „Design and construction of flapping wing micro aerial vehicle robot platform“. In 2017 7th IEEE International Conference on System Engineering and Technology (ICSET). IEEE, 2017. http://dx.doi.org/10.1109/icsengt.2017.8123444.

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Olejnik, A., L. Kiszkowiak, M. Jędrak, J. Milczarczyk und A. Dziubiński. „Crash Analysis of Wing of Large Airplane with a Tree“. In 17th Biennial International Conference on Engineering, Science, Construction, and Operations in Challenging Environments. Reston, VA: American Society of Civil Engineers, 2021. http://dx.doi.org/10.1061/9780784483381.014.

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Aguillon Balderas, Nestor Abraham, Gerardo Emanuel Cardona Sanchez, Jessica Jazmin Maldonado Ramos, Carlos Antonio Tovar Garcia und Alejandro J. Malo Tamayo. „Construction and instrumentation of a fixed wing aircraft guillow's aeronca champion 85“. In 2015 Workshop on Research, Education and Development of Unmanned Aerial Systems (RED-UAS). IEEE, 2015. http://dx.doi.org/10.1109/red-uas.2015.7441031.

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Ding, Menglong, und Wieslaw Binienda. „Numerical Study of a Transport Aircraft Wing Impact with a Birch Tree“. In 17th Biennial International Conference on Engineering, Science, Construction, and Operations in Challenging Environments. Reston, VA: American Society of Civil Engineers, 2021. http://dx.doi.org/10.1061/9780784483381.007.

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Henry, Jonathon, David Schwartz, Michael Soukup und Aaron Altman. „Design, Construction, and Testing of a Folding-Wing, Tube-Launched Micro Air Vehicle“. In 43rd AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-1451.

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Salistean, Adrian, Carmen Mihai, Doina Toma und Sabina Olaru. „Theoretical and practical aspects of the design phase for a single skin textile wing“. In The 8th International Conference on Advanced Materials and Systems. INCDTP - Leather and Footwear Research Institute (ICPI), Bucharest, Romania, 2020. http://dx.doi.org/10.24264/icams-2020.iii.16.

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This paper depicts the early phase in the research development for an integrated support system tailored for emergency response actions and remote sensing. The support system is envisioned as an integrated Unmanned Aerial System (UAS) system that consists of one or more ultralight multifunctional aerial units with a configuration that can be adapted to the nature of the intervention: monitoring, mapping, observation and logistics etc. These aerial units comprise of para-motor type UAVs that use textile paraglider wings of a special design. The paper summarizes the basic materials used in the construction of parachutes, as well as it depicts the design phase for the main material used on the wing construction. Starting from wing airfoil and materials selection, a design phase is ongoing for a single sail paraglider wing that can meet the operational demands for emergency response situations. The wing is designed mainly to have an easy handling and to have a predictable deployment at all times. The entire system and the aerial units are designed with increased modularity in order to be tailored for specific operational requirements of the intervention. A numerical model is under development and rigorous testing to validate the theoretical aspects and the design choices.

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Abeysinghe, Asith, Shameera Abeysiriwardena, Roshan Nanayakkarawasam, Walallawita Wimalsiri, Thilina Dulantha Lalitharatne und Salinda Tennakoon. „Development of a numerically controlled hot wire foam cutting machine for wing mould construction“. In 2016 Moratuwa Engineering Research Conference (MERCon). IEEE, 2016. http://dx.doi.org/10.1109/mercon.2016.7480116.

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Berichte der Organisationen zum Thema "Wing construction"

URS CORP OAKLAND CA. Environmental Assessment of Short-Term Construction Projects at the 150th Fighter Wing, New Mexico Air National Guard, Kirtland Air Force Base, New Mexico. Fort Belvoir, VA: Defense Technical Information Center, Januar 2003. http://dx.doi.org/10.21236/ada639962.

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Worachek, Alden, und Forest Button. Bethel Wind Energy Construction Project. Office of Scientific and Technical Information (OSTI), März 2020. http://dx.doi.org/10.2172/1607624.

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Worachek, Alden, und Forest Button. Pitka's Point/St. Mary's Wind Energy Construction Project. Office of Scientific and Technical Information (OSTI), März 2020. http://dx.doi.org/10.2172/1607457.

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McMillan, Andy. Cherokee Wind Energy Development - Feasibility and Pre-Construction Studies. Office of Scientific and Technical Information (OSTI), Juni 2017. http://dx.doi.org/10.2172/1395350.

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Connolly, Michael. Pre-construction Activities for Phase 1 of Shu'luuk Wind Project. Office of Scientific and Technical Information (OSTI), Juli 2015. http://dx.doi.org/10.2172/1208019.

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DeRenzis, A., und V. Kochkin. High-R Walls for New Construction Structural Performance. Wind Pressure Testing. Office of Scientific and Technical Information (OSTI), Januar 2013. http://dx.doi.org/10.2172/1219901.

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DeRenzis, A., und V. Kochkin. High-R Walls for New Construction Structural Performance: Wind Pressure Testing. Office of Scientific and Technical Information (OSTI), Januar 2013. http://dx.doi.org/10.2172/1067930.

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Matlack, Raymond S. Wind Energy and Wildlife Pre- and Post-Construction Project at Pantex Plant. Office of Scientific and Technical Information (OSTI), Januar 2018. http://dx.doi.org/10.2172/1416956.

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Ligotke, M. W., G. W. Dennis und L. L. Bushaw. Wind tunnel tests of biodegradable fugitive dust suppressants being considered to reduce soil erosion by wind at radioactive waste construction sites. Office of Scientific and Technical Information (OSTI), Oktober 1993. http://dx.doi.org/10.2172/10190697.

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Dagher, Habib, Anthony Viselli, Andrew Goupee, Richard Kimball und Christopher Allen. The VolturnUS 1:8 Floating Wind Turbine: Design, Construction, Deployment, Testing, Retrieval, and Inspection of the First Grid-Connected Offshore Wind Turbine in US. Office of Scientific and Technical Information (OSTI), August 2017. http://dx.doi.org/10.2172/1375022.

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