Bibliographies thématiques / Integrated Wing Design

Littérature scientifique sur le sujet « Integrated Wing Design »

Auteur : Grafiati
Publié le 14 mars 2023

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Articles de revues sur le sujet "Integrated Wing Design"

1

Rais-Rohani, M., R. T. Haftka, B. Grossman et E. R. Unger. « Integrated aerodynamic-structural-control wing design ». Computing Systems in Engineering 3, no 6 (décembre 1992) : 639–50. http://dx.doi.org/10.1016/0956-0521(92)90015-b.

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Oleinikov, Alexander Ivanovich. « Integrated Design of Wing Panel Manufacture Processes ». Key Engineering Materials 554-557 (juin 2013) : 2175–86. http://dx.doi.org/10.4028/www.scientific.net/kem.554-557.2175.

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ALEXANDER IVANOVICH OLEINIKOV Aircraft Engineering Faculty, Komsomolsk-on-Amur State Technical University Lenina prospect 27, 681013 Komsomolsk-on-Amur, Russian Federation a.i.oleinikov@mail.ru Keywords: forming, creep, age, transversely isotropic, kind of the stress state effect, wing panel, inverse problem, reverse engineering, computer-aided process design system. Abstract. Problems of inelastic straining of three-dimensional bodies with large displacements and turns are considered. In addition to the sought fields, surface forces and boundary displacements, original size and shape have also to be determined from specified residual displacements in these problems. Currently, forming of light metals poses tremendous challenges due to their low ductility at room temperature and their unusual deformation characteristics at hot-cold work: strong asymmetry between tensile and compressive behavior, and a very pronounced anisotropy. We proposed the constitutive models of steady-state creep of initially transverse isotropy structural materials the kind of the stress state has influence [1]. The forming process considered includes two stages: active stage of elastoviscoplastic straining of the blank in the die tooling and passive stage of unloading of the blank withdrawn from the die tooling. The final stress-strain state at the active stage is the initial state for the passive stage. Unloading is considered as purely elastic straining, with no increments of inelastic strains. The active stage, in turn, also includes two steps. At the first step, the frontal faces of the “cold” blank are pressed to the working surfaces of the die tooling, which results in elastoplastic straining of the blank. The second step includes the processes of stress relaxation and creep strain in the blank fixed in this die tooling during a given time at an elevated ageing temperature. Computer modeling of these forming processes involves the use of the finite element method for consecutive solutions of three-dimensional quasi-static problems of elastoplastic straining, relaxation, and unloading, and also determining boundary conditions from given residual displacements [2] . The paper gives basics of the developed computer-aided system of design, modeling, and electronic simulation targeting the processes of manufacture of wing integral panels. System application data resulting from computation of 3D-involute of a CAD-based panel model, determination of working surfaces of die tooling, three-dimensional analysis of stresses, and simulation of panel shaping under diverse thermo-mechanical and speed conditions are demonstrated. Modeling of forming of wing panels of the SSJ-100 aircraft are considered [2,3]. The modeling results can be used to calculate the die tooling, determine the panel processibility, and control panel rejection in the course of forming [3]. References [1] A.I. Oleinikov, Models for the steady-state creep of transversely isotropic materials with different tension and compression characteristics, J. Ind. Appl. Math. 5 (2011) 406-409. [2] B.D. Annin, A.I. Oleinikov and K.S. Bormotin, Modeling of forming of wing panels of the SSJ-100 aircraft, J. Appl. Mech. Physics 51 (2010) 579-589. [3] A.I. Oleinikov, A.I. Pekarsh, Integrated Design of Integral Panel Manufacture Processes. Dalnauka, Vladivostok, 2010.
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Grossman, B., Z. Gurdal, G. J. Strauch, W. M. Eppard et R. T. Haftka. « Integrated aerodynamic/structural design of a sailplane wing ». Journal of Aircraft 25, no 9 (septembre 1988) : 855–60. http://dx.doi.org/10.2514/3.45670.

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Grossman, B., R. T. Haftka, P. J. Kao, D. M. Polen, M. Rais-Rohani et J. Sobieszczanski-Sobieski. « Integrated aerodynamic-structural design of a transport wing ». Journal of Aircraft 27, no 12 (décembre 1990) : 1050–56. http://dx.doi.org/10.2514/3.45980.

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SALISTEAN, ADRIAN, DOINA TOMA, IONELA BADEA et MIHAELA JOMIR. « Design of a small-scale UAV textile wing fluid-structure numerical modelling ». Industria Textila 72, no 04 (1 septembre 2021) : 449–53. http://dx.doi.org/10.35530/it.072.04.1844.

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This paper depicts the early phase in the research development for an integrated UAV (Unmanned Aerial Vehicle)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, logistics etc. These aerial units comprise of para-motor type UAVs that use textile paraglider wings of a special design. The overall development and theoretical design aspects that are involved in this research is subject of change been part of an ongoing research study. Starting from wing airfoil and material selection, a design phase is under development for a single sail paraglider wing that can meet the operational demands for the envisioned system. The wing is designed mainly to have an easy handling, predictable deployment at all times and good aerodynamic characteristics. The paper tackles in particular the stretch effect on the wing and the influence on these aerodynamic characteristics as well as means of minimizing the adverse effects.
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Patil, Ankur S., et Emily J. Arnold. « Sensor-Driven Preliminary Wing Ground Plane Sizing Approach and Applications ». International Journal of Aerospace Engineering 2018 (2 juillet 2018) : 1–15. http://dx.doi.org/10.1155/2018/6378635.

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Structurally integrated antenna arrays provide synergies allowing the integration of large apertures onto airborne platforms. However, the surrounding airframe can greatly impact the performance of the antenna array. This paper presents a sensor-driven preliminary wing ground plane sizing approach to provide insight into the implications of design decisions on payload performance. The improvement of a wing-integrated antenna array that utilizes the wing as a ground plane motivated this study. Relationships for wing span, wing chord, and thickness are derived from extensive parametric electromagnetic simulations based on optimum antenna performance. It is expected that these equations would be used after an initial wing-loading design point has been selected to provide the designer guidance into how various wing parameters might affect the integrated antenna performance.
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Maute, K., et G. W. Reich. « Integrated Multidisciplinary Topology Optimization Approach to Adaptive Wing Design ». Journal of Aircraft 43, no 1 (janvier 2006) : 253–63. http://dx.doi.org/10.2514/1.12802.

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Botez, R. M., M. J. Tchatchueng Kammegne et L. T. Grigorie. « Design, numerical simulation and experimental testing of a controlled electrical actuation system in a real aircraft morphing wing model ». Aeronautical Journal 119, no 1219 (septembre 2015) : 1047–72. http://dx.doi.org/10.1017/s0001924000011131.

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AbstractThe paper focuses on the modelling, simulation and control of an electrical miniature actuator integrated in the actuation mechanism of a new morphing wing application. The morphed wing is a portion of an existing regional aircraft wing, its interior consisting of spars, stringers, and ribs, and having a structural rigidity similar to the rigidity of a real aircraft. The upper surface of the wing is a flexible skin, made of composite materials, and optimised in order to fulfill the morphing wing project requirements. In addition, a controllable rigid aileron is attached on the wing. The established architecture of the actuation mechanism uses four similar miniature actuators fixed inside the wing and actuating directly the flexible upper surface of the wing. The actuator was designed in-house, as there is no actuator on the market that could fit directly inside our morphing wing model. It consists of a brushless direct current (BLDC) motor with a gearbox and a screw for pushing and pulling the flexible upper surface of the wing. The electrical motor and the screw are coupled through a gearing system. Before proceeding with the modelling, the actuator is tested experimentally (stand alone configuration) to ensure that the entire range of the requirements (rated or nominal torque, nominal current, nominal speed, static force, size) would be fulfilled. In order to validate the theoretical, simulation and standalone configuration experimental studies, a bench testing and a wind-tunnel testing of four similar actuators integrated on the real morphing wing model are performed.
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Zhang, Gong Ping, Zhi Zhong Liao, Chao Yang Duan et Peng Ju Wang. « Optimal Design of Configuration Change Program for Tactical Missile with Morphing Wings ». Applied Mechanics and Materials 101-102 (septembre 2011) : 410–13. http://dx.doi.org/10.4028/www.scientific.net/amm.101-102.410.

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The flight Performance of missile can be improved by adaptive morphing wing serving as main lift surface. A novel compounded morphing missile, a complicated nonlinear and non-analytical multivariable constrained optimization problem, is modeled to design adaptive program of the wing geometry versus flight states. Based on reformed optimal algorithms such as Monte Carlo and Particle Swarm Optimization (PSO), a set of integrated approach is developed to optimize the shape change program of wings by interactively reading and writing data files from missile DATCOM. The simulation results show that the proposed algorithms can be used to obtain an optimal missile configuration over large flight envelope, characterized by maximal lift-to-drag ratio and a required normal overload.
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de Mattos, Bento Silva, Paulo Jiniche Komatsu et Jesuíno Takachi Tomita. « Optimal wingtip device design for transport airplane ». Aircraft Engineering and Aerospace Technology 90, no 5 (2 juillet 2018) : 743–63. http://dx.doi.org/10.1108/aeat-07-2015-0183.

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Purpose The present work aims to analyze the feasibility of wingtip device incorporation into transport airplane configurations considering many aspects such as performance, cost and environmental impact. A design framework encompassing optimization for wing-body configurations with and without winglets is described and application examples are presented and discussed. Design/methodology/approach modeFrontier, an object-oriented optimization design framework, was used to perform optimization tasks of configurations with wingtip devices. A full potential code with viscous effects correction was used to calculate the aerodynamic characteristics of the fuselage–wing–winglet configuration. MATLAB® was also used to perform some computations and was easily integrated into the modeFrontier frameworks. CFD analyses of transport airplanes configurations were also performed with Fluent and CFD++ codes. Findings Winglet provides considerable aerodynamic benefits regarding similar wings without winglets. Drag coefficient reduction in the order of 15 drag counts was achieved in the cruise condition. Winglet also provides a small boost in the clean-wing maximum lift coefficient. In addition, less fuel burn means fewer emissions and contributes toward preserving the environment. Practical implications More efficient transport airplanes, presenting considerable lower fuel burn. Social implications Among other contributions, wingtip devices reduce fuel burn, engine emissions and contribute to a longer engine lifespan, reducing direct operating costs. This way, they are in tune with a greener world. Originality/value The paper provides valuable wind-tunnel data of several winglet configurations, an impact of the incorporation of winglets on airplane design diagram and a direct comparison of two optimizations, one performed with winglets in the configuration and the other without winglets. These simulations showed that their Pareto fronts are clearly apart from each other, with the one from the configuration with winglets placed well above the other without winglets. The present simulations indicate that there are always aerodynamic benefits present regardless the skeptical statements of some engineers. that a well-designed wing does not need any winglet.
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Thèses sur le sujet "Integrated Wing Design"

1

Unger, Eric Robert. « Integrated aerodynamic-structural wing design optimization ». Diss., This resource online, 1992. http://scholar.lib.vt.edu/theses/available/etd-09042008-063104/.

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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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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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4

MAININI, LAURA. « Multidisciplinary and multi-fidelity optimization environment for wing integrated design ». Doctoral thesis, Politecnico di Torino, 2012. http://hdl.handle.net/11583/2500000.

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The Ph.D. program has been focused on the development of a multidisciplinary integrated environment for the design of wing for which large changes in shape are expected to be allowed during the flight in order to be better adapted for the different flight segments. The first phase of study has been dedicated to the investigation of the proper Multidisciplinary Design Optimization (MDO) architecture for the integrated management of the design process and a multilevel solution has been proposed and implemented. Such framework involves several disciplinary analysis and optimization loops: in particular aerodynamic analysis, structural analysis, material optimization and mission and performance evaluation are the main components considered for the preliminary design development for such a “morphing” wing. This stage addressed basically the multidisciplinarity and interdisciplinarity issues. The second phase has been dedicated to the investigation of possible techniques for the reduction of the computational burden that characterizes typically this kind of integrated design processes. For this purpose multi-fidelity analysis techniques have been considered involving the use of surrogate models. In particular the attention has been focused on the study of a proper methodology to build an approximated model for the estimation of aerodynamic coefficients to be used for performance evaluation in the mission optimization stage. In this case a procedure involving variables screening phase, data-fit surrogate models evaluation and assessment phase and a final crucial global correction phase of the best surrogate model has been proposed.
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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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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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Bortolotti, Pietro [Verfasser]. « Integrated Design of Wind Turbines / Pietro Bortolotti ». München : Verlag Dr. Hut, 2018. http://d-nb.info/1166482456/34.

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Zhang, Hui. « Wind turbine adaptive blade integrated design and analysis ». Thesis, Northumbria University, 2013. http://nrl.northumbria.ac.uk/21439/.

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This project aims to develop efficient and robust tools for optimal design of wind turbine adaptive blades. In general, wind turbine adaptive blade design is an aero-structure coupled design process, in which, the evaluation of aerodynamic performance cannot be carried out precisely without structural deformation analysis of the adaptive blade. However, employing finite element analysis (FEA) based structural analysis commercial packages as part of the aerodynamic objective evaluation process has been proven time consuming and it results in inefficient and redundant design optimisation of adaptive blades caused by elastic-coupled (bend-twist or stretch-twist) iteration. In order to achieve the goal of wind turbine adaptive blade integrated design and analysis, this project is carried out from three aspects. Firstly, a general geometrically linear model for thin-walled composite beams with multi-cell, non-uniform cross-section and arbitrary lay-ups under various types of loadings is developed for implementing structural deformation analysis. After that, this model is validated by a simple box-beam, single- and multi-cell wind turbine blades. Through validation, it denotes that this thin-walled composite beam model is efficient and accurate for predicting the structural deformations compared to FEA based commercial packages (ANSYS). This developed beam model thus provides more probabilities for further investigations of dynamic performance of adaptive blades. Secondly in order to investigate the effects of aero elastic tailoring and implanting elastic coupling on aerodynamic performance of adaptive blades, auxiliary software tools with graphical interfaces are developed via MATLAB codes. Structural/material characteristics and configurations of adaptive blades (i.e. elastic coupling topology, layup configuration and material properties of blade) are defined by these auxiliary software tools. By interfacing these software tools to the structural analysers based on the developed thin-walled composite beam model to an aerodynamic performance evaluator, an integrated design environment is developed. Lastly, by using the developed thin-walled composite beam model as a search platform, the application of the decoupled design method, a method of design of smart aero-structures based on the concept of variable state design parameter, is also extended.
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Rogers, Mary C. M. « Control aspects of integrated design of wind turbines : a foundation ». Thesis, University of Strathclyde, 1998. http://oleg.lib.strath.ac.uk:80/R/?func=dbin-jump-full&object_id=21367.

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The configuration of a wind turbine and its control system dictate the dynamics of the machine. Since the dynamics of each part of the wind turbine affect those of the others, the machine should be considered as an integrated unit. The objective of the research reported here is to lay the foundations for the control aspects of integrated design by determining the dependence of the power controller performance of medium- and largescale, actively regulated, up-wind, horizontal-axis, grid-connected wind turbines on their configuration, that is, the dependence of the magnitude of the loads experienced by the drive train on the machine characteristics. There is a tendency amongst manufacturers to move from conventional, heavy and stiff machines to ones with lighter and more flexible components which makes machines more dynamically active and hence makes the power control task more difficult. Simple thoroughly derived linear and non-linear models of the significant wind turbine dynamics for power control are used to obtain a greater understanding of how machine parameters effect the overall behaviour of the power train. The dependence of the power controller performance of different full-span and tip-regulated machines is discussed. Finally, explanation of the results is illustrated with regard to the design of a 1 MW wind turbine.
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Perez, Damas Carlos Emilio. « Design of an airborne wind energy (AWE) research platform ». Thesis, Massachusetts Institute of Technology, 2018. http://hdl.handle.net/1721.1/118530.

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Thesis: S.M. in Engineering and Management, Massachusetts Institute of Technology, System Design and Management Program, 2018.
Thesis: S.M., Massachusetts Institute of Technology, Department of Mechanical Engineering, 2018.
Cataloged from PDF version of thesis.
Includes bibliographical references (pages 121-126).
Airborne wind energy (AWE) technologies have the potential to become a dominant source of clean electricity generation and help humanity reach many of the key sustainable development goals (SDGs) established by the United Nations as part of the 2030 Agenda for Sustainable Development. AWE systems eliminate the need for a tower, large blades and substantial foundations used in modern wind turbines and replace it with a wing (i.e. kite or glider aircraft) tethered to the ground. This technology can reach higher-altitude winds which is an untapped source of clean and highly abundant energy with the potential to power civilization 100 times over. As part of this work, an AWE research platform has been designed and developed based on a concept that emphasizes low-complexity, safety and low-cost. This research platform can be used to evaluate different sensor frameworks, airfoil/tether designs, control systems and optimal operational strategies for AWE systems operating under lift mode. A first-order techno-economic analysis was also performed to assess the cost and technical feasibility of developing a small-scale AWE system for distributed generation applications. In addition to estimating the approximate cost of the system, the analysis also determines the potential power generated by a specific AWE system design operating at a maximum elevation of 152 meters, to comply with existing regulation. The results of the techno-economic analysis suggest that small-scale AWE systems have the potential to produce electricity at a much lower cost than small-wind turbines of the same rated capacity.
by Carlos Emilio Perez Damas.
S.M. in Engineering and Management
S.M.
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Livres sur le sujet "Integrated Wing Design"

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United States. National Aeronautics and Space Administration., dir. Integrated design and manufacturing for the high speed civil transport : Preliminary design methodology and optimization for an HSCT Nacelle/Wing configuration : final report. [Washington, DC : National Aeronautics and Space Administration, 1994.

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Bartoli, Gianni, Francesco Ricciardelli, Anna Saetta et Vincenzo Sepe, dir. Performance of Wind Exposed Structures. Florence : Firenze University Press, 2006. http://dx.doi.org/10.36253/978-88-6453-156-4.

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PERBACCO (a free Italian acronym for Life-cycle Performance, Innovation and Design Criteria for Structures and Infrastructures Facing Æolian and Other Natural Hazards) is a research project partly funded by the Italian Ministry for University (MIUR) in the PRIN (Progetti di Ricerca di Interesse Nazionale) framework, for the years 2004-05.Within the project, a first attempt has been made to integrate different disciplines aiming at an overall optimization of the performance of a wide range of wind exposed structures and infrastructures, with consequent benefi cial impact on the society.The overall objectives were (a) to provide unifi ed concepts for "expected performance" and "risks induced by æolian and other natural hazards", to be applied to structures and infrastructures over their whole life-cycle, such to be acceptable to stakeholders in the construction process (i.e. from the owner to the end-user), (b) to provide models and methodologies for dynamic monitoring of the performance of structures and infrastructures, to be integrated in appropriately designed procedures, and (c) to collect, refi ne, fi le and disseminate the knowledge available on a European basis, concerning the performance of wind-exposed structures and facilities, in a way such to be of use to Construction Industry. This volume summarises the main results obtained during the Project, with each Section addressing a different class of problems, to which many research Units have contributed. A list of papers containing the main results of the research activities carried out within the Project is also provided in each Section.
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Center, Langley Research, dir. Design of the wind tunnel model communication controller board. Hampton, Va : National Aeronautics and Space Administration, Langley Research Center, 1999.

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Gevorkian, Peter. Alternative energy systems in building design. New York : McGraw-Hill, 2010.

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Alternative energy systems in building design. New York : McGraw-Hill, 2010.

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Gevorkian, Peter. Sustainable Energy Systems in Architectural Design. New York : McGraw-Hill, 2006.

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Sustainable energy systems in architectural design : A blueprint for green building. New York : McGraw-Hill, 2006.

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Yuan, Chao. Urban Wind Environment : Integrated Climate-Sensitive Planning and Design. Springer, 2018.

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Yuan, Chao. Urban Wind Environment : Integrated Climate Sensitive Planning and Design. Springer Singapore Pte. Limited, 2018.

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10

Doquang, Mailan S. The Lithic Garden. Oxford University Press, 2018. http://dx.doi.org/10.1093/oso/9780190631796.001.0001.

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This ambitious book offers new perspectives on the role of vegetal ornament in medieval church design. Focusing on an extensive series of foliate friezes articulating iconic French monuments, such as Cluny III, Amiens Cathedral, and Mont-Saint-Michel, it demonstrates that church builders strategically used organic motifs to integrate the interior and exterior of their structures, and to reinforce the connections and distinctions between the entirety of the sacred edifice and the profane world beyond its boundaries. Mailan S. Doquang shows that, contrary to widespread belief, monumental flora was not just an extravagant embellishment devoid of meaning and purpose, or an epiphenomenon, but a semantically charged, critical design component that inflected the stratified spaces of churches in myriad ways. The friezes encapsulated and promoted core aspects of the Christian faith for medieval beholders, evoking the viridity of the paradisiacal garden, Christ as the True Vine, the Eucharistic wine and ritual, and the golden vine of the Temple of Jerusalem, originally built by the wise King Solomon. By situating the proliferation of foliate friezes within the context of the Crusades, moreover, this study provides new insights into the networks of exchange between France, Byzantium, and the Levant, and contributes substantially to the “global turn” in the field of medieval art and architectural history.
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Chapitres de livres sur le sujet "Integrated Wing Design"

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Lukens, Jennifer M., Gregory W. Reich et Brian Sanders. « Wing Mechanization Design and Wind Tunnel Testing for a Perching Micro Air Vehicle ». Dans Emboding Intelligence in Structures and Integrated Systems, 589–94. Stafa : Trans Tech Publications Ltd., 2008. http://dx.doi.org/10.4028/3-908158-13-3.589.

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Wunderlich, Tobias, et Lars Reimer. « Integrated Process Chain for Aerostructural Wing Optimization and Application to an NLF Forward Swept Composite Wing ». Dans Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 3–33. Cham : Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-72020-3_1.

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Denieul, Yann, Joël Bordeneuve, Daniel Alazard, Clément Toussaint et Gilles Taquin. « Integrated Design and Control of a Flying Wing Using Nonsmooth Optimization Techniques ». Dans Advances in Aerospace Guidance, Navigation and Control, 475–89. Cham : Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-17518-8_27.

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Soukal, Ivan, et Aneta Bartuskova. « WINE : Web Integrated Navigation Extension ; Conceptual Design, Model and Interface ». Dans Computational Collective Intelligence, 462–72. Cham : Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-67074-4_45.

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Harbola, Shubhi, Martin Storz et Volker Coors. « Augmented Reality for Windy Cities : 3D Visualization of Future Wind Nature Analysis in City Planning ». Dans iCity. Transformative Research for the Livable, Intelligent, and Sustainable City, 241–50. Cham : Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-030-92096-8_15.

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AbstractEffective government management, convenient public services, and sustainable industrial development are achieved by the thorough utilization and management of green, renewable resources. The research and the study of meteorological data and its effect on devising renewable solutions as a replacement for nonrenewable ones is the motive of researchers and city planners. Sources of energy like wind and solar are free, green, and popularly being integrated into sustainable development and city planning to preserve environmental quality. Sensor networks have become a convenient tool for environmental monitoring. Wind energy generated through the use and maintenance of wind turbines requires knowledge of wind parameters such as speed and direction for proper maintenance. An augmented reality (AR) tool for interactive visualization and exploration of future wind nature analyses for experts is still missing. Existing solutions are limited to graphs, tabular data, two-dimensional space (2D) maps, globe view, and GIS tool designed for the desktop and not adapted with AR for easy, interactive mobile use. This work aims to provide a novel AR-based mobile supported application (App) that serves as a bridge between three-dimensional space (3D) temporal wind dataset visualization and predictive analysis through machine learning (ML). The proposed development is a dynamic application of AR supported with ML. It provides a user interactive designed approach, presenting a multilayered infrastructure process accessed through a mobile AR platform that supports 3D visualization of temporal wind data through future wind analysis. Thus, a novel AR visualization App with the prediction of wind nature using ML algorithms would provide city planners with advanced knowledge of wind conditions and help in easy decision-making with interactive 3D visualization.
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Uzunoglu, E., et C. Guedes Soares. « An integrated design approach for a self-float capable tension leg platform for wind energy ». Dans Developments in Maritime Technology and Engineering, 673–81. London : CRC Press, 2021. http://dx.doi.org/10.1201/9781003216599-71.

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Koitz, Roxane, Johannes Lüftenegger et Franz Wotawa. « Model-Based Diagnosis in Practice : Interaction Design of an Integrated Diagnosis Application for Industrial Wind Turbines ». Dans Advances in Artificial Intelligence : From Theory to Practice, 440–45. Cham : Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-60042-0_48.

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Zillner, Sonja. « Business Models and Ecosystem for Big Data ». Dans The Elements of Big Data Value, 269–88. Cham : Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-68176-0_11.

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AbstractWith the recent technical advances in digitalisation and big data, the real and the virtual worlds are continuously merging, which, again, leads to entire value-added chains being digitalised and integrated. The increase in industrial data combined with big data technologies triggers a wide range of new technical applications with new forms of value propositions that shift the logic of how business is done. To capture these new types of value, data-driven solutions for the industry will require new business models. The design of data-driven AI-based business models needs to incorporate various perspectives ranging from customer and user needs and their willingness to pay for new data-driven solutions to data access and the optimal use of technologies, while taking into account the currently established relationships with customers and partners. Successful data-driven business models are often based on strategic partnerships, with two or more players establishing the basis for sustainable win-win situations through transparent resource-, investment-, risk-, data- and value-sharing. This chapter will explore the different data-driven business approaches and highlight in this context the importance of functioning ecosystems on the various levels. The chapter will conclude with an introduction to the data-driven innovation framework, a proven methodology to guide the systematic investigation of data-driven business opportunities while incorporating the dynamics of the underlying ecosystems.
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Beghdadi, M., K. Kouzi et A. Ameur. « New Design of an Optimized Synergetic Control by Hybrid BFO-PSO for PMSG Integrated in Wind Energy Conversion System Using Variable Step HCS Fuzzy MPPT ». Dans Lecture Notes in Networks and Systems, 30–40. Cham : Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-37207-1_4.

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Yawson, David O., Michael O. Adu, Paul A. Asare et Frederick A. Armah. « Multifunctional Landscape Transformation of Urban Idle Spaces for Climate Resilience in Sub-Saharan Africa ». Dans African Handbook of Climate Change Adaptation, 1–27. Cham : Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-42091-8_214-1.

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AbstractPoor physical and land use planning underpin the chaotic evolution and expansion in cities and towns in sub-Saharan Africa. This situation amplifies urban vulnerability to climate change. Worse, urban landscapes are rarely considered part of the discourse on urban development in sub-Saharan Africa, let alone in climate change adaptation. Yet, landscapes are known to play crucial roles in social, economic, and cultural resilience in cities and towns. Hence, designing basic forms of appealing and functional urban landscapes that support multiple ecosystem services is essential to the drive towards resilience, which relates to the ability to maintain or improve the supply of life support services and products (such as food and water) in the face of disturbance. In this chapter, the idea of transforming idle urban spaces into multifunctional edible urban landscapes is introduced and explored as instrumental for cost-effective adaptation and resilience to climate change in cities and towns in sub-Saharan Africa. Multifunctional edible urban landscape is defined here as a managed landscape that integrates food production and ornamental design, in harmonious coexistence with other urban structures to promote or provide targeted, multiple services. These services include food security, scenic beauty, green spaces for active living and learning, jobs and livelihoods support, environmental protection, climate adaptation, and overall urban resilience. This approach constitutes a triple-win multifunctional land use system that is beneficial to landowners, city managers, and the general community. This chapter explores the benefits, challenges, and prospects for practically transforming urban idle spaces into multifunctional edible urban landscapes using an example project from Ghana. The chapter shows that multifunctional edible urban landscape transformation for resilience is practically feasible, and sheds light on the possibility of the food production component paying for landscaping and landscape management. It concludes with thoughts on actions required across sectors and multiple scales, including mobilizing stakeholders, laws, policies, and incentives, to actualize multifunctional edible urban landscapes as key transformational components of resilience in sub-Saharan Africa.
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Actes de conférences sur le sujet "Integrated Wing Design"

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RAIS-ROHANI, M., R. HAFTKA, B. GROSSMAN et E. UNGER. « Integrated aerodynamic-structural-control wing design ». Dans 4th Symposium on Multidisciplinary Analysis and Optimization. Reston, Virigina : American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-4694.

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Shi, Guoqin, Guillaume Renaud, Fengxian Zhang, Suzhen Chen et XinFeng Yang. « Integrated Wing Design with Three Disciplines ». Dans 9th AIAA/ISSMO Symposium on Multidisciplinary Analysis and Optimization. Reston, Virigina : American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/6.2002-5405.

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GROSSMAN, B., R. HAFTKA, P. J. KAO, D. POLEN, M. RAIS-ROHANI et J. SOBIESZCZANSKI-SOBIESKI. « Integrated aerodynamic-structural design of a transport wing ». Dans Aircraft Design and Operations Meeting. Reston, Virigina : American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2129.

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Henderson, Joseph, Terrence Weisshaar et Brian Sanders. « Integrated wing design with adaptive control surfaces ». Dans 19th AIAA Applied Aerodynamics Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-1428.

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GROSSMAN, B., Z. GURDAL et R. HAFTKA. « Integrated aerodynamic/structural design of a sailplane wing ». Dans Aircraft Systems, Design and Technology Meeting. Reston, Virigina : American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-2623.

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Miyakawa, Junichi, Takeshi Ohnuki et Nobuhiko Kamiya. « Aero-Structural Integrated Design of Forward Swept Wing ». Dans International Pacific Air & Space Technolgy Conference. 400 Commonwealth Drive, Warrendale, PA, United States : SAE International, 1991. http://dx.doi.org/10.4271/912021.

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Mainini, Laura, Massimiliano Mattone, Marco Di Sciuva et Paolo Maggiore. « Multidisciplinary Integrated design Environment for Aircraft Wing Sizing ». Dans 13th AIAA/ISSMO Multidisciplinary Analysis Optimization Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-9190.

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Borer, Nicholas K., et Mark D. Moore. « Integrated Propeller-Wing Design Exploration for Distributed Propulsion Concepts ». Dans 53rd AIAA Aerospace Sciences Meeting. Reston, Virginia : American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-1672.

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Holness, Alex, Ella Steins, Hugh Bruck, Martin Peckerar et S. K. Gupta. « Performance Characterization of Multifunctional Wings With Integrated Flexible Batteries for Flapping Wing Unmanned Air Vehicles ». Dans ASME 2016 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/detc2016-60379.

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In this work, we investigate the integration of ultrathin galvanic cell batteries with high energy density and flexibility into the highly deformable wings of the flapping wing air vehicle (FWAV) known as “Robo Raven” that we previously developed for independent wing control. The goal of this research was to create a multifunctional wing structure that provides higher energy density than the existing, singular function, lithium polymer batteries currently being used to power the platform. The key areas of inquiry explored are the effect the integration of batteries has on the aerodynamic forces generated during flapping under simulated flight conditions, and whether there is an adverse effect on flight performance where the platform payload capacity is diminished for similar flight time. Upon investigation, we determine that the electrical performance of the battery is as expected after integration into the wing structure, while force generation is not significantly affected, which enhances flight time enhancement and/or payload capacity.
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Cole, Julia A., Travis D. Krebs, Devin F. Barcelos, Alton Yeung et Goetz Bramesfeld. « On the Integrated Aerodynamic Design of a Propeller-Wing System ». Dans AIAA Scitech 2019 Forum. Reston, Virginia : American Institute of Aeronautics and Astronautics, 2019. http://dx.doi.org/10.2514/6.2019-2300.

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