Relevant bibliographies by topics / BWB

Academic literature on the topic 'BWB'

Author: Grafiati

Published: 4 June 2021

Last updated: 14 February 2022

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Journal articles on the topic "BWB"

van Dommelen, Jorrit, and Roelof Vos. "Conceptual design and analysis of blended-wing-body aircraft." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 228, no. 13 (January 29, 2014): 2452–74. http://dx.doi.org/10.1177/0954410013518696.

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Due to the unconventional nature of the blended wing body (BWB) no off-the-shelf software package exists for its conceptual design. This study details a first step towards the implementation of traditional and BWB-specific design and analysis methods into a software tool to enable preliminary sizing of a BWB. The tool is able to generate and analyze different BWB configurations on a conceptual level. This paper investigates three different BWB configurations. The first configuration is an aft-swept BWB with aft-mounted engines, the second configuration is an aft-swept BWB with wing-mounted engines and the third configuration is a forward-swept BWB with wing-mounted engines. These aircraft comply with the same set of top-level requirements and airworthiness requirements. Each of the designs has been optimized for maximum harmonic range, while keeping its maximum take-off weight constant and identical. Results show that the forward-swept configuration with wing-mounted engines has the highest harmonic range. These findings warrant further investigation in this configuration and other alternative BWB configurations.

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Li, Jinglu, Peng Wang, Xu Chen, and Huachao Dong. "Shape Optimization of Blended-Wing-Body Underwater Gliders Based on Free-Form Deformation." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 38, no. 3 (June 2020): 459–64. http://dx.doi.org/10.1051/jnwpu/20203830459.

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Currently developed underwater gliders can be roughly divided into the two types:traditional configuration and unconventional configuration. As a type of underwater gliders with unconventional configuration, a blended-wing-body (BWB) underwater glider has better fluid dynamic performances because of its unique shape. However, it is difficult to design the shape of the BWB underwater glider that has excellent hydrodynamic performances. Therefore, it is of great significance to optimize its shape, which this paper carries out by using the free-form deformation (FFD). The complete and automatic shape optimization framework is established by jointly using FFD parameterization method, CFD solver, optimization algorithm and mesh deformation method. The framework is used to optimize the shape of a BWB underwater glider. The average drag coefficient of the BWB underwater glider during its sinking and floating in one working period is used as the objective function to optimize its shape, with the volume constraints considered. The optimization results show that the gliding performance of the BWB underwater glider is remarkably enhanced.

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Zhang, Yong Jie, and Bin Tuan Wang. "Non-Cylindrical Fuselage Structural Optimization of BWB Civil Aircraft." Key Engineering Materials 474-476 (April 2011): 1736–39. http://dx.doi.org/10.4028/www.scientific.net/kem.474-476.1736.

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Blended-Wing-Body (BWB) civil aircraft possesses so light structure, high lift-drag ratio and low fuel burn that it has been an important topic of future civil aircraft. But internal pressure causes large bending stress instead of skin-membrane stress in BWB non-cylindrical fuselage. For 150 seats BWB fuselage, a composite 3-bay fuselage model is analyzed and two improved configurations of braced fuselage derivatives are designed in this paper. By optimization analysis, the optimized non-cylindrical fuselage structures are obtained in low bending stress and deformation condition, and optimized layer thicknesses ratio of composite material are presented. The optimization conclusions are very valuable and applicable for the fuselage structural design of BWB civil aircraft.

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Ignatov, S. D., and S. I. Tsekhosh. "ELASTIC CHARACTERISTICS OF BRUSH PILE ON THE MUNICIPAL MACHINE WORKING EQUIPMENT." Russian Automobile and Highway Industry Journal 16, no. 1 (March 1, 2019): 6–17. http://dx.doi.org/10.26518/2071-7296-2019-1-6-17.

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Introduction. The paper describes the actual problem of increasing the operating life of the brush working body (BWB) and improving the cleaning quality. Moreover, the authors discuss the factors affecting the quality of the road surface cleaning and the brush pile resource.Materials and methods. The research presents the results of the interaction process of the BWB pile with the cleaned surface of the roadway. In addition, the authors demonstrate the mathematical model of the interaction process with the basic surface. The simulation is carried out using the MATLAB software and Simulink extension. The authors also identify the factors that contribute the efficiency reduction of the municipal machine working process.Results. As a result of the simulation, the authors obtained the graphs of the pile deformation changing and the BWB pressing force changing. When processing the experimental data the researches also obtained the graphs of the brush pile plotted deformation from the BWB contact force and from 2, 3, 4 disks. For further mathematical modeling the authors determined the stiffness of the BWB pile under various loads. Therefore, the paper presents the approximation of the experimental dependence of the brush pile deformation on the pressing force and shows the regression equation.Conclusion. In conclusion, the authors determined the elastic characteristics of the BWB pile. By the comparing process of the experimental and theoretical data obtained from the mathematical model analysis, the authors found that the difference between them was less than 10%. The obtained results allowed confirming the mathematical model adequacy of the interaction process between the BWB pile and the cleaning surface.

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Panagiotou, Pericles, Thomas Dimopoulos, Stylianos Dimitriou, and Kyros Yakinthos. "Quasi-3D Aerodynamic Analysis Method for Blended-Wing-Body UAV Configurations." Aerospace 8, no. 1 (January 6, 2021): 13. http://dx.doi.org/10.3390/aerospace8010013.

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The current study presents a low-fidelity, quasi-3D aerodynamic analysis method for Blended-Wing-Body (BWB) Unmanned Aerial Vehicle (UAV) configurations. A tactical BWB UAV experimental prototype is used as a reference platform. The method utilizes 2D panel method analyses and theoretical aerodynamic calculations to rapidly compute lift and pitching moment coefficients. The philosophy and the underlying theoretical and semi-empirical equations of the proposed method are extensively described. Corrections related to control surfaces deflection and ground effect are also suggested, so that the BWB pitching stability and trimming calculations can be supported. The method is validated against low-fidelity 3D aerodynamic analysis methods and high-fidelity, Computational Fluid Dynamics (CFD) results for various BWB configurations. The validation procedures show that the proposed method is considerably more accurate than existing low-fidelity ones, can provide predictions for both lift and pitching moment coefficients and requires far less computational resources and time when compared to CFD modeling. Hence, it can serve as a valuable aerodynamics and stability analysis tool for BWB UAV configurations.

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WU, WENHUA, DEHUA CHEN, NING QIN, XIN PENG, and XINWU TANG. "A NEW EFFICIENT CONTROL METHOD FOR BLENDED WING BODY." International Journal of Modern Physics: Conference Series 19 (January 2012): 396–405. http://dx.doi.org/10.1142/s2010194512008999.

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The blended wing body (BWB) is the hottest one of the aerodynamic shapes of next generation airliner because of its' high lift-drag ratio, but there are still some flaws that cut down its aerodynamical performance. One of the most harmful flaws is the low efficiency of elevator and direction rudder, this makes the BWB hard to be controlled. In this paper, we proposed a new control method to solve this problem by morphing wing—that is, to control the BWB only by changing its wing shape but without any rudder. The pitching moments, rolling moments and yawing moments are plotted versus the parameters section and the wing shape in figures and are discussed in the paper. The result shows that the morphing wing can control the moments of BWB more precisely and in wider range. The pitching moments, rolling moments and yawing moments increases or decreases linearly or almost linearly, with the value of the selected parameters. These results show that using morphing wing is an excellent aerodynamic control way for a BWB craft.

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Dimopoulos, Thomas, Pericles Panagiotou, and Kyros Yakinthos. "Stability study and flight simulation of a blended-wing-body UAV." MATEC Web of Conferences 304 (2019): 02013. http://dx.doi.org/10.1051/matecconf/201930402013.

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This article is a product of the design process of a Blended-Wing- Body Unmanned Aerial Vehicle (BWB UAV). The BWB geometry blends the wing and the fuselage so that the fuselage also contributes in lift generation. This geometry reduces the lift to drag ratio significantly, however it also compromises the aircraft’s stability and controllability, since there is no horizontal and vertical tail. As these features are absent from the BWB layout, the need to incorporate their functions in the new geometry arises so that they cover stability demands sufficiently, according to aircraft of similar size, use and speed. Additionally, the method used for stability studies of conventional aircraft must also be adapted. This article covers the adaptation of the method to the new BWB geometry, its results in comparison to those of conventional aircraft and the use of the results for a computational simulation of the aircraft’ flight.

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Galea, E. R., L. Filippidis, Z. Wang, and J. Ewer. "Fire and evacuation analysis in BWB aircraft configurations: computer simulations and large-scale evacuation experiment." Aeronautical Journal 114, no. 1154 (April 2010): 271–77. http://dx.doi.org/10.1017/s0001924000003717.

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Abstract How long would it take to evacuate a blended wing body (BWB) aircraft with around 1,000 passengers and crew? How long would it take an external post-crash fire to develop non-survivable conditions within the cabin of a BWB aircraft? Is it possible for all the passengers to safely evacuate from a BWB cabin subjected to a post-crash fire? These questions are explored in this paper through computer simulation. As part of project NACRE, the airEXODUS evacuation model was used to explore evacuation issues associated with BWB aircraft and to investigate fire issues, the CFD fire simulation software SMARTFIRE was used. The fire and evacuation simulations were then coupled to investigate how the evacuation would proceed under the conditions produced by a post-crash fire. In conjunction with this work, a large-scale evacuation experiment was conducted in February 2008 to verify evacuation model predictions. This paper presents some of the results produced from this analysis.

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Ma, Yunlong, Guang Pan, Qiaogao Huang, and Jinglu Li. "Research on Hydrodynamic Characteristics of Blended Wing Body Underwater Glider with Rudder." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 38, no. 1 (February 2020): 24–30. http://dx.doi.org/10.1051/jnwpu/20203810024.

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In order to improve the maneuverability and stability of the Blended Wing Body (BWB) underwater glider, the trailing edge rudder is integrated into its shape design in this paper. Through the numerical simulation of CFD, the variation laws of the hydraulic parameters such as lift, drag, lift-to-drag ratio with the angle of attack and rudder angle are given. Compared with the traditional underwater glider, the BWB underwater glider not only has high loading capacity, but also has a maximum lift-to-drag ratio three times that of the former, resulting in higher energy efficiency. At the same time, by adding trailing edge rudders, the maneuverability of the BWB underwater glider is improved, and the lift-to-drag ratio under the same large rudder angle is increased by more than 30% compared with the variable-wing underwater glider. Finally, through the analysis of the numerical results and the cloud image, the difference interaction extent between the rudder and the body of the BWB underwater glider and the traditional torpedo or AUV is illustrated.

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Marcone, C., K. S. Gibb, C. Streten, and B. Schneider. "‘Candidatus Phytoplasma spartii’, ‘Candidatus Phytoplasma rhamni’ and ‘Candidatus Phytoplasma allocasuarinae’, respectively associated with spartium witches'-broom, buckthorn witches'-broom and allocasuarina yellows diseases." International Journal of Systematic and Evolutionary Microbiology 54, no. 4 (July 1, 2004): 1025–29. http://dx.doi.org/10.1099/ijs.0.02838-0.

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Spartium witches'-broom (SpaWB), buckthorn witches'-broom (BWB) and allocasuarina yellows (AlloY) are witches'-broom and yellows diseases of Spartium junceum (Spanish broom), Rhamnus catharticus (buckthorn) and Allocasuarina muelleriana (Slaty she-oak), respectively. These diseases are associated with distinct phytoplasmas. The SpaWB, BWB and AlloY phytoplasmas share <97·5 % 16S rDNA sequence similarity with each other and with other known phytoplasmas, including the closely related phytoplasmas of the apple proliferation group. Also, the SpaWB, BWB and AlloY phytoplasmas each have a different natural plant host. Based on their unique properties, it is proposed to designate the mentioned phytoplasmas as novel ‘Candidatus’ species under the names ‘Candidatus Phytoplasma spartii’, ‘Candidatus Phytoplasma rhamni’ and ‘Candidatus Phytoplasma allocasuarinae’, respectively.

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Dissertations / Theses on the topic "BWB"

Le, Moigne Alan. "A discrete Navier-Stokes adjoint method for aerodynamic optimisation of BlendedWing-Body configurations." Thesis, Cranfield University, 2002. http://hdl.handle.net/1826/826.

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An aerodynamic shape optimisation capability based on a discrete adjoint solver for Navier- Stokes flows is developed and applied to a Blended Wing-Body future transport aircraft. The optimisation is gradient-based and employs either directly a Sequential Quadratic Programming optimiser or a variable-fidelity optimisation method that combines low- and high-fidelity models. The shape deformations are parameterised using a B´ezier-Bernstein formulation and the structured grid is automatically deformed to represent the design changes. The flow solver at the heart of this optimisation chain is a Reynolds averaged Navier- Stokes code for multiblock structured grids. It uses Osher’s approximate Riemann solver for accurate shock and boundary layer capturing, an implicit temporal discretisation and the algebraic turbulence model of Baldwin-Lomax. The discrete Navier-Stokes adjoint solver based on this CFD code shares the same implicit formulation but has to calculate accurately the flow Jacobian. This implies a linearisation of the Baldwin-Lomax model. The accuracy of the resulting adjoint solver is verified through comparison with finitedifference. The aerodynamic shape optimisation chain is applied to an aerofoil drag minimisation problem. This serves as a test case to try and reduce computing time by simplifying the fidelity of the model. The simplifications investigated include changing the convergence level of the adjoint solver, reducing the grid size and modifying the physical model of the adjoint solver independently or in the entire optimisation process. A feasible optimiser and the use of a penalty function are also tested. The variable-fidelity method proves to be the most ef- ficient formulation so it is employed for the three-dimensional optimisations in addition to parallelisation of the flow and adjoint solvers with OpenMP. A three-dimensional Navier- Stokes optimisation of the ONERA M6 wing is presented. After describing the concept of Blended Wing-Body and the studies carried out on this aircraft, several aerodynamic optimisations are performed on this geometry with the capability developed in this thesis.

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Le, Moigne Alan. "A discrete Navier-Stokes adjoint method for aerodynamic optimisation of Blended Wing-Body configurations." Thesis, Cranfield University, 2002. http://dspace.lib.cranfield.ac.uk/handle/1826/826.

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An aerodynamic shape optimisation capability based on a discrete adjoint solver for Navier-Stokes flows is developed and applied to a Blended Wing-Body future transport aircraft. The optimisation is gradient-based and employs either directly a Sequential Quadratic Programming optimiser or a variable-fidelity optimisation method that combines low- and high-fidelity models. The shape deformations are parameterised using a B´ezier-Bernstein formulation and the structured grid is automatically deformed to represent the design changes. The flow solver at the heart of this optimisation chain is a Reynolds averaged Navier- Stokes code for multiblock structured grids. It uses Osher’s approximate Riemann solver for accurate shock and boundary layer capturing, an implicit temporal discretisation and the algebraic turbulence model of Baldwin-Lomax. The discrete Navier-Stokes adjoint solver based on this CFD code shares the same implicit formulation but has to calculate accurately the flow Jacobian. This implies a linearisation of the Baldwin-Lomax model. The accuracy of the resulting adjoint solver is verified through comparison with finitedifference. The aerodynamic shape optimisation chain is applied to an aerofoil drag minimisation problem. This serves as a test case to try and reduce computing time by simplifying the fidelity of the model. The simplifications investigated include changing the convergence level of the adjoint solver, reducing the grid size and modifying the physical model of the adjoint solver independently or in the entire optimisation process. A feasible optimiser and the use of a penalty function are also tested. The variable-fidelity method proves to be the most efficient formulation so it is employed for the three-dimensional optimisations in addition to parallelisation of the flow and adjoint solvers with OpenMP. A three-dimensional Navier-Stokes optimisation of the ONERA M6 wing is presented. After describing the concept of Blended Wing-Body and the studies carried out on this aircraft, several aerodynamic optimisations are performed on this geometry with the capability developed in this thesis.

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Sodzi, P. "Damage tolerant wing-fuselage integration structural design applicable to future BWB transport aircraft." Thesis, Cranfield University, 2009. http://dspace.lib.cranfield.ac.uk/handle/1826/6863.

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Wing joint design is one of the most critical areas in aircraft structures. Efficient and damage tolerant wing-fuselage integration structure, applicable to the next generation of transport aircraft, will facilitate the realisation of the benefits offered by new aircraft concepts. The Blended Wing Body (BWB) aircraft concept represents a potential revolution in subsonic transport efficiency for large airplanes. Studies have shown the BWB to be superior to conventional airframes in all key measures. Apart from the aerodynamic advantages, the BWB aircraft also provides a platform for wing-fuselage design changes. The main objective of this research is to design a damage tolerant wing-fuselage joint with a novel bird’s mouth termination for a BWB aircraft that has a similar payload range to the B767 aircraft. The damage tolerance analysis of the proposed BWB wing/fuselage integration structure includes assessments of fatigue crack growth life, residual strength and inspection capability. The proposed structure includes a bird’s mouth termination of the spars that facilitates smooth transfer of loading from the spar web into the root rib and the upper and lower skins and is novel in its application to the blended wing body configuration. A finite element analysis was required to determine local stresses for the prediction of fatigue crack growth life, residual strength and inspection capability and to identify weak spots in the proposed structure. The project aircraft wing comprises of three spars (front, centre and rear) and a false rear spar thus defining a four cell wing box. Wing root shear, bending moment and torque loads were derived and applied to a thin-walled three box idealisation of the proposed structure. The challenges experienced in replicating the loads obtained from the three box idealisation were addressed by modification of the boundary conditions. Checks for compression and shear buckling were also undertaken that confirmed that the applied loads were below the limits of the proposed structure. The finite element analysis showed very clearly that the stresses in the novel bird’s mouth spar termination were significantly lower than in the skin and that the skin remained the more critical damage tolerant component at the wing root when the structure was subjected to ultimate design stresses. The spar web at the bird’s mouth termination was shown to have a larger crack growth life compared to the skin. The thickness of the skin requires further investigation as a significant amount of local bending was experienced due to the applied pressure. The skin will sustain a two-bay crack at the design limit load thus proving the proposed wing fuselage integration structure to be damage tolerant. In conclusion, the main objective of the thesis has been achieved. An integrated wingfuselage joint with novel bird’s mouth spar termination and surrounding structure have been designed and substantiated (evaluated) by damage tolerance requirements.

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Ikeda, Toshihiro, and toshi ikeda@gmail com. "Aerodynamic Analysis of a Blended-Wing-Body Aircraft Configuration." RMIT University. Aerospace, Mechanical and Manufacturing Engineering, 2006. http://adt.lib.rmit.edu.au/adt/public/adt-VIT20070122.163030.

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In recent years unconventional aircraft configurations, such as Blended-Wing-Body (BWB) aircraft, are being investigated and researched with the aim to develop more efficient aircraft configurations, in particular for very large transport aircraft that are more efficient and environmentally-friendly. The BWB configuration designates an alternative aircraft configuration where the wing and fuselage are integrated which results essentially in a hybrid flying wing shape. The first example of a BWB design was researched at the Loughead Company in the United States of America in 1917. The Junkers G. 38, the largest land plane in the world at the time, was produced in 1929 for Luft Hansa (present day; Lufthansa). Since 1939 Northrop Aircraft Inc. (USA), currently Northrop Grumman Corporation and the Horten brothers (Germany) investigated and developed BWB aircraft for military purposes. At present, the major aircraft industries and several universities has been researching the BWB concept aircraft for civil and military activities, although the BWB design concept has not been adapted for civil transport yet. The B-2 Spirit, (produced by the Northrop Corporation) has been used in military service since the late 1980s. The BWB design seems to show greater potential for very large passenger transport aircraft. A NASA BWB research team found an 800 passenger BWB concept consumed 27 percent less fuel per passenger per flight operation than an equivalent conventional configuration (Leiebeck 2005). The purpose of this research is to assess the aerodynamic efficiency of a BWB aircraft with respect to a conventional configuration, and to identify design issues that determine the effectiveness of BWB performance as a function of aircraft payload capacity. The approach was undertaken to develop a new conceptual design of a BWB aircraft using Computational Aided Design (CAD) tools and Computational Fluid Dynamics (CFD) software. An existing high-capacity aircraft, the Airbus A380 Contents RMIT University, Australia was modelled, and its aerodynamic characteristics assessed using CFD to enable comparison with the BWB design. The BWB design had to be compatible with airports that took conventional aircraft, meaning a wingspan of not more than 80 meters for what the International Civil Aviation Organisation (ICAO) regulation calls class 7 airports (Amano 2001). From the literature review, five contentions were addressed; i. Is a BWB aircraft design more aerodynamically efficient than a conventional aircraft configuration? ii. How does the BWB compare overall with a conventional design configuration? iii. What is the trade-off between conventional designs and a BWB arrangement? iv. What mission requirements, such as payload and endurance, will a BWB design concept become attractive for? v. What are the practical issues associated with the BWB design that need to be addressed? In an aircraft multidisciplinary design environment, there are two major branches of engineering science; CFD analysis and structural analysis; which is required to commence producing an aircraft. In this research, conceptual BWB designs and CFD simulations were iterated to evaluate the aerodynamic performance of an optimal BWB design, and a theoretical calculation of structural analysis was done based on the CFD results. The following hypothesis was prompted; A BWB configuration has superior in flight performance due to a higher Lift-to-Drag (L/D) ratio, and could improve upon existing conventional aircraft, in the areas of noise emission, fuel consumption and Direct Operation Cost (DOC) on service. However, a BWB configuration needs to employ a new structural system for passenger safety procedures, such as passenger ingress/egress. The research confirmed that the BWB configuration achieves higher aerodynamic performance with an achievement of the current airport compatibility issue. The beneficial results of the BWB design were that the parasite drag was decreased and the spanwise body as a whole can generate lift. In a BWB design environment, several advanced computational techniques were required to compute a CFD simulation with the CAD model using pre-processing and CFD software.

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Pettersson, Emil. "Design of a drone system for maritime search and rescue missions." Thesis, KTH, Flygdynamik, 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-290180.

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The work summarized in this report aims to investigate how a drone airplane design can be optimized to create a safer and more efficient sea rescue by providing staff with an early picture, performing search missions and aiding communication through visual contact. A flying wing is in theory one of the most efficient designs for a fixed wing aircraft, at the same time as it also offers high structural efficiency for its given size. In this report, an overview of aerodynamics, stability and flying quality for a flying wing is discussed and analysed. XFLR5 was used for this project, and a comparison between the analytical results and wind tunnel test data for a prototype was conducted. A strong correlation was found between the theoretical analyses and the wind tunnel data. A simple control solution using only one set of elevons has been proposed and simulated, resulting in Level 1 dynamic stability for all modes except Dutch-roll (where the drone’s damping is 𝜁𝑑𝑟=0.07 and the requirement for Level 1 is 𝜁𝑑𝑟=0.08). For the range of angle of attack used, the autopilot system will have to trim the drone in flight to achieve stability. As the drone only has one set of control surfaces there will be a loss of efficiency in this scenario, meaning that 𝐶𝐿/𝐶𝐷 = 15.7 for loiter speed of 15 𝑚/𝑠 and 7.9 for full speed at 35 𝑚/𝑠. In regular flight, with a total mass <1 𝑘𝑔, the drone is able to fly at full speed for 214 𝑘𝑚 or loiter for 6.3 ℎ with a battery package of 130 𝑊ℎ. As such, the objective of this project was achieved, and the proposed design met the given requirements.
betet som sammanfattas i denna rapport syftar till att undersöka huruvida ett drönar-flygplan bäst kan utformas för att skapa en säkrare och effektivare sjöräddning genom att ge räddningspersonalen en tidig överblick, utföra sökuppdrag och bistå till kommunikation genom visuell kontakt. En flygande vinge är i teorin en av de mest effektiva konstruktionerna för ett flygplan, likaså erbjuder den en hög strukturell effektivitet för en given storlek. I denna rapport diskuteras och genomförs en översikt över aerodynamik, stabilitet och flygkvalitet hos en flygande vinge. XFLR5 användes för detta projekt, och en jämförelse mellan analysresultaten och ett vindtunneltest med en prototyp genomfördes. I allmänhet är överenskommelsen mellan de teoretiska analyserna och vindtunneldatan god. En enkel lösning som enbart består av en uppsättning kontrollytor har föreslagits och simulerats, vilket resulterar i en Nivå 1 dynamisk stabilitet för alla lägen utom Dutch-roll, där drönarens dämpning är 𝜁𝑑𝑟 = 0.07 och kravet för Nivå 1 är 𝜁𝑑𝑟 = 0.08. Autopilotsystemet behöver trimma drönaren under flygning för att uppnå nödvändig stabilitet för det spann av attackvinklar som används, med endast en uppsättning kontrollytor, vilket minskar effektiviteten för BWB-drönaren till 𝐶𝐿/𝐶𝐷=15.7 för cirkuleringshastigheten på 15 𝑚/𝑠 och 7.9 för full hastighet vid 35 𝑚/𝑠. Drönaren kan flyga i full hastighet i 214 𝑘𝑚 eller cirkulera runt olycksplatsen under 6.3 timmar med ett batteripaket på 130 𝑊ℎ, med en vikt som är lägre än 1 𝑘𝑔. Målen med detta projekt uppnåddes och drönaren utformades enligt kraven.

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Zhang, Hao. "Neuroimmune communication BBB dependent and BBB independent pathways /." Columbus, Ohio : Ohio State University, 2007. http://rave.ohiolink.edu/etdc/view?acc%5Fnum=osu1193686898.

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Dillman, Raymond E. "Fat Bob." Auburn, Ala., 2007. http://repo.lib.auburn.edu/2007%20Spring%20Theses/DILLMAN_RAYMOND_5.pdf.

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Douša, Jan. "Bob Krčil." Master's thesis, Akademie múzických umění v Praze.Filmová a televizní fakulta. Knihovna, 2016. http://www.nusl.cz/ntk/nusl-261609.

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The life and work of Bob Krčil have so far been known from fragments and unsubstantiated legends. The aim of this essayistic piece is to lay out the deeper motives of his personal trajectory, photographic oeuvre, and activities for the Czech exile community. Krčil’s photographic body of work is inseparably connected with his eventful life. The writing of the thesis was preceded by tracking down and putting together Krčil’s fragmented estate, sorting out his correspondence and writings, and interviewing people who knew him personally. By drawing on these materials, the thesis aims to provide insight into the life and motivations of this important figure of Czech exile culture.

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Cechetti, Junior Dorremi. "Comércio eletrônico B2B." Florianópolis, SC, 2003. http://repositorio.ufsc.br/xmlui/handle/123456789/85216.

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Dissertação (mestrado) - Universidade Federal de Santa Catarina, Centro Tecnológico. Programa de Pós-Graduação em Ciência da Computação.
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Fonte de diversos estudos em diferentes áreas do conhecimento, o Comércio Eletrônico (CE) vem tendo um papel de crescimento de utilização entre pessoas e organizações a cada ano. A evolução das TIC's (Tecnologias de Informação e Comunicações) possibilitam a disseminação do CE por grandes, médias e pequenas organizações. O Business-to-Business (B2B) é uma categoria de CE que possui aspectos comuns com as outras categorias, mas também aspectos próprios, como a interoperabilidade entre o site WEB e sistemas de back-end organizacionais. Neste trabalho estuda-se aspectos como privacidade e segurança, sistemas eletrônicos de pagamentos e o relacionamento entre clientes e fornecedores abordando aspectos do CE B2B. A interoperabilidade nos sistemas de CE B2B é um aspecto bastante considerado basicamente por: reduzir as chances de erros operacionais e possibilitar a obtenção de informação em tempo real. Inicialmente constituída pela tecnologia EDI, a interoperabilidade evolui para soluções como a tecnologia XML, adotada por grande parte dos frameworks disponíveis no mercado atual. Este trabalho estuda os principais frameworks disponíveis no mercado que propõem a interoperabilidade em sistemas de CE B2B, bem como apresenta uma estrutura utilizando a tendência tecnológica XML para demonstrar a integração de sites WEB B2B com sistemas de back-end organizacionais. O presente trabalho demonstra que a tecnologia atual torna possível o desenvolvimento de interoperabilidade entre sites WEB B2B e entidades empresariais utilizando o modelo de agregação, onde uma entidade (site WEB B2B) agrega valor para produtores, fornecedores, clientes e consumidores criando uma identificação e realizando serviços que agregam valor aos demais participantes.

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Lundahl, Robert. "Fördelar och nackdelar med B2B : en studie om hur företag upplever B2B." Thesis, University of Skövde, Department of Computer Science, 2002. http://urn.kb.se/resolve?urn=urn:nbn:se:his:diva-669.

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I detta arbete undersöks företag med utgångspunkt från hur de upplever B2B och då främst vilka för respektive nackdelar som upplevs. Denna undersökning är gjord genom intervjuer med personer som har erfarenhet utav B2B från olika företag runt om i Västsverige.

Rapporten inleds med en inledande introduktion och bakgrund till ämnet. En presentation av e-handel följs av en presentation utav B2B, därefter beskrivs Internetterminologi följt av en genomgång utav dagens informationssystemsutveckling.

Som grund för arbetet ligger en fallstudie gjord av Stefansson (2002), arbetet är en fortsättning utav hans arbete som var att kartlägga användandet utav EDI. Resultatet utav de intervjuer som genomförts har jämförts först internt med varandra men också med de konstateranden som Stefansson (2002) gjort.

Resultatet visar att företagen som deltagit undersökningen anser att deras satsning mot B2B har bidragit med mest positiva effekter, då framförallt att den har bidragit till mindre administrativt arbete, snabbare transaktioner och en bättre överblick av verksamheten.

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Books on the topic "BWB"

Li, Fang Zheng. BWB Shao er bai ke quan shu - zhi wu. [Place of publication not identified]: [publisher not identified], 2003.

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Dah, Thramu Lhe. Kī tī ʼū bha tī bhhai mi pha bhyā thaṃ kha raṃ phi ta ʼi phhi sa kiʺ ta ʼi phhi ʼa thū ʼa thaṃʺ dīʺ ta phaṃʺ ta ma, naṃ (150) laṃ caṃ ci nu 1856-2006 =: The chronicles of Tounggu-Thandaung Bwe Moe Bwa Baptist Association, 1856-2006. Tounggu?: s.n., 2006.

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Bonn, Moritz J. Bundeswahlgesetz (BWG) und Bundeswahlordnung (BWO): Vollständige Textausgabe mit Terminkalender und Stichwortverzeichnis. 4th ed. Kronach: C. Link, 1986.

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Braun, Karl. BGB — Familienrecht, BGB — Erbrecht. Wiesbaden: Gabler Verlag, 1988. http://dx.doi.org/10.1007/978-3-663-13727-6.

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Richard, Lewis. Bob. New York: Simon & Schuster Books for Young Readers, 2009.

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Bob. New York: Farrar, Straus, Giroux, 2002.

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ill, Gannon Nicholas, and Stead Rebecca author, eds. Bob. New York: Feiwel & Friends, 2018.

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Köhler, Helmut. BGB. München: C.H. Beck, 1995.

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Bonn, Moritz J. BGB. Köln: Komet, 2003.

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Supomo. Bab-bab tentang hukum adat. Jakarta: Pradnya Paramita, 2000.

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Book chapters on the topic "BWB"

Beveridge, Ross. "Assessing the BWB partial privatisation." In A Politics of Inevitability, 189–201. Wiesbaden: VS Verlag für Sozialwissenschaften, 2012. http://dx.doi.org/10.1007/978-3-531-94056-4_7.

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Zhang, Ning, Feng Li, and Lixin Wang. "Control Allocation Approach Study for BWB Aircraft." In Lecture Notes in Electrical Engineering, 2099–115. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-3305-7_168.

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Noori, Mohammad, Hamid Davoodi, and Thomas T. Baber. "A Comprehensive Stationary Non-Gaussian Analysis of BWB Hysteresis." In Nonlinear Stochastic Mechanics, 415–25. Berlin, Heidelberg: Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-642-84789-9_36.

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Beveridge, Ross. "The global city policy discourse and water policy-making: making the privatisation of BWB ‘inevitable’." In A Politics of Inevitability, 107–45. Wiesbaden: VS Verlag für Sozialwissenschaften, 2012. http://dx.doi.org/10.1007/978-3-531-94056-4_5.

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Beveridge, Ross. "From ready-made accounts to a politics in the making account of the privatisation of BWB." In A Politics of Inevitability, 147–88. Wiesbaden: VS Verlag für Sozialwissenschaften, 2012. http://dx.doi.org/10.1007/978-3-531-94056-4_6.

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Arnaiz-Villena, A., M. Belvedere, F. Decary, M. Fotino, E. Heise, V. Hogan, M. Martinetti, et al. "Antigen Society #15 Report (Bw4 and Bw6)." In Immunobiology of HLA, 214–17. New York, NY: Springer New York, 1989. http://dx.doi.org/10.1007/978-1-4612-3552-1_37.

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Leung, Alexander K. C., Marcus Schmitt, Christie P. Thomas, Cord Sunderkötter, Meinhard Schiller, Thomas Schwarz, Mark Berneburg, et al. "BWS." In Encyclopedia of Molecular Mechanisms of Disease, 262. Berlin, Heidelberg: Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-540-29676-8_5005.

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Augustsson, Lennart. "BWM." In Functional Programming, Glasgow 1991, 36–50. London: Springer London, 1992. http://dx.doi.org/10.1007/978-1-4471-3196-0_3.

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Moynihan, Tony. "Bob." In Practitioner Series, 69–72. London: Springer London, 2002. http://dx.doi.org/10.1007/978-1-4471-0155-0_8.

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"BAYERISCHES WÖRTERBUCH (BWB)." In Dorn – Trätzer(er), 1–98. De Gruyter Akademie Forschung, 2020. http://dx.doi.org/10.1515/9783110705973-004.

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Conference papers on the topic "BWB"

Cho, Sung Hwan, and Cees Bil. "Columned Multi Bubble Fuselage (CMBF) for BWB." In Aerospace Technology Conference and Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2007. http://dx.doi.org/10.4271/2007-01-3889.

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Anand, A. Kaushik, Ganesh Nair, and S. R. Nagaraja. "Design and development of a BWB aircraft." In 1ST INTERNATIONAL CONFERENCE ON MANUFACTURING, MATERIAL SCIENCE AND ENGINEERING (ICMMSE-2019). AIP Publishing, 2019. http://dx.doi.org/10.1063/1.5141245.

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Clarke, Matthew A., Narcrisha S. Norman, and Sonya T. Smith. "Hybrid-MCX-1, BWB and 777 Aircraft Comparison." In ASME 2015 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/imece2015-52526.

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Conceptual design is the first and most important phase of an aircraft’s configuration and system development process. That being said, there is no denying that innovation in aviation has stunted over the last 50 years; the once every present fascination of flying has been blanketed by the rapid profit-driven commercializing of an industry. Moreover, we have reached an apex of maximizing the efficiency of current passenger aircraft model configurations. In recent times, new research and development has culminated to the introduction of aerodynamic structures to address key issues such as stability and fuel efficiency. This research paper seeks to push the envelope of innovation with a brand new perspective on how we view air travel — redefining the Why, What and How. It explores novel concepts such as Boeing Blended Wing Body (BWB) aircraft shown in, which does not follow the conventional Tube and Wing (TAW) configuration. It is a tailless design that integrates the wing and the fuselage into a single-lifting surface. The most common advantages include a higher lift-to-drag ratio and higher payload capacity due to a distribute load along the centerline of the aircraft. On the other hand, a tailless configuration comes at a cost to in-flight maneuvering and stability. The unique design of the Hybrid-MCX-1 aircraft involves the application of the active aero-elastic tailoring to aircraft topology optimization for both subsonic and transonic regimes. With a focus on experimental wind tunnel testing and high-fidelity simulations, this project proposes a new concept that deviates from today’s tubular and wing concept. The aircraft has a unique shape with a forward fuselage that starts off with the conventional tubular and winged aircraft design currently flown in commercial travel, but deviates to a wider cross section at the center of the fuselage. The model has self-supporting, cantilever, dihedral, swept wings, with pronounced fillets at the junction of the wing root and fuselage, blending them smoothly. This smooth transition reduce interference between airflow over the wing root and the adjacent body surface, ultimately reducing drag. The engines of the Hybrid-MCX-1 are mounted by at 45-degree angle on the rear of the plane. This engine location offers the opportunity for swallowing the boundary layer of air from that portion of the center body upstream of the inlet, providing improved propulsive efficiency by reducing the ram drag. The Hybrid-MCX-1 also possesses a vertical tail that bisects the engines. As with current commercial aircraft, this tail provides lateral stability and controls the yaw. In the case of the BWB, yaw control is made possible by sweeping the wing and downloading the wingtips. However, this approach reduces the effective aerodynamic wingspan of the aircraft and imposes a significant induced drag penalty. The presence of a tail on the concept model addresses the aforementioned issue and rectifies unwanted yawing that may arise during cross wind flight conditions. The rear end of the aircraft decrease significantly in vertical thickness when compared to the lateral thickness to minimize the possibility of flow separation as air passes around the wings and over the front half of the aircraft while maximizing total lifting surface area. The pylons are adequately sized to avoid aerodynamic interference between fuselage, pylon and nacelle but still relatively short to minimize drag.

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Ruiz Jimenez, Gilberto, Joan Mas Colomer, and Joseph Morlier. "Multifidelity Aeroelastic Optimization with Application to a BWB." In AIAA AVIATION 2021 FORUM. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2021. http://dx.doi.org/10.2514/6.2021-3099.

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Ammar, Sami, and Jean-Yves Trépanier. "Conceptual Design of a 200 Passenger Blended Wing Body Aircraft." In ASME 2014 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/imece2014-36676.

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The Blended Wing Body (BWB) aircraft is based on the flying wing concept. For this aircraft the literature has reported performance improvements compared to conventional aircraft. However, most BWB studies have focused on large aircraft and it is not sure whether the gains are the same for smaller aircraft. The main objective of this work is to perform the conceptual design of a 200 passengers BWB and compare its performance against an equivalent conventional A320 aircraft in terms of payload and range. Moreover, an emphasis will be placed on obtaining a stable aircraft, with the analysis of static and dynamic stability. The design of BWB was carried out under the platform called Computerized Environment for Aircraft Synthesis and Integrated Optimization Methods (CEASIOM). This design platform, suitable for conventional aircraft design, has been modified and additional tools have been integrated in order to achieve the aerodynamic analysis, performance and stability of the BWB aircraft.

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Mirzoyan, Artur, Alik Isianov, Marco Fioriti, Luca Boggero, Francesca Tomasella, Pier D. Ciampa, and Prajwal S. Prakasha. "Propulsion System for BWB Configurations in the Agile project." In 2018 Joint Propulsion Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-4848.

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Kawai, Ronald. "Benefit Potential for a Cost Efficient Dual Fuel Propulsion BWB." In 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2013. http://dx.doi.org/10.2514/6.2013-937.

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Bil, Cees, S. Cho, and R. Adams. "Design and Analysis of BWB Military Cargo Centre Body Structure." In AIAA Centennial of Naval Aviation Forum "100 Years of Achievement and Progress". Reston, Virigina: American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-7026.

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Mukhopadhyay, Vivek. "Blended Wing Body (BWB) Fuselage Structural Design for Weight Reduction." In 46th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-2349.

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Vile, Liam, Halim Alwi, and Christopher Edwards. "Scheduled Fault Tolerant Integral Sliding Mode Control for BWB Aircraft." In 2020 European Control Conference (ECC). IEEE, 2020. http://dx.doi.org/10.23919/ecc51009.2020.9143978.

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Reports on the topic "BWB"

Revill, James, Alisha Anand, and Giacomo Persi Paoli. Exploring Science and Technology Review Mechanisms Under the Biological Weapons Convention. The United Nations Institute for Disarmament Research, June 2021. http://dx.doi.org/10.37559/sectec/2021/sandtreviews/01.

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Since the Biological Weapons Convention (BWC) opened for signature in 1972, biology and other converging disciplines have advanced considerably. These changes could have profound implications for a science-based disarmament agreement like the BWC. To address changes in biology and biotechnology, BWC States Parties have established processes to review developments in science and technology (S&T), including annual expert meetings on this topic. However, shortcomings are evident in the current approaches and many BWC States Parties have expressed support for a more systematic review of science and technology under the Convention. This study seeks to inform discussions on establishing a dedicated and systematic S&T review process under the BWC through an examination of existing S&T review-type mechanisms employed in different regimes beyond the BWC, a survey of States Parties views on a possible review mechanism and a study of past and present discourse on this issue in the BWC. Based on the analysis conducted, this study also presents options for BWC States Parties to consider ahead of the Ninth BWC Review Conference.

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A. Alsaed. BWR AXIAL PROFILE. Office of Scientific and Technical Information (OSTI), July 2005. http://dx.doi.org/10.2172/862029.

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J. Huffer. BWR AXIAL PROFILE. Office of Scientific and Technical Information (OSTI), September 2004. http://dx.doi.org/10.2172/862152.

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Tan, C. P., and G. Bagchi. BWR steel containment corrosion. Office of Scientific and Technical Information (OSTI), April 1996. http://dx.doi.org/10.2172/219387.

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Goldstein, L. B., A. M. Dechovskaia, S. Bullman, K. H. Jones, and A. A. Abdel-Rahman. Daily Dermal Co-Exposure of Rats to DEET and Permethrin Produces Sensorimotor Deficit, and Changes in Blood-Brain Barrier (BBB) and Blood-Testis Barrier (BTB). Fort Belvoir, VA: Defense Technical Information Center, March 2001. http://dx.doi.org/10.21236/ada402081.

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Yoon, Su Jong. High Fidelity BWR Fuel Simulations. Office of Scientific and Technical Information (OSTI), August 2016. http://dx.doi.org/10.2172/1364486.

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Ruscher, Paul. Short Range Model for BWS. Fort Belvoir, VA: Defense Technical Information Center, August 2002. http://dx.doi.org/10.21236/ada405630.

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Kamel, Magdi N. B2B Models for DoD Acquisition. Fort Belvoir, VA: Defense Technical Information Center, January 2008. http://dx.doi.org/10.21236/ada476790.

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Sutherland, W., M. Alamgir, J. Findlay, and W. Hwang. BWR Full Integral Simulation Test (FIST) Phase II test results and TRAC-BWR model qualification. Office of Scientific and Technical Information (OSTI), October 1985. http://dx.doi.org/10.2172/6349740.

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Cheng, L. Y., D. Diamond, and Gilad Raitses, Arnold Aronson Arantxa Cuadra. Trace Assessment for BWR ATWS Analysis. Office of Scientific and Technical Information (OSTI), April 2010. http://dx.doi.org/10.2172/1013471.

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