Relevant bibliographies by topics / Wing stress analysis

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Wing stress analysis'

Author: Grafiati
Published: 28 June 2021
Last updated: 17 February 2022

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Journal articles on the topic "Wing stress analysis"

1

Jemitola, P. O., J. Fielding, and P. Stocking. "Joint fixity effect on structural design of a box wing aircraft." Aeronautical Journal 116, no. 1178 (April 2012): 363–72. http://dx.doi.org/10.1017/s0001924000005261.

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Abstract A computational study was performed to compare the stress distributions in finite element torsion box models of a box wing structure that result from employing four different wing/end fin joint fixities. All considered wings were trimmed in pitch. The joint fixities refer to the type of attachment that connects the tip of the fore and aft wings to the end fin. Using loads from a vortex lattice tool, the analysis determined the best wing-joint fixity of a statically loaded idealised box wing configuration by comparing the stress distributions resulting from the different wing joints in addition to other essential aerodynamic requirements. Analysis of the wing joint fixity indicates that the rigid joint is the most suitable.
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Yu, Chun Jin, Jin Zhang, Wei Song, and Ke Hong Yi. "Deformation and Stress Analysis of Flapping Wing Aerial Vehicles Based on Composites Model." Advanced Materials Research 1006-1007 (August 2014): 7–10. http://dx.doi.org/10.4028/www.scientific.net/amr.1006-1007.7.

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Flapping wing aerial vehicles continue to be a growing field, with ongoing research into unsteady, low Reynolds number aerodynamics and micro fabrication. However research into deformation and stress of flapping wing continues to lag, especially based on composites model. One flapping cycle was divided into twelve segments, and maximum defmortion and stress were calculated in each segment. The results show that the maximum sdeformation at the beginning stages of downstroke is 19% larger than the maximum deformation at the beginning stages of upstroke, and the maximum stress at the beginning stages of downstroke is 29.9 larger than the maximum stress at the beginning stages of upstroke. This research is helpful to answer that why insect wings are so perfect through long evolution, thus improving the design of flapping-wing aerial vehicles.
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Jin, Guo Dong, Li Bin Lu, Liang Xian Gu, and Juan Liang. "Numerical Simulation Analysis on Repairing Hole of UAV Wing." Advanced Materials Research 690-693 (May 2013): 2891–95. http://dx.doi.org/10.4028/www.scientific.net/amr.690-693.2891.

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Parachute recovery of UAV is often caused of holes and other injuries on wings, that are required repair and maintenance. The surface of the patch will form the high stress area, that affects UAV using life and safety .But repair method is good or bad directly affects size of the high stress area. Based on finite element method, the broken hole repairing method was formulated and validated by ANSYS. The method could minimize the high stress area as far as possible, and economically repair broken hole of wing in certain precision and safety standards condition. It has a certain reference value for UAV repair and management, and has reference significance for extending the service life of the UAV. Key words: Finite element method; Unmanned Aerial Vehicle (UAV); Simulation; Hole of wings
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Kalavagunta, Veeranjaneyulu, and Shaik Hussain. "Wing Rib Stress Analysis of DLR-F6 aircraft." IOP Conference Series: Materials Science and Engineering 455 (December 19, 2018): 012033. http://dx.doi.org/10.1088/1757-899x/455/1/012033.

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Rabbey, M. Fazlay, Anik Mahmood Rumi, Farhan Hasan Nuri, Hafez M. Monerujjaman, and M. Mehedi Hassan. "Structural Deformation and Stress Analysis of Aircraft Wing by Finite Element Method." Advanced Materials Research 906 (April 2014): 318–22. http://dx.doi.org/10.4028/www.scientific.net/amr.906.318.

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Wing of an aircraft is lift producing component. It makes aircraft airborne by generating lift>weight. The wing must take the full aircraft weight during flying. So, it is very sophisticated task for designing a wing by keeping consideration of every design parameters simultaneously. This paper contains analysis of structural properties of wing by using finite element method. For well-organized design all the variables must be considered from the beginning of the design phase. The design phases for aircraft are: conceptual, preliminary and detail design. Until the preliminary design phase the aircraft structure is not considered. During these phases the material of the wing should be selected in such a way so that it can perform efficiently with less unexpected phenomena (drag) for which responsible properties are displacement, stress etc. Currently the most focusing area for the aero-elastic investigation is to design wing with good aerodynamic shape which will associated with less dragging structural behavior. It helps to reduce SFC (Specific Fuel Consumption) and so the cost. The analysis on that has done through Computational means as well as simulation technique to develop knowledge about the variation of aircraft wing structural properties.
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Esakkiraj, E. S., S. Anish, and V. Anish. "Static and Dynamic Analysis of Aluminium Composite in Wing Section Using ANSYS." Advanced Materials Research 984-985 (July 2014): 367–71. http://dx.doi.org/10.4028/www.scientific.net/amr.984-985.367.

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The cold of this cardboard is to abstraction and analyze the amount accustomed accommodation and weight accumulation of blended aircraft (Aluminium Silicon Carbide) addition with that of Aluminium wing and appropriately access the acceptable aircraft addition of minimum weight accomplished of address a accustomed changeless amount after failure. And also this paper presents a model and a static analysis of the aircraft wing, using the finite element software ANSYS. The geometry was created in CATIA V5 R18 and imported. The static and model analysis are carried out in analysis software ANSYS. The result of from the static analysis refers to the total deformation, equivalent stress, shear stress and shear intensity on the skin of the aircraft wing. The model analysis will be carried out to find out the first six modes of vibrations and the different mode shape in which wing can deform without the application of load. Compared to the conventional Aluminium wing, the hybridized composite wing experience far lower stresses and the aircraft wing weight nearly 40% and 50% lower stress.
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Zhu, Wen Qing, and Yang Yong Zhu. "The Vibration Response Analysis about High-Speed Train’s Braking Wing." Applied Mechanics and Materials 226-228 (November 2012): 102–5. http://dx.doi.org/10.4028/www.scientific.net/amm.226-228.102.

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With the rapid development of high-speed railway in China, the aerodynamic brake is very likely to be an important emergency braking mode of high-speed train in the future. This paper takes aerodynamic braking wing as the object, and uses the finite element software to divide the meshes, then analyses the model influenced by static stress. After simulating the vibratory frequency response of the model in the flow field, it finds that the largest deformation happens in the middle of the upper edge of the wind wing, when the wind speed gets to 500km/h and the load frequency to 4Hz. Some conclusions of this thesis can provide reference for researching the applying the aerodynamic brake in the high-speed trains and laying the foundation for solving the riding and braking safety problems.
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Alsaidi, Bashir, Woong Yeol Joe, and Muhammad Akbar. "Computational Analysis of 3D Lattice Structures for Skin in Real-Scale Camber Morphing Aircraft." Aerospace 6, no. 7 (July 7, 2019): 79. http://dx.doi.org/10.3390/aerospace6070079.

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Conventional or fixed wings require a certain thickness of skin material selection that guarantees structurally reliable strength under expected aerodynamic loadings. However, skin structures of morphing wings need to be flexible as well as stiff enough to deal with multi-axial structural stresses from changed geometry and the coupled aerodynamic loadings. Many works in the design of skin structures for morphing wings take the approach either of only geometric compliance or a simplified model that does not fully represent 3D real-scale wing models. Thus, the main theme of this study is (1) to numerically identify the multi-axial stress, strain, and deformation of skin in a camber morphing wing aircraft under both structure and aerodynamic loadings, and then (2) to show the effectiveness of a direct approach that uses 3D lattice structures for skin. Various lattice structures and their direct 3D wing models have been numerically analyzed for advanced skin design.
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Sun, Ya Zhen, Xiao Xing Zhai, and Jie Min Liu. "Analysis of Failure Mode and Propagation for Crack in Uniaxial Compression." Applied Mechanics and Materials 166-169 (May 2012): 2929–32. http://dx.doi.org/10.4028/www.scientific.net/amm.166-169.2929.

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This paper analyzed the failure mode for crack in uniaxial compression according to the stress intensity factor, and obtain that the failure mode for crack in uniaxial compression is compression-shear. The wing crack was deformed, after the crack tip initiate. By analyzing the dimensionless stress intensity factor, we obtain that the failure mode for wing crack in uniaxial compression is tension-shear, and we obtain that the dimensionless stress intensity factor for wing crack decreased with inclined angle increased. The inclined crack propagation in uniaxial compression was numerically studied using rock failure process analysis code (rfpa), and obtain that one inclined crack in uniaxial compression formed mode I offset crack parallel to load direction in the end. The numerical results of failure mode are accordance with stress intensity factor.
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Nabawy, M. R. A., M. M. ElNomrossy, M. M. Abdelrahman, and G. M. ElBayoumi. "Aerodynamic shape optimisation, wind tunnel measurements and CFD analysis of a MAV wing." Aeronautical Journal 116, no. 1181 (July 2012): 685–708. http://dx.doi.org/10.1017/s000192400000717x.

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Abstract The aerodynamic shape optimisation of a micro air vehicle (MAV) wing is performed to obtain the basic wing geometrical characteristics which produce the maximum range and endurance requirements. Multhopp’s method based on Prandtl’s classical lifting line theory is used for the determination of the spanwise load distribution required during the optimisation process. The obtained lift and drag characteristics are used for the derivation of the range and endurance equations of an electrically driven micro air vehicle. The optimisation process is based on the modified feasible directions gradient based optimisation algorithm. Results are validated using wind tunnel measurements showing very good agreement. Results are also compared with solutions to the Navier-Stokes equations obtained with ANSYS-CFX finite elements using different turbulence models. These include the k-ε and the shear stress transport (SST) models as well as the Reynolds stress model.
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Dissertations / Theses on the topic "Wing stress analysis"

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

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The main aim of the this diploma thesis is the wing design of the UAV aircraft, including the appropriate material choice, calculation of the wing load and also strength analysis. Other goals include the design of the location and volume of fuel tanks, as well as the design of wingspan reduction after landing.
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Hemmel, Radek. "Výpočet zatížení a pevnostní kontrola křídla a ocasních ploch letounu Parrot." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2008. http://www.nusl.cz/ntk/nusl-228128.

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Freisleben, Michal. "Výpočet zatížení a pevnostní kontrola křídla kluzáku." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2009. http://www.nusl.cz/ntk/nusl-228533.

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Světlík, Martin. "Výpočet zatížení a pevnostní kontrola křídla a ocasních ploch letounu Mermaid." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2008. http://www.nusl.cz/ntk/nusl-228118.

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The amphibious fullmetall plane Mermaid is made by company Czech Aircraft Works in Kunovice. Subject of this diploma thesis was involve changes of structure, which pass through during development, to calculation. Within this published work was process: Load calculation of wing Stress analysis of wing Load calculation of aileron Load calculation of flap Load calculation of horizontail tail
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Devaney, Louise Claire. "Breaking wave loads and stress analysis of jacket structures supporting offshore wind turbines." Thesis, University of Manchester, 2012. https://www.research.manchester.ac.uk/portal/en/theses/breaking-wave-loads-and-stress-analysis-of-jacket-structures-supporting-offshore-wind-turbines(acef8efd-eae2-4a52-9513-b2873e7a3a25).html.

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In terms of future power generation in UK and Germany, offshore wind is the next big player with 40GW and 32GW capacity planned for installation in both countries respectively by 2030. The latest Round 3 of sites owned by the Crown Estate explore deeper water depths of up to 78m in the Irish Sea. Foundations for offshore wind structures consume around 25% of the total project cost therefore the design of support structures is the subject of this thesis. The current state-of-the-art support structure options available for offshore wind turbines have been outlined in this thesis with an evaluation of the preliminary design of monopile and jacket solutions. This assessment resulted in further studies into the loading acting on a monopile foundation along with research into the fatigue design of multiplanar tubular joints for jacket structures. Mathematical modelling of linear and nonlinear waves combined with the Morison equation was completed to check the effects of breaking waves on a monopile foundation. Results indicated that measured forces were up to a factor of 2.5 times greater than calculated values, which suggests that loads could be under predicted if the effects of breaking are not considered. The theoretical maximum wave height before breaking was then linked to wind speed and a comparison of overturning moments from the two loads was made. Wave loads dominated at water depths of around 30m for lower wind speeds but this depth decreased to around 12m as wind speeds approached cut-out of 25m/s. For deeper water depths and larger capacity turbines, jackets are the preferred design solution. Joint design in FLS is the critical aspect of jacket design with castings often required to provide adequate capacity. A review of stress concentration factors (SCF) for tubular joints indicated that the coded approach, which uses SCF equations for uniplanar joints, could be missing the multiplanar effects. Finite element (FE) modelling of multiplanar tubular joints was completed using ANSYS Workbench to examine the effects of loading in out-of plane braces. Carry-over of stress from the loaded brace of the joint to unloaded neighbouring braces was observed which implies the importance of modelling joints as multiplanar geometries. A parameter study in ANSYS Workbench covering 1806 different geometrical configurations and loads was carried out with a regression of the data to give new sets of SCF equations for multiplanar tubular joints. SCFs from these equations were improved compared to Efthymiou but difficulties were encountered when superimposing the output (including Efthymiou). Further work on the superposition of individual load cases was therefore recommended for future work.
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Silva, Junior Laercio Meneses. "Stress analysis on a thin-walled composite blade of a large wind turbine." reponame:Repositório Institucional da UFSC, 2016. https://repositorio.ufsc.br/xmlui/handle/123456789/175894.

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Dissertação (mestrado) - Universidade Federal de Santa Catarina, Centro Tecnológico, Programa de Pós-Graduação em Engenharia Mecânica, Florianópolis, 2016.
Made available in DSpace on 2017-05-23T04:22:08Z (GMT). No. of bitstreams: 1 345248.pdf: 4540254 bytes, checksum: b61753d1576a6ca395e102d19e3c04e0 (MD5) Previous issue date: 2016
Abstract : Research institutes and industry have recently initiated the development of wind turbines for energy production at sites with lower wind speeds. The relatively high electric power production of this type of wind turbine is related to the growing of the swept area. Thus, in order to increase the swept area, the length of the new blades must be greater than the ones of traditional blades for horizontal axis wind turbines. The expansion of the rotors diameter of large wind turbines has some implications, such as the increase of gravity loads and new transportation logistics challenges. To overcome these challenges, advances in the blade technology have led to more efficient structural and aerodynamic design and optimized material usage. In this context, analytical models have to accurately predict aerodynamic loads acting on the blades and calculate the structural stresses developed during the turbine operation. Since composite materials have high strength/weight ratio compared to other structural materials and are flexible with respect to the fabrication process, they are more appropriate for blade applications. This dissertation presents an improvement in the aerodynamic model that takes into account an iterative procedure for determining Reynolds number instead of depending on experimental data for the process of airfoil selection along the blade span that maximize the power extracted from the wind. The multilayer shell theories and the relationship between the aerodynamic bending and torsional moments acting on the blade are presented. The in-plane normal and shear stresses on the thin-walled multilayer blade are determined by using the Shear Flow Theory. A case study is conducted on a 20 MW wind turbine developed in the Energy Research Centre of the Netherlands-ECN. The normal and shear stresses are calculated and the Tsai-Wu criterion is applied for the strength evaluation of the blade made of glass/epoxy. Results obtained with two stacking sequences are presented.

Institutos de pesquisa e a indústria iniciaram recentemente o desenvolvimento de turbinas eólicas para a produção de energia em locais com baixas velocidades de vento. A produção de energia elétrica relativamente alta deste tipo de turbina está relacionada com o crescimento da área varrida pelo rotor. Assim, de forma a aumentar a área varrida, o comprimento das novas pás deve ser maior que o das pás tradicionais de turbinas eólicas de eixo horizontal. O aumento do diâmetro dos rotores das turbinas eólicas tem algumas implicações, tais como o aumento das cargas gravitacionais e desafios no seu transporte. Para superá-los, avanços na tecnologia de pás têm levado a projetos estruturais e aerodinâmicos mais eficientes. Neste contexto, modelos analíticos têm de prever com precisão as cargas aerodinâmicas atuando sobre as pás, além de calcular as tensões estruturais desenvolvidas durante sua operação. Uma vez que materiais compostos têm uma elevada relação resistência/peso em comparação com outros materiais estruturais, além de serem flexíveis no que diz respeito ao processo de fabricação, estes materiais têm sido os mais investigados para aplicações em pás de turbina eólica. Esta dissertação apresenta uma melhoria no modelo aerodinâmico que leva em conta um processo iterativo para a determinação do número de Reynolds, em vez de depender de dados experimentais para o processo de escolha do aerofólio ao longo da envergadura da pá que maximiza a potência extraída do vento. As teorias de cascas multilaminares e a relação entre os momentos aerodinâmicos fletores e de torção que atuam sobre a pá são apresentados. As tensões normais e de cisalhamento atuantes no plano da pá multilaminar de parede fina são determinadas utilizando a Teoria do Fluxo de Cisalhamento. Um estudo de caso é conduzido em uma turbina eólica de 20 MW desenvolvida no Centro de Pesquisa em Energia dos Países Baixos (ECN). As tensões normais e de cisalhamento são calculadas e o critério de Tsai-Wu é aplicado para a avaliação da resistência da pá feita em vidro/epóxi. Os resultados obtidos com duas sequências de empilhamento de lâminas são apresentados.
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Muthirevula, Neeharika. "Cross-Sectional Stiffness Properties of Complex Drone Wings." Thesis, Virginia Tech, 2017. http://hdl.handle.net/10919/73988.

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The main purpose of this thesis is to develop a beam element in order to model the wing of a drone, made of composite materials. The proposed model consists of the framework for the structural design and analysis of long slender beam like structures, e.g., wings, wind turbine blades, and helicopter rotor blades, etc. The main feature consists of the addition of the coupling between axial and bending with torsional effects that may arise when using composite materials and the coupling stemming from the inhomogeneity in cross-sections of any arbitrary geometry. This type of modeling approach allows for an accurate yet computationally inexpensive representation of a general class of beam-like structures. The framework for beam analysis consists of main two parts, cross-sectional analysis of the beam sections and then using this section analysis to build up the finite element model. The cross-sectional analysis is performed in order to predict the structural properties for composite sections, which are used for the beam model. The thesis consists of the model to validate the convergence of the element size required for the cross-sectional analysis. This follows by the validation of the shell models of constant cross-section to assess the performance of the beam elements, including coupling terms. This framework also has the capability of calculating the strains and displacements at various points of the cross-section. Natural frequencies and mode shapes are compared for different cases of increasing complexity with those available in the papers. Then, the framework is used to analyze the wing of a drone and compare the results to a model developed in NASTRAN.
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Kumar, Nikhil. "Stress analysis of wood-framed low-rise buildings under wind loads due to tornados." [Ames, Iowa : Iowa State University], 2008.

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Fernandez, Rodriguez Emmanuel. "Analysis of floating support structures for marine and wind energy." Thesis, University of Manchester, 2015. https://www.research.manchester.ac.uk/portal/en/theses/analysis-of-floating-support-structures-for-marine-and-wind-energy(f4870ce2-b8b5-4c7e-ba7e-f91a1d3c4bc9).html.

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Bed connected support structures such as monopiles are expected to be impractical for water depths greater than 30 m and so there is increasing interest in alternative structure concepts to enable cost-effective deployment of wind and tidal stream turbines. Floating, moored platforms supporting multiple rotors are being considered for this purpose. This thesis investigates the dynamic response of such floating structures, taking into account the coupling between loading due to both turbulent flow and waves and the dynamic response of the system. The performance and loading of a single rotor in steady and quasi-steady flows are quantified with a Blade Element Momentum Theory (BEMT) code. This model is validated for steady flow against published data for two 0.8 m diameter rotors (Bahaj, Batten, et al., 2007; Galloway et al., 2011) and a 0.27 m diameter rotor (Whelan and Stallard, 2011). Time-averaged coefficients of thrust and power measured by experiment in steady turbulent flow were in agreement with BEMT predictions over a range of angular speeds. The standard deviation of force on the rotor is comparable to that on a porous grid for comparable turbulence characteristics. Drag and added mass coefficients are determined for a porous disc forced to oscillate normal to the rotor plane in quiescent flow and in the streamwise axis in turbulent flow. Added mass is negligible for the Keulegan Carpenter number range considered ( less than 1). The drag coefficient in turbulent flow was found to decay exponentially with number, to 2±10% for values greater than 0.5. These coefficients were found to be in good agreement with those for a rotor in the same turbulent flow with disc drag coefficient within 12.5% for less than 0.65. An extreme-value analysis is applied to the measured time-varying thrust due to turbulent flow and turbulent flow with waves to obtain forces with 1%, 0.1% and 0.01% probability of exceedance during operating conditions. The 1% exceedance force in turbulent flow with turbulence intensity of 12% is around 40% greater than the mean thrust. The peak force in turbulent flow with opposing waves was predicted to within 6% by superposition of the extreme force due to turbulence only with a drag force based on the relative wave-induced velocity at hub-height estimated by linear wave theory and with drag coefficient of 2.0. Response of a floating structure in surge and pitch is studied due to both wave- forcing on the platform defined by the linear diffraction code WAMIT and due to loading of the operating turbine defined by a thrust coefficient and drag coefficient. Platform response can either increase or decrease the loading on the rotor and this was dependant on the hydrodynamic characteristics of the support platform. A reduction of the force on the rotor is attained when the phase difference between the wave force on the support and the surface elevation is close to ± and when the damping of the support is increased. For a typical support and for a wave condition with phase difference close to , the 1% rotor forces were reduced by 8% when compared to the force obtained with a rotor supported on a stiff tower.
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Katsanis, George R. Mr. "Transient Small Wind Turbine Tower Structural Analysis with Coupled Rotor Dynamic Interaction." DigitalCommons@CalPoly, 2013. https://digitalcommons.calpoly.edu/theses/960.

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Structural dynamics is at the center of wind turbine tower design - excessive vibrations can be caused by a wide range of environmental and mechanical sources and can lead to reduced component life due to fatigue, noise, and impaired public perception of system integrity. Furthermore, periodic turbulent wind conditions can cause system resonance resulting in significantly increased structural loads. Structural vibration issues may become exacerbated in small wind applications where the analytical and experimental resources for system verification and optimization are scarce. This study combines several structural analysis techniques and packages them into a novel and integrated form that can be readily used by the small wind community/designer to gain insight into tower/rotor dynamic interaction, system modal characteristics, and to optimize the design for reduced tower loads and cost. The finite element method is used to model the tower structure and can accommodate various configurations including fixed monopole towers, guy-wire supported towers, and gin-pole and strut supported towers. The turbine rotor is modeled using the Equivalent Hinge-Offset blade model and coupled to the tower structure through the use of Lagrange’s Equations. Standard IEC Aeroelastic load cases are evaluated and transient solutions developed using the Modal Superposition Method and Runge-Kutta 4th order numerical integration. Validation is performed through comparisons to theoretical closed form solutions, physical laboratory test results, and peer studies. Finally a case study is performed by using the tool to simulate the Cal Poly Wind Power Research Center Wind Turbine and Tower System. Included in the case study is an optimization for hypothetical guy-wire placement to minimize tower stresses and maximize the tower’s natural frequency.
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Books on the topic "Wing stress analysis"

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Ko, William L. Thermal stress analysis of space shuttle orbiter wing skin panel and thermal protection system. Edwards, Calif: National Aeronautics and Space Administration, Ames Researach Center, Dryden Flight Research Facility, 1987.

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Gregory, Peyton B. Thermal/structural analysis of the shaft disk region of a fan drive system. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1990.

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Larry, Sobel, and Langley Research Center, eds. Novel composites for wing and fuselage applications: Speedy Nonlinear Analysis of Postbuckled Panels in Shear (SNAPPS) : under contract NAS1-18784. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

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Larry, Sobel, and Langley Research Center, eds. Novel composites for wing and fuselage applications: Speedy Nonlinear Analysis of Postbuckled Panels in Shear (SNAPPS) : under contract NAS1-18784. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

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H, Hoffmann P., and Joint Institute for Aeronautics and Acoustics., eds. A study of the factors affecting boundary layer two-dimensionality in wind tunnels. Stanford, CA: Stanford University, Dept. of Aeronautics and Astronautics, 1986.

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Frondizi, Alexandre, and Simon Porcher. Sidewalk Queens. Edited by Scott Cunningham and Manisha Shah. Oxford University Press, 2016. http://dx.doi.org/10.1093/oxfordhb/9780199915248.013.14.

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This chapter provides an in-depth historical analysis of prostitution markets in Paris during the 19th century. More specifically, it explores the economic rationalities of the different actors in the informal public prostitution network and how their behavior affects the financial considerations of the other actors in the urban economy. Before discussing the economics of popular prostitutions in fin-de-siècle Paris, the chapter takes a look at streetwalkers and their role in the local economy. It then considers the supply and demand for street prostitutes in Paris, along with the negative externalities of public prostitution in the city. In particular, it examines the impact of street prostitution on regulated brothels, shopkeepers, and annuitants. It also takes into account the positive externalities of street prostitution in relation to wine merchants and slumlords and concludes with an assessment of the red-light district of fin-de-siècle Paris.
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D, Holland Anne, and Langley Research Center, eds. Thermal/structural analysis of the shaft disk region of a fan drive system. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1990.

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(Foreword), Anne Devereaux Jordan, Ira Mark Milne (Editor), and Timothy Sisler (Editor), eds. Novels for Students: Presenting Analysis, Context, and Criticism on Commonly Studies Novels (Novels for Students). Gale Cengage, 2004.

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Group, Abbey. No. 45 province street, Boston, Massachusetts, draft and final project impact report. 1988.

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Book chapters on the topic "Wing stress analysis"

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Sondankar, Piyush, and R. R. Arakerimath. "Stress and Failure Analysis of Aircraft Wing Using Glare Composite and Aluminum 7075." In ICRRM 2019 – System Reliability, Quality Control, Safety, Maintenance and Management, 33–39. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-8507-0_6.

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Ngouani, M. M. Siewe, Yong Kang Chen, R. Day, and O. David-West. "Low-Speed Aerodynamic Analysis Using Four Different Turbulent Models of Solver of a Wind Turbine Shroud." In Springer Proceedings in Energy, 149–54. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-63916-7_19.

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AbstractThis study presents the effect of four different turbulent models of solver on the aerodynamic analysis of a shroud at wind speed below 6 m/s. The converting shroud uses a combination of a cylindrical case and an inverted circular wing base which captures the wind from a 360° direction. The CFD models used are: the SST (Menter) k-ω model, the Reynolds Stress Transport (RST) model, the Improved Delay Detached Eddies Simulation model (IDDES) SST k-ω model and the Large Eddies Simulation Wall Adaptive model. It was found that all models have predicted a convergent surface pressure. The RST, the IDDES and the WALE LES are the only models which have well described regions of pressure gradient. They have all predicted a pressure difference between the planes (1–5) which shows a movement of the air from the lower plane 1 (inlet) to the higher plane 5 (outlet). The RST and IDDES have predicted better vorticities on the plane 1 (inlet). It was also found that the model RST, IDDES, and WALE LES have captured properly the area of turbulences across the internal region of the case. All models have predicted the point of flow separation. They have also revealed that the IDDES and the WALE LES can capture and model the wake eddies at different planes. Thus, they are the most appropriate for such simulation although demanding in computational power. The movement of air predicted by almost all models could be used to drive a turbine.
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Kinne, Marko, Ronald Schneider, and Sebastian Thöns. "Reconstructing Stress Resultants in Wind Turbine Towers Based on Strain Measurements." In Lecture Notes in Mechanical Engineering, 224–35. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-77256-7_18.

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AbstractSupport structures of offshore wind turbines are subject to cyclic stresses generated by different time-variant random loadings such as wind, waves, and currents in combination with the excitation by the rotor. In the design phase, the cyclic demand on wind turbine support structure is calculated and forecasted with semi or fully probabilistic engineering models. In some cases, additional cyclic stresses may be induced by construction deviations, unbalanced rotor masses and structural dynamic phenomena such as, for example, the Sommerfeld effect. Both, the significant uncertainties in the design and a validation of absence of unforeseen adverse dynamic phenomena necessitate the employment of measurement systems on the support structures. The quality of the measurements of the cyclic demand on the support structures depends on (a) the precision of the measurement system consisting of sensors, amplifier and data normalization and (b) algorithms for analyzing and converting data to structural health information. This paper presents the probabilistic modelling and analysis of uncertainties in strain measurements performed for the purposes of reconstructing stress resultants in wind turbine towers. It is shown how the uncertainties in the strain measurements affect the uncertainty in the individual components of the reconstructed forces and moments. The analysis identifies the components of the vector of stress resultants that can be reconstructed with sufficient precision.
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Ma, Ke. "Stress Analysis of 3L-NPC Wind Power Converter Under Fault Condition." In Research Topics in Wind Energy, 63–93. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-21248-7_5.

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Ugwuanyi, Samson O., Opeyeolu Timothy Laseinde, and Lagouge Tartibu. "Physical Approach to Stress Analysis of Horizontal Axis Wind Turbine Blade Using Finite Element Analysis." In Advances in Intelligent Systems and Computing, 392–99. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-51328-3_54.

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Lee, Myoungwoo, Seok-Gyu Yoon, and Youn-Jea Kim. "Stress Analysis of Wind Turbine Tower Flange Using Fluid-Structure Interaction Method." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 115–23. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-55594-8_12.

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Borovsky, Joseph E., and John T. Steinberg. "The freestream turbulence effect in solar-wind/magnetosphere coupling: Analysis through the solar cycle and for various types of solar wind." In Recurrent Magnetic Storms: Corotating Solar Wind Streams, 59–76. Washington, D. C.: American Geophysical Union, 2006. http://dx.doi.org/10.1029/167gm07.

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Cavazzini, A., M. S. Campobasso, M. Marconcini, R. Pacciani, and A. Arnone. "Harmonic Balance Navier–Stokes Analysis of Tidal Stream Turbine Wave Loads." In Recent Advances in CFD for Wind and Tidal Offshore Turbines, 37–49. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-11887-7_4.

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Fiedler, Torben, Joachim Rösler, Martin Bäker, Felix Hötte, Christoph von Sethe, Dennis Daub, Matthias Haupt, Oskar J. Haidn, Burkard Esser, and Ali Gülhan. "Mechanical Integrity of Thermal Barrier Coatings: Coating Development and Micromechanics." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 295–307. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_19.

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Abstract To protect the copper liners of liquid-fuel rocket combustion chambers, a thermal barrier coating can be applied. Previously, a new metallic coating system was developed, consisting of a NiCuCrAl bond-coat and a Rene 80 top-coat, applied with high velocity oxyfuel spray (HVOF). The coatings are tested in laser cycling experiments to develop a detailed failure model, and critical loads for coating failure were defined. In this work, a coating system is designed for a generic engine to demonstrate the benefits of TBCs in rocket engines, and the mechanical loads and possible coating failure are analysed. Finally, the coatings are tested in a hypersonic wind tunnel with surface temperatures of 1350 K and above, where no coating failure was observed. Furthermore, cyclic experiments with a subscale combustion chamber were carried out. With a diffusion heat treatment, no large-scale coating delamination was observed, but the coating cracked vertically due to large cooling-induced stresses. These cracks are inevitable in rocket engines due to the very large thermal-strain differences between hot coating and cooled substrate. It is supposed that the cracks can be tolerated in rocket-engine application.
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Yermolaev, Y. I., I. G. Lodkina, N. S. Nikolaeva, and M. Y. Yermolaev. "Dynamics of Large-Scale Solar-Wind Streams Obtained by the Double Superposed Epoch Analysis: 2. Comparisons of CIRs vs. Sheaths and MCs vs. Ejecta." In Earth-affecting Solar Transients, 607–20. Dordrecht: Springer Netherlands, 2017. http://dx.doi.org/10.1007/978-94-024-1570-4_28.

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Conference papers on the topic "Wing stress analysis"

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Alsaidi, Bashir, Muhammad Akbar, Sara La, W. Yeol Joe, Hangil You, Seongik Kim, and Gunjin Yun. "Modeling and Stress Analysis of Composite Skin Structure for Camber Morphing Wing." In 2018 Multidisciplinary Analysis and Optimization Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-2934.

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Alsaidi, Bashir, Muhammad Akbar, Sara La, W. Yeol Joe, Hangil You, Seongik Kim, and Gunjin Yun. "Correction: Modeling and Stress Analysis of Composite Skin Structure for Camber Morphing Wing." In 2018 Multidisciplinary Analysis and Optimization Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-2934.c1.

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Milos, F., and T. Squire. "Thermal stress analysis of X-34 wing leading edge tile TPS." In 31st Thermophysics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1996. http://dx.doi.org/10.2514/6.1996-1821.

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Hasan, Zeaid, Hamzeh Hammoudeh, and Ghassan Atmeh. "Design and Analysis of a Smart Composite Wing." In ASME 2011 International Mechanical Engineering Congress and Exposition. ASMEDC, 2011. http://dx.doi.org/10.1115/imece2011-64802.

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This paper focuses on the design and analysis of a general aviation airplane wing which is fabricated of fiber reinforced composite laminates. The use of composite materials in commercial transport has continued to increase over the past 30 years. Composites materials are intended to be used more extensively as an alternative to aluminum structure in aircraft and aerospace applications. This is due to their attractive properties such as high strength-to-weight ratio and flexibility. The design of a general aviation aircraft is initially implemented in the first section. Using fiber-reinforced composite materials, an initial design of the wing box is assumed for the preliminary layout. The load carrying members of the wing are modeled as a rectangular box beam with taper while excluding the sweep angle. Aerodynamic analysis is conducted in order to extract the aerodynamic loads applied on the wing. These loads (lift, drag) are applied to the wing structure in order to conduct the proper stress analysis to attain the static structural behavior of the wing. An iterative procedure based on applying the stress analysis results to the appropriate macromechanical failure of composite materials (such as Tsai-Hill) is incorporated in order to evaluate the structural integrity of the wing against the applied loads. Moreover, static shape control of the composite wing is also considered using surface mounted and embedded piezoelectric actuators distributed along the wing span which have the capability to sense and take corrective actions under undesirable stimuli. The sequence of actuation of piezoelectric actuators embedded between the composite plies controls the elastic deformation response to loading of the composite wing. The analysis is conducted using the commercial finite element software Abaqus for several different types of piezoelectric actuators such as Lead Zirconate Titanate (PZT) and other piezoelectric fiber composites such as Active Fiber Composite (AFC) and Microfiber Composite (MFC). Finally, cost analysis of composite wings is briefly discussed.
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Jammi, Srinivasa R., and P. Shivakumar. "Bird Strike Analysis of a Composite Aircraft Wing." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-42818.

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Bird strikes have been a concern to aviation safety in both civil and military aircrafts. The external surfaces of an aircraft which include wing leading edges are susceptible to bird-strikes. Recently topology optimization is used to realize an aircraft wing concept design using Aluminum in (2009) [1] and optimize its weight. To make it lighter further, a composite wing was derived in (2010) [2]. Here, Fibre Metal Laminates (FMLs) with layers of aluminium alloy and high strength glass fibre have been used. The impact analysis is performed using a SPH model for the bird. Based on the modal analysis, the impact time is determined to capture the modes with high participation factor. The response obtained in time domain is converted to frequency domain and it is shown that the response has predominantly these modal components. For the given FMLs wing configuration the stress levels obtained are well within the orthotropic yield limits of the structure. All the layers of the composite structure are found to be intact.
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Goravi Vijaya Dev, Naveen Prakash, Anoop Kumar Koduru Satish, and Doddabasappa Veerapur. "Optimization of Air Plane Wing Rib Using Finite Element Analysis." In ASME 2013 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/imece2013-62192.

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Ribs are the stiffening members in the wing of air plane. Ribs usually have a thin flat plate shape accommodating cutouts, stiffeners and attachments. Most of the time there is a failure of rib due to critical buckling load even though the component is stressed well below the ultimate stress. Hence the rib is designed to carry maximum buckling load. The objective was to increase the critical buckling strength and reduce the weight of the rib. Linear static and buckling analysis were performed on the idealized configuration using FEM packages. Simply supported rectangular plate with different number of inline holes subjected to compression load was evaluated. The material considered was aluminum alloy. Various parametric studies were carried out to arrive at the optimum rib thickness and cross section. Once the optimum thickness of the plate was found out, reduction in the weight of the plate was done by providing various in line circular holes. From the study it was found that inserting circular hole in the plate enhances the buckling strength of the plate. The buckling strength of the plate was increased as the number of holes increased.
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Tang, Xiang-qiong, Chun-yue Huang, Sheng-jun Zhao, and Ying Liang. "Stress and strain analysis of solder joints of gull wing lead in the cooling process of reflow." In 2019 20th International Conference on Electronic Packaging Technology(ICEPT). IEEE, 2019. http://dx.doi.org/10.1109/icept47577.2019.245834.

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Carrera, E., A. Pagani, P. H. Cabral, A. Prado, and G. Silva. "Component-Wise Models for the Accurate Dynamic and Buckling Analysis of Composite Wing Structures." In ASME 2016 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/imece2016-65645.

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In the present work, a higher-order beam model able to characterize correctly the three-dimensional strain and stress fields with minimum computational efforts is proposed. One-dimensional models are formulated by employing the Carrera Unified Formulation (CUF), according to which the generic 3D displacement field is expressed as the expansion of the primary mechanical variables. In such a way, by employing a recursive index notation, the governing equations and the related finite element arrays of arbitrarily refined beam models can be written in a very compact and unified manner. A Component-Wise (CW) approach is developed in this work by using Lagrange polynomials as expanding cross-sectional functions. By using the principle of virtual work and CUF, free vibration and linearized buckling analyses of composite aerospace structures are investigated. The capabilities of the proposed methodology and the advantages over the classical methods and state-of-the-art tools are widely demonstrated by numerical results.
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Zhang, Xiaoqin, and Ling Tian. "Numerical Simulation of Micro Air Vehicles With Membrane Wings." In 2007 First International Conference on Integration and Commercialization of Micro and Nanosystems. ASMEDC, 2007. http://dx.doi.org/10.1115/mnc2007-21265.

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Micro Air Vehicles (MAVs) have advantages of small size, low cost, flexibility and controllability etc., so they will be applied widely in military and civilian fields. They have obviously low Reynolds number aerodynamics, which is different from traditional aircrafts. In this paper, numerical simulation based on fluid-structure interaction for flexible wing MAVs is presented. Flexible wings are composed of carbon frames and covered with membrane skins. Because flexible wing MAVs easily deform in airflow, both structure model and fluid model should be built. The two models are connected by interfaces of membrane wings, which transmit distributed pressure and deformations of membrane wings. When membrane wings are located in airflow, they will deform with actions of surrounding airflow. Deformation of membrane wings also affects airflow and pressure distributed on the wings’ surfaces will also be changed relatively, which will compel the shape of membrane wings to be changed once more. Therefore, numerical simulation of flexible wing MAVs is not only the analysis of fluid field, but also the structure deformation effects. Navier-Stokes Equations are nonlinear and complicated, so direct interaction of fluid and structure equations is rather difficult and costs too much time. Indirect interaction method is more feasible and it is adopted in this paper. Structure deformation and distributed pressure on membrane wings surfaces are calculated separately, and then pressure distribution from fluid solver is transmitted to structure solver. After structure deformation is calculated in structure solver, it will be transmitted to fluid field again. Iteration goes on in this way and finally converges. Simulation results show the deformation, stress and pressure distribution of flexible wings. All these results are good reference for MAVs design, modification and wind tunnel experiments generally.
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Radestock, Martin, Johannes Riemenschneider, Alexander Falken, and Johannes Achleitner. "Experimental Study of Flexible Skin Designs Between a Moving Wing Segment and a Fixed Wing Part on a Full Scale Demonstrator." In ASME 2020 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/smasis2020-2310.

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Abstract Commercial aircraft today require efficient high-lift and control systems on the wings to reduce the drag in flight or decrease the take-off and landing speeds. Morphing mechanisms are one approach for improved high-lift systems. In most cases the objective function is an increased lift to drag ratio or the noise reduction. On closer examination control systems as well as morphing mechanisms are located in a certain wing segment. The transition between a moving wing part and the fixed wing is a step, which creates additional vortices. This segments the wing in span-wise direction and reduces the efficiency. A flexible skin between a moving and a fixed wing parts smooths the contour and minimize the efficiency reduction of the wing. A full scale demonstrator of a wing segment was manufactured with two flexible skin designs. The first subcomponent connects a morphing leading edge with a rib of the wing over a span of one meter. The skin is a material mix of ethylene-propylene-diene monomer (EPDM) rubber and fiberglass-reinforced plastic. The rubber is the basis of the skin and the glass-fiber is added as local skin stiffeners in the form of strips in chord-wise direction. The second subcomponent blends the aileron with a rib of the wing in a triangular design. The connection of three different hinges realizes a morphing triangle, which is loaded in an in-plane shear only state of stress in each aileron position. The core of the triangle is a 3D printed structure, which is free in shear. The covering skin is a combination of EPDM with carbon fibers oriented in +/−30° direction to obtain shear compliance and to resist the loads on the triangle. The deformation of each concept is identified at the demonstrator. Therefore, an optical measurement system scans the surface in the initial and deflected state. The required deformation precision of the concepts differs due to their design. The contour at the leading edge requires a certain shape over the span. The analysis of the skin buckling is one requirement at the transition triangle during the aileron motion. The experimental results show a smooth transition contour at the leading edge and no buckling effects at the triangle. The results can be used for the validation of simulation models. Furthermore, both skin concepts cover the gap between a moving wing segment and a fixed wing part. The elimination of steps in span-wise direction can improve the aero-acoustic behavior along the wing for future aircraft.
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Reports on the topic "Wing stress analysis"

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Brandt, Leslie A., Cait Rottler, Wendy S. Gordon, Stacey L. Clark, Lisa O'Donnell, April Rose, Annamarie Rutledge, and Emily King. Vulnerability of Austin’s urban forest and natural areas: A report from the Urban Forestry Climate Change Response Framework. U.S. Department of Agriculture, Northern Forests Climate Hub, October 2020. http://dx.doi.org/10.32747/2020.7204069.ch.

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The trees, developed green spaces, and natural areas within the City of Austin’s 400,882 acres will face direct and indirect impacts from a changing climate over the 21st century. This assessment evaluates the vulnerability of urban trees and natural and developed landscapes within the City Austin to a range of future climates. We synthesized and summarized information on the contemporary landscape, provided information on past climate trends, and illustrated a range of projected future climates. We used this information to inform models of habitat suitability for trees native to the area. Projected shifts in plant hardiness and heat zones were used to understand how less common native species, nonnative species, and cultivars may tolerate future conditions. We also assessed the adaptability of planted and naturally occurring trees to stressors that may not be accounted for in habitat suitability models such as drought, flooding, wind damage, and air pollution. The summary of the contemporary landscape identifies major stressors currently threatening trees and forests in Austin. Major current threats to the region’s urban forest include invasive species, pests and disease, and development. Austin has been warming at a rate of about 0.4°F per decade since measurements began in 1938 and temperature is expected to increase by 5 to 10°F by the end of this century compared to the most recent 30-year average. Both increases in heavy rain events and severe droughts are projected for the future, and the overall balance of precipitation and temperature may shift Austin’s climate to be more similar to the arid Southwest. Species distribution modeling of native trees suggests that suitable habitat may decrease for 14 primarily northern species, and increase for four more southern species. An analysis of tree species vulnerability that combines model projections, shifts in hardiness and heat zones, and adaptive capacity showed that only 3% of the trees estimated to be present in Austin based on the most recent Urban FIA estimate were considered to have low vulnerability in developed areas. Using a panel of local experts, we also assessed the vulnerability of developed and natural areas. All areas were rated as having moderate to moderate-high vulnerability, but the underlying factors driving that vulnerability differed by natural community and between East and West Austin. These projected changes in climate and their associated impacts and vulnerabilities will have important implications for urban forest management, including the planting and maintenance of street and park trees, management of natural areas, and long-term planning.
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