Thematische Bibliographien / Semi-monocoque

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Auswahl der wissenschaftlichen Literatur zum Thema „Semi-monocoque“

Autor: Grafiati

Veröffentlicht am 28. Juni 2021

Zuletzt aktualisiert am 10. Februar 2022

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Zeitschriftenartikel zum Thema "Semi-monocoque"

Singhanart, Thanyarat, Kulanun Chutisemachai, Kiatnathee Dilokthonsakun, Jintasarn Sanchai und Kasemphan Siriployngam. „On the Use of Composite-Steel Joint for Semi-Monocoque Frame Design“. Applied Mechanics and Materials 619 (August 2014): 23–27. http://dx.doi.org/10.4028/www.scientific.net/amm.619.23.

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The design of semi-monocoque frame by using the composite-steel joint is considered in this paper. The frame is designed with weight less than 30kg and torsional stiffness more than 1200 Nm/deg. In order to design the semi-monocoque frame, the analysis of the composite-steel joint has to be clearly investigated. Therefore, the stress analysis of composite-steel joint is performed and then the frame is designed. The double lab joint with two holes is tested and verified by the experiments. The carbon-fiber fabric laminated with the KEVLAR fabric composite laminate is used for composite part. From experiments, the joint’s strength can be increased by using the eccentric holes. Therefore, in order to meet the requirement of the SAE rules; load capacity more than 30 kN, the eccentric hole double lap joint is numerically designed and applied to semi-monocoque frame. The joint has strength of 32 kN and can be used in frame design. The semi-monocoque frame is designed and analyzed by finite element analysis. The maximum stress at maximum load is 208 MPa which is less than the yield strength of the materials so it can withstand the loads, the mass is 29.6kg, and the torsional stiffness of the frame is 1408 Nm/degree. Therefore, the semi-monocoque frame can be successfully designed.

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Alonso, L., C. Bedoya, B. Lauret und F. Alonso. „F²TE³: a Transparent Semi-Monocoque VIP Envelope“. Applied Mechanics and Materials 71-78 (Juli 2011): 594–97. http://dx.doi.org/10.4028/www.scientific.net/amm.71-78.594.

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This article examines a new lightweight, slim, high energy efficient, light-transmitting, self-supporting envelope system, providing for seamless, free-form designs for use in architectural projects. The system exploits vacuum insulation panel technology. The research was based on envelope components already existing on the market and patents and prototypes built by independent laboratories, especially components implemented with silica gel insulation, as this is the most effective transparent thermal insulation there is today. The tests run on these materials revealed that there is not one that has all the features required of the new envelope model, although some do have properties that could be exploited to generate this envelope, namely, the vacuum chamber of vacuum insulation panels, the use of monolithic aerogel as insulation in some prototypes, and reinforced polyester barriers. These three design components have been combined and tested to design a new, variable geometry, energy-saving envelope system that also solves many of the problems that other studies ascribe to the use of vacuum insulation panels.

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Farrow, Ian. „Design, Build and Test of a Semi-Monocoque Wing Structure“. International Journal of Mechanical Engineering Education 30, Nr. 1 (Januar 2002): 73–89. http://dx.doi.org/10.7227/ijmee.30.1.7.

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Katrňák, Tomáš, Jaroslav Juračka und Ivo Jebáček. „RESEARCH OF EFFECTS OF DEFECTS ON STABILITY FAILURES OF SEMI-MONOCOQUE STIFFENERS“. Aviation 23, Nr. 3 (29.01.2020): 83–90. http://dx.doi.org/10.3846/aviation.2019.11903.

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This article presents further results of the research of effects of model defects on the local buckling of compressed stiffeners in nonlinear finite element (FE) analyses. The main outcomes are confirmation of trends for 10 sets of profile dimensions, final validations of various sets of FE simulations, and designs of practical types of defects with appropriate ratio values. A single node defect and then complex types of defects with alternating distributions of node shifts along one edge, two free flange edges, one flange surface and both flange surfaces are analyzed in this research project. First parts of this paper describe designed FE models with defects, their effects on simulation results, colored graphic visualizations with stress scales and determinations of the sudden failure of stability in the local mode. Then, particular results of FE analyses are validated by a comparison with the results of analytical methods of stability failure. Final detail comparisons of analytical and FE simulation results with data of experimental tests confirm predicted critical buckling forces. The validation of results and design parameters together with the knowledge of effects of model defects on buckling behaviors allows more accurate simulations of internal stiffeners of thin-walled semi-monocoque structures.

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Dababneh, Odeh, und Altan Kayran. „Design, analysis and optimization of thin walled semi-monocoque wing structures using different structural idealization in the preliminary design phase“. International Journal of Structural Integrity 5, Nr. 3 (12.08.2014): 214–26. http://dx.doi.org/10.1108/ijsi-12-2013-0050.

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Purpose – In modeling an aircraft wing, structural idealizations are often employed in hand calculations to simplify the structural analysis. In real applications of structural design, analysis and optimization, finite element methods are used because of the complexity of the geometry, combined and complex loading conditions. The purpose of this paper is to give a comprehensive study on the effect of using different structural idealizations on the design, analysis and optimization of thin walled semi-monocoque wing structures in the preliminary design phase. Design/methodology/approach – In the design part of the paper, wing structures are designed by employing two different structural idealizations that are typically used in the preliminary design phase. In the structural analysis part, finite element analysis of one of the designed wing configurations is performed using six different one and two dimensional finite element pairs which are typically used to model the sub-elements of semi-monocoque wing structures. Finally in the optimization part, wing structure is optimized for minimum weight by using finite element models which have the same six different finite element pairs used in the analysis phase. Findings – Based on the results presented in the paper, it is concluded that with the simplified methods, preliminary sizing of the wing configurations can be performed with enough confidence as long as the simplified method based designs are also optimized iteratively, which is what is practiced in the design phase of this study. Originality/value – This research aims at investigating the effect of using different one and two dimensional element pairs on the final analyzed and optimized configurations of the wing structure, and conclusions are inferred with regard to the sensitivity of the optimized wing configurations with respect to the choice of different element types in the finite element model.

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Webster, J. M., T. Schmidt und J. Mew. „A Holographic Interferometric Technique for the Detection and Computerized Recognition of Structural Faults in Semi-Monocoque Structures“. Imaging Science Journal 46, Nr. 1 (Januar 1998): 16–20. http://dx.doi.org/10.1080/13682199.1998.11736438.

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S. Mohamed Ali, J., Hasna Nur Fadhila, Burhani M. Burhani und Miah Mohammed Riyadh. „Educational Software for Stress Analysis of Idealized Closed Thin Walled Sections“. International Journal of Engineering & Technology 7, Nr. 4.36 (09.12.2018): 368. http://dx.doi.org/10.14419/ijet.v7i4.36.28144.

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Aerospace structures are typically semi-monocoque structures that are made up of thin-walled closed section reinforced with stiffeners. Stress analysis of such closed thin-walled structures which are statically indeterminate is tedious and time consuming. An educational software which can aid students in carrying out stress analysis of such idealized thin-walled closed sections has been developed. The software enables students to select different types of wing torsion box sections with stiffeners, which may be subjected to bending, shear or torsional loads and evaluate the resulting stresses on it. The software allows the student to idealize a selected twin spar unsymmetrical wing section with multiple booms under multiple loads. Results from this software have been validated against the results in the literature. The software has been developed using MATLAB with graphical user interface (GUI) which is very user friendly.

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Niemann, S., B. Kolesnikov, H. Lohse-Busch, C. Hühne, O. M. Querin, V. V. Toropov und D. Liu. „The use of topology optimisation in the conceptual design of next generation lattice composite aircraft fuselage structures“. Aeronautical Journal 117, Nr. 1197 (November 2013): 1139–54. http://dx.doi.org/10.1017/s0001924000008745.

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Abstract Conventional commercial aircraft fuselages use all-aluminium semi-monocoque structures where the skin carries the external loads, the internal fuselage pressurisation and is strengthen using frames and stringers. Environmental and economic issues force aircraft designers to minimise weight and costs to keep air transport competitive and safe. But as metal designs have reached a high degree of perfection, extraordinary weight and cost savings are unlikely in the future. Carbon composite materials combined with lattice structures and the use of topology optimisation have the potential to offer such weight reductions. The EU FP7 project Advanced Lattice Structures for Composite Airframes (ALaSCA) was started to investigate this. This article present some of this research which has now led to the development of a new airframe concept which consists of: a load carrying inner skin; transverse frames; CFRP-metal hybrid stiffeners helically arranged in a grid configuration; insulating foam and an additional aerodynamic outer skin.

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Гребеников, А. Г., И. В. Малков, В. А. Урбанович, Н. И. Москаленко und Д. С. Колодийчик. „КОНСТРУКТИВНО-ТЕХНОЛОГІЧНІ ОСОБЛИВОСТІ ХВОСТО-ВИХ БАЛОК СІТЧАСТОГО ТИПУ З ПОЛІМЕРНИХ КОМПО-ЗИЦІЙНИХ МАТЕРІАЛІВ ВЕРТОЛЬОТІВ ТРАНСПОРТНОЇ КАТЕГОРІЇ“. Open Information and Computer Integrated Technologies, Nr. 88 (06.11.2020): 15–30. http://dx.doi.org/10.32620/oikit.2020.88.02.

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The analysis of the design and technological features of the tail boom (ТB) of a helicopter made of polymer composite materials (PCM) is carried out.Three structural and technological concepts are distinguished - semi-monocoque (reinforced metal structure), monocoque (three-layer structure) and mesh-type structure. The high weight and economic efficiency of mesh structures is shown, which allows them to be used in aerospace engineering. The physicomechanical characteristics of the network structures are estimated and their uniqueness is shown. The use of mesh structures can reduce the weight of the product by a factor of two or more.The stress-strain state (SSS) of the proposed tail boom design is determined. The analysis of methods for calculating the characteristics of the total SSS of conical mesh shells is carried out. The design of the tail boom is presented, the design diagram of the tail boom of the transport category rotorcraft is developed. A finite element model was created using the Siemens NX 7.5 system. The calculation of the stress-strain state (SSS) of the HC of the helicopter was carried out on the basis of the developed structural scheme using the Advanced Simulation module of the Siemens NX 7.5 system. The main zones of probable fatigue failure of tail booms are determined. Finite Element Analysis (FEA) provides a theoretical basis for design decisions.Shown is the effect of the type of technological process selected for the production of the tail boom on the strength of the HB structure. The stability of the characteristics of the PCM tail boom largely depends on the extent to which its design is suitable for the use of mechanized and automated production processes.A method for the manufacture of a helicopter tail boom from PCM by the automated winding method is proposed. A variant of computer modeling of the tail boom of a mesh structure made of PCM is shown.The automated winding technology can be recommended for implementation in the design of the composite tail boom of the Mi-2 and Mi-8 helicopters.

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Hafid, M., Abian Nurrohmad und Redha Akbar Ramadhan. „NUMERICAL INVESTIGATION ON THE FUSELAGE AIRFRAME OF LSU 05 NG AIRCRAFT“. Jurnal Teknologi Dirgantara 18, Nr. 2 (27.12.2020): 93. http://dx.doi.org/10.30536/j.jtd.2020.v18.a3327.

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In this paper, numerical investigation on the fuselage structure of LSU 05 NG was carried out. This fuselage is designed to carry the payload up to 30 kg. Statical numerical analysis using finite element method was done using Simulia Abaqus. The fuselage structure that has been design consists of frame, longeron, and skin that can also be semi-monocoque structure. This airframe use combination of balsa and GFRP type of composite as the material. There are three load case: take-off condition, cruise condition, and landing condition. Tsai-hill failure criteria is used to investigate the strength of the composite structure due to the load that applied. Maximum stress from this calculation is 48 Mpa at the ground condition (take-off and landing) while the cruise stress analysis is 16 Mpa. The maximum tsai-hill criterion is 0,83. With such simulation results it can be said that the fuselage structure is still safe when operated and can also be optimized for several components so that the weight of the aircraft can be reduced.

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Dissertationen zum Thema "Semi-monocoque"

Santos, Fábio Henrique Massuia de Souza. „Modelagem computacional para análise de tensões e deslocamentos em fuselagem semi-monocoque“. Instituto Tecnológico de Aeronáutica, 2004. http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=2905.

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Este trabalho apresenta a análise de tensões e deslocamentos de uma fuselagem semi-monocoque através do método dos elementos finitos. Os diversos modelos utilizados nas análises possuem variações a partir de dois modelos básicos. O primeiro modelo considera o modelamento de cavernas e reforçadores como elementos de barra. O segundo modelo considera que somente os reforçadores devem ser modelados com elementos de barra; as cavernas, neste modelo, são modeladas com elementos de placa. As variações consideradas são: modelamento e não modelamento dos shear clips, presença e ausência de offsets nos reforçares e discretização da malha (malhas mais grosseira e malhas mais refinidas). Os resultados obtidos mostram que a quantidade e qualidade da malha influenciam muito mais os resultados do que presença ou não de offsets. Modelos com mesma malha, porém com diferença entre os offsets, possuem resultados muito próximos. A modelagem ou não dos shear clips influência na rigidez da estrutura e conseqüentemente deve ser modelado para melhor representar a estrutura real.

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Paulin, Julio Cezar. „Dimensionamento preliminar de uma seção de fuselagem semi-monocoque de uma aeronave de passageiros“. Instituto Tecnológico de Aeronáutica, 2008. http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=1173.

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Um método de pré-dimensionamento da estrutura da fuselagem de uma aeronave foi desenvolvido nesse trabalho com o objetivo de possibilitar ao engenheiro de estruturas o cálculo rápido dos esforços primários e secundários, bem como das margens de segurança dessa estrutura. Para tanto, as teorias de cálculo desse tipo de estrutura foram implementadas em uma planilha de forma a permitir que o engenheiro mude com facilidade os parâmetros de projeto, podendo assim buscar uma solução mais eficiente. Neste trabalho são discutidas também as conseqüências de não se considerar as reduções das áreas efetivas do revestimento, devido à flambagem dos mesmos, no cálculo da área total resistente à compressão axial.

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Mello, Pedro Paulo Serrajordia Rocha de. „Análise da influência dos esforços primários em fuselagem semi-monocoque nas tensões de da tração diagonal“. Instituto Tecnológico de Aeronáutica, 2004. http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=611.

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A determinação dos esforços primários via NASTRAN, ao contrário do que ocorre ao se utilizar a teoria do engenheiro que faz uso extensivo de larguras efetivas de chapa, baseia-se na hipótese de que os painéis não flambam. A redistribuição das tensões ocorre apenas levando-se em conta os efeitos da tração diagonal, enquanto a flambagem dos painéis não é levada em conta neste estudo. Sabendo-se que ao não considerar a flambagem, erros podem ser cometidos, este trabalho realiza uma comparação entre duas análises da estrutura primária: análise usando NASTRAN, levando-se em conta a redistribuição de tensão devido à tração diagonal - sem considerar a flambagem dos painéis; e análise da teoria do engenheiro considerando a flambagem dos painéis, através do uso de larguras e áreas efetivas dos painéis flambados, também se levando em conta a redistribuição de tensões devido à tração diagonal. Aqui se apresenta a questão de como devem ser utilizados os resultados obtidos através de uma análise de uma fuselagem semi-monocoque pelo NASTRAN, face ao fato de que existe a possibilidade real de flambagem de chapas dessa estrutura.

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Dababneh, Odeh. „Design, Analysis And Optimization Of Thin Walled Semi-monocoque Wing Structures Using Different Structural Idealizations In The Preliminary Design Phase“. Master's thesis, METU, 2011. http://etd.lib.metu.edu.tr/upload/12613759/index.pdf.

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This thesis gives a comprehensive study on the effect of using different structural idealizations on the design, analysis and optimization of thin walled semi-monocoque wing structures in the preliminary design phase. In the design part, wing structures are designed by employing two different structural idealizations that are typically used in the preliminary design phase. In the structural analysis part, finite element analysis of one of the designed wing configurations is performed using six different one and two dimensional element pairs which are typically used to model the sub-elements of semi-monocoque wing structures. The effect of using different finite element types on the analysis results of the wing structure is investigated. During the analysis study, depending on the mesh size used, conclusions are also inferred with regard to the deficiency of certain element types in handling the true external load acting on the wing structure. Finally in the optimization part, wing structure is optimized for minimum weight by using finite element models which have the same six different element pairs used in the analysis phase. The effect of using different one and two dimensional element pairs on the final optimized configurations of the wing structure is investigated, and conclusions are inferred with regard to the sensitivity of the optimized wing configurations with respect to the choice of different element types in the finite element model. Final optimized wing structure configurations are also compared with the simplified method based designs which are also optimized iteratively. Based on the results presented in the thesis, it is concluded that with the simplified methods, preliminary sizing of the wing structures can be performed with enough confidence, as long as the simplified method based designs are also optimized. Results of the simplified method of analysis showed that simplified method is applicable to be used as an analysis tool in performing the preliminary sizing of the wing structure before moving on to more refined finite element based analysis.

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Čížková, Markéta. „Analýza poškození dopravního letounu při teroristickém útoku“. Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2021. http://www.nusl.cz/ntk/nusl-443754.

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In its theoretical part, the diploma thesis deals with the reasons leading to terrorist attacks and a brief list of some attacks on aircraft. It also focuses on the aircraft as the target of a terrorist attack, especially the aircraft kite as the major researched part. The conclusion of the theoretical part summarizes a list of types of aircraft fuselage structures in respect of design solutions for load transfer. The practical part determines the extent of damage caused by a missile with a fragmentation warhead. This scope is then applied to the illustrative case. In the following chapters, the calculation of the critical force of a panel loaded with pressure depends on the different nature and extent of damage. Then the work highlights the evaluation of the obtained results, which are also summarized in the conclusions of the work.

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Zamazal, Jakub. „Návrh rekonstrukce střední části trupu letounu Z 143 náhradou za poloskořepinu“. Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2017. http://www.nusl.cz/ntk/nusl-318137.

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The thesis is focused on reconstruction of middle part of fuselage Z 143 aircraft from truss frame to semi-monocoque frame. In the thesis there is a conceptual design of semi-monocoque middle part of fuselage. The spars of centre wing section are strength controlled. In thesis there is weight analysis according to use the semi-monocoque middle part of fuselage. In second half of the thesis there is a study of retractable landing gear. The thesis shows weight savings according to use a semi-monocoque frame. The thesis also shows that semi-monocoque frame allows other option to upgrade Z 143 aircraft. This thesis can serve as a feasibility study of the reconstruction of the middle part of the fuselage Z 143 aircraft.

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Konferenzberichte zum Thema "Semi-monocoque"

Kalyanasundaram, Haribaskar, und Masoud Rais-Rohani. „Design optimization and residual strength assessment of a semi-monocoque cylindrical structure“. In 8th Symposium on Multidisciplinary Analysis and Optimization. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-4742.

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Ravindren, Prabu Ganesh, Kirti Ghia und Urmila Ghia. „Dynamic Analysis of the Joined-Wing Configuration in High-Altitude Long-Endurance Aircraft Using Fluid-Structure Interaction Model“. In ASME/JSME 2007 5th Joint Fluids Engineering Conference. ASMEDC, 2007. http://dx.doi.org/10.1115/fedsm2007-37683.

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Recent studies of the joined-wing configuration of the High Altitude Long Endurance (HALE) aircraft have been performed by analyzing the aerodynamic and structural behaviors separately. In the present work, a fluid-structure interaction (FSI) analysis is performed, where the fluid pressure on the wing, and the corresponding non-linear structural deformation, are analyzed simultaneously using a finite-element matrix which couples both fluid and structural solution vectors. An unsteady, viscous flow past the high-aspect ratio wing causes it to undergo large deflections, thus changing the domain shape at each time step. The finite element software ANSYS 11.0 is used for the structural analysis and CFX 11.0 is used for the fluid analysis. The structural mesh of the semi-monocoque joined-wing consists of finite elements to model the skin panel, ribs and spars. Appropriate mass and stress distributions are applied across the joined-wing structure [Kaloyanova et al. (2005)], which has been optimized in order to reduce global and local buckling. The fluid region is meshed with very high mesh density at the fluid-structure interface and where flow separation is predicted across the joint of the wing. The FSI module uses a sequentially-coupled finite element equation, where the main coupling matrix utilizes the direction of the normal vector defined for each pair of coincident fluid and structural element faces at the interface [ANSYS 11.0 Documentation]. The k-omega turbulence model captures the fine-scale turbulence effects in the flow. An angle of attack of 12°, at a Mach number of 0.6 [Rangarajan et al. (2003)], is used in the simulation. A 1-way FSI analysis has been performed to verify the proper transfer of loads across the fluid-structure interface. The CFX pressure results on the wing were transferred across the comparatively coarser mesh on the structural surface. A maximum deflection of 16 ft is found at the wing tip with a calculated lift coefficient of 1.35. The results have been compared with the previous study and have proven to be highly accurate. This will be taken as the first step for the 2-way simulation. The effect of a coupled 2-way FSI analysis on the HALE aircraft joined wing configuration will be shown. The structural deformation history will be presented, showing the displacement of the joined-wing, along the wing span over a period of aerodynamic loading. The fluid-structure interface meshing and the convergence at each time step, based on the quantities transferred across the interface will also be discussed.

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