Tesis sobre el tema "Aerospace Structure"
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Ahn, Junghyun. "Integrated analysis procedure of aerospace composite structure". Thesis, Massachusetts Institute of Technology, 2008. http://hdl.handle.net/1721.1/43106.
Texto completoIncludes bibliographical references (p. 50).
The emergence of composite material application in major commercial aircraft design, represented by the Boeing 787 and Airbus A350-XWB, signals a new era in the aerospace industry. The high stiffness to weight ratio of continuous fiber composites (CFC) makes CFCs one of the most important materials to be introduced in modern aircraft industry. In addition to inherent strength (per given weight) of CFCs, they also offer the unusual opportunity to design the structure and material concurrently. The directional properties (and the ability to change these properties through the design process) of composite materials can be used in aeroelastically tailored wings, the fuselage and other critical areas. Due to the longer lifecycle (25-30 years) of a commercial airliner and the tools and processes developed for the airplane of previous product development cycles, new technology often ends up being deployed less effectively because of the mismatch in the technical potential (what can be done) vs. design tools and processes (what was done before). Tools and processes need to be current to take advantage of latest technology, and this thesis will describe one possible approach in primary composite structural design area using integrated structural analysis
by Junghyun Ahn.
S.M.
Key, Ross A. "Automated manufacturing processes for secondary structure aerospace composites". Thesis, University of Nottingham, 2016. http://eprints.nottingham.ac.uk/33572/.
Texto completoHu, Zhuopei. "Finite Element Modeling of Aerospace Materials and Structure". University of Akron / OhioLINK, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=akron1344224158.
Texto completoZheng, LiangKan 1972. "Fluid-structure coupling for aeroelastic computations in the time domain using low fidelity structural models". Thesis, McGill University, 2005. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=99127.
Texto completoSeddon, Caroline Michelle. "Modelling transient dynamic fluid-structure interaction in aerospace applications". Thesis, University of Salford, 2006. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.492434.
Texto completoBhatti, Wasim. "Mechanical integration of a PEM fuel cell for a multifunctional aerospace structure". Thesis, Loughborough University, 2016. https://dspace.lboro.ac.uk/2134/21513.
Texto completoPalsule, Sanjay. "Structure and properties of aerospace molecular composites : third generation polymers". Thesis, Heriot-Watt University, 1994. http://hdl.handle.net/10399/1388.
Texto completoKhataee, Amin. "Structure and properties of some Ti-Al-Ru alloys". Thesis, Imperial College London, 1987. http://hdl.handle.net/10044/1/46915.
Texto completoLiang, Lijun. "Experimental investigation of an aeroelastic structure with continuous nonlinear stiffness". Thesis, McGill University, 2003. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=80123.
Texto completoSeveral linear and nonlinear system tests are presented, and the results compared and analyzed. The effects of linear plunge stiffness on the stability of the aeroelastic system are discussed, and the nonlinear system response is studied for different degrees of cubic nonlinearity in pitch.
In several nonlinear system tests, limit cycle oscillations (LCO) are observed when the air speed is above the linear flutter speed. The effects of airfoil initial conditions and air speeds on the LCO amplitude, frequency, and convergence rate are studied.
The effective linear flutter speed is predicted using the so-called "flutter-margin" method for both the linear and nonlinear cases. The prediction results for the nonlinear cases are compared with those for the linear cases and with the actual flutter speed.
Ozsoy, Serhan. "Vibration Induced Stress And Accelerated Life Analyses Of An Aerospace Structure". Master's thesis, METU, 2006. http://etd.lib.metu.edu.tr/upload/2/12606966/index.pdf.
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s dynamic characteristics and varying loadings. Therefore, experimental, numerical or a combination of both methods are used for fatigue evaluations. Fatigue failure can occur on systems and platforms as well as components to be mounted on the platform. In this thesis, a helicopter&
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s Missile Warning Sensor - Cowling assembly is analyzed. Analytical, numerical and experimental approaches are used wherever necessary to perform stress and fatigue analyses. Operational flight tests are used for obtaining the loading history at the analyzed location by using sensors. Operational vibration profiles are created by synthesizing the data (LMS Mission Synthesis). Numerical fatigue analysis of the assembly is done for determining the natural modes and the critical locations on the assembly by using a finite element model (MSC Fatigue). In addition, numerical multiaxial PSD analysis is performed for relating the experimental results (Ansys). Residual stresses due to riveting are determined (MSC Marc) and included in experimental analysis as mean stresses. Bolt analysis is performed analytically (Hexagon) for keeping the v assembly stresses in safe levels while mounting the experimental prototype to the test fixture. Fatigue tests for determining the accelerated life parameters are done by an electromagnetic shaker and stress data is collected. Afterwards, fatigue test is performed for determining whether the assembly satisfies the required operational life. Resonance test is performed at the frequency in which the critical location is at resonance, since there was no failure observed after fatigue testing. A failure is obtained during resonance test. At the end of the study, an analytical equation is brought up which relates accelerated life test durations with equivalent alternating stresses. Therefore, optimization of the accelerated life test duration can be done, especially in military applications, by avoiding the maximum stress level to reach or exceed the yield limit.
Beji, Faycel Ben Hedi. "Buckling Analysis of Composite Stiffened Panels and Shells in Aerospace Structure". Thesis, Virginia Tech, 2018. http://hdl.handle.net/10919/81620.
Texto completoMaster of Science
Vestlund, Oscar. "Aerodynamics and Structure of a Large UAV". Thesis, Mälardalens högskola, Akademin för innovation, design och teknik, 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:mdh:diva-38562.
Texto completoBingham, Christopher Malcolm. "Application of variable structure control methods to actuator nonlinearities in aerospace systems". Thesis, Cranfield University, 1994. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.358823.
Texto completoRoy, Steven. "Mechanical modeling and testing of a composite helicopter structure made by resin transfer moulding". Thesis, McGill University, 2009. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=40829.
Texto completoLe design et la performance mécanique d’un bec de bord d’attaque de stabilisateur horizontal d’hélicoptère fabriqué par moulage par injection sur renfort (« resin transfer moulding ») peuvent être évalués par des analyses par éléments finis. Pour vérifier la validité des hypothèses utilisées dans la modélisation du bec de bord d’attaque, des essais mécaniques ont été effectués sur des prototypes demi-longueurs. Les conditions frontières complexes ont été simplifiées pour rendre les essais mécaniques possibles. Deux gabarits ont été conçus et construits pour introduire les chargements simplifiés dans les pièces d’essai possédant deux configurations de support: un support complet et un demi-support. Un modèle par éléments finis des pièces d’essai a été réalisé avec des éléments de type membrane et la solution est comparée avec les résultats expérimentaux. Dans la plupart des cas, la comparaison entre la solution par éléments finis et les résultats expérimentaux coïncide concernant la rigidité de la structure, la résistance, l’allongement et la localisation de l’endommagement. Les contraintes hors du plan devraient être considérées pour améliorer la précision de la solution par éléments finis.
Farinha, Marques Vitor Manuel. "Lead free solders for aerospace applications". Thesis, University of Oxford, 2010. http://ora.ox.ac.uk/objects/uuid:85707054-bc46-44f3-b9c6-9fd29358ad25.
Texto completoFry, Zachary S. "A LABORATORY SCALE STUDY OF INTUMESCENT COATINGS FOR PROTECTION OF BUILDING STRUCTURE MEMBERS FROM FIRES". Case Western Reserve University School of Graduate Studies / OhioLINK, 2014. http://rave.ohiolink.edu/etdc/view?acc_num=case1402055149.
Texto completoHolder, Justin. "Fluid Structure Interaction in Compressible Flows". University of Cincinnati / OhioLINK, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=ucin159584692691518.
Texto completoVishwakarma, R. "The use of inverse methods in determining applied dynamic loads on aerospace structure". Thesis, University of Hertfordshire, 2012. https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.691048.
Texto completoPark, Conrad. "Mechanical Performance and Structure-Property Relations in6061B Aluminum Metal Matrix Composites". Case Western Reserve University School of Graduate Studies / OhioLINK, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=case1547842396716777.
Texto completoDrury, William David. "An adaptive structure based sensorless position estimator for permanent magnet machines in aerospace applications". Thesis, University of Bristol, 2010. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.654114.
Texto completoKorobenko, Artem. "Advanced Fluid--Structure Interaction Techniques in Application to Horizontal and Vertical Axis Wind Turbines". Thesis, University of California, San Diego, 2015. http://pqdtopen.proquest.com/#viewpdf?dispub=3670451.
Texto completoDuring the last several decades engineers and scientists put significant effort into developing reliable and efficient wind turbines. As a wind power production demands grow, the wind energy research and development need to be enhanced with high-precision methods and tools. These include time-dependent, full-scale, complex-geometry advanced computational simulations at large-scale. Those, computational analysis of wind turbines, including fluid-structure interaction simulations (FSI) at full scale is important for accurate and reliable modeling, as well as blade failure prediction and design optimization.
In current dissertation the FSI framework is applied to most challenging class of problems, such as large scale horizontal axis wind turbines and vertical axis wind turbines. The governing equations for aerodynamics and structural mechanics together with coupled formulation are explained in details. The simulations are performed for different wind turbine designs, operational conditions and validated against field-test and wind tunnel experimental data.
Bail, Justin L. "Non-desctructive investigation & FEA correlation on an aircraft sandwich composite structure". Akron, OH : University of Akron, 2007. http://rave.ohiolink.edu/etdc/view?acc%5Fnum=akron1196702586.
Texto completo"December, 2007." Title from electronic thesis title page (viewed 02/25/2008) Advisor, Wieslaw Binienda; Faculty readers, Craig Menzemer, Robert Goldbert; Department Chair, Wieslaw Binienda; Dean of the College, George K. Haritos; Dean of the Graduate School, George R. Newkome. Includes bibliographical references.
Bin, Abdullah Nur Azam. "Numerical modelling and interaction of crack and aeroelastic behaviour of composite structure for aerospace applications". Thesis, University of Sheffield, 2018. http://etheses.whiterose.ac.uk/21462/.
Texto completoMichaels, Simone Colette. "Development and Assessment of Artificial Manduca sexta Forewings: How Wing Structure Affects Performance". Case Western Reserve University School of Graduate Studies / OhioLINK, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=case1446206590.
Texto completoHe, Yunzheng. "Modeling and Simulation of Tensegrity Structure based on SimMechanics". University of Cincinnati / OhioLINK, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1592395403390476.
Texto completoHinton, David A. "The organization as a system : structure, process, and human capital considerations in aerospace R&T". Thesis, Massachusetts Institute of Technology, 2003. http://hdl.handle.net/1721.1/91790.
Texto completoPuttmann, John Paul. "Spatially Targeted Activation of a SMP". University of Dayton / OhioLINK, 2018. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1525166147319011.
Texto completoInman, Jennifer Ann. "Fluorescence imaging study of free and impinging supersonic jets: Jet structure and turbulent transition". W&M ScholarWorks, 2007. https://scholarworks.wm.edu/etd/1539623513.
Texto completoNwankpa, Uzoma Vincent. "Effectiveness of arc based processes and deposition strategies on additive manufacture structure for naval and aerospace applications". Thesis, Ecole centrale de Nantes, 2022. http://www.theses.fr/2022ECDN0010.
Texto completoWire and Arc Additive Manufacturing process is becoming an alternative technique used in manufacturing components of complex structures, which were unimaginable to achieve by conventional manufacturing methods. Various arc-based processes have been applied with titanium, aluminium, steel, and stainless steel to produce large components. Nevertheless, the best arc-based process for any given material of choice is yet to be addressed. In this research, several arc-based processes were investigated for their suitability to manufacture austenitic stainless steel and aluminium structures. However, the latter was confined to be deposited by cold metal transfer process (CMT) due to its high deposition rate and low heat input. Different deposition strategies and the use of gas metal arc, tungsten inert gas and plasma arc as heat sources for the deposition of austenitic stainless steel were investigated. An in-depth investigation of the process parameters such as current, wire feed speed and travel speed were carried out. It was found that the mechanical properties on each structure deposited by various arc-based processes satisfied the required mechanical properties Moreover, deposition strategies had moreimpact on the mechanical properties. Inaddition, the geometry accuracy and ferrite number decrease with respect to increased heat input. Aluminium studies were investigated with CMT process; a methodology to select the best CMT synergy and deposition mode for a prototype wire was proposed. Furthermore, the impact of deposition strategies and alternating these strategies with various CMT modes on mitigating crack propagation from the root of a WAAM component was investigated. Detailed studies on impact of ramping parameters on the aluminium thin wall geometry accuracy were performed. Afterwards the ramping parameters was implemented in the manufacture of suspended aluminium structures on steel support. Finally, the investigation showed that deposition of aluminium structure on a support of dissimilar properties is subject to crack due to uneven thermal expansion and contraction. The results of these research work on austenitic stainless steel and aluminium alloys for WAAM component can be of significance in the naval and aerospace applications
Chamberlain, Britany L. "Additively-Manufactured Hybrid Rocket Consumable Structure for CubeSat Propulsion". DigitalCommons@USU, 2018. https://digitalcommons.usu.edu/etd/7285.
Texto completoMignee, Juliette L. "Proper Orthogonal Decomposition Applied to a Supersonic Single Flow Jet". University of Cincinnati / OhioLINK, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1329935384.
Texto completoKhasawneh, Firas Abdallah. "Characterization of drillability of sandwich structure of carbon fiber reinforced epoxy composite over titanium alloy". Diss., Columbia, Mo. : University of Missouri-Columbia, 2006. http://hdl.handle.net/10355/5871.
Texto completoThe entire dissertation/thesis text is included in the research.pdf file; the official abstract appears in the short.pdf file (which also appears in the research.pdf); a non-technical general description, or public abstract, appears in the public.pdf file. Title from title screen of research.pdf file (viewed on September 13, 2007). Vita. Includes bibliographical references.
Bail, Justin. "Non-Destructive Investigation & FEA Correlation on an Aircraft Sandwich Composite STructure". University of Akron / OhioLINK, 2007. http://rave.ohiolink.edu/etdc/view?acc_num=akron1196702586.
Texto completoBrod, Stephen P. 1970. "A testbed for investigating the effect of electrode structure on the performance of a solid oxide electrolysis system". Thesis, The University of Arizona, 1995. http://hdl.handle.net/10150/291547.
Texto completoBOLLINO, ARCANGELA. "QUASI STATIC GRAVITY SIGNATURES IN SLOW TECTONIC ZONES: ASSIMILATION OF NOVEL AEROSPACE DATA AND GEOPHYSICAL MODELING". Doctoral thesis, Università degli Studi di Milano, 2023. https://hdl.handle.net/2434/956505.
Texto completoWiteof, Zachary. "Exploratory Study on the Design of Combined Aero-Thermo-Structural Experiments in High Speed Flows". The Ohio State University, 2013. http://rave.ohiolink.edu/etdc/view?acc_num=osu1366213825.
Texto completoRinehart, Aidan Walker. "A Characterization of Seal Whisker Morphology and the Effects of Angle of Incidence on Wake Structure". Cleveland State University / OhioLINK, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=csu1483991011265196.
Texto completoMiller, Samuel C. "Fluid-Structure Interaction of a Variable Camber Compliant Wing". University of Dayton / OhioLINK, 2015. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1428575972.
Texto completoMagal, Rithvik. "Development and validation of a mathematical model for a monotube automotive damper". Master's thesis, Alma Mater Studiorum - Università di Bologna, 2021. http://amslaurea.unibo.it/22951/.
Texto completoByrd, Alex W. "Fluid-Structure Interaction Simulations of a Flapping Wing Micro Air Vehicle". Wright State University / OhioLINK, 2014. http://rave.ohiolink.edu/etdc/view?acc_num=wright1401559891.
Texto completoHart, Peter Bartholomew. "A plm implementation for aerospace systems engineering-conceptual rotorcraft design". Thesis, Georgia Institute of Technology, 2009. http://hdl.handle.net/1853/28278.
Texto completoFernández, Bravo Elena. "Modelling and testing of a solar panel structure for KNATTE (Kinesthetic Node and Autonomous Table-Top Emulator)". Thesis, Luleå tekniska universitet, Institutionen för system- och rymdteknik, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-87200.
Texto completoMikol, Collin Everett. "Design, Modeling, and Experimental Testing of a Variable Stiffness Structure for Shape Morphing". The Ohio State University, 2018. http://rave.ohiolink.edu/etdc/view?acc_num=osu1523454926569658.
Texto completoMills, Austin Shelley. "The Structural Suitability of Tensegrity Aircraft Wings". University of Dayton / OhioLINK, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1590172090108379.
Texto completoKnöös, Franzén Ludvig y Erik Magnusson. "Weight Penalty Methods for Conceptual Aircraft Design". Thesis, Linköpings universitet, Fluida och mekatroniska system, 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-175012.
Texto completoPesich, Justin M. "Steady Aeroelastic Response Prediction and Validation for Automobile Hoods". The Ohio State University, 2017. http://rave.ohiolink.edu/etdc/view?acc_num=osu1482329426783128.
Texto completoWilmoth, Nathan G. "Determining the Mechanical Properties of Lattice Block Structures". Cleveland State University / OhioLINK, 2013. http://rave.ohiolink.edu/etdc/view?acc_num=csu1366275566.
Texto completoReilly, Daniel Oliver. "Inlet Distortion Effects on the Unsteady Aerodynamics of a Transonic Fan Stage". Wright State University / OhioLINK, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=wright1482139741887976.
Texto completoJenett, Benjamin (Benjamin Eric). "Digital material aerospace structures". Thesis, Massachusetts Institute of Technology, 2015. http://hdl.handle.net/1721.1/101837.
Texto completoCataloged from PDF version of thesis.
Includes bibliographical references (pages 71-76).
This thesis explores the design, fabrication, and performance of digital materials in aerospace structures in three areas: (1) a morphing wing design that adjusts its form to respond to different behavioral requirements; (2) an automated assembly method for truss column structures; and (3) an analysis of the payload and structural performance requirements of space structure elements made from digital materials. Aerospace structures are among the most difficult to design, engineer, and manufacture. Digital materials are discrete building block parts, reversibly joined, with a discrete set of positions and orientations. Aerospace structures built from digital materials have high performance characteristics that can surpass current technology, while also offering potential for analysis simplification and assembly automation. First, this thesis presents a novel approach for the design, analysis, and manufacturing of composite aerostructures through the use of digital materials. This approach can be used to create morphing wing structures with customizable structural properties, and the simplified composite fabrication strategy results in rapid manufacturing time with future potential for automation. The presented approach combines aircraft structure with morphing technology to accomplish tuned global deformation with a single degree of freedom actuator. Guidelines are proposed to design a digital material morphing wing, a prototype is manufactured and assembled, and preliminary experimental wind tunnel testing is conducted. Seconds, automatic deployment of structures has been a focus of much academic and industrial work on infrastructure applications and robotics in general. This thesis presents a robotic truss assembler designed for space applications - the Space Robot Universal Truss System (SpRoUTS) - that reversibly assembles a truss column from a feedstock of flat-packed components, by folding the sides of each component up and locking onto the assembled structure. The thesis describes the design and implementation of the robot and shows that an assembled truss compares favorably with prior truss deployment systems. Thirds, space structures are limited by launch shroud mass and volume constraints. Digital material space structures can be reversibly assembled on orbit by autonomous relative robots using discrete, incremental parts. This will enable the on-orbit assembly of larger space structures than currently possible. The engineering of these structures, from macro scale to discrete part scale, is presented. Comparison with traditional structural elements is shown and favorable mechanical performance as well as the ability to efficiently transport the material in a medium to heavy launch vehicle. In summary, this thesis contributes the methodology and evaluation of novel applications of digital materials in aerospace structures.
by Benjamin Jenett.
S.M.
Villalva, Gómez Rodrigo. "Structure, Stability and Emissions of Lean Direct Injection Combustion, including a Novel Multi-Point LDI System for NOx Reduction". University of Cincinnati / OhioLINK, 2013. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1384427714.
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