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Dissertations / Theses on the topic 'Airplane structures'

Author: Grafiati

Published: 4 June 2021

Last updated: 6 February 2022

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1

Llopart, Prieto Llorenç. "Modelling And Analysis Of Crack Turning On Aeronautical Structures." Doctoral thesis, Universitat Politècnica de Catalunya, 2007. http://hdl.handle.net/10803/6055.

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La motivació de la tesis deriva en el interès de la indústria aeronàutica a explotar, per mitjà d'un disseny adaptat, la utilització del gir d'esquerda per protegir els reforços situats davant una esquerda que s'està propagant en la xapa d'una estructura integral. L'objectiu principal és l'avaluació i predicció del gir d'esquerda en situacions de càrrega pròximes a Mode I, proporcionant una eina de modelització i un criteri confident. L'entorn industrial sota el qual s'ha realitzat aquest treball requereix una predicció ràpida del comportament estructural proporcionant informació útil als cons

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2

Swanson, Gary D. "Structural efficiency study of composite wing rib structures." Thesis, This resource online, 1987. http://scholar.lib.vt.edu/theses/available/etd-04292010-020010/.

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3

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

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4

Koh, Yeow Leung 1976. "In-situ structural health monitoring of composite repair patches." Monash University, Dept. of Mechanical Engineering, 2002. http://arrow.monash.edu.au/hdl/1959.1/7698.

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5

Ragon, Scott A. "Optimization of composite box-beam structures including effects of subcomponent interaction /." This resource online, 1994. http://scholar.lib.vt.edu/theses/available/etd-06162009-063327/.

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6

Aljets, Dirk. "Acoustic emission source location in composite aircraft structures using modal analysis." Thesis, University of South Wales, 2011. https://pure.southwales.ac.uk/en/studentthesis/acoustic-emission-source-location-in-composite-aircraft-structures-using-modal-analysis(6871e94b-6e94-4efd-b563-41b254ee27b4).html.

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The aim of this research work was to develop an Acoustic Emission (AE) source location method suitable for Structural Health Monitoring (SHM) of composite aircraft structures. Therefore useful key signal features and sensor configurations were identified and the proposed method was validated using both artificially generated AE as well as actual AE resulting from damage. Acoustic Emission is a phenomenon where waves are generated in stressed materials. These waves travel through the material and can be detected with suitable sensors on the surface of the structure. These stress waves are attri

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7

Seitz, Timothy J. "Formulation of a structural model for flutter analysis of low aspect ratio composite aircraft wings." Diss., This resource online, 1992. http://scholar.lib.vt.edu/theses/available/etd-05042006-164511/.

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8

Zhou, Weiyu. "Crash-impact behavior of graphite/epoxy composite sine wave webs." Diss., Georgia Institute of Technology, 1989. http://hdl.handle.net/1853/12226.

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9

Mosinyi, Bao Rasebolai Awerbuch Jonathan Lau Alan C. W. Tan Tein-Min. "Fatigue damage assessment of high-usage in-service aircraft fuselage structure /." Philadelphia, Pa. : Drexel University, 2007. http://hdl.handle.net/1860/2762.

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10

Dayyani, Iman. "Mechanical behavior of composite corrugated structures for skin of morphing aircraft." Thesis, Swansea University, 2015. https://cronfa.swan.ac.uk/Record/cronfa42865.

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Corrugated panels have gained considerable popularity in a range of engineering applications, particularly in morphing skin applications due to their remarkable anisotropic characteristics. They are stiff to withstand the aerodynamic loads and flexible to enable the morphing deformations. In this thesis a detailed review of the literature on corrugated structures is presented. The specific characteristics of corrugated structures such as: high anisotropic behaviour, high stiffness and good durability, lightness and cost effectiveness are discussed comprehensively. However for the application i

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11

Zhang, Haochuan. "Nonlinear aeroelastic effects in damaged composite aerospace structures." Thesis, Georgia Institute of Technology, 1996. http://hdl.handle.net/1853/12150.

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12

Rais-Rohani, Masoud. "Integral aerodynamic-structural-control wing design." Diss., Virginia Tech, 1991. http://hdl.handle.net/10919/39867.

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13

Hubner, James Paul. "An investigation of quasiperiodic structures in the vortical flow over Delta wing configuration." Diss., Georgia Institute of Technology, 1995. http://hdl.handle.net/1853/12243.

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14

Ma, Leong. "Crack link up and residual strength of aircraft structure containing multiple site damage /." Thesis, Connect to this title online; UW restricted, 1999. http://hdl.handle.net/1773/7039.

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15

Luo, Huageng. "Damage detection and health monitoring of structures using dynamic response and neural network techniques." Diss., Georgia Institute of Technology, 1996. http://hdl.handle.net/1853/12929.

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16

Jin, Jingzhe. "A mixed mode function : boundary element method for very large floating structure : water interaction systems excited by airplane landing impacts." Thesis, University of Southampton, 2008. https://eprints.soton.ac.uk/52018/.

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This thesis develops a mixed mode function – boundary element method (BEM) to analyze the dynamics of an integrated airplane – floating structure – water interaction system subject to airplane landing impacts. The airplane and the floating structure are treated as two solid substructures of which the motions are represented by their respective modal functions. The landing gear system of the airplane is modelled with a few linear spring – damper units connecting the airplane and the floating structure. The water is assumed to be inviscid and incompressible and the fluid motion is irrotational.

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17

Tjatra, I. Wayan. "Transonic aeroelastic analysis of systems with structural nonlinearities." Diss., Virginia Tech, 1991. http://hdl.handle.net/10919/39912.

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18

Huang, Ximing. "Structural optimization and its interaction with aerodynamic optimization for a high speed civil transport wing." Diss., Virginia Tech, 1994. http://hdl.handle.net/10919/40132.

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A variable-complexity design strategy with combined aerodynamic and structural optimization procedures is presented for the high speed civil transport design (HSCT). Variable-complexity analysis methods are used to reduce the computational expense. A finite element-model based structural optimization procedure with flexible loads is implemented to evaluate the wing bending material weight. Static aeroelastic effects, evaluated through the comparison of rigid and flexible wing models, are found to be small in the HSCT design. The results of structural optimization are compared with two quasi-em

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19

Dater, Brian Scott. "Structural acoustic optimization of an aircraft fuselage using the complex method." Thesis, Georgia Institute of Technology, 1997. http://hdl.handle.net/1853/17689.

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20

Kannappan, Laxmikant Aerospace Civil &amp Mechanical Engineering Australian Defence Force Academy UNSW. "Damage detection in structures using natural frequency measurements." Awarded by:University of New South Wales - Australian Defence Force Academy. Aerospace, Civil & Mechanical Engineering, 2009. http://handle.unsw.edu.au/1959.4/44852.

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In the last two decades, the emphasis in aircraft maintenance has been on developing online structural health monitoring systems to replace conventional non destructive inspection techniques which require considerable down-time, human effort and cost. Vibration based damage detection is one of the most promising techniques for implementation in Structural Health Monitoring (SHM). In vibration based methods, the presence of damage is detected by monitoring changes in one of the dynamic parameters of the structure, resonant frequencies, modeshapes or damping characteristics. Compared to modes

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21

Crane, Scott P. "Structural acoustic design optimization of cylinders using FEM/BEM." Thesis, Georgia Institute of Technology, 1995. http://hdl.handle.net/1853/17699.

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22

Ajaj, Rafic Mohammad. "Design, modelling and optimisation of morphing structures for medium altitude long endurance UAVs." Thesis, Swansea University, 2013. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.678283.

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23

Potter, Charles Lee. "A conceptual level framework for wing box structural design and analysis using a physics-based approach." Diss., Georgia Institute of Technology, 2016. http://hdl.handle.net/1853/54940.

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There are many challenges facing the aerospace industry that can be addressed with new concepts, technologies, and materials. However, current design methods make it difficult to include these new ideas early in the design of aircraft. This is especially true in the structures discipline, which often uses weight-based methods based upon statistical regressions of historical data. A way to address this is to use physics-based structural analysis and design to create more detailed structural data. Thus, the overall research objective of this dissertation is to develop a physics-based structural

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24

Kao, Pi-Jen. "Efficient methods for integrated structural-aerodynamic wing optimum design." Diss., Virginia Polytechnic Institute and State University, 1989. http://hdl.handle.net/10919/54211.

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The dissertation is focused on the large computational costs of integrated multidisciplinary design. Efficient techniques are developed to reduce the computational costs associated with integrated structural-aerodynamic design. First efficient methods for the calculations of the derivatives of the flexibility matrix and the aerodynamic influence coefficient matrix are developed. An adjoint method is used for the flexibility sensitivity, and a perturbation method is used for the aerodynamic sensitivity. Second a sequential optimization algorithm that employs approximate analysis methods is impl

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25

Polen, David M. "Integrated aerodynamic-structural design of a subsonic, forward- swept transport wing." Thesis, Virginia Tech, 1989. http://hdl.handle.net/10919/46059.

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<p>The introduction of composite materials and the ability to tailor these materials to improve aerodynamic and structural performance is having a distinct effect upon aircraft design. In order to optimize the efficiency of the design procedure, a design process which is more integrated than the traditional approach is required. Currently the utilization of such design procedures produces enormous computational costs. An ongoing effort to reduce these costs is the development of efficient methods for cross-disciplinary sensitivities and approximate optimization techniques.</p> <p>The pr

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26

Good, Matthew G. "Development of a Variable Camber Compliant Aircraft Tail using Structural Optimization." Thesis, Virginia Tech, 2004. http://hdl.handle.net/10919/33976.

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The objectives of the research presented in this thesis are the development of a seven degree-of-freedom morphing airplane and the design and integration of a variable camber compliant tail. The morphing airplane was designed and manufactured to study the benefits of large planform changes and flight control morphing. Morphing capabilities of each wing consist of 8 in. wing extension and contraction, 40° of wing sweep and ±20.25° of outboard wing twist in addition to 6 in. of tail extension and contraction. Initial wind-tunnel tests proved that for a large range of lift coefficients, the optim

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27

Firesheets, Nathan. "Modeling the transmission loss of typical home constructions exposed to aircraft noise." Thesis, Georgia Institute of Technology, 2012. http://hdl.handle.net/1853/50133.

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Current aircraft noise guidelines are based primarily on outdoor sound levels. However, human perception is highly related to indoor response, particularly for residences. A research project has been conducted that provides insight into how typical residential dwelling envelopes affect sound transmitted indoors. A focus has been placed on the effect of residential dwelling envelopes on subsonic civil aircraft noise. Typical construction types across the United States have been identified and used to develop model predictions of outdoor-to-indoor transmission loss. While it was initially hypoth

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28

Thareja, Rajiv R. "Efficient single-level solution of hierarchical problems in structural optimization." Diss., Virginia Polytechnic Institute and State University, 1986. http://hdl.handle.net/10919/71195.

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Engineering design is hierarchical in nature, and if no attempt is made to benefit from this hierarchical nature, design optimization can be very expensive. There are two alternatives to taking advantage of the hierarchical nature of structural design problems. Multi-level optimization techniques incorporate the hierarchy at the formulation stage, and result in the coordinated optimization of a hierarchy of subsystems. The use of multi-level optimization techniques often necessitates the use of equality constraints. These constraints can sometimes cause numerical difficulties during optimizati

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29

Ragon, Scott Alan. "Optimization of composite box-beam structures including effects of subcomponent interaction." Thesis, Virginia Tech, 1994. http://hdl.handle.net/10919/43336.

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Minimum mass designs are obtained for a simple box beam structure subject to bending, torque and combined bending/torque load cases. These designs are obtained subject to point strain and linear buckling constraints. The present work differs from previous efforts in that special attention is payed to including the effects of subcomponent panel interaction in the optimal design process. Two different approaches are used to impose the buckling constraints. When the global approach is used, buckling constraints are imposed on the global structure via a linear eigenvalue analysis. This approach al

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30

Goksel, Lorens Sarim. "Fatigue and damage tolerance assessment of aircraft structure under uncertainty." Thesis, Georgia Institute of Technology, 2013. http://hdl.handle.net/1853/49124.

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This thesis presents a new modeling framework and application methodology for the study of aircraft structures. The framework provides a ‘cradle-to-grave’ approach to structural analysis of a component, where structural integrity encompasses all phases of its lifespan. The methodology examines the holistic structural design of aircraft components by integrating fatigue and damage tolerance methodologies. It accomplishes this by marrying the load inputs from a fatigue analysis for new design, into a risk analysis for an existing design. The risk analysis incorporates the variability found from

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31

Vandeveld, Thierry F. R. "Etude expérimentale multisensorielle de la dynamique des impacts d'oiseaux sur structures d'avions." Doctoral thesis, Universite Libre de Bruxelles, 2009. http://hdl.handle.net/2013/ULB-DIPOT:oai:dipot.ulb.ac.be:2013/210274.

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Chaque année, d'innombrables collisions se produisent entre des avions en vol et des oiseaux. L'impact aviaire, menace redoutée par les pilotes, concerne tant l'aviation civile que son pendant militaire. Les statistiques démontrent que, même si fort heureusement le nombre d'accidents graves reste limité, les incidents sont de plus en plus nombreux.<p>Parmi les acteurs qui luttent contre ce danger, les constructeurs d'avions jouent un rôle prépondérant. Contraints par des réglementations internationales, ils s'attachent à produire des éléments de structure qui résistent à l'impact d'oiseaux.<p>

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32

Fulton, Neale Leslie Aerospace &amp Mechanical Engineering Australian Defence Force Academy UNSW. "Regional airspace design: a structured systems engineering approach." Awarded by:University of New South Wales - Australian Defence Force Academy. School of Aerospace and Mechanical Engineering, 2002. http://handle.unsw.edu.au/1959.4/38722.

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There has been almost fifteen years of political controversy surrounding changes to the rules and procedures by which aircraft conduct their flight within regional Australia. Decisions based on a predominately heuristic (rule of thumb) approach to design have had many adverse consequences for the integrity of the proximity warning function. A sound mathematical model is required to establish this function on a mature engineering foundation. To achieve this, the proximity warning function has been investigated as a hybrid-system. This approach recognises the dual nature of the design: that airc

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33

Raub, Corey Bevan. "Geometric analysis of axisymmetric disk forging." Ohio : Ohio University, 2000. http://www.ohiolink.edu/etd/view.cgi?ohiou1172778393.

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34

Bhardwaj, Manoj K. "A CFD/CSD Interaction Methodology for Aircraft Wings." Diss., web access:, 1997. http://scholar.lib.vt.edu/theses/public/etd-91097-165322/etd-title.html.

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35

Goltsch, Mandy. "A small perturbation based optimization approach for the frequency placement of." Diss., Atlanta, Ga. : Georgia Institute of Technology, 2009. http://hdl.handle.net/1853/28173.

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Thesis (M. S.)--Aerospace Engineering, Georgia Institute of Technology, 2009.<br>Committee Chair: Mavris, Dimitri; Committee Member: Bauchau, Olivier; Committee Member: Schrage, Daniel; Committee Member: Volovoi, Vitali; Committee Member: Yu, Wenbin.

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36

Rebrova, Tatiana. "Galerie letecké techniky a tradic letectví na letišti Medlánky v Brně." Master's thesis, Vysoké učení technické v Brně. Fakulta stavební, 2016. http://www.nusl.cz/ntk/nusl-354967.

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Area of the airport Medlánky is situated on the border of city districts Brno-Medlánky and Brno-Komín near the nature reserve "Medlánecké kopce". The designed gallery of aviation is a two-storey building, which consists of three parts. The main part is the exhibition space for airplanes, which is formed of a single-storey long-span hall, with the two-storey entrance part of the complex of buildings connected to it, in which are situated the area of the entrance, the training center (detached workplace of the institute of aviation FS BUT in Brno) and the administration. In the building of the o

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37

Bělehradová, Věra. "Galerie letecké techniky a tradic letectví na letišti Medlánky v Brně." Master's thesis, Vysoké učení technické v Brně. Fakulta stavební, 2016. http://www.nusl.cz/ntk/nusl-354975.

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Sport Airport complex Brno-Medlánky is nestled in the undulating hilly terrain in fields just beyond populated areas in Brno-Medlánky. The history of the airport dates back to 1924 when it was built the first wooden hangar for training purposes glider flights. Current state urban of airport is orderless. The aim is to streamline the complex and give it the order, allowing easy and efficient orientation in the space. The main intervention was the creation of a new central building - Aviation Museum. The concept of the design is based on the division of the whole area into two branches - communi

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38

Kao, Huai-En, and 高懷恩. "Structure Design and Analysis of a Ultralight Airplane." Thesis, 2009. http://ndltd.ncl.edu.tw/handle/15472723371105715965.

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碩士<br>國立屏東科技大學<br>車輛工程系所<br>97<br>This research presents the structural design and analysis, including normal mode , structural stiffness and impact strength, for Ultralight Aircraft by using Finite Element Analysis (FEA). The finite element model of the full aircraft structure is established by using the software ANSYS. Static tests are first conducted on the main aircraft structure to obtain the weight and center of gravity in order to validate the finite element models. The mechanical properties of aircraft structures are obtained from the tensile tests. Normal mode analysis was performed t

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39

Rocha, Joana Luíz Torres da. "An experimental study and flight testing of active aeroelastic aircraft wing structures." 2005. http://hdl.handle.net/1828/783.

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40

Yavuz, Mehmet Metin. "Origin and control of the flow structure and topology on delta wings /." Diss., 2006. http://gateway.proquest.com/openurl?url_ver=Z39.88-2004&rft_val_fmt=info:ofi/fmt:kev:mtx:dissertation&res_dat=xri:pqdiss&rft_dat=xri:pqdiss:3203830.

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41

Coetzee, Gerhard. "'n Aanpasbare energieabsorbeerder vir 'n helikoptersitplek." Thesis, 2014. http://hdl.handle.net/10210/12100.

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M.Ing. (Mechanical Engineering)<br>The development of crashworthy seats for helicopters during the past three decades is discussed. The primary design criteria is mentioned and the disadvantages of crashworthy seats that are currently in use are highlighted. An hydraulic energy absorber which automatically compensates for the mass of the seat occupant was designed and a simulation model was developed. The concept for the control valve used was obtained from WARRICK [25]. Results of the simulations correlated well with those of WARRICK. A prototype of a mechanical/hydraulic accelerometer was de

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42

Harrison, Stephen J. "Military aircraft structural testing in Australia : supporting the ADF." 2004. http://arrow.unisa.edu.au:8081/1959.8/80477.

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This minor thesis examines whether or not the Australian Defence Force (ADF) needs an indigenous aircraft structural testing program for military aircraft. Aircraft structural testing is a major test and evaluation activity currently undertaken by the DSTO to provide structural integrity information about particular aircraft for the ADF. The ADF has required this testing to be undertaken because, in general terms, testing undertaken by an aircraft's manufacturer has not been sufficient to meet the needs of the ADF. The research was divided into five sub-problems, which examined the need for ai

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43

Christie, V. Latha. "Analysis Of Coupled-Resonator Slow-Wave Structures For Traveling-Wave Tubes For Aerospace Applications." Thesis, 2007. http://hdl.handle.net/2005/478.

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Through continued innovation and growth, traveling wave tube amplifiers (TWTAs) remains the microwave power amplifiers of choice in a wide range of high power microwave and millimeter-wave applications specifically for aerospace applications with the volume, weight, bandwidth and power constraints. These advances can be credited to device innovation, improved modeling and design and development of advanced materials and construction techniques. This thesis aims at advancing the present technology of TWTs with coupled resonator slow-wave structures (SWSs) by a combination of device innovation,

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44

Sahoo, Pradeep Kumar. "Strength Prediction And Fatigue De-Bond Growth In Bonded Joints In Metallic And Composite Structures." Thesis, 2010. http://hdl.handle.net/2005/2002.

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Large scale structures such as those in aerospace flight vehicles are made in parts and assembled. Joints are inevitable in these systems and they are potential threats to the structural integrity of the flight vehicles. Fastener and bonded joints are the most commonly used methods of joining in these structures. Among these, adhesive bonding has become more popular with the advent of composite structures, due to the presence of less number of points of stress concentration and the resulting benefit for static strength and fatigue life. In modern aircraft in which maximum percentage of comp

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