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Dissertations / Theses on the topic 'Airplanes – Design and construction'

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Published: 4 June 2021

Last updated: 29 July 2024

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1

Kay, Jacob. "Control authority assessment in aircraft conceptual design." Thesis, This resource online, 1992. http://scholar.lib.vt.edu/theses/available/etd-03242009-040703/.

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2

Wang, Fan. "Conceptual design and analysis of a 3D flapping actuation mechanism." Thesis, The University of Sydney, 2006. https://hdl.handle.net/2123/28090.

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This thesis presents a novel full 3D (flapping, leading/lagging, feathering) actuation mechanism which may be applied in future small size flying vehicle development. It is prompted by the kinematics limitations of current flapping wing actuation systems for bird-size UAV. Firstly, the current zoological flight motions including insects flapping and birds’ flapping manoeuvrability as well as the creatures’ morphology background are investigated. Then it presents the conceptual design of a 3D flapping mechanism inspired from the pigeon thorax skeleton and being able to perform the high

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3

Jimeno, Jesus. "A physics based robust methodology for aerodynamic design analysis and optimization." Thesis, Georgia Institute of Technology, 2000. http://hdl.handle.net/1853/12472.

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4

Cabrera, Antonio Trani. "Combat aircraft scenario tradeoff models for conceptual design evaluation." Diss., Virginia Polytechnic Institute and State University, 1988. http://hdl.handle.net/10919/53920.

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The purpose of this research is to apply engineering-based knowledge to the field of combat aircraft survivability, and to create scenario-specific models in order to estimate the tradeoff between aircraft survivability and lethality metrics at the encounter and sortie levels. The development of scenario-specific models serves to identify and quantify technological changes that have Ieverage on the overall performance of the aircraft from a survivability point of view. Also, the models focus on the fighter aircraft susceptibility assessment and are capable of incorporating outputs from offline

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5

Rohl, Peter Jurgen. "A multilevel decomposition procedure for the preliminary wing design of a high-speed civil transport aircraft." Diss., Georgia Institute of Technology, 1995. http://hdl.handle.net/1853/11827.

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6

Scharl, Julien. "Formulation and implementation of a methodology for dynamic modeling and simulation in early aerospace design." Diss., Georgia Institute of Technology, 2001. http://hdl.handle.net/1853/12973.

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7

Upton, Eric George. "An Intelligent, Robust Approach to Volumetric Aircraft Sizing." Diss., Georgia Institute of Technology, 2007. http://hdl.handle.net/1853/16128.

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Advances in computational power have produced great strides in the later design and production portions of an aircraft s life cycle, and these advances have included the internal layout component of the design and manufacturing process. However, conceptual and preliminary design tools for internal layout remain primarily based on historical regressions and estimations a situation that becomes untenable when considering revolutionary designs or component technologies. Bringing internal layout information forward in the design process can encourage the same level of benefits enjoyed by other d

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8

Kelly, John H. "Rule-based fuselage and spine and cross-section methods for computer aided design of aircraft components." Thesis, This resource online, 1993. http://scholar.lib.vt.edu/theses/available/etd-06232009-063138/.

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9

Kim, Inn B. "Development and analysis of elastically tailored composite star shaped beam sections." Diss., Available online, Georgia Institute of Technology, 2004:, 2003. http://etd.gatech.edu/theses/available/etd-04062004-164703/unrestricted/kim%5Finn%5Fb%5F200312%5Fphd.pdf.

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10

Soban, Danielle Suzanne. "A methodology for the probabalistic assessment of system effectiveness as applied to aircraft survivability and susceptibiliy." Diss., Georgia Institute of Technology, 2001. http://hdl.handle.net/1853/11739.

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11

Kirby, Michelle Rene. "A methodology for technology identification, evaluation, and selection in conceptual and preliminary aircraft design." Diss., Georgia Institute of Technology, 2001. http://hdl.handle.net/1853/12042.

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12

Grieshaber, Michele Marie. "Interactive calculation of cross-sectional areas for aircraft design and analysis." Thesis, This resource online, 1988. http://scholar.lib.vt.edu/theses/available/etd-04272010-020357/.

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13

Ellwood, Jeffrey L. "Design and construction of a composite airframe for UAV research." Thesis, Monterey, California : Naval Postgraduate School, 1990. http://handle.dtic.mil/100.2/ADA232422.

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Thesis (M.S. in Aeronautical Engineering)--Naval Postgraduate School, June 1990.<br>Thesis Advisor(s): Howard, Richard M. Second Reader: Lindsey, Gerald H. "June 1990." Description based on signature page as viewed on October 21, 2009. DTIC Identifier(s): Composite materials, ducted fan, airframes, vertical takeoff aircraft, remotely piloted vehicles. Author(s) subject terms: UAV, composites, AROD, TDF, RPV, ducted fan, vertical takeoff. Includes bibliographical references (p. 74-75). Also available online.

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14

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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15

Dewitz, Michael B. "The effect of a fillet on a wing/body junction flow." Thesis, Virginia Tech, 1988. http://hdl.handle.net/10919/43843.

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16

Strauch, Gregory J. "Integrated multi-disciplinary design of a sailplane wing." Thesis, Virginia Tech, 1985. http://hdl.handle.net/10919/45660.

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<p>The objective of this research is to investigate the techniques and payoffs of integrated aircraft design. Lifting line theory and beam theory are used for the analysis of the aerodynamics and the structures of a composite sailplane wing. The wing is described by 33 - 34 design variables which involve the planform geometry, the twist distribution, and thicknesses of the spar caps, spar webs, and the skin at various stations along the wing. The wing design must satisfy 30 â 31 aeroelastic, structural, aerodynamic, and performance constraints.</p> <p> Two design procedures are inve

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17

DeLaurentis, Daniel A. "A probabilistic approach to aircraft design emphasizing stability and control uncertainties." Diss., Georgia Institute of Technology, 1998. http://hdl.handle.net/1853/12948.

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18

Ippolito, Corey A. "Software architectures for flight simulation." Thesis, Georgia Institute of Technology, 2000. http://hdl.handle.net/1853/15749.

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19

Gonzalez, Luis F. "Robust evolutionary methods for multi-objective and multdisciplinary design optimisation in aeronautics." Phd thesis, School of Aerospace, Mechanical and Mechatronic Engineering, 2005. http://hdl.handle.net/2123/6296.

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20

Wong, Kee Choon. "The development of a low-cost research R.P.V. system." Thesis, The University of Sydney, 1992. https://hdl.handle.net/2123/26648.

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Flight testing is recognised to be the definitive validation of an aerodynamic concept or of an aircraft configuration’s performance. However, flight testing of manned aircraft presents concerns for safety and increasingly prohibitive cost requirements. Complementing wind tunnels, an instrumented Remotely Piloted Vehicle (RPV) is a valuable tool for aeronautical research, with which many aspects of flight mechanics and applied aerodynamics can be investigated economically before the final design of the full size prototype. The aim of this research project is to develop a research RPV system wi

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21

Hines, Nathan Robert. "A probabilistic methodology for radar cross section prediction in conceptual aircraft design." Diss., Georgia Institute of Technology, 2001. http://hdl.handle.net/1853/12517.

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22

Malone, Brett. "Multidisciplinary optimization in aircraft design using analysis technology models." Thesis, This resource online, 1991. http://scholar.lib.vt.edu/theses/available/etd-10102009-020042/.

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23

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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24

Nafziger, John S. "Reverse parameterization of B-spline surfaces for data transfer." Thesis, This resource online, 1993. http://scholar.lib.vt.edu/theses/available/etd-06302009-040414/.

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25

Arledge, Thomas K. "ACSYNT aerodynamic estimation : an examination and validation for use in conceptual design /." Thesis, This resource online, 1993. http://scholar.lib.vt.edu/theses/available/etd-12052009-020129/.

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26

Marx, William J. "Integrating design and manufacturing for the high speed civil transport." Diss., Georgia Institute of Technology, 1996. http://hdl.handle.net/1853/12410.

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27

Patil, Mayuresh J. "Nonlinear aeroelastic analysis, flight dynamics, and control of a complete aircraft." Diss., Georgia Institute of Technology, 1999. http://hdl.handle.net/1853/12099.

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28

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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29

Jones, Robert W. "Intersection and filleting of non-uniform B-spline surfaces." Thesis, Virginia Tech, 1991. http://hdl.handle.net/10919/42189.

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<p>Preliminary aircraft design codes requIre a more complete and integrated geometry definition than that used by conceptual design codes. This thesis documents the design and creation of an interactive CAD system which converts the geometry descriptions commonly used in conceptual aircraft design codes to descriptions that meet the requirements of preliminary design systems. In particular, the conversion of ACSYNT Hermite surface data of aircraft models to the non-uniform hi-cubic B-Spline surface representation is addressed. The topics discussed in this thesis include the design and developm

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30

Hall, Neil Scott. "Impact of data modeling and database implementation methods on the optimization of conceptual aircraft design." Thesis, Georgia Institute of Technology, 1996. http://hdl.handle.net/1853/16847.

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31

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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32

Bryant, David. "Design and prototyping of an aircraft to maximize the triaviation score." University of Western Australia. School of Mechanical Engineering, 2009. http://theses.library.uwa.edu.au/adt-WU2009.0113.

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This thesis describes some of the processes and results obtained during the design and prototyping of a single seat experimental aircraft. The major aim was to maximise the Triaviation score of the aircraft. This score is a combination of the top speed, the stall speed and the rate of climb. The aircraft has been designed constructed, inspected and flown. The process of designing and prototyping is outlined in this thesis. Details are provided regarding preliminary design, numerical optimisation and the process of building the prototype. The aircraft registered VH-ZYY is a shoulder wing monopl

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33

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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34

Unger, Eric Robert. "Computational aspects of the integrated multi-disciplinary design of a transport wing." Thesis, Virginia Tech, 1990. http://hdl.handle.net/10919/42125.

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Past research at this university has proven the feasibility of the multi-disciplinary design of a complex system involving the complete interaction of aerodynamics and structural mechanics. Critical to this design process, is the ability to accurately and efficiently calculate the sensitivities of the involved quantities (such as drag and dynamic pressure) with respect to the design variables. These calculations had been addressed in past research, but it was felt that insufficient accuracy had been obtained. The focus of this research was to improve the accuracy of these sensitivity calculati

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35

Papay, Michael L. "A general inverse design procedure for aerodynamic bodies." Diss., Virginia Tech, 1994. http://hdl.handle.net/10919/38556.

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36

Harman, Alex Bruce Mechanical &amp Manufacturing Engineering Faculty of Engineering UNSW. "Optimisation and improvement of the design of scarf repairs to aircraft." Awarded by:University of New South Wales. School of Mechanical and Manufacturing Engineering, 2006. http://handle.unsw.edu.au/1959.4/26788.

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Flush repairs to military aircraft are expected to become more prevalent as more thick skin composites are used, particularly on the surface of the fuselage, wings and other external surfaces. The use of these repairs, whilst difficult to manufacture provide an aerodynamic, ???stealthy??? finish that is also more structurally efficient than overlap repairs. This research was undertaken to improve the design methodology of scarf repairs with reduced material removal and to investigate the damage tolerance of scarf repair to low velocity impact damage. Scarf repairs involve shallow bevel angles

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37

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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38

Hasan, Shahab. "An object-oriented, PHIGS-based Internal Layout Module for aircraft design." Thesis, This resource online, 1993. http://scholar.lib.vt.edu/theses/available/etd-03032009-040349/.

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39

Lucas, Tamara J. H. "Formulation and solution of hierarchical decision support problems." Thesis, Georgia Institute of Technology, 1995. http://hdl.handle.net/1853/17291.

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40

Msomi, Velaphi. "Modelling and testing smart aileron servo tabs : developing simulation tools for smart materials." Thesis, Cape Peninsula University of Technology, 2015. http://hdl.handle.net/20.500.11838/2150.

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Thesis (DTech (Mechanical Engineering))--Cape Peninsula University of Technology, 2015.<br>This dissertation addresses the development and the testing of a simulation tool to be used to predict the behaviour of smart material/structures. Along with the development of the simulation tool, a new form of the model describing the behaviour of shape-memory alloy was developed and implemented. The proposed model was developed based on the existing cosine model, conventionally used in literature, but it uses hyperbolic tangent functions. The hyperbolic tangent function was chosen so as to allow the s

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41

Nam, Taewoo. "A Generalized Sizing Method for Revolutionary Concepts under Probabilistic Design Constraints." Diss., Georgia Institute of Technology, 2007. http://hdl.handle.net/1853/14575.

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Internal combustion (IC) engines that consume hydrocarbon fuels have dominated the propulsion systems of air-vehicles for the first century of aviation. In recent years, however, growing concern over rapid climate changes and national energy security has galvanized the aerospace community into delving into new alternatives that could challenge the dominance of the IC engine. Nevertheless, traditional aircraft sizing methods have significant shortcomings for the design of such unconventionally powered aircraft. First, the methods are specialized for aircraft powered by IC engines, and thus are

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42

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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43

Gloudemans, James R. "Filleting of aircraft components using non-uniform B-spline surfaces." Thesis, Virginia Tech, 1989. http://hdl.handle.net/10919/44637.

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<p>Conceptual and preliminary aircraft design codes have different geometry requirements. Conceptual design codes use component based models, while preliminary design codes require a more complete and integrated geometry. An automatic procedure to convert between the two types of models would prevent geometry inconsistencies and speed up the design process. This thesis describes some of the concepts and algorithms necessary to develop such a procedure. Specifically, the theory and development of C2 continuous fillets between aircraft components is discussed. B-spline surface generation f

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44

Rivera, Francisco. "An object-oriented method of mission profile input for aircraft design." Thesis, This resource online, 1993. http://scholar.lib.vt.edu/theses/available/etd-09122009-040526/.

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45

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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46

Zhao, Wei. "Feature-Based Hierarchical Knowledge Engineering for Aircraft Life Cycle Design Decision Support." Diss., Georgia Institute of Technology, 2007. http://hdl.handle.net/1853/14639.

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The design process of aerospace systems is becoming more and more complex. As the process is progressively becoming enterprise-wide, it involves multiple vendors and encompasses the entire life-cycle of the system, as well as a system-of-systems perspective. The amount of data and information generated under this paradigm has increased exponentially creating a difficult situation as it pertains to data storage, management, and retrieval. Furthermore, the data themselves are not suitable or adequate for use in most cases and must be translated into knowledge with a proper level of abstraction.

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47

Pfaender, Jens Holger. "Competitive Assessment of Aerospace Systems using System Dynamics." Diss., Georgia Institute of Technology, 2006. http://hdl.handle.net/1853/14014.

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Aircraft design has recently experienced a trend away from performance centric design towards a more balanced approach with increased emphasis on engineering an economically successful system. This approach focuses on bringing forward a comprehensive economic and life-cycle cost analysis, which can be addressed by the introduction of a dynamic method allowing the analysis of the future attractiveness of such a concept in the presence of uncertainty. One way of addressing this is through the use of a competitive market model. However, existing market models do not focus on the dynamics of the m

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48

Jayaram, Uma. "Extracting dimensional geometric parameters from B-spline surface models." Diss., Virginia Tech, 1991. http://hdl.handle.net/10919/37877.

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In an integrated design environment, the common thread between the different design stages is usually the geometric model of the part. However, the requirements for the geometric definition of the design is usually different for each stage. The transformation of data between these different stages is essential for the success of the integrated design environment. For example, conceptual design systems usually deal with geometric dimensional parameters (e.g. length, radius, etc.) whereas preliminary design systems frequently require the geometry definition to be in the form of surface models.

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49

Mason, Kevin Richard. "Development of numerical schemes to improve the efficiency of CFD simulation of high speed viscous aerodynamic flows." Thesis, Swansea University, 2013. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.678434.

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50

Ha, Kwangtae. "A Combined Piezoelectric Composite Actuator and Its Application to Wing/Blade Tips." Diss., Georgia Institute of Technology, 2005. http://hdl.handle.net/1853/7575.

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A novel combined piezoelectric-composite actuator configuration is proposed and analytically modeled in this work. The actuator is a low complexity, active compliant mechanism obtained by coupling a modified star cross sectional configuration composite beam with a helicoidal bimorph piezoelectric actuator coiled around it. This novel actuator is a good candidate as a hinge tension-torsion bar actuator for a helicopter rotor blade flap or blade tip and mirror rotational positioning. In the wing tip case, the tip deflection angle is different only according to the aerodynamic moment depending

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