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Dissertations / Theses on the topic 'Aircraf'

Author: Grafiati

Published: 28 June 2021

Last updated: 1 February 2022

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1

Torres, Calderon Rosa Maria. "Multi-objective environmentally-friendly departure procedures for civil aircraf : modeling, optimization and robustness assessment." Toulouse 3, 2011. http://www.theses.fr/2011TOU30320.

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Cette thèse présente le concept MCDP (Multi-Criteria Departure Procedure), qui a comme objectif l’optimisation des procédures de départ afin de minimiser l’impact environnemental des avions. Ces impacts portent essentiellement sur les nuisances acoustiques, la qualité de l’air et l’émission des gaz d’effet de serre. Il n’existe pas une seule procédure capable de minimiser les trois critères simultanément. Le concept MCDP est donc modélisé par un problème d’optimisation multi-objectif sous contraintes. La technique de recherche directe MADS est utilisée pour obtenir les trajectoires Pareto opti

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2

Urbano, Simone. "Detection and diagnostic of freeplay induced limit cycle oscillation in the flight control system of a civil aircraf." Thesis, Toulouse, INPT, 2019. http://www.theses.fr/2019INPT0023/document.

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Cette étude est le résultat d’une thèse CIFRE de trois ans entre le bureau d’étude d’Airbus (domaine du contrôle de l’avion) et le laboratoire TéSA à Toulouse. L’objectif principal est de proposer, développer et valider une solution logicielle pour la détection et le diagnostic d’un type spécifique de vibrations des gouvernes de profondeur et direction, appelée oscillation en cycle limite (limit cycle oscillation ou LCO en anglais), basée sur les signaux existants dans les avions civils. LCO est un terme mathématique générique définissant un mode périodique indépendant de conditions initiales

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3

Dvořáček, Zdeněk. "Návrh hlavního podvozku pro letouny řady Zlín 40." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2021. http://www.nusl.cz/ntk/nusl-442850.

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This master thesis deals with the modernization of the main landing gear of the Z 143 LSi aircraft. The main emphasis is placed on optimizing of the landing gear shape and its deformation characteristics. Along with this change, variants made of different materials are examined. The landing load is calculated analytically and the load-bearing capacity of the structure is verified using the numerical FEM method. This work brings a possible replacement of the current chassis, which is production-intensive not only in time and money, but also in terms of cooperation with external companies. The o

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4

Bauer, David O. "A historical perspective of aircrew systems effects on aircraft design." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1996. http://handle.dtic.mil/100.2/ADA320281.

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Thesis (M.S. in Aeronautical Engineering) Naval Postgraduate School, September 1996.<br>Thesis advisor(s): Conrad F. Newberry. "September 1996." Includes bibliographical references (p. 99-100). Also available online.

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5

Megas, Vasileios. "Aircraft to Aircraft Connectivity Analysis." Thesis, KTH, Skolan för elektroteknik och datavetenskap (EECS), 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-254887.

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It is very common to feel the need to be connected, especially in cases where we are idle, such as in airplanes. Aircraft connectivity has already been implemented by using direct air-to-ground communication and satellite communication. However, since the current solutions are not satisfying, more ways to provide connectivity to aircraft are being researched. One solution is to use aircraft as relay nodes and forward signals to aircraft which are out of range of the ground base stations, creating an ad-hoc network.This thesis aims in evaluating the performance of such networks over the North A

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6

Federico, Claudio Antonio. "Dosimetria da radiação cósmica no interior de aeronaves no espaço aéreo Brasileiro." Universidade de São Paulo, 2011. http://www.teses.usp.br/teses/disponiveis/85/85131/tde-26012012-104504/.

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Neste trabalho, cujo objetivo foi fornecer subsídios que permitam estabelecer um sistema de dosimetria para as tripulações de aeronaves que operam no território nacional, foi desenvolvida uma técnica para realizar medições do equivalente de dose ambiente em aeronaves. Foi testado um detector ativo, para uso embarcado em aeronaves, avaliando-se sua adequação a este tipo específico de medição, assim como sua suscetibilidade às interferências magnética e eletromagnética. O equipamento foi calibrado em campos metrologicamente rastreados e foi verificado em um campo especial do laboratório europeu

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7

Serrano, Ignacio. "Unmanned Aircraft System (UAS) vs. Manned Aircraft System (MAS): A Military Aircraft Study." Digital Commons at Loyola Marymount University and Loyola Law School, 2015. https://digitalcommons.lmu.edu/etd/430.

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Unmanned Aerial Vehicles (UAVs) are common place in the 21st century, whether they are small to medium sized remotely piloted vehicles (aka drones) or large advanced Unmanned Aerial Systems with a preprogrammed flight path. There is anticipation that these Unmanned Systems will, in the future assume the roles of their traditional manned aircraft counterparts. There is also the perception that these Unmanned Systems should be developed partly because they would be less expensive when compared to their manned aircraft. This integrative paper asserts that this perception is not reality with regar

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8

Iskender, Hani. "Aircraft Simulator." Thesis, Linköping University, Department of Electrical Engineering, 2005. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-2936.

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<p>At Saab Bofors Dynamics there are projects running which purpose are to develop simulators for various weapon systems like RBS 70. In order to manage creating real working simulators Saab Bofors Dynamics has to do more research and this final thesis is a part of this process.</p><p>This final thesis has been performed at Saab Bofors Dynamics in the department of modelling and simulation, RTRKM, in Karlskoga. The purpose was to develop a control algorithm which makes it possible for an aircraft to behave real when controlling through a joystick.</p><p>The conclusions show that further improv

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9

Thompson, Brian G. "Aircraft agility." Thesis, This resource online, 1992. http://scholar.lib.vt.edu/theses/available/etd-09192009-040436/.

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10

Hacker, Earl W. "One-year UDP: a cost/benefit analysis of a proposed alternative to the Marine Corps' Unit Deployment Program for fighter aviation." Thesis, Monterey, California. Naval Postgraduate School, 1988. http://hdl.handle.net/10945/23337.

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Approved for public release; distribution is unlimited<br>The author examines the incremental costs and benefits associated with a change from six-month unit deployments to one-year unit deployments. The analysis is based primarily on five fighter squadrons participating in the Marine Corps' Unit Deployment Program and takes in the period July 1976 to October 1988. Regression analysis is used to project transportation cost savings of $4 million in real terms from FY 1989 through FY 1993. With a change to a one-year Unit Deployment Program, fighter squadrons should experience net increases

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11

Wan, Husain Wan Mohd Sufian Bin. "Maintainability prediction for aircraft mechanical components utilising aircraft feedback information." Thesis, Cranfield University, 2011. http://dspace.lib.cranfield.ac.uk/handle/1826/7272.

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The aim of this research is to propose an alternative approach to determine the maintainability prediction for aircraft components. In this research, the author looks at certain areas of the maintainability prediction process where missteps or misapplications most commonly occur. The first of these is during the early stage of the Design for Maintainability (DfMt) process. The author discovered the importance of utilising historical information or feedback information. The second area is during the maintainability prediction where the maintenance of components is quantified; here, the author p

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12

Black, Gary Douglas. "Aircraft configuration study for experimental 2-place aircraft and RPVs." Thesis, Monterey, California : Naval Postgraduate School, 1990. http://handle.dtic.mil/100.2/ADA227604.

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Thesis (M.S. in Aeronautical Engineering)--Naval Postgraduate School, March 1990.<br>Thesis Advisor(s): Howard, Richard M. Second Reader: Hauser, James P. "March 1990." Description based on signature page as viewed on August 25, 2009. DTIC Descriptor(s): Aerodynamic configurations, remotely piloted vehicles, military aircraft, lightweight, research aircraft, canard configurations, wings, aerodynamic drag, computer programs, scaling factor, aerodynamic stability, performance(engineering), comparison, microcomputers, trade off analysis, aeronautical engineering, theses. DTIC Identifier(s): Pushe

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13

Recktenwald, Bryan David Ahmed Anwar. "Aerodynamic testing of a circular planform concept aircraft." Auburn, Ala, 2008. http://repo.lib.auburn.edu/EtdRoot/2008/SUMMER/Aerospace_Engineering/Thesis/Recktenwald_Bryan_48.pdf.

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14

Ionescu, Irina Gabriela. "Aircraft noise regulation." Thesis, McGill University, 2004. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=82660.

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Aircraft noise is one of the most controversial environmental concerns in the aviation industry, partly due to the difficulty in harmonizing countries' regulation regarding this issue. The purpose of this thesis is to analyze the ways in which aircraft noise is regulated at the national and international levels, and to compare the legislative responses to aircraft noise issues in Europe and North America. Each of the four main chapters of the thesis takes into consideration a different aspect of the problem. The first chapter describes the objective and subjective ways of measuring airc

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15

彭遠輝 and Yuen-fai Alson Pang. "Managing aircraft noise." Thesis, The University of Hong Kong (Pokfulam, Hong Kong), 2002. http://hub.hku.hk/bib/B31255280.

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16

Wagner, Michael J. "AEW aircraft design." Thesis, Monterey, California. Naval Postgraduate School, 1992. http://hdl.handle.net/10945/23815.

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17

Brentnall, Adam Robert. "Aircraft arrival management." Thesis, University of Southampton, 2006. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.432622.

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Pang, Yuen-fai Alson. "Managing aircraft noise /." Hong Kong : University of Hong Kong, 2002. http://sunzi.lib.hku.hk/hkuto/record.jsp?B2543598x.

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19

Elsayed, M. A. N. "Aircraft trajectory optimization." Thesis, Loughborough University, 1985. https://dspace.lboro.ac.uk/2134/32873.

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A typical aircraft flight consists of three phases, namely climb, cruise and descent. The purpose of this research was to study the control schedules for a transport aircraft which would result in least fuel expenditure in each flight-segment.

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20

GongZhang, Hanlin, and Eric Axtelius. "Aircraft Winglet Design." Thesis, KTH, Skolan för teknikvetenskap (SCI), 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-276586.

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Aerodynamic drag can be decreased with respect to a wing’s geometry, and wingtip devices, so called winglets, play a vital role in wing design. The focus has been laid on studying the lift and drag forces generated by merging various winglet designs with a constrained aircraft wing. By using computational fluid dynamic (CFD) simulations alongside wind tunnel testing of scaled down 3D-printed models, one can evaluate such forces and determine each respective winglet’s contribution to the total lift and drag forces of the wing. At last, the efficiency of the wing was furtherly determined by eval

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21

Vallone, Michael. "Parameter Estimation of Fundamental Technical Aircraft Information Applied to Aircraft Performance." DigitalCommons@CalPoly, 2010. https://digitalcommons.calpoly.edu/theses/382.

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Inverse problems can be applied to aircraft in many areas. One of the disciplines within the aerospace industry with the most openly published data is in the area of aircraft performance. Many aircraft manufacturers publish performance claims, flight manuals and Standard Aircraft Characteristics (SAC) charts without any mention of the more fundamental technical information of the drag and engine data. With accurate tools, generalized aircraft models and a few curve-fitting techniques, it is possible to evaluate vehicle performance and estimate the drag, thrust and fuel consumption (TSFC) with

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22

Hintze, Joshua. "Autonomous landing of a rotary unmanned aerial vehicle in a non-cooperative environment using machine vision /." Diss., CLICK HERE for online access, 2004. http://contentdm.lib.byu.edu/ETD/image/etd359.pdf.

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23

Thate, Timothy J. Michels Adam S. "Requirements for digitized aircraft spotting (Ouija) board for use on U.S. Navy aircraft carriers /." Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2002. http://library.nps.navy.mil/uhtbin/hyperion-image/02sep%5FThate.pdf.

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Thesis (M.S. in Information Systems Management)--Naval Postgraduate School, September 2002.<br>Thesis advisor(s): Alex Bordetsky, Glenn Cook. Includes bibliographical references. Also available online.

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24

Li, Bo Lim Alvin S. "Multiple UAV simulation with multiresolution multistage models and decision support." Auburn, Ala., 2008. http://hdl.handle.net/10415/1547.

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25

Miao, Zhisong. "Aircraft engine performance and integration in a flying wing aircraft conceptual design." Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/7249.

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The increasing demand of more economical and environmentally friendly aero engines leads to the proposal of a new concept – geared turbofan. In this thesis, the characteristics of this kind of engine and relevant considerations of integration on a flying wing aircraft were studied. The studies can be divided into four levels: GTF-11 engine modelling and performance simulation; aircraft performance calculation; nacelle design and aerodynamic performance evaluation; preliminary engine installation. Firstly, a geared concept engine model was constructed using TURBOMATCH software. Based on paramet

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Seresinhe, R. "Impact of aircraft systems within aircraft operation : a MEA trajectory optimisation study." Thesis, Cranfield University, 2014. http://dspace.lib.cranfield.ac.uk/handle/1826/9261.

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Air transport has been a key component of the socio-economic globalisation. The ever increasing demand for air travel and air transport is a testament to the success of the aircraft. But this growing demand presents many challenges. One of which is the environmental impact due to aviation. The scope of the environmental impact of aircraft can be discussed from many viewpoints. This research focuses on the environmental impact due to aircraft operation. Aircraft operation causes many environmental penalties. The most obvious is the fossil fuel based fuel burn and the consequent greenhouse gas e

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Flodin, Linus, and Oscar Hag. "Energy Efficient Concept Aircraft." Thesis, KTH, Farkost och flyg, 2012. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-102886.

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A concept study for an environmentally friendly aircraft is made with the help of mathematical models. The aircraft has a capacity of 4 passengers and is powered by electrical engines and lithium-air batteries so that no greenhouse gases are emitted. The aim of the study is to find a concept that can compete with today’s petrol powered aircraft, with applications in entertainment flying and transportation. Flight conditions such as steady state flight and steady climbing are modeled to estimate the performance of the aircraft and to find the most efficient way to fly. A static stability analys

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Zhu, Zhongxi. "The aircraft rotation problem." Diss., Georgia Institute of Technology, 1994. http://hdl.handle.net/1853/21788.

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29

Swift, Adam. "Simulation of aircraft aeroelasticity." Thesis, University of Liverpool, 2011. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.569519.

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Aeroelastic phenomena such as flutter can have a detrimental effect on aircraft performance and can lead to severe damage or destruction. Buffet leads to a re- duced fatigue life and therefore higher operating costs and a limited performance envelope. As such the simulation of these aeroelastic phenomena is of utmost importance. Computational aeroelasticity couples computational fluid dynamics and computational structural dynamics solvers through the use of a transforma- tion method. There have been interesting developments over the years towards more efficient methods for predicting the flutt

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Sonei, Arash. "Designing A Conventional Aircraft." Thesis, KTH, Skolan för teknikvetenskap (SCI), 2014. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-153225.

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This paper is explaining the important design phases of dimensioning an unmanned conventional aircraft from scratch and will also design one according to a few chosen requirements. The design phases discussed will be all from wing dimensioning to stability and spin recovery, aircraft performance requirements and how to select a motor which overcomes these. As well as the optimal rate of climb for improved efficiency is discussed. In the end an aircraft which manages the set requirements and is stable in pitch managing spin recovery with no problem will have been dimensioned.

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Hartland, A. J. "Dispersed base combat aircraft." Thesis, Cranfield University, 1989. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.237543.

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Heffernon, Timothy James. "Aircraft noise installation effects." Thesis, University of Southampton, 2017. https://eprints.soton.ac.uk/415885/.

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Airframe noise is currently of a comparable level to engine noise for an aircraft on approach with high-lift devices and landing gears deployed. The landing gears are a large contributor to the overall airframe noise in this situation. Main landing gears are typically installed beneath a lifting wing. The wing surfaces act as scattering surfaces for the noise generated by these landing gears, and the non-uniform flow around the wing affects both the propagation and strength of the noise. This thesis focuses on investigating the propagation and scattering of installed landing gear noise sources

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Tsentseris, Michail. "ARES: aircraft propulsion integration." Thesis, Cranfield University, 2013. http://dspace.lib.cranfield.ac.uk/handle/1826/12121.

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The combat aircraft and the gas turbine engine interact with one another. These interactions have become of even greater significance than previously due to the fact that the modern aircraft have increased requirements in terms of thrust, efficiency, reliability and ease of maintenance. Issues that affect the performance and operational capability of combat aircraft are the aircraft aerodynamic characteristics, propulsion system performance and the airframe/engine matching. This study focuses on the evaluation of the propulsion system of modern jet powered combat aircraft and combines computat

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Karlsson, Albin, and Anton Lomaeus. "Transport Aircraft Conceptual Design." Thesis, KTH, Skolan för teknikvetenskap (SCI), 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-210778.

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A conceptual design for a transport aircraft has been created, tailored for human-itarian missions along the equator with its home base in the European Union while optimizing for fuel eciency and speed. An initial estimate of the empty weight was made using historical data and Breguet equations, based on a required payload of 60 tonnes and range of 5 500 nautical miles. A constraint diagram consisting of require-ments for stall speed, takeo distance, climb rate and landing distance was used to determine wing loading and thrust to weight ratio, resulting in a main wing area of 387m 2 and thrust

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Filho, Nelson Whitaker. "Aircraft Distance Measurement System." International Foundation for Telemetering, 1994. http://hdl.handle.net/10150/611674.

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International Telemetering Conference Proceedings / October 17-20, 1994 / Town & Country Hotel and Conference Center, San Diego, California<br>The Aircraft Distance Measurement System (ADMS) could be used in Flight Test application to determine the aircraft position and speed during takeoff, landing and acceleration-stop performance test within runway limits using a microwave link.

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Andersson, Henric. "Aircraft Systems Modeling : Model Based Systems Engineering in Avionics Design and Aircraft Simulation." Licentiate thesis, Linköping University, Linköping University, Machine Design, 2009. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-17573.

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<p>Aircraft developers like other development and manufacturing companies, are experiencing increasing complexity in their products and growing competition in the global market. One way to confront the challenges is to make the development process more efficient and to shorten time to market for new products/variants by using design and development methods based on models. Model Based Systems Engineering (MBSE) is introduced to, in a structured way, support engineers with aids and rules in order to engineer systems in a new way.</p><p>In this thesis, model based strategies for aircraft and avi

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Bergkvist, Erik, and Tommy Sabbagh. "Smart Future Solutions for Maintenance of Aircraft : Enhancing Aircraft Maintenance at Saab AB." Thesis, Linköpings universitet, Industriell Produktion, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-176561.

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This master thesis has the purpose to analyse and identify smart efficient future solutions within the Maintenance, Repair and Overhaul (MRO) process for aircraft. The efficiency solutions, in form of new technologies and tools, should present a foundation that MRO suppliers can continue to develop to enhance and streamline their maintenance processes. The project was performed as a case study at the aerospace and defense company Saab AB in Linköping, where the company's MRO process was investigated. Through identifying possibilities and alternative technologies available today and in the near

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Cummins, Lane, and Tony Wilborn. "Cost-benefit analysis of the Department of the Navy's transition from C-9 Aircraft to C-40 Aircraft for logistic support aircraft." Monterey, California: Naval Postgraduate School, 2009. http://hdl.handle.net/10945/10395.

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Approved for public release, distribution unlimited<br>MBA Professional Report<br>The Navy began transitioning from the aging C-9s, which peaked at a total fleet size of 27 C-9B/DC-9 aircraft, to the C-40A. However, in response to increasing defense budget scrutiny and competing priorities, the Navy has decided to put this program on hold. Although the C-9B is an aging airframe and will require mandatory Federal Aviation Administration mandated modifications and upgrades, the DC-9/C-9B airframe has recently been determined to have significant operational service life remaining. This proje

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Cummins, Lane Wilborn Tony. "Cost-benefit analysis of the Department of the Navy's transition from C-9 Aircraft to C-40 Aircraft for logistic support aircraft." Monterey, California : Naval Postgraduate School, 2009. http://edocs.nps.edu/npspubs/scholarly/MBAPR/2009/Dec/09Dec%5FCummins%5FMBA.pdf.

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"Submitted in partial fulfillment of the requirements for the degree of Master of Business Administration from the Naval Postgraduate School, December 2009."<br>Advisor(s): Franck, Raymond E. ; Hildebrandt, Gregory. "December 2009." "MBA Professional report"--Cover. Description based on title screen as viewed on January 27, 2010. Author(s) subject terms: Cost-benefit Analysis, C-9B Skytrain, C-40A Clipper, NUFEA, Fleet Logistic Support Wing, Acquisition. Includes bibliographical references (p. 85-86). Also available in print.

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Kehayas, N. "ASTOVL Combat Aircraft Design Synthesis and Optimization." Thesis, Cranfield University, 1992. http://hdl.handle.net/1826/3387.

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This thesis presents the development of a Baseline Configuration for an Advanced Short Take-Off and Vertical Landing (ASTOVL) Combat Aircraft, the Design Synthesis and coding of this Baseline Congiguration (Code VERTI), the interfacing of the Design Synthesis Code VERTI with the Optimizer code RQPMIN and the optimization of the Baseline Configuration. The background and the objectives of this Research Programme are initially examined. The evaluation of the ASTOVL Combat Aircraft Baseline Configuration is then described, including all the problems, assumptions, choices and compromises that led

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Altman, Aaron. "A conceptual design methodology for low speed high altitude long endurance unmanned aerial vehicles." Thesis, Cranfield University, 2000. http://hdl.handle.net/1826/3998.

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A conceptual design methodology was produced and subsequently coded into a Visual C++ (GUI) environment to facilitate the rapid comparison of several possible configurations to satisfy High Altitude Long Endurance (FIALE) unmanned aircraft (UAV) missions in the Low Speed (propeller driven aircraft) regime. Several comparative studies were performed to verify the applicability of traditional design methods. The traditional computational design methodologies fail in several areas such as high aspect ratio wing weight estimation and design, low Reynolds number wing design, high altitude engine pe

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Alsina, J. "Development of an aircraft design expert system." Thesis, Cranfield University, 1988. http://hdl.handle.net/1826/3442.

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The aircraft design process is characterised by the application of a wide range of knowledge across many disciplines based upon a certain degree of judgement and experience of the designer. A two pass approach has been taken towards the development of an aircraft design expert system based on the requirements of two conceptually different design steps namely, wing design and aircraft configuration. The current status of the work is one where an actual program for wing design exists with supporting documentation, and a very effective examination of the knowledge base performed based on the deta

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Souahi, A. "Structural optimization of aircraft lifting surfaces to satisfy flutter requirements." Thesis, Cranfield University, 1986. http://hdl.handle.net/1826/3657.

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The research reported in this thesis is concerned with the structural weight optimization of aircraft lifting surfaces when subjected to the satisfaction of flutter requirements. The main text is intended primarily as an expository account on the work and as such it aims at introducing and defining the subject of research and presenting the results. Accordingly, the mathematics have been simplified to the utmost in the main text and heavy theoretical treatments are revealed in the appendices. As the aim of this work is not directed at in-depth studies of the physical nature of flutter nor for

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Broadley, Jonathan I. "The control of trailing edge separation on highly swept wings using vortex generators." Thesis, Cranfield University, 1998. http://hdl.handle.net/1826/3966.

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The results from a series of low speed wind tunnel tests on two half model highly swept wings (a symmetrical aerofoil section and a highly cambered aerofail section) are presented in order to examine the trailing edge flow separation mechanism and its development with wing sweep between 30' and 60'. The tests involved surface oil flow visualisation, smoke flow visualisation, surface static pressure and force balance measurements at streamwise chord Reynolds numbers from 1.5 x 105 to 5.2 x 106 and Mach number from 0.09 to 0.17. These results are used to assess two viscous-inviscid interaction C

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Markiewicz, R. H. "A study of the aeroelastic behaviour of helicopter rotor blades featuring swept tips." Thesis, Cranfield University, 1990. http://hdl.handle.net/1826/4188.

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The design of a model helicopter rotor blade incorporating a swept tip is described. The swept tip is chosen to provide a coupling between the lift at the tip and the blade twist thus achieving a variation of blade tvist both with azimuth and with forward speed. The design is the first stop in an investigation of aeroelastic tailoring as a means of reducing helicopter vibration and increasing rotor performance. The first prototype blade encountered stability problems and further designs were evaluated using a new modes/stability computer program developed within RAE. Comparisons are made betwe

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Al-Ahmed, S. M. "Integrating combat effectiveness disciplines into the aircraft conceptual/preliminary design phase." Thesis, Cranfield University, 1996. http://hdl.handle.net/1826/3631.

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An assessment methodology has been developed for - use during the conceptual/preliminary design phase to quantify the effectiveness of newly designed aircraft. The effectiveness is measured by a squadron Sortie Generation Rate (SGR). Key elements of this methodology were the establishment of link parameters between design synthesis and the main effectiveness disciplines. These were Reliability and Maintainability (R&M), Survivability / Vulnerability and Acquisition Cost. A programmable solid modeller was used to create a solid CAD assembly of the aircraft critical components. A ray tracing tec

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Macci, S. H. M. "Structural and mechanical feasibility study of a variable camber wing (VCW) for a transport aircraft." Thesis, Cranfield University, 1992. http://hdl.handle.net/1826/4168.

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Aerodynamic investigations have shown' that variable camber wings (VCW) for transport aircraft have considerable potential in terms of improving aircraft performance and enhancing their operational flexibility. In order to justify these benefits it is essential that the camber varying system is structurally and mechanically feasible. This research examined the feasibility of providing variable camber to two supercritical aerofoil sections of different'characteristics. The unique method of camber vaTiation was applied by rotating the forward and aft regions of the aerofoil on a circular arc and

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48

Gantois, K. "An MDO concept for large civil airliner wings." Thesis, Online version, 1998. http://ethos.bl.uk/OrderDetails.do?did=1&uin=uk.bl.ethos.266980.

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Simpson, Mark N. "The application of semi-active control technology to aircraft landing gear." Thesis, Loughborough University, 1988. https://dspace.lboro.ac.uk/2134/6764.

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The purpose of the research investigation was to study the application of semi-active control technology to the design of a suspension system to be used in a landing gear of a high speed military aircraft. A semi-active system was used because it will allow a system to be driven from the hydraulic systems already existing in the aircraft without extensive modification. The research work involved establishing a theoretical mathematical model for the semi-active damping system. This model involved a large number of non-linear dynamic phenomena and elements including a two-stage gas spring, lever

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Guo, Shijun. "Improvement of analytical dynamic models using vibration test data." Thesis, University of Hertfordshire, 1993. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.332846.

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Generally speaking, difficulties encountered during the improvement of an Analytical Dynamic Model (ADM) using vibration test data come from both the Spatial Coordinate Incompatibility (SCI) and especially the Modal Coordinate Incompatibility (MCI) between the ADM and the test data. Efforts were therefore made in this project to cope with these two problems by extending some of the existing methods and also by developing new methods with consideration of their feasibility, efficiency and accuracy. A general description of this part of the project and the literature survey of this study area ar

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