Relevant bibliographies by topics / Aircraft analysis / Dissertations / Theses
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Dissertations / Theses on the topic 'Aircraft analysis'

Author: Grafiati
Published: 4 June 2021
Last updated: 3 February 2022

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1

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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2

Cuppernull, Michael J. 1957. "Aircraft remanufacturing process improvement analysis." Thesis, Massachusetts Institute of Technology, 1999. http://hdl.handle.net/1721.1/88823.

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3

Behroozi, Mohammad H. "Finite element analysis of aircraft tyres." Thesis, University of Birmingham, 2014. http://etheses.bham.ac.uk//id/eprint/5390/.

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In this thesis, the Finite Element (FE) Analysis of aircraft tyres is presented. The modelling and simulations of detailed construction of tyre enable tyre manufacturers to evaluate new designs and development before a prototype is fabricated, and aim to reduce the research costs and efforts to optimise the current tyre design of tyres. The material properties is key in the FE modelling and analysis, a number of sample from the rubber compounds and reinforcement were used to characterise the elastic, hyperelastic and viscoelastic behaviour of material. In this research, two aircraft tyres were
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4

Magnani, Federico. "Analysis of aircraft cirrus clouds spectral measurements." Bachelor's thesis, Alma Mater Studiorum - Università di Bologna, 2019.

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In questa tesi vengono descritte le proprietà dell’atmosfera terrestre nel lontano infrarosso (FIR) e il loro impatto climatico. Negli ultimi anni sempre più attenzione è stata posta nella ricerca in questo campo e sono stati sviluppati strumenti e metodi di analisi innovativi, come dimostrato dalla nascita della missione Far-infrared-Outgoing-Radiation Understanding and Monitoring (FORUM) che propone il lancio di un satellite attrezzato con strumenti FIR. Quasi il 45% dell’energia emessa dal pianeta è portata da onde nel FIR, attraverso il meccanismo del trasferimento radiativo: poichè l’atmo
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5

Baghdadi, Nadjib. "Bifurcation and continuation analysis : flexible aircraft dynamics." Thesis, University of Bristol, 2011. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.539769.

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6

Muller, Kurt W. "Analysis of a semi-tailless aircraft design." Thesis, Monterey, California. Naval Postgraduate School, 2002. http://hdl.handle.net/10945/6044.

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Approved for public release; distribution is unlimited<br>Many unique aircraft configurations came out of Germany in World War II, one of these was the Blohm and Voss BV P 208. By using longitudinal and directional control surfaces located outboard of the wing tips they are removed from the downwash of the main wing. Additionally, the result is fewer component surfaces with less total surface area, thereby reducing both friction and interference drag and manufacturing cost. The configuration should lend itself well to low-observability, making it a good stealth candidate. The P 208,
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7

Rubin, Felix. "Modelling & Analysis of a TiltWing Aircraft." Thesis, KTH, Flygdynamik, 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-244832.

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The aim of this report is the investigation of a hybrid vertical take-off and landing (VTOL) tilt wing aircraft which is in development at the company Dufour Aerospace. Using a model, programmed in MATLAB® different stages of flight can be simulated and investigated. Maininvestigation area of this report is the transition between cruise and hover conditions of the aircraft.The simulation is based on the six-degree-of-freedom nonlinear equations of motion for aircraft modified for tilt wing operation. The model characteristics have been determined using various CFD programs, wind tunnel data, a
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8

Dowdle, Aidan Patrick. "A Requirements analysis methodology for turboelectric aircraft." Thesis, Massachusetts Institute of Technology, 2017. http://hdl.handle.net/1721.1/111912.

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Thesis: S.M., Massachusetts Institute of Technology, Department of Electrical Engineering and Computer Science, 2017.<br>Cataloged from PDF version of thesis.<br>Includes bibliographical references (pages 81-82).<br>The aviation industry today requires novel aircraft technology to provide for its rapidly growing demand. Of the many aircraft technologies being proposed, turboelectric is of particular interest for commercial-sized aircraft. Turboelectric propulsion enables novel airframe configurations, boundary layer ingestion, and distributed propulsion, each of which can reduce the amount of
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9

Poudel, Minesh. "Aircraft emergency evacuation : analysis, modelling and simulation." Toulouse 2, 2008. http://www.theses.fr/2008TOU20026.

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Cette thèse s’intéresse à l’évacuation d’urgence des avions et plus particulièrement à la conception d’un simulateur numérique capable de représenter de façon réaliste ce processus afin de contribuer à la certification de configurations et de procédures d’évacuation d’urgence pour les avions gros porteurs. Cette thèse est composée de deux grandes parties. Dans la première partie, il s’est agi d’identifier le problème, de réaliser un état de l’art et de caractériser le comportement des passagers pendant l’évacuation. Dans la deuxième partie de la thèse il s’est agi de concevoir les élément cons
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10

Erlandsson, Tina. "Situation analysis for fighter aircraft combat survivability." Licentiate thesis, Örebro universitet, Akademin för naturvetenskap och teknik, 2011. http://urn.kb.se/resolve?urn=urn:nbn:se:oru:diva-20544.

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Fighter pilots operate in environments where an erroneous decision may have fatal consequences. A tactical decision support system (TDSS) could aid the pilots to analyze the situation and make correct decisions. The TDSS can, for instance, highlight important information and suggest suitable actions. The aim of this thesis is to provide a situation analysis model of combat survival that can be utilized in a TDSS. The first part of this thesis describes an analysis of what the model needs to describe and how it can be used. It is concluded that the model should evaluate the outcome of different
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11

Davidson, Gordon Westly. "Aircraft NLG shimmy : methods, tools and analysis." Thesis, Imperial College London, 2012. http://hdl.handle.net/10044/1/10554.

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ELGEAR was a UK government/industry partnership created in 2006 to research electrical technology in aircraft landing gear systems. The project designed, built and ground tested electrical technology for a Landing Gear Extension/Retraction system (LGERS) and Nose Wheel Steering systems (NWS) for a 120 passenger aircraft. One thread of this research, and the topic of the present thesis, was to develop analysis methods and tools to investigate the effects of shimmy. Shimmy is the self excited vibration of a castored wheel assembly. It may be experienced on assemblies such as wheel chairs, shoppi
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12

Adams, Jason W. Adams Jason W. "An analysis of port-visit costs of U.S. Navy aircraft carriers." Monterey, Calif. : Naval Postgraduate School, 2008. http://handle.dtic.mil/100.2/ADA483584.

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13

Theos, Athanasios. "Design and analysis of welded aircraft wing panels." Thesis, Cranfield University, 2005. http://hdl.handle.net/1826/3901.

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Nowadays, increasing manufacturing cost effectiveness becomes a vital condition for the commercial success of the next generation of large wide body aircrafts. Welding is a very strong candidate process to be used in manufacturing, allowing both sensible cost reductions and structural efficiency. The main aim of the work is to study the fatigue crack propagation in welded structures. The study is focused on the effect of welding residual stresses to the damage tolerance behaviour of the structure. The welding technique under investigation is the Variable Polarity Plasma Arc (VPPA). Two stringe
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14

Furr, David M. "An analysis of Naval aircraft engine container management." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1998. http://handle.dtic.mil/100.2/ADA359190.

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Thesis (M.S. in Management) Naval Postgraduate School, December 1998.<br>"December 1998." Thesis advisor(s): Michael W. Boudreau. Includes bibliographical references (p. 65-67). Also available online.
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15

Areerak, Kongpan. "Modelling and stability analysis of aircraft power systems." Thesis, University of Nottingham, 2009. http://eprints.nottingham.ac.uk/12944/.

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The more-electric aircraft concept is a major trend in aircraft electrical power system engineering and results in an increase in electrical loads based on power electronic converters and motor drive systems. Unfortunately, power electronic driven loads often behave as constant power loads having the small-signal negative impedance that can significantly degrade the power system stability margin. Therefore, the stability issue of aircraft power systems is of great importance. The research of the thesis deals with the modelling and stability analysis of an aircraft power system. The aircraft po
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16

Rankin, James. "Bifurcation Analysis of Nonlinear Ground Handling of Aircraft." Thesis, University of Bristol, 2010. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.521073.

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17

Coetzee, Etienne. "Modelling and nonlinear analysis of aircraft ground manoeuvres." Thesis, University of Bristol, 2011. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.541611.

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18

Matherne, Ray P. "Fuel savings through aircraft modification : a cost analysis /." Wright-Patterson Air Force Base, Ohio : Ft. Belvior, VA : Alexandria, Va. : Air Force Institute of Technology, Graduate School of Engineering and Management (AFIT/EN) ; Available to the public through the Defense Technical Information Center ; National Technical Information Service [distributor], 2009. http://www.dtic.mil/dtic/.

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Thesis (M.S. in Logistics)--Department of Operational Sciences, Graduate School of Engineering and Management, Air Force Institute of Technology, Air University, Air Education and Training Command, June 2009.<br>"June 2009." Thesis advisor: Dr. James T. Moore. Performed by the Air Force Institute of Technology, Graduate School of Engineering and Management (AFIT/EN), Wright-Patterson Air Force Base, Ohio. "Presented to the Faculty Department of Operational Sciences, Graduate School of Engineering and Management, Air Force Institute of Technology, Air University, Air Education and Training Comm
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19

Bekemeyer, P. "Rapid computational aerodynamics for aircraft gust response analysis." Thesis, University of Liverpool, 2018. http://livrepository.liverpool.ac.uk/3027827/.

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Computational engineering methods play a more and more important role in building aircraft that move people and goods. Particular in high-speed civil air transport increased usage of higher fidelity simulation tools are expected to enable greener designs with a reduced environmental footprint. The challenge of including computational fluid dynamics in aircraft loads and aeroelasticity is addressed herein. During the aircraft design and certification process a tremendous number of dynamic responses to atmospheric turbulence need to be analysed. Current industrial loads computations are based on
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20

Aubin, Pierre-Etienne. "Bifurcation analysis and control of a fighter aircraft." Thesis, Massachusetts Institute of Technology, 1993. http://hdl.handle.net/1721.1/46417.

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21

Loureiro, Marcos Vinicius Pirrho. "A 174 passenger aircraft pylon design and analysis." Instituto Tecnológico de Aeronáutica, 2006. http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=792.

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The goal of this work is to verify the pylon design of a 174 passenger aircraft. This aircraft was studied by the fourth class of Embraer's Engineer Specialization Program (PEE 4). The engine of this aircraft is located below the wing and its model is GE CFM-56. The fan size was increased in order to reach a higher air passage ratio. This pylon concept presented here was studied and adopted by the group as the better option for this type of airplane. Due to the short time allowable to this study along the program, this dissertation aim to verify the design chosen, analyzing the pylon loads and
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22

Silva, Flavia Renata Dantas Alves. "Ergonomic analysis for a regional aircraft interior design." Instituto Tecnológico de Aeronáutica, 2007. http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=968.

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The purpose of this work is to develop a preliminary interior design of a regional aircraft considering ergonomic and cost aspects. The use of virtual humans provides a better interpretation of the aircraft interior environment, making possible to simulate movements and passenger comfort aspects. The importance of this study becomes evident through the necessity of the aircraft manufacturer of predicting human behavior during all the flight phases. This text also aims to present the difficulty to accomplish the design requirements and at same time meet the market expectations without oversizin
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23

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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24

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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25

King, Merrill F. "A reliability centered maintenance analysis of aircraft control bearings used in the Navy's S-3 aircraft." Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1997. http://handle.dtic.mil/100.2/ADA342292.

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Thesis (M.S. in Management) Naval Postgraduate School, December 1997.<br>"December 1997." Thesis advisor(s): Keebom Kang, Donald R. Eaton. Includes bibliographical references (p. 73-74). Also available online.
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26

Heinze, Sebastian. "Aeroelastic Concepts for Flexible Aircraft Structures." Doctoral thesis, Stockholm : Farkost och flyg Aeronautics and Vehicle Engineering, Kungliga Tekniska högskolan, 2007. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-4419.

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27

Dudgeon, Graham John William. "Individual channel analysis and design and its application to helicopter flight control." Thesis, University of Glasgow, 1996. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.325388.

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28

Oliva, A. P. "The design and analysis of a reconfigurable flight control system for advanced civil aircraft." Thesis, Cranfield University, 1994. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.385764.

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29

Alexander, Richard. "Analysis of Aircraft Power Systems, Including System Modeling and Energy Optimization, with Predictions of Future Aircraft Development." The Ohio State University, 2018. http://rave.ohiolink.edu/etdc/view?acc_num=osu1523541008209354.

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30

Ding, Menglong. "Development of Advanced Numerical Tools for Aircraft Crash Analysis." University of Akron / OhioLINK, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=akron1596125161606626.

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31

Chang, Chong-Seok. "Vibration and Aeroelastic Analysis of Highly Flexible HALE Aircraft." Diss., Georgia Institute of Technology, 2006. http://hdl.handle.net/1853/14089.

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The highly flexible HALE (High Altitude Long Endurance) aircraft analysis methodology is of interest because early studies indicated that HALE aircraft might have different vibration and aeroelastic characteristics from those of conventional aircraft. Recently the computer code Nonlinear Aeroelastic Trim And Stability of HALE Aircraft (NATASHA) was developed and used to the flight dynamics and aeroelastic analysis of flying wing HALE aircraft. Further analysis improvements were required to extend its capability to the ground vibration test (GVT) environment and to both GVT and aeroelastic be
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32

Knife, S. "Propulsion system safety analysis methodology for commercial transport aircraft." Thesis, Cranfield University, 1997. http://hdl.handle.net/1826/4256.

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Airworthiness certification of commercial transport aircraft requires a safety analysis of the propulsion system to establish that the probability of a failure jeopardising the safety of the aeroplane is acceptably low. The needs and desired features of such a propulsion system safety analysis are discussed, and current techniques and assumptions employed in such analyses are evaluated. It is concluded that current assumptions and techniques are not well suited to predicting behaviour of the propulsion system in service. The propulsion accident history of the high bypass ratio commercial trans
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33

Andrews, Melissa S. Hickey Suzanne Christine. "Analysis of Navy aircraft engine and engine component warranties /." Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1993. http://handle.dtic.mil/100.2/ADA276936.

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Thesis (M.S. in Management) Naval Postgraduate School, December 1993.<br>Thesis advisor(s): Alan W. McMasters ; Jeffrey A. Warmington. "December 1993." Bibliography: p. 123-124. Also available online.
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34

Kim, Kiun. "Nonlinear aeroelastic analysis of aircraft wing-with-store configurations." Diss., Texas A&M University, 2004. http://hdl.handle.net/1969.1/361.

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The author examines nonlinear aeroelastic responses of air vehicle systems. Herein, the governing equations for a cantilevered configuration are developed and the methods of analysis are explored. Based on the developed nonlinear bending-bending-torsion equations, internal resonance, which is possible in future air vehicles, and the possible cause of limit cycle oscillations of aircraft wings with stores are investigated. The nonlinear equations have three types of nonlinearities caused by wing flexibility, store geometry and aerodynamic stall, and retain up to third-order nonlinear terms. The
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35

Ikeda, Toshihiro, and toshi ikeda@gmail com. "Aerodynamic Analysis of a Blended-Wing-Body Aircraft Configuration." RMIT University. Aerospace, Mechanical and Manufacturing Engineering, 2006. http://adt.lib.rmit.edu.au/adt/public/adt-VIT20070122.163030.

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In recent years unconventional aircraft configurations, such as Blended-Wing-Body (BWB) aircraft, are being investigated and researched with the aim to develop more efficient aircraft configurations, in particular for very large transport aircraft that are more efficient and environmentally-friendly. The BWB configuration designates an alternative aircraft configuration where the wing and fuselage are integrated which results essentially in a hybrid flying wing shape. The first example of a BWB design was researched at the Loughead Company in the United States of America in 1917. T
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36

Moodie, Simon James. "The hydraukic shock analysis of aircraft wing box structures." Thesis, Imperial College London, 2010. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.530455.

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37

Chakraborty, Imon. "Subsystem architecture sizing and analysis for aircraft conceptual design." Diss., Georgia Institute of Technology, 2015. http://hdl.handle.net/1853/54427.

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In traditional aircraft conceptual design, subsystems are largely accounted for implicitly based on available historical data and trends. Such an approach has limitations when novel subsystem architectures such as More Electric or All Electric aircraft are considered, since historical data regarding such architectures is either limited or non-existent. In such cases, the incorporation of more thorough and explicit consideration of the aircraft subsystems into the conceptual design phase is warranted. The first objective of this dissertation is to integrate subsystem sizing and analysis metho
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38

Andrews, Melissa S., and Suzanne Christine Hickey. "Analysis of Navy aircraft engine and engine component warranties." Thesis, Monterey, California. Naval Postgraduate School, 1993. http://hdl.handle.net/10945/39656.

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Approved for public release; distribution is unlimited.<br>Since the enactment of Title 10, Section 2403 of the United States Code in 1985, written warranty clauses have been mandated for the procurement of all major weapon systems. This thesis discusses the aircraft engine warranty program established by the Naval Air Systems Command in response to that warranty legislation. Warranty procedures and issues are examined during procurement, contract negotiations, and in the daily operations of the fleet. The aircraft engine warranty program of a major commercial airline (United Airlines) is pres
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39

Rampurawala, Abdul Moosa. "Aeroelastic analysis of aircraft with control surfaces using CFD." Thesis, University of Glasgow, 2005. http://theses.gla.ac.uk/5499/.

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For the simulation of control surface buzz accurate prediction of the shock location and the chock strength is essential and this is currently achieved using Euler and RANS based CFD analysis. To calculate the motion of the control surface only the flap rotation mode needs to be modelled. In the current work the CFD solver is coupled with a modal based FEM solver. The multi-level hierarchical blending transformation methodology is applied for the aeroelastic analyses of complex geometries. The methodology is used for the treatment of blended control surfaces and the effect of the blending on t
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Moore, Rachel Ann. "Analysis driven design and optimisation methods for aircraft structures." Thesis, Queen's University Belfast, 2008. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.479406.

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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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Abbott, Troy D. "Aircraft stability and departure prediction using Eigenvalue Sensitivity analysis." Thesis, This resource online, 1995. http://scholar.lib.vt.edu/theses/available/etd-06112009-063745/.

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Wang, Andrew 1973. "Design and analysis of production systems in aircraft assembly." Thesis, Massachusetts Institute of Technology, 1999. http://hdl.handle.net/1721.1/80044.

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Hall, David Kenneth. "Analysis of civil aircraft propulsors with boundary layer ingestion." Thesis, Massachusetts Institute of Technology, 2015. http://hdl.handle.net/1721.1/97353.

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Thesis: Ph. D., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2015.<br>Cataloged from PDF version of thesis.<br>Includes bibliographical references (pages 113-116).<br>This thesis describes (i) guidelines for propulsor sizing, and (ii) strategies for fan turbomachinery conceptual design, for a boundary layer ingesting (BLI) propulsion system for advanced civil transport aircraft. For the former, configuration performance analysis shows BLI yields a reduction in mechanical power required to propel a given aircraft. For the latter, fan turbomachinery design a
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45

Júnior, Francival Barbosa. "Analysis of electro-hydrostatic actuator in more electric aircraft." Instituto Tecnológico de Aeronáutica, 2006. http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=900.

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The aim of this dissertation is to evaluate the possibility of using electrically powered systems instead of a centralized hydraulic system composed of set of distribution pipes for aircrafts' primary control surfaces actuation. Focus will be given in the following topics: Description of new actuation technologies; Option chosen to be studied among the new possibilities; Comparison between the traditional system and the new proposal e System engineering evaluation regarding: weight, safety, thermal issue, connection with electric system, maintenance and certification. Besides that, a more elec
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Rowles, Craig M. 1962. "System integration analysis of a large commercial aircraft engine." Thesis, Massachusetts Institute of Technology, 1999. http://hdl.handle.net/1721.1/9753.

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Thesis (S.M.)--Massachusetts Institute of Technology, System Design and Management Program, 1999.<br>10912289<br>Includes bibliographical references (p. 93-94).<br>In this thesis we develop and demonstrate a method, called a System Integration Analysis, to produce a comprehensive understanding of the activities Integrated Product Teams (IPTs) perform in designing and developing a large complex product or system. The methodology is applied to an existing product or system whose physical architecture can be partitioned into comparable sections, or chunks, as the IPTs who design and develop it. I
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47

McCormick, Daniel John. "An Analysis of Using CFD in Conceptual Aircraft Design." Thesis, Virginia Tech, 2002. http://hdl.handle.net/10919/33409.

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The evaluation of how Computational Fluid Dynamics (CFD) package may be incorporated into a conceptual design method is performed. The repeatability of the CFD solution as well as the accuracy of the calculated aerodynamic coefficients and pressure distributions was also evaluated on two different wing-body models. The overall run times of three different mesh densities was also evaluated to investigate if the mesh density could be reduced enough so that the computational stage of the CFD cycle may become affordable to use in the conceptual design stage. A farfield method was derived and us
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TIAN, BINYU. "COMPUTATIONAL AEROELASTIC ANALYSIS OF AIRCRAFT WINGS INCLUDING GEOMETRY NONLINEARITY." University of Cincinnati / OhioLINK, 2003. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1070398084.

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49

Persson, Björn. "Assessment of Aircraft Radar Cross-Section for Detection Analysis." Doctoral thesis, Försvarshögskolan, Militärtekniska avdelningen (MTA), 2016. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-185214.

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Hiding from and surprising an opponent are tactics that have been used in warfare throughout history. They were features that aircraft originally possessed when they were first used in military operations. However, development of military technology is an endless struggle between advances in technology and counter technology. During World War II this struggle led to the development of a new technology called radar, which was designed to detect sea vessels and aircraft at a distance and deny them the element of surprise. This laid the foundation for modern air defenses and simultaneously create
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Lowenberg, Mark H. "Application of bifurcation analysis to multiple attractor flight dynamics." Thesis, University of Bristol, 1998. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.264065.

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