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Dissertations / Theses on the topic 'Airplanes, fuel'
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1
Ciaravino, John S. "Study of hydrogen as an aircraft fuel." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2003. http://library.nps.navy.mil/uhtbin/hyperion-image/03Jun%5FCiaravino.pdf.
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Thesis (M.S. in Aeronautical Engineering)--Naval Postgraduate School, June 2003.Thesis advisor(s): Oscar Biblarz, Garth Hobson. Includes bibliographical references (p. 45-47). Also available online.
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Bradley, Thomas Heenan. "Modeling, design and energy management of fuel cell systems for aircraft." Diss., Atlanta, Ga. : Georgia Institute of Technology, 2008. http://hdl.handle.net/1853/26592.
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Thesis (Ph.D)--Mechanical Engineering, Georgia Institute of Technology, 2009.Committee Chair: Parekh, David; Committee Member: Fuller, Thomas; Committee Member: Joshi, Yogendra; Committee Member: Mavris, Dimitri; Committee Member: Wepfer, William. Part of the SMARTech Electronic Thesis and Dissertation Collection.
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Xie, Tieling. "Electrochemical corrosion effects of ethanol based fuel on general aviation aircraft fuel system components." Diss., Mississippi State : Mississippi State University, 2004. http://library.msstate.edu/etd/show.asp?etd=etd-11072004-122317.
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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."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 Command In Partial Fulfillment of the Requirements for the Degree of Master of Logistics, June 2009."--P. [ii]. "AFIT/IMO/ENS/09-07." Includes bibliographical references. Also available online from the Air University Research Information Management System Web site and the DTIC Online Web site.
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Compton, Timothy James Shauck Maxwell Eustace. "Flight performance testing of ethanol/100LL fuel blends during cruise flight." Waco, Tex. : Baylor University, 2008. http://hdl.handle.net/2104/5150.
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Rawson, Paul Stansfield Christy-Anne. "Field method for detection of metal deactivator additive in jet fuel." Fishermans Bend, Victoria : Defence Science and Technology Organisation, 2009. http://nla.gov.au/nla.arc-24592.
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Kwan, Pok Wang. "Flow management in heat exchanger installations for intercooled turbofan engines." Thesis, University of Oxford, 2011. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.711622.
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Davis, James Arthur. "Acoustic-vortical-combustion interaction in a solid fuel ramjet simulator." Diss., Georgia Institute of Technology, 1989. http://hdl.handle.net/1853/12947.
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Jones, James D. "A study of active control techniques for noise reduction in an aircraft fuselage model." Diss., Virginia Polytechnic Institute and State University, 1987. http://hdl.handle.net/10919/77809.
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A simplified cylindrical model is used to investigate the elementary mechanisms of control of sound transmission into aircraft cabins by two active control techniques: propeller synchrophasing and active vibration control. Propeller synchrophasing involves controlling the relative rotational phase of the engines to achieve maximum cabin noise reduction. Active vibration control involves structurally controlling the vibrational response of the cabin wall to reduce the important modes which transmit their energy into the cabin.
Noise reductions for harmonic excitation at acoustic cavity resonance are shown to be in excess of 20 dB throughout most of the cavity whether synchrophasing or active vibration control is used. Off-resonance reductions are substantially less due to increased modal density requiring a larger number of actuators for effective control of the complex sound field. Additional studies were performed using synchrophasing in conjunction with active vibration control to study their joint capabilities in controlling complex sound fields. The dual control system displayed improved control performance with noise reductions on the order of 25-35 dB and a more uniform sound field. Also, the complementary control characteristics of the system clearly demonstrated effective control of orthogonal acoustic modes of the cavity. However, the improved effectiveness of the control system was dependent upon judiciously positioning the actuators for optimal control of the sound field.
An independent study was performed to identify the effects of a complex geometry on sound transmission into an aircraft fuselage model interior. For this study, a geometrically scaled cabin floor was installed in the unstiffened test cylinder to investigate the structural and acoustic influence of the simulated cabin floor. Results indicated that the stiffening of the cylindrical model associated with insertion of the floor strongly influenced the structural response of the cylinder but generally had little effect on the coupled pressure response. Conversely, the modification of the interior acoustic cavity tended to have little influence on the cylinder response but substantially reduced the coupled pressure response.
Thus, this investigation identified the fundamental mechanisms of control of sound transmission into simplified models of aircraft fuselages by active control techniques.Ph. D.
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Vasudevan, Gopal. "Fuel optimal rendezvous including a radial constraint." Thesis, Virginia Polytechnic Institute and State University, 1986. http://hdl.handle.net/10919/94484.
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Fuel-optimal rendezvous in orbit is examined using thrust-impulses and coasting arcs. Necessary conditions for the optimality of fuel-optimal rendezvous with and without radial constraints are derived. These conditions are then used to verify the optimality of trajectories obtained from a parameter-optimization technique.
For rendezvous problems with radial constraint, locally optimal trajectories include constrained arcs or touch-point arcs. Numerical procedures to compute the costates and the jumps in the costates at the touch point and at the entry point to the constraint arc are provided. Locally optimal solutions for non-optimal trajectories with a minimum radius-constraint are obtained using criteria due to Lion and Handelsmann.
Numerical solutions show that multiple-impulse trajectories almost always result in a lower cost function than the corresponding two impulse trajectories. It is also observed that trajectories comprised of only touch-point arcs can often be improved by using an additional impulse.M. S.
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Burzlaff, Marcus. "Aircraft Fuel Consumption - Estimation and Visualization." Aircraft Design and Systems Group (AERO), Department of Automotive and Aeronautical Engineering, Hamburg University of Applied Sciences, 2017. http://d-nb.info/1148997490.
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In order to uncover the best kept secret in today's commercial aviation, this project deals with the calculation of fuel consumption of aircraft. With only the reference of the aircraft manufacturer's information, given within the airport planning documents, a method is established that allows computing values for the fuel consumption of every aircraft in question. The aircraft's fuel consumption per passenger and 100 flown kilometers decreases rapidly with range, until a near constant level is reached around the aircraft's average range. At longer range, where payload reduction becomes necessary, fuel consumption increases significantly. Numerical results are visualized, explained, and discussed. With regard to today's increasing number of long-haul flights, the results are investigated in terms of efficiency and viability. The environmental impact of burning fuel is not considered in this report. The presented method allows calculating aircraft type specific fuel consumption based on publicly available information. In this way, the fuel consumption of every aircraft can be investigated and can be discussed openly.
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Bensel, Artur. "Characteristics of the Specific Fuel Consumption for Jet Engines." Aircraft Design and Systems Group (AERO), Department of Automotive and Aeronautical Engineering, Hamburg University of Applied Sciences, 2018. http://d-nb.info/1175791237.
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Purpose of this project is a) the evaluation of the Thrust Specific Fuel Consumption (TSFC) of jet engines in cruise as a function of flight altitude, speed and thrust and b) the determination of the optimum cruise speed for maximum range of jet airplanes based on TSFC characteristics from a). Related to a) a literature review shows different models for the influence of altitude and speed on TSFC. A simple model describing the influence of thrust on TSFC seems not to exist in the literature. Here, openly available data was collected and evaluated. TSFC versus thrust is described by the so-called bucket curve with lowest TSFC at the bucket point at a certain thrust setting. A new simple equation was devised approximating the influence of thrust on TSFC. It was found that the influence of thrust as well as of altitude on TSFC is small and can be neglected in cruise conditions in many cases. However, TSFC is roughly a linear function of speed. This follows already from first principles. Related to b) it was found that the academically taught optimum flight speed (1.316 times minimum drag speed) for maximum range of jet airplanes is inaccurate, because the derivation is based on the unrealistic assumption of TSFC being constant with speed. Taking account of the influence of speed on TSFC and on drag, the optimum flight speed is only about 1.05 to 1.11 the minimum drag speed depending on aircraft weight. The amount of actual engine data was extremely limited in this project and the results will, therefore, only be as accurate as the input data. Results may only have a limited universal validity, because only four jet engine types were analyzed. One of the project's original value is the new simple polynomial function to estimate variations in TSFC from variations in thrust while maintaining constant speed and altitude.
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Ahuja, Vivek Hartfield Roy J. "Optimization of fuel-air mixing for a scramjet combustor geometry using CFD and a genetic algorithm." Auburn, Ala, 2008. http://hdl.handle.net/10415/1406.
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Caers, Brecht. "Conditions for Passenger Aircraft Minimum Fuel Consumption, Direct Operating Costs and Environmental Impact." Master's thesis, Aircraft Design and Systems Group (AERO), Department of Automotive and Aeronautical Engineering, Hamburg University of Applied Sciences, 2019. http://d-nb.info/1204494622.
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Purpose - Find optimal flight and design parameters for three objectives: minimum fuel consumption, Direct Operating Costs (DOC), and environmental impact of a passenger jet aircraft. ---
Approach - Combining multiple models (this includes aerodynamics, specific fuel consumption, DOC, and equivalent CO2 mass) into one generic model. In this combined model, each objective's importance is determined by a weighting factor. Additionally, the possibility of further optimizing this model by altering an aircraft's wing loading is analyzed. ---
Research limitations - Most models use estimating equations based on first principles and statistical data. ---
Practical implications - The optimal cruise altitude and speed for a specific objective can be approximated for any passenger jet aircraft. ---
Social implications - By using a simple approach, the discussion of optimizing aircraft opens up to a level where everyone can participate. ---
Value - To find a general answer on how to optimize aviation, operational and design-wise, by using a simple approach.
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Ahlefelder, Sebastian. "Kraftstoffverbrauch durch Entnahme von Zapfluft und Wellenleistung von Strahltriebwerken." Aircraft Design and Systems Group (AERO), Department of Automotive and Aeronautical Engineering, Hamburg University of Applied Sciences, 2006. http://d-nb.info/1179514394.
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Zapfluft und Wellenleistung wird den Triebwerken entnommen, um die Energie für beispielsweise die Kraftstoffpumpen, das Inflight Entertainment oder die Flügelvorderkantenenteisung zu erzeugen. Diese Energiegenerierung, hat einen Anstieg des Kraftstoffverbrauches zur Folge. Es hat sich herausgestellt, dass die Stelle der Zapfluftentnahme einen starken Einfluss auf den Gradienten des Brennstoffverbrauches hat. Das Projekt beschäftigt sich mit zwei- und dreiwelligen Turbofantriebwerken und untersucht an ihnen, die Effekte der Leistungsnahmen. Als Simulationssoftware wurde GasTurb 8.0 eingesetzt und auf die integrierten Triebwerkskonfigurationen zurückgegriffen. Ziel der Arbeit ist die Ermittlung einer mathematischen Beziehung zur Berechnung des zusätzlichen Kraftstoffmassenstromes infolge einer Zapfluft- oder Wellenleistungsentnahme. So stellt sich die Frage, welche Triebwerksparameter dafür berücksichtigt werden müssen. Eine Wellenleistungsentnahme verursacht beispielsweise einen linearen Anstieg des spezifischen Kraftstoffverbrauches. Ist diese Zunahme, identisch mit der einer Zapfluftentnahme? Am Ende der Kapitel werden die Ergebnisse mit Literaturwerten verglichen und versucht Tendenzen zu erkennen bzw. bestehende zu erhärten.
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Carboni, Mattia. "Consequence assessment for the accidental release of the aviation turbine fuel Jet A-1." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2018.
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In questo lavoro di tesi si è svolto in prima istanza uno studio preliminare atto a individuare una miscela rappresentativa del combustibile aeronautico Jet A-1, a partire dai limiti imposti dal mercato e dagli standard europei. Esso è stato identificato come miscela di n-decano e toluene in composizione relativa tale da avere proprietà chimiche e fisiche simili rispetto alla miscela reale.
Successivamente è stato individuato un set ridotto di cinetiche (reazioni) e di composti tale da rendere possibile l’implementazione in codici fluidodinamici computerizzati (CFD). Ciò è stato ottenuto utilizzando un'analisi di sensitività numerica e utilizzando il software Cantera.
Nella seconda fase del lavoro è stato utilizzato il software di simulazione dinamica di incendi denominato Fire Dynamic Simulator (FDS) sviluppato dal National Institute of Standards and Technology (NIST). Tale software è stato applicato per la simulazione degli incendi di pozza (pool fire) e per la simulazione della dispersione dei vapori del surrogato Jet A-1 su pista, seguito da un innesco ritardato (flash fire).
Nel caso del pool fire sono state valutate le temperature e i flussi termici radiativi in funzione del tempo e dello spazio. Nel caso della dispersione dei vapori del combustibile in atmosfera è stata invece valutata la frazione molare di combustibile presente nell’aria rispetto alla distanza dal punto sorgente, ed è stata valutata la dimensione della nuvola infiammabile avendo come riferimento il limite inferiore di infiammabilità della miscela in esame.
Il confronto con i dati sperimentali presenti in letteratura, in particolare per il pool fire - nei termini di flusso termico rispetto alla distanza dell’incendio - ha evidenziato una notevole discrepanza con i valori ottenuti dal modello di default di FDS, mentre ha invece confermato la bontà dei risultati ottenuti utilizzando il modello cinetico semplificato – ma di dettaglio - ottenuto in questo lavoro.
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Benegas, Jayme Diego. "Evaluation of the Hybrid-Electric Aircraft Project Airbus E-Fan X." Master's thesis, Aircraft Design and Systems Group (AERO), Department of Automotive and Aeronautical Engineering, Hamburg University of Applied Sciences, 2019. http://d-nb.info/1204685894.
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Purpose - This master thesis evaluates the hybrid-electric aircraft project E-Fan X with respect to its economical and environmental performance in comparison to its reference aircraft, the BAe 146-100. The E-Fan X is replacing one of the four jet engines of the reference aircraft by an electric motor and a fan. A turboshaft engine in the cargo compartment drives a generator to power the electric motor. --- Methodology - The evaluation of this project is based on standard aircraft design equations. Economics are based on Direct Operating Costs (DOC), which are calculated with the method of the Association of European Airlines (AEA) from 1989, inflated to 2019 values. Environmental impact is assessed based on local air quality (NOx, Ozone and Particulate Matter), climate impact (CO2, NOx, Aircraft-Induced Cloudiness known as AIC) and noise pollution estimated with fundamental acoustic equations. --- Findings - The battery on board the E-Fan X it is not necessary. In order to improve the proposed design, the battery was eliminated. Nevertheless, due to additional parts required in the new configuration, the aircraft is 902 kg heavier. The turboshaft engine saves only 59 kg of fuel. The additional mass has to be compensated by a payload reduced by 9 passengers. The DOC per seat-mile are up by more than 10% and equivalent CO2 per seat-mile are more than 16% up in the new aircraft. --- Research limitations - Results are limited in accuracy by the underlying standard aircraft design calculations. The results are also limited in accuracy by the lack of knowledge of some data of the project. --- Practical implications - The report contributes arguments to the discussion about electric flight. --- Social implications - Results show that unconditional praise given to the environmental characteristics of this industry project are not justified.
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Rodrigo, Clinton. "Basic Comparison of Three Aircraft Concepts: Classic Jet Propulsion, Turbo-Electric Propulsion and Turbo-Hydraulic Propulsion." Master's thesis, Aircraft Design and Systems Group (AERO), Department of Automotive and Aeronautical Engineering, Hamburg University of Applied Sciences, 2019. http://d-nb.info/1204558019.
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Purpose - This thesis presents a comparison of aircraft design concepts to identify the superior propulsion system model among turbo-hydraulic, turbo-electric and classic jet propulsion with respect to Direct Operating Costs (DOC), environmental impact and fuel burn. --- Approach - A simple aircraft model was designed based on the Top-Level Aircraft Requirements of the Airbus A320 passenger aircraft, and novel engine concepts were integrated to establish new models. Numerous types of propulsion system configurations were created by varying the type of gas turbine engine and number of propulsors. --- Findings - After an elaborate comparison of the aforementioned concepts, the all turbo-hydraulic propulsion system is found to be superior to the all turbo-electric propulsion system. A new propulsion system concept was developed by combining the thrust of a turbofan engine and utilizing the power produced by the turbo-hydraulic propulsion system that is delivered via propellers. The new partial turbo-hydraulic propulsion concept in which 20% of the total cruise power is coming from the (hydraulic driven) propellers is even more efficient than an all turbo-hydraulic concept in terms of DOC, environmental impact and fuel burn. --- Research Limitations - The aircraft were modelled with a spreadsheet based on handbook methods and relevant statistics. The investigation was done only for one type of reference aircraft and one route. A detailed analysis with a greater number of reference aircraft and types of routes could lead to other results. --- Practical Implications - With the provided spreadsheet, the DOC and environmental impact can be approximated for any commercial reference aircraft combined with the aforementioned propulsion system concepts. --- Social Implications - Based on the results of this thesis, the public will be able to discuss the demerits of otherwise highly lauded electric propulsion concepts. --- Value - To evaluate the viability of the hydraulic propulsion systems for passenger aircraft using simple mass models and aircraft design concept.
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Retaureau, Ghislain J. "Detection of Surface Corrosion by Ultrasonic Backscattering." Thesis, Georgia Institute of Technology, 2006. http://hdl.handle.net/1853/11498.
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Corrosion often occurs in the inner aluminum lining of the HB-53 helicopter external fuel tank, resulting in fuel leaks. This project centers on developing an in-situ ultrasonic inspection technique to detect corroded areas inside the fuel tank. Due to the complexity of the composite structure of the tank, the ultrasonic inspection is carried out from inside the tank using a monostatic backscattering technique. The backscattered field contains information related to the insonified surface properties (surface roughness scales). Numerical predictions are implemented with a simplified model of backscattered intensity (Ogilvy, 1991). Experimental results are obtained on artificially corroded plates, and on the actual fuel tank of the HB-53 helicopter. Signal processing techniques (Envelope Correlation and Inverse Technique) are used to detect corroded surfaces with data obtained with a focused 10 MHz pulsed transducer.
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De, Grave Emiel. "Reverse Engineering of Passenger Jets - Classified Design Parameters." Master's thesis, Aircraft Design and Systems Group (AERO), Department of Automotive and Aeronautical Engineering, Hamburg University of Applied Sciences, 2017. http://d-nb.info/1204457298.
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This thesis explains how the classified design parameters of existing passenger jets can be determined. The classified design parameters are; the maximum lift coefficient for landing and take-off, the maximum aerodynamic efficiency and the specific fuel consumption. The entire concept is based on the preliminary sizing of jet powered civil aeroplanes. This preliminary sizing is explained in detail because it is the foundation of the final result. The preliminary sizing is combined using reverse engineering which is not a strict method. Therefore, only the basics are explained. By applying reverse engineering on the preliminary sizing and aiming for the classified design parameters as output, formulas are derived to calculate the maximum lift coefficients, the maximum aerodynamic efficiency and the specific fuel consumption. The goal is to calculate these parameters, using only aircraft specifications that are made public by the manufacturer. The calculations are complex with mutual relations, iterative processes and optimizations. Therefore, it is interesting to integrate everything in a tool. The tool is built in Microsoft Excel and explained in detail adding operating instructions. The program is executed for miscellaneous aeroplanes, supported with the necessary comments. Investigated aeroplanes are: Caravelle 10B (Sud-Aviation), Boeing 707-320C, BAe 146-200 (British Aerospance), A320-200 (Airbus), "The Rebel" (based on A320), Boeing SUGAR High, Boeing 747-400, Blended Wing Body VELA 2 (VELA) and Dassault Falcon 8X.
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Zhao, Yiming. "Efficient and robust aircraft landing trajectory optimization." Diss., Georgia Institute of Technology, 2012. http://hdl.handle.net/1853/43586.
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This thesis addresses the challenges in the efficient and robust generation and optimization of three-dimensional landing trajectories for fixed-wing aircraft subject to prescribed boundary conditions and constraints on maneuverability and collision avoidance. In particular, this thesis focuses on the airliner emergency landing scenario and the minimization of landing time.
The main contribution of the thesis is two-fold. First, it provides a hierarchical scheme for integrating the complementary strength of a variety of methods in path planning and trajectory optimization for the improvement in efficiency and robustness of the overall landing trajectory optimization algorithm. The second contribution is the development of new techniques and results in mesh refinement for numerical optimal control, optimal path tracking, and smooth path generation, which are all integrated in a hierarchical scheme and applied to the landing trajectory optimization problem.
A density function based grid generation method is developed for the mesh refinement process during numerical optimal control. A numerical algorithm is developed based on this technique for solving general optimal control problems, and is used for optimizing aircraft landing trajectories. A path smoothing technique is proposed for recovering feasibility of the path and improving the tracking performance by modifying the path geometry. The optimal aircraft path tracking problem is studied and analytical results are presented for both the minimum-time, and minimum-energy tracking with fixed time of arrival. The path smoothing and optimal path tracking methods work together with the geometric path planner to provide a set of feasible initial guess to the numerical optimal control algorithm.
The trajectory optimization algorithm in this thesis was tested by simulation experiments using flight data from two previous airliner accidents under emergency landing scenarios.The real-time application of the landing trajectory optimization algorithm as part of the aircraft on-board automation avionics system has the potential to provide effective guidelines to the pilots for improving the fuel consumption during normal landing process, and help enhancing flight safety under emergency landing scenarios. The proposed algorithms can also help design optimal take-off and landing trajectories and procedures for airports.
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Najafiyazdi, Alireza. "Theoretical and numerical analysis of supersonic inlet starting by mass spillage." Thesis, McGill University, 2007. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=111524.
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Supersonic inlet starting by mass spillage is studied theoretically and numerically in the present thesis. A quasi-one-dimensional, quasi-steady theory is developed for the analysis of flow inside a perforated inlet. The theory results in closed-form relations applicable to flow starting by the mass spillage technique in supersonic and hypersonic inlets.The theory involves three parameters to incorporate the multi-dimensional nature of mass spillage through a wall perforation. Mass spillage through an individual slot is studied to determine these parameters; analytical expressions for these parameters are derived for both subsonic and supersonic flow conditions. In the case of mass spillage from supersonic flows, the relations are exact. However, due to the complexity of flow field, the theory is an approximation for subsonic flows. Therefore, a correction factor is introduced which is determined from an empirical relation obtained from numerical simulations.
A methodology is also proposed to determine perforation size and distribution to achieve flow starting for a given inlet at a desired free-stream Mach number. The problem of shock stability inside a perforated inlet designed with the proposed method is also discussed.
The method is demonstrated for some test cases. Time-realistic CFD simulations and experimental results in the literature confirm the accuracy of the theory and the reliability of the proposed design methodology.
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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 aircraft noise. This process is necessary in order to allow the legislation to meet its purpose, namely, to protect the environment, the sources of the aircraft noise, and the effects of the aircraft noise on people. The second chapter describes the evolution of aircraft noise issues at the national levels in the US and throughout the EU, respectively, as well as at the international level, such as at the ICAO. The third chapter analyses the EU Regulation 925/1999, which created tension between the EU and the US due to its alleged discriminatory nature. This thesis examines the arguments of both sides. Finally, the fourth chapter analyses the noise certification standards developed by ICAO, namely the "balanced approach".
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Aliaga, Rivera Cristhian Neil. "An unsteady multiphase approach to in-flight icing /." Thesis, McGill University, 2008. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=112552.
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Ice accretion is a purely unsteady phenomenon that is presently approximated by most icing codes using quasi-steady modeling. The accuracy of ice prediction is thus directly related to the arbitrarily prescribed time span during which the impact of ice growth on both flow and droplets is neglected. The objective of this work is to remove this limitation by implementing a cost-effective unsteady approach. This is done by fully coupling, in time, a diphasic flow (interacting air and droplet particles) with the ice accretion model. The two-phase flow is solved using the Navier-Stokes and Eulerian droplet equations with dual-time stepping in order to improve computational time. The ice shape is either obtained from the conservation of mass and energy within a thin film layer for glaze and mixed icing conditions, or from a mass balance between water droplets impingement and mass flux of ice for rime icing conditions. The iced surface being constantly displaced in time, Arbitrary Lagrangian-Eulerian terms are added to the governing equations to account for mesh movement. Moreover, surface smoothing techniques are developed to prevent degradation of the iced-surface geometric discretization. For rime ice, the numerical results clearly show that the new full unsteady modeling improves the accuracy of ice prediction, compared to the quasi-steady approach, while in addition ensuring time span independence. The applicability of the unsteady icing model for predicting glaze ice accretion is also demonstrated by coupling the diphasic model to the Shallow Water Icing Model. A more rigorous analysis reveals that this model requires the implementation of local surface roughness and that previous quasi-steady validations cannot be carried out using a small number of shots, therefore the need for unsteady simulation.
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Nakakita, Kunio. "Toward real-time aero-icing simulation using reduced order models." Thesis, McGill University, 2007. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=99781.
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Even though the power of supercomputers has increased extraordinarily, there is still an insatiable need for more advanced multi-disciplinary CFD simulations in the aircraft analysis and design fields. A particular current interest is in the realistic three-dimensional fully viscous turbulent flow simulation of the highly non-linear aspects of aero-icing. This highly complex simulation is still computationally too demanding in industry, especially when several runs, such as parametric studies, are needed. In order to make such compute-intensive simulations more affordable, this work presents a reduced order modeling approach, based on the "Proper Orthogonal Decomposition", (POD), method to predict a wider swath of flow fields and ice shapes based on a limited number of "snapshots" obtained from complete high-fidelity CFD computations. The procedure of the POD approach is to first decompose the fields into modes, using a limited number of full-calculations snapshots, and then to reconstruct the field and/or ice shapes using those decomposed modes for other conditions, leading to reduced order calculations. The use of the POD technique drastically reduces the computational cost and can provide a more complete map of the performance degradation of an iced aircraft over a wide range of flight and weather conditions.
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Tremblay, Michel 1955 Feb 27. "The legal status of military aircraft in international law /." Thesis, McGill University, 2003. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=81237.
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Since the beginning of the history of aviation, the use of aircraft for military purposes revealed an efficient and dangerous weapon in the arsenal of a State. First it was used as observatory post, and then the aircraft took a more active role in combat until it became a destructive and deadly weapon. The definition of military aircraft in international law is not clear as States only wish to regulate international civil air navigation and not state aircraft. On the other hand, the Law of armed conflict defines the status of every aircraft with their respective duties and rights in the conduct of hostilities. The interception of civil aircraft by military aircraft shall be done in accordance with the international standards adopted by the International Civil Aviation Organization in virtue of the Chicago Convention and it's limited to determine the identity of the aircraft. The use of deadly force against civilian aircraft in flight is equivalent of pronouncing the death sentence of its occupants without the hearing of a trial. Respecting the international standards of interception of civil aircraft is a necessity.
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Dhanji, Nasreen. "Comparative study of aerial platforms for Mars exploration." Thesis, McGill University, 2007. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=112565.
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The primary objective of this thesis is to develop a framework to compare the performance of fixed-wing aircraft, airships, and the rotary-wing aircraft in the Martian environment and through that framework, determine which of these platforms is best suited to conduct a series of scientific investigations on Mars. Three Mars mission scenarios provide the context within which the performance of the platforms is evaluated. The mission scenarios are used to derive the performance requirements including the range and flight path to be covered, the altitude at which the platforms fly, and the scientific investigations to be performed along with the associated scientific instrumentation to be carried as payload. Existing platform designs are used for the purpose of this comparative study and are modified depending on specific mission requirements. A set of weighted performance metrics, including the gross takeoff mass, power required, manoeuvrability, and complexity, serves as a common basis for comparing the performance of the three aerial platforms. The results of this comparative study indicate that the airship is best suited for all mission scenarios considered due to its simplicity and high degree of manoeuvrability. However, it is important to note that a series of subjective design choices with respect to platform speed and available power were made that significantly impact the overall performance of the platforms. Altering these design choices as well as the mission requirements could result in a different platform being best suited for each Mars mission. For instance, increasing the cruising velocity of the fixed-wing aircraft may allow its dimensions to be scaled down thereby reducing the complexity and making it a more competitive platform for long-range missions. In addition, for short-range missions that do not require a high degree of manoeuvrability but where the gross takeoff mass and complexity are more important factors, the rotary-wing aircraft becomes the best option.
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Thomas, Peter W. 1969. "The effects of low-level flying military aircraft on the reproductive output of osprey in Labrador and northeastern Québec /." Thesis, McGill University, 1999. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=21654.
Full textAbstract:
The objective of this study was to determine whether low-level flying military aircraft affected the reproductive success of Osprey (Pandion haliaetus), and if so, to determine the optimal avoidance distance to minimize these effects. I studied 49 nests in 1995, and 68 nests in 1996 within the military low-level flying zone. Nest occupancy, clutch size, number of hatchlings, and number of young at 41 days of age were assessed at each nest. GIS flight track records provided frequency of aircraft at given distances and altitudes from the nest. Logistic regression analysis assessed the impact of flight frequency in four distance categories and four altitude categories on Osprey reproduction. The frequency of flights within each category were not accurate predictors of Osprey reproductive output. Nests were then randomly assigned to a buffer-zone radius of either 0, 1.85, 3.7, or to a control of 7.4 km, and reproductive output was compared among treatments, and between years. No significant differences were discovered among the reproductive parameters within either 1995 or 1996, but reproductive output was significantly higher in 1995, likely due to adverse weather conditions experienced in 1996.
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Venter, Jeanne Marie. "Autonomous air-to-air refueling : a comparison of control strategies." Thesis, Stellenbosch : Stellenbosch University, 2012. http://hdl.handle.net/10019.1/20239.
Full textAbstract:
Thesis (MScEng)--Stellenbosch University, 2012.ENGLISH ABSTRACT: The air-to-air refuelling of large aircraft presents challenges such as a long fuel transfer time, slow aircraft responses and a large distance between the aircraft CG and the receptacle position. This project addresses some of these issues by adding a control system to keep the receiver aircraft in the correct position relative to the tanker to enable fuel transfer. This project investigates different control strategies which are designed to control the A330-300 during refuelling at one trim condition. The controllers are based on a mathematical aircraft model which was derived from a simulation model received from Airbus. The first set of controllers uses the aircraft actuators directly. Controllers that are based on the CG dynamics and the receptacle dynamics are compared. Due to the large distance between the CG and the receptacle it was found to be essential to control the receptacle position, and not only the CG position. Also, a controller that is based on a model of the receptacle dynamics performs better. The second set of controllers uses the aircraft manual control laws as an inner loop controller. This set of controllers and the last direct actuator controller use the same axial controller that uses the engine thrust to control axial position. It was found that both the direct actuator controller and the manual control laws controller are able to keep the receptacle within the disconnect envelope in moderate turbulence. In both sets of controllers the axial controller fails to keep the receptacle reliably within the disconnect envelope in light turbulence. From the results it is concluded that both the direct actuator control and manual control laws can be used to successfully control the receptacle position in the normal and lateral positions as long as the receptacle kinematics are included in the control design. Using only the engine thrust for axial control is insufficient. Several recommendations are made to improve the axial control and also how these results can be used in future work.
AFRIKAANSE OPSOMMING: Die lug-tot-lug brandstof hervulling van groot vliegtuie het uitdagings soos ’n lang hervullingstyd, stadige vliegtuig dinamika en ’n groot afstand tussen die hervullingspoort en die vliegtuig massamiddelpunt. Hierdie projek spreek sommige van hierdie uitdagings aan deur ’n beheerstelsel by te voeg wat die vliegtuig in die korrekte posisie relatief tot die tenker hou vir brandstofoordrag om plaas te vind. Hierdie projek ondersoek verskillende beheerstrategieë wat ontwerp is om die A330- 300 te beheer by ’n enkele gestadigde toestand. Die beheerders is gebaseer op ’n wiskundige vliegtuigmodel wat vanaf ’n simulasiemodel afgelei is. Die simulasiemodel is vanaf Airbus verkry. Die eerste stel beheerders beheer direk die vliegtuig se beheeroppervlakke. Beheerders wat onderskeidelik die massamiddelpunt en die hervullingspoort beheer word vergelyk. Daar is gevind dat dit essensieel is om die hervullingspoort te beheer en nie slegs die massamiddelpunt nie, as gevolg van die groot afstand tussen hierdie twee punte. Die tweede stel beheerders gebruik die vliegtuig se eie beheerwette as ’n binnelusbeheerder en vorm self die buitelus. Albei stelle beheerders gebruik dieselfde aksiale beheerder wat enjin stukrag gebruik om die aksiale posisie te beheer. Daar is gevind dat beide stelle beheerders die hervullingspoort binne die ontkoppelingsbestek kan hou in die normale en laterale rigtings tydens matige turbulensie. In beide stelle beheerders is dit die aksiale beheerder wat faal om die hervullingspoort betroubaar in posisie te hou, selfs in ligte turbulensie. Vanaf die resultate word afgelei dat beide die direkte beheerder en die buitelusbeheerder gepas is om die laterale en normale posisiebeheer toe te pas mits die dinamika van die hervullingspoort in ag geneem word. Om slegs stukrag te gebruik vir aksiale beheer is nie voldoende nie, en verskeie voorstelle word gemaak om die aksiale beheer te verbeter in toekomstige navorsing.
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Aguilar, Cortés Carlos Ezequiel. "Air carrier liability and automation issues." Thesis, McGill University, 2002. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=78196.
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Our intended topic is a general discussion of the basic elements of liability related to airline accidents to which fully automated cockpits have constituted an associated contributory factor. In addition we addressed the liability of air carriers arising from injuries or death caused to passengers traveling on international flights. For this purpose, we reviewed the Warsaw System and the different international instruments that constitute it. We also reviewed principles of common law applicable to aircraft manufacturers and the "Free Flight" as an example of the growing automation environment, which is a general benefit to commercial aviation but also a likely contributory cause for accidents in particular cases. In the last part we briefly discuss a personal view regarding the interplay between manufacturers and airlines under the 1999 Montreal Convention, which is an international treaty unifying the desegregated Warsaw System into one single instrument that is expected to enter into force in a few years.
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Monferran, Paul. "Modèles numérique et stochastique des fixations pour la contrainte foudre des lignes d’assemblages sur avion." Thesis, Limoges, 2018. http://www.theses.fr/2018LIMO0095/document.
Full textAbstract:
Les effets de la foudre sur les lignes d'assemblage des avions peuvent s'avérer catastrophiques. L'un des phénomènes redoutés est l'étincelage au niveau d'une fixation bien souvent associé à un défaut sur les résistances de contact. Au vu des contraintes normatives, du manque de connaissance de cette problématique multi-physiques et de l'incapacité structurelle à avoir une approche uniquement expérimentale, les avionneurs se sont notamment tournés vers la modélisation. Dans ce manuscrit, on s'intéresse particulièrement à la modélisation des lignes d'assemblage pour le dimensionnement de la contrainte locale sur celles-ci. La méthode des différences finies dans le domaine temporel (FDTD), couramment utilisée pour la problématique foudre en aéronautique, nous sert de méthode de résolution. De multiples modèles de fixations allant de modèles simplifiés, représentant par exemple la fixation par un fil résistif, à des modèles plus complexes, représentant l'ensemble des résistances de contact, sont développés et validés. Par ailleurs, pour répondre aux incertitudes associées aux résistances de contact des fixations, des modèles statistiques sont appliqués aux paramètres résistifs des modèles de fixation. Ces mêmes modèles statistiques découlent de l'étude d'une base de données issue d’une campagne de mesures menée par Dassault Aviation sur un ensemble d’éprouvettes tests. A l'aide de ces modèles, la contrainte sur les fixations d'un caisson représentant un réservoir de carburant d'un avion est étudiée de manière stochastiqueThe lightning effects on the fastening assemblies of an airplane may be critical. One of the most critical phenomenon is the sparking effect around the fasteners. This effect is usually associated to the contact resistances. Due to the standards, the lack of knowledge about this multiphysics issue and the inability to follow only an experimental approach, the aircraft manufacturers have chosen a modelling way. In this manuscript, we model the fastening assemblies in order to understand the local constraint on these assemblies. The finite difference time domain (FDTD) method mostly used for the lightning issue in the aircraft industry is chosen as the solving method. Several fastener models are developed and validated. We present simplified models, as the resistive wire model for instance, up to complex one with all the contact resistance of the fastener. Furthermore, due to the large uncertainties from one fastener to the other one in the same family, the fastener models are supplemented with statistical models. Thanks to a data base measurement created from several measurement campaigns made by Dassault Aviation, distribution laws are established to characterize the lightning injection effects or the state after lightning injection on the fasteners. Using this statistical models, a stochastic study is presented in order to evaluate the uncertainties in a fuel tank modelling
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Bencalík, Karol. "Návrh úprav letounu VUT 001 MARABU s pohonem vodíkovými palivovými články a bateriemi." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2009. http://www.nusl.cz/ntk/nusl-374587.
Full textAbstract:
The main topic of this thesis is a design of VUT 001 airplane fuel transformation by means of fuel cells and storage batteries. A list of components available on the market was drawn up, their building in the airplane and the engineering design for mounting the electric motor into the structure. The thesis also includes the mass and centering analysis of flight performance and stability control.
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Weldon, John Phillips. "Dimensioned system dynamics modeling with external subprograms for Air Force aviation fuel." Phd thesis, 1993. http://hdl.handle.net/1885/145688.
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Nahorniak, Matthew T. "Feasibility of Lorentz mixing to enhance combustion in supersonic diffusion flames." Thesis, 1996. http://hdl.handle.net/1957/34208.
Full textAbstract:
The purpose of this research was to determine if it is feasible to apply Lorentz
mixing to supersonic diffusion flames, such as those found in SCRAMjet engines. The
combustion rate in supersonic diffusion flames is limited by the rate at which air and fuel
mix. Lorentz mixing increases turbulence within a flow, which increases the rate at which
species mix and thus increases the rate of combustion.
In order to determine the feasibility of Lorentz mixing for this application, a two-dimensional model of supersonic reacting flow with the application of a Lorentz force has been examined numerically. The flow model includes the complete Navier-Stokes equations, the ideal gas law, and terms to account for diffusion of chemical species, heat release due to chemical reaction, change in species density due to chemical reaction, and the Lorentz forces applied during Lorentz mixing. In addition, the Baldwin-Lomax turbulence model is used to approximate turbulent transport properties.
A FORTRAN program using the MacCormack method, a commonly used computational fluid dynamics algorithm, was used to solve the governing equations. The accuracy of the program was verified by using the program to model flows with known solutions.
Results were obtained for flows with Lorentz forces applied over a series of power levels and frequencies. The results show significant increases in the rate of combustion
when Lorentz mixing is applied. The amount of power required to drive Lorentz mixing is small relative to the rate at which energy is released in the chemical reaction. An optimum frequency at which to apply Lorentz mixing was also found for the flow being considered.
The results of the current study show that Lorentz mixing looks promising for increasing combustion rates in supersonic reacting flows, and that future study is warranted. In particular, researchers attempting to improve combustion in SCRAMjet engines may want to consider Lorentz mixing as a way to improve combustion.Graduation date: 1997
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Diggines, Colin Neville. "A business analysis of the South African domestic commercial air transport market : low-cost carriers and full-service carriers in the context of the business environment and passenger behaviours." Thesis, 2017. http://hdl.handle.net/10500/23853.
Full textAbstract:
This study attempted to establish the travel behaviours and choice criteria of the South African domestic air passenger and how they differed between low-cost carriers (LCCs) and full-service carriers (FSCs). The study was quantitative and used structured questionnaires to collect data via personal interviews. Descriptive and inferential techniques were used to analyse the data, including a binomial logistic
regression to identify predictors of model choice. Analysis This study attempted to establish the travel behaviours and choice criteria of the South African domestic air passenger and how they differed between low-cost carriers (LCCs) and full-service carriers (FSCs).
The study was quantitative and used structured questionnaires to collect data via personal interviews. Descriptive and inferential techniques were used to analyse the data, including a binomial logistic
regression to identify predictors of model choice. Analysis showed that passengers had a limited understanding of the functioning of the models. This results in consumer perceptions and expectations being discordant with the true differences. In distinguishing between models, LCC passengers rate LCCs more favourably than FSC passengers, but
both rate FSCs higher than LCCs. This shows the need of consumers to have the features and services of the FSCs. Amongst the key findings was the absolute importance of price to the passengers on both models when purchasing the ticket. The analysis showed that LCC passengers are highly price sensitive and show loyalty to the lowest price (not airline model). It was apparent that frequent flyer programmes (FFP), or linkages to 3rd party loyalty programmes, for LCCs need to be reconsidered. Younger LCC passengers especially, indicated a need for a simple FFP to receive some form of ‘reward’, as well as benefits traditionally only offered by FSCs. FSC passengers show a greater degree of loyalty and less fare sensitivity. This provides the FSCs with a degree of fare flexibility and the opportunity to move
their loyal, less price-sensitive consumers up the price curve to maximise revenue. It was shown that, in distinguishing themselves from FSCs, it is important that LCCs are perceived as being more affordable than FSCs and are offering a value-for-money service. In essence, LCCs have to defend their positioning by (i) ensuring that their fares are not perceived to be as high as a FSCs and (ii)
watching that the FSC fares are not declining to a level where FSCs are perceived as being as cheap as a LCC. For LCCs, brand building strategies around issues other than fare need to be devised, with
attention paid to identifying determinant factors.Business Management
D. Com (Business Management)