Dissertations / Theses: 'Concept of aircraft leasing'

1

Pompongsuk, Prasert. "International aircraft leasing : impact on international air law treaties." Thesis, McGill University, 1997. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=20544.

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Aircraft leasing is a method of fleet acquisition. It was known to none at the outset of the air traffic era; as a result, international air law treaties were not formulated upon the concept that realized the practices as such. The moment international aircraft leasing materialized, many regimes of international air law became unsuited to the situation.
On the one hand, public international air law treaties have faced the problems ranging from safety oversight responsibilities and aircraft accident investigation to airport charges and criminal jurisdiction.
On the other hand, private international air law treaties have faced the problems ranging from applicability of the 1952 Rome Convention and preferential rights under the 1948 Geneva Convention to aircraft engine leasing and the idiosyncrasy of leasing transactions.
This study is not aimed at scrutinizing leasing transactions but at examining the aforementioned difficulties, especially the issues of public international air law.

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2

Pompongsuk, Prasert. "International aircraft leasing, impact on international air law treaties." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 1998. http://www.collectionscanada.ca/obj/s4/f2/dsk1/tape11/PQDD_0004/MQ44072.pdf.

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3

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 analysis is made to determine a geometry for which the aircraft is statically stable in pitch. The study shows that a canard configuration together with pusher contra rotating propellers is a good way to design a very efficient aircraft. It is also found out that the most energy efficient way to climb is to use a high rate of climb and a low velocity and that it can be profitable to increase the weight of the aircraft with more batteries.

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4

Guidone, Luigi. "Lease and leasing of aircraft in Italy and Quebec : default of the lessee." Thesis, McGill University, 1999. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=30301.

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Although the contracts of lease and leasing have been used for many years by airline companies, increase in traffic volume predicted for the following years will certainly determine a greater need for aircrafts and consequently a greater demand for use of these kind of contracts.
Not only do they offer economic benefits but they are also very important instruments in the hands of an airline for fleet planning.
Operating and financial lessors have a wide market for their costly "toys", but, as the market and profits expand, so does the need for lessors to be at any time able to keep total control of them. In fact, one of the biggest fears for a lessor is to loose his property because he is not able to repossess it after a default of the lessee.
This thesis first briefly overviews the contract of lease and leasing and how the latter, being a contract of common law origin, has been included in the legal systems of two civil law countries like Italy and Quebec. Subsequently, the main clauses of a contract of aircraft lease or leasing are analysed not only to see the duties that a lessee entering into such a contract has, but also to see if these clauses follow the provisions which govern the contract, in general, and the contract of lease and leasing, in particular, in Italy and Quebec.
Chapter II deals with the remedies that, in case of the lessee's default, a lessor has, in Italy and Quebec, in order to repossess his aircraft; whether these remedies can guarantee speedy repossession and whether the remedy of the "self-help repossession", which is a typical common law legal instrument, can be applied in Italy and Quebec.
Finally there is a short analysis of the "Convention on International Interests in Mobile Equipment" which is being drafted by Unidroit and its possible help in solving the problem of quick repossession in the case of a default by the lessee.

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5

Kellogg, Erin C. "Internal dynamics of the short-term commercial aircraft engine leasing market." Thesis, Massachusetts Institute of Technology, 2016. http://hdl.handle.net/1721.1/104566.

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Thesis: M.B.A., Massachusetts Institute of Technology, Sloan School of Management, 2016. In conjunction with the Leaders for Global Operations Program at MIT.
Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2016. In conjunction with the Leaders for Global Operations Program at MIT.
Cataloged from PDF version of thesis.
Includes bibliographical references (pages 71-72).
General trends in the commercial aircraft aftermarket indicate an increased reliance of leased engines in operators' spare engine strategies. A methodology for forecasting short-term engine lease demand is developed using Pratt & Whitney's existing simulation capability. This method demonstrates the ability to estimate demand mean and variance. This forecast is then used in a single SKU inventory model to set inventory levels. Using historical data this method demonstrates the ability to recommend inventory levels that minimize stock outs. A less computationally intensive system dynamics model is then constructed to replicate the lease demand forecasting model. Sensitivity analysis is performed using the system dynamic model and influential parameters are identified. The results of the sensitivity study are used to propose and test a new sales strategy for short-term engine lessors.
by Erin C. Kellogg.
M.B.A.
S.M.

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6

Eustace, Paul Alan. "Structural mass of innovative concept aircraft." Thesis, Loughborough University, 2001. https://dspace.lboro.ac.uk/2134/7361.

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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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8

Guidone, Luigi. "Lease and leasing of aircraft in Italy and Quebec, default of the lessee." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 2000. http://www.collectionscanada.ca/obj/s4/f2/dsk2/ftp03/MQ64277.pdf.

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9

Mo, Yuet-ha Rita, and 巫月霞. "An international comparison of the accounting treatment of aircraft leasing in airline accounts." Thesis, The University of Hong Kong (Pokfulam, Hong Kong), 1989. http://hub.hku.hk/bib/B3126444X.

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10

Mo, Yuet-ha Rita. "An international comparison of the accounting treatment of aircraft leasing in airline accounts /." [Hong Kong] : University of Hong Kong, 1989. http://sunzi.lib.hku.hk/hkuto/record.jsp?B12373904.

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11

Wang, Yan 1973. "Evolution of aircraft finance law : considerations of the UNIDROIT reform project relating to aircraft equipment." Thesis, McGill University, 2000. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=30332.

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After more than ten years from its initiation by the Canadian delegation in 1988, the UNIDROIT's legal reform in the area of international security and leasing interests in mobile equipment reached its final stage of discussion at the international level. A Preliminary Draft UNIDROIT Convention on International Interests in Mobile Equipment (" Convention") and a Preliminary Draft Protocol on Matters Specific to Aircraft Equipment ("Protocol") present an evolution of the international security law and the aircraft finance law in particular. The "Convention", as applied through the "Protocol", particularly aims at economic benefits for the aviation industry, which has to cope with considerable financing difficulties due to the uncoordinated national security laws. This thesis addresses legal and economic issues behind the UNIDROIT proposal.
The texts of the "Convention" and the " Protocol" as reviewed by the Drafting Committee of the First Joint Session (Rome, 1--12 February 1999), are attached in the Appendix. (Abstract shortened by UMI.)

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12

Teo, Cheng Hang 1976. "Advanced aircraft seat design : the webbing concept." Thesis, Massachusetts Institute of Technology, 1999. http://hdl.handle.net/1721.1/50543.

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Thesis (M.Eng.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1999.
Includes bibliographical references (leaf 95).
Air travel is so common in this day and age that any significant improvement in seat comfort on board a commercial passenger jet is likely to affect almost everybody. A proposed design concept in this project is the use of webbing as the substitute for current foam cushioning in the seat back. The result is a webbing-foam hybrid cushioning design that utilizes the benefits of both cushioning types to maximum effect. Experimental tests suggest that this design would also provide better overall comfort for the passenger. As a result, both consumer and industry would profit immensely from the implementation of such a design.
by Cheng Hang Teo.
M.Eng.

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13

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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14

Hučíková, Julie. "Vykazování Leasingu dle IFRS." Master's thesis, Vysoká škola ekonomická v Praze, 2015. http://www.nusl.cz/ntk/nusl-264016.

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In the final thesis I deal with problems of lease reporting according to effective framework of International Financing and Reporting Standards. In the thesis, which is divided into theoretical and practical part, I focus on impacts of leasing transactions primarily on the lessee side. In the theoretical part of thesis that is divided into three subchapters I summarize facts about leasing. The first two subchapters are based on standard IAS 17. I devote the third subchapter to preparation of new standard, which should replace IAS 17. The aim of the practical part of the thesis is to find out which way the European airlines use to finance their aircraft, I focus especially on using of both types of leasing. Therefore in the second part of the thesis I analyze annual reports of European aircrafts and examine how much these airlines exploit the possibility to finance the aircraft by leasing and how they report it in their annual reports.

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15

Krupski, Jan A. "Conflict of laws in aircraft securitisation : jurisdictional and material aspects of the 1998 Unidroit Reform Project relating to aircraft equipment." Thesis, McGill University, 1998. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=21689.

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In June 1998, a Steering and Revisions Committee of the International Institute for the Unification of Private Law (Unidroit) fleshed out the final version of a "Draft Unidroit Convention on International Interests in Mobile Equipment".
Framed by introductory and concluding remarks, the thesis is divided into five chapters. One after the other, these components will expound the generation and elaboration of the reform project, synchronise its jurisdictional aspects with the pre-existing law of international civil procedure and of conflict of jurisdictions, trace intimately related other harmonisation efforts, and briefly compare conventional and up-to-date substantive and conflict of law rules of selected Common and Civil Law jurisdictions that apply to secured transactions and their underlying contractual relationships. It will also review the essential legal characteristics of the 50 years old Geneva Convention on the International Recognition of Rights in Aircraft and ascertain its qualities in the light of present-day demands, before turning to the gist of substantive and uniform security and assignment law as applicable on the basis of the newly created transnational registration mechanism. (Abstract shortened by UMI.)

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16

Gómez, González Victor, and Collado Emilio José Izquierdo. "The Cormoran project: a new concept in commercial aircraft design." Thesis, KTH, Aerodynamik, 2013. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-121357.

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This paper presents a new revolutionary design in commercial aircraft: the conven-tional vertical and horizontal tails are not present as generally known, and their contri-bution to the manoeuvering of the aircraft, namely the presence of the rudder and theelevators, is achieved by locating them at the wingtips and in the canard, respectively.Substituting the horizontal tail with the canard, the possibility of dividing the fuel be-tween the wing (where it is located conventionally) and the canard allows the pilot tochange the center of gravity during the ight with more freedom, while the eect of theelevators continues present. Locating the vertical stabilizers at the wingtips combinesthe eect of the vertical stabilizer and the winglet all in one, with the corresponding lostof weight. In this sense, the aerodynamic, stability and aeroelastic characteristics of anaircraft such as the one described have been analyzed using dierent modules belongingto CEASIOM program, and the results are very encouraging, showing that it is reallyfeasible to change the current concept of the commercial aircraft without penalizing theperformance.

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17

Iglesias-Badillo, Eduardo J. "International recognition of property interests in leased aircraft : the new unidroit convention on mobile equipment." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 1999. http://www.collectionscanada.ca/obj/s4/f2/dsk2/ftp03/MQ64283.pdf.

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18

Park, Eun Ho M. B. A. Massachusetts Institute of Technology. "Lease classification of aircraft leasing : a case study of cross-border leases between Korean Air and its subsidiary." Thesis, Massachusetts Institute of Technology, 2007. http://hdl.handle.net/1721.1/39522.

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Thesis (M.B.A.)--Massachusetts Institute of Technology, Sloan School of Management, 2007.
"June 2007."
Includes bibliographical references (leaf 59).
Aircraft leasing represents a significant portion of the financial statements of airline firms. Accounting treatment of lease transactions is becoming more complicated as firms attempt to achieve off-balance-sheet outcomes vis a vis special purpose entities(SPC). Cross-border leasing involving SPCs in particular raises a variety issues stemming from international differences between accounting regimes. This thesis utilizes an example of cross-border leasing between Korean Air and its Irish subsidiary to illustrate the complexity related to lease classification. It begins by exploring the industry background, the concept of leasing, traditional lease criteria and current issues/trends in accounting. Next, relevant lease accounting rules are reviewed and compared to international and US GAAP. This includes key issues in lease classification such as 'substance of transactions' and 'the financial impact on the related parties'. The study reveals that the case can be assessed differently within the context of terms and conditions of the lease and related accounting rules. While such accounting interpretation may vary, the best answer appears that it is essential that firms present transparent financial information to the related parties.
by Eun Ho Park.
M.B.A.

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19

Buonanno, Michael Alexander. "A Method for Aircraft Concept Exploration using Multicriteria Interactive Genetic Algorithms." Diss., Georgia Institute of Technology, 2005. http://hdl.handle.net/1853/7571.

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The problem of aircraft concept selection has become increasingly difficult in recent years due to changes in the primary evaluation criteria of concepts. In the past, performance was often the primary discriminator whereas modern programs have placed increased emphasis on factors such as environmental impact, economics, supportability, aesthetics, and other metrics. The revolutionary nature of the vehicles required to simultaneously meet these conflicting requirements has prompted a shift from design using historical data regression techniques for metric prediction to the use of sophisticated physics-based analysis tools that are capable of analyzing designs outside of the historical database. The use of optimization methods with these physics-based tools, however, has proven difficult because of the tendency of optimizers to exploit assumptions present in the models and drive the design towards a solution which, while promising to the computer, may be infeasible due to factors not considered by the computer codes. In addition to this difficulty, the number of discrete options available at this stage may be unmanageable due to the combinatorial nature of the concept selection problem, leading the analyst to select a sub-optimum baseline vehicle. Some extremely important concept decisions, such as the type of control surface arrangement to use, are frequently made without sufficient understanding of their impact on the important system metrics due to a lack of historical guidance, computational resources, or analysis tools. This thesis discusses the difficulties associated with revolutionary system design, and introduces several new techniques designed to remedy them. First, an interactive design method has been developed that allows the designer to provide feedback to a numerical optimization algorithm during runtime, thereby preventing the optimizer from exploiting weaknesses in the analytical model. This method can be used to account for subjective criteria, or as a crude measure of un-modeled quantitative criteria. Other contributions of the work include a modified Structured Genetic Algorithm that enables the efficient search of large combinatorial design hierarchies and an improved multi-objective optimization procedure that can effectively optimize several objectives simultaneously. A new conceptual design method has been created by drawing upon each of these new capabilities and aspects of more traditional design methods. The ability of this new technique to assist in the design of revolutionary vehicles has been demonstrated using a problem of contemporary interest: the concept exploration of a supersonic business jet. This problem was found to be a good demonstration case because of its novelty and unique requirements, and the results of this proof of concept exercise indicate that the new method is effective at providing additional insight into the relationship between a vehicle's requirements and its favorable attributes.

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20

Perrella, Sil A. "The mobile aircraft maintenance office concept from a wide area perspective." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2003. http://library.nps.navy.mil/uhtbin/hyperion-image/03Mar%5FPerrella.pdf.

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Thesis (M.S. in Information Technology Management)--Naval Postgraduate School, March 2003.
Thesis advisor(s): Norman F. Schneidewind, Douglas E. Brinkley. Includes bibliographical references (p. 101-102). Also available online.

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21

Welstead, Jason Crouse Gilbert L. "Stability analysis of a segmented free-wing concept for UAS gust alleviation in adverse environments." Auburn, Ala, 2009. http://hdl.handle.net/10415/1847.

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22

Broszat, Dominik. "Aircraft engine noise footprint reduction via a non-uniform inlet liner concept." kostenfrei, 2008. http://mediatum2.ub.tum.de/node?id=654812.

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23

Mesrobian, Chris Eden. "Concept Study of a High-Speed, Vertical Take-Off and Landing Aircraft." Thesis, Virginia Tech, 2009. http://hdl.handle.net/10919/35574.

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The purpose of the study was to evaluate the merits of the DiscRotor concept that combine the features of a retractable rotor system for vertical take-off and landing (VTOL) with an integral, circular wing for high-speed flight. Tests were conducted to generate basic aerodynamic characteristics of the DiscRotor in hover and in fixed-wing flight.

To assess the DiscRotor during hover, small scale tests were conducted on a 3ft diameter rotor without the presence of a fuselage. A â hover rigâ was constructed capable of rotating the model rotor at speeds up to 3,500 RPM to reach tip speeds of 500fps. Thrust and torque generated by the rotating model were measured via a two-component load cell, and time averaged values were obtained for various speeds and pitch angles. It has been shown that the DiscRotor will perform well in hover. Ground Effects in hover were examined by simulating the ground with a movable, solid wall. The thrust was found to increase by 50% compared to the ground-independent case. Pressure distributions were measured on the ground and disc surfaces. Velocity measurements examined the flow field downstream of the rotor by traversing a seven hole velocity probe. A wake behind the rotor was shown to contract due to a low pressure region that develops downstream of the disc.

Wind tunnel experimentation was also performed to examine the fixed wing flight of the DiscRotor. These experiments were performed in the VA Tech 6â X6â Stability Tunnel. A model of the fuselage and a circular wing was fabricated based upon an initial sizing study completed by our partners at Boeing. Forces were directly measured via a six degree of freedom load cell, or balance, for free stream velocities up to 200fps. Reynolds numbers of 2 and 0.5 million have been investigated for multiple angles of attack. Low lift-to-drag ratios were found placing high power requirements for the DiscRotor during fixed-wing flight. By traversing a seven-hole velocity probe, velocities in a 2-D grid perpendicular to the flow were measured on the model. The strengths of shed vortices from the model were calculated. A method to improve fixed-wing performance was considered where two blades were extended from the disc. An increase of 0.17 in the CL was measured due to the interaction between the disc and blades.

This research utilized a wide range of experiments, with the aim of generating basic aerodynamic characteristics of the DiscRotor. A substantial amount of quantitative data was collected that could not be included in this document. Results aided in the initial designs of this aircraft for the purpose of evaluating the merit of the DiscRotor concept.
Master of Science

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24

Gatley, Sarah Lee. "Integrated flight and propulsion control of a future V/STOL aircraft concept." Thesis, University of Leicester, 2001. http://hdl.handle.net/2381/30190.

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A robust integrated flight and propulsion control (IFPC) system is designed and analysed for an experimental vertical/short take-off and landing (V/STOL) aircraft configuration, using multivariable design techniques. The model used for the design is based on the DERA VAAC Harrier wide envelope model (WEM) airframe with a Rolls-Royce Spey engine. This provides a detailed, large-scale, interacting full-envelope, nonlinear simulation model, thought likely to be representative of the next generation of V/STOL aircraft. The centralised IFPC system is evaluated in piloted simulation trials on DERA's real-time all-vehicle simulator (RTAVS), the results of which indicate that level 1 or 2 handling qualities are achieved over the low-speed powered-lift region of the flight envelope. The application of the structured singular value, , and the -gap metric to the problem of evaluating the robustness properties of this multivariable IFPC system is presented. The centralised controller is subsequently partitioned into decentralised lower-order airframe and engine subcontrollers, in order to address implementation and testing issues. The partitioned system is seen to retain largely both the performance and robustness properties of the centralised system. Due to the particular implementation structure used for the centralised H loop shaping controller, the partitioning procedure described can be applied to general two-degree-of-freedom control systems. A scheme to guarantee maximum limits on safety-critical engine variables is developed and applied, to preserve the structural integrity of the engine during extreme manoeuvres. As the system frequently operates on the position limits of the engine actuators, an anti-windup scheme is implemented to maintain the performance of the system during actuator saturation.

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25

Djojonegoro, Anda. "The UNIDROIT international aviation finance law reform project : preparing the world to adopt to a new aircraft mortgage convention." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 2000. http://www.collectionscanada.ca/obj/s4/f2/dsk2/ftp03/MQ64270.pdf.

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26

Knöös, Franzén Ludvig, and Erik Magnusson. "Weight Penalty Methods for Conceptual Aircraft Design." Thesis, Linköpings universitet, Fluida och mekatroniska system, 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-175012.

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This report addresses a project conducted at Saab Aeronautics during the spring of 2018. The goal of the project was to investigate aircraft weight estimations in the conceptual design phase. The work was divided into two major parts: finding new weight estimation techniques and implementing an existing technique called the Berry Weight Estimation in to the Pacelab APD software. Several weight estimation techniques were found during an extensive literature review but in the end, only one was chosen for further investigation. The chosen technique was the NASA Wing Weight Build-Up which proposed calculations for wing weights based on aircraft statistics. It contained material data tables for determining so called K-factors that were used to essentially scale the individual wing weight formulas. The data tables did not include K-factors up to a load factor of 9 which was a requirement from Saab. Extrapolations of the material data tables were done to approximate the missing values. The NASA wing weight build-up showed promising results with little deviation from the actual wing weight for a few chosen aircraft. This weight estimation technique was consequently chosen as a worthy candidate for a future implementation in the Pacelab APD software. The task of implementing the Berry Weight Estimation in Pacelab APD was divided into a fuselage- and a wing part. This was done to ease the implementation since it would resemble the original description of the method. The wing and fuselage weights were both calculated in two steps. The first step was to calculate a gross shell weight. This is the weight of an idealized structure without cut-outs or imperfections. The second step was to add so called weight penalties for various components within the wing or fuselage. Typical aircraft components had associating weight penalty functions described in the Berry Weight Estimation. Most of the implemented calculations used Pacelab APD to get involved parameters automatically. However, some of the needed parameters had to be user specified for the implemented Berry Weight Estimation to work. Once the implementation task was finished, several sensitivity studies were made to establish a perception about the involved parameters impact on the Berry Weight Estimation results. The new implementation gave benefits compared with the Berry Weight Estimation in Bex. One of these was the ability to perform extensive trade- and sensitivity studies. The sensitivity studies gave verdicts on the most influencing parameters of the implemented code and guide lines on future improvements of the calculations. These sensitivity studies show, among other things, that is recommended to increase the number of wing and fuselage stations significantly in order to get a converged result for the Berry Weight Estimation.

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Munjulury, Raghu Chaitanya. "Knowledge-Based Integrated Aircraft Design : An Applied Approach from Design to Concept Demonstration." Doctoral thesis, Linköpings universitet, Fluida och mekatroniska system, 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-137646.

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The design and development of new aircraft are becoming increasingly expensive and timeconsuming. To assist the design process in reducing the development cost, time, and late design changes, the conceptual design needs enhancement using new tools and methods. Integration of several disciplines in the conceptual design as one entity enables to keep the design process intact at every step and obtain a high understanding of the aircraft concepts at early stages. This thesis presents a Knowledge-Based Engineering (KBE) approach and integration of several disciplines in a holistic approach for use in aircraft conceptual design. KBE allows the reuse of obtained aircrafts’ data, information, and knowledge to gain more awareness and a better understanding of the concept under consideration at early stages of design. For this purpose, Knowledge-Based (KB) methodologies are investigated for enhanced geometrical representation and enable variable fidelity tools and Multidisciplinary Design Optimization (MDO). The geometry parameterization techniques are qualitative approaches that produce quantitative results in terms of both robustness and flexibility of the design parameterization. The information/parameters from all tools/disciplines and the design intent of the generated concepts are saved and shared via a central database. The integrated framework facilitates multi-fidelity analysis, combining low-fidelity models with high-fidelity models for a quick estimation, enabling a rapid analysis and enhancing the time for a MDO process. The geometry is further propagated to other disciplines [Computational Fluid Dynamics (CFD), Finite Element Analysis (FEA)] for analysis. This is possible with an automated streamlined process (for CFD, FEM, system simulation) to analyze and increase knowledge early in the design process. Several processes were studied to streamline the geometry for CFD. Two working practices, one for parametric geometry and another for KB geometry are presented for automatic mesh generation. It is observed that analytical methods provide quicker weight estimation of the design and when coupled with KBE provide a better understanding. Integration of 1-D and 3-D models offers the best of both models: faster simulation, and superior geometrical representation. To validate both the framework and concepts generated from the tools, they are implemented in academia in several courses at Linköping University and in industry

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28

Peterson, Gustav. "Sizing and Balance Module Development for Aircraft Conceptual Design." Thesis, Linköping University, Department of Management and Engineering, 2007. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-9999.

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This thesis work was done in order to improve the capabilities in a preliminary aircraft analysis program, DIBA, at Saab Aerosystems. The areas that this was done are in the sizing and balance. One sizing tool was developed in order to make a performance analysis with the DIBA generated geometry and customer and/or regulation based criteria. A balance diagram, a neutral point estimation function, a landing gear plot and a trim program was created in order to extend the weight and balance analysis.

Results show that various aircraft both military and civil can be analyzed with good comparison to other analysis and reality. For example EXCEL implemented analysis and graphs over real aircrafts shown in the report.

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29

Seeger, J., and K. Wolf. "Multi-objective design of complex aircraft structures using evolutionary algorithms." Sage, 2011. https://publish.fid-move.qucosa.de/id/qucosa%3A38441.

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In this article, a design methodology for complex composite aircraft structures is presented. The developed approach combines a multi-objective optimization method and a parameterized simulation model using a design concept database. Due to the combination of discrete and continuous design variables describing the structures, evolutionary algorithms are used within the presented optimization approach. The approach requires an evaluation of the design alternatives that is performed by parameterized simulation models. The variability of these models is achieved using a design concept database that contains different layouts for each implemented structural part. Due to the complexity of the generated aircraft structures, the finite element method is applied for the calculation of the structural behaviour. The applicability of the developed design approach will be demonstrated by optimizing two composite aircraft fuselage examples. The obtained results show that the developed methodology is useful and reliable for designing complex aircraft structures.

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30

Greguš, Adam. "Způsoby pořizování dopravních letadel a fleet management letecké společnosti." Master's thesis, Vysoká škola ekonomická v Praze, 2017. http://www.nusl.cz/ntk/nusl-359233.

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The aim of this thesis is to work out a topic regarding airliner acquisition and financing methods. Fleet planning is an important decision-making process because acquiring an aircraft is a capital-intensive investment. There are different methods of acquiring and financing and each of them have its advantages and disadvantages which complies different operational, tactical and strategical needs of an airline. The aim is also to analyze and describe current and forecast situation within the airline industry both globally and regionally. The last part is dedicated to flight fleet management instruments, such as performance, operational, financial metrics and indicators that helps an airline to operate its fleet efficiently, and a case study based upon a real ACMI contract.

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31

Colvard, Richard D. "A case study of the teaming concept in the procurement of the V-22 aircraft." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1994. http://handle.dtic.mil/100.2/ADA293770.

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32

Schön, Sofia. "Design Space Exploration for Structural Aircraft Components : A method for using topology optimization in concept development." Thesis, Linköpings universitet, Maskinkonstruktion, 2019. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-159955.

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When building aircrafts, structural components must be designed for high strength, low cost, and easy assembly.To meet these conditions structural components are often based upon previous designs, even if a new component is developed.Refining previous designs can be a good way of preserving knowledge but can also limit the exploration of new design concepts. Currently the design process for structural aircraft components at SAAB is managed by design engineers. The design engineer is responsible for ensuring the design meets requirements from several different disciplines such as structural analysis, manufacturing, tool design, and assembly.Therefore, the design engineer needs to have good communication with all disciplines and an effective flow of information. The previous design is refined, it is then reviewed and approved by adjacent disciplines.Reviewing designs is an iterative process, and when several disciplines are involved it quickly becomes time consuming.Any time the design is altered it has to be reviewed once more by all disciplines to ensure the change is acceptable.So there is a need for further customizing the design concept to decrease the number of iterations when reviewing. Design Space Exploration DSE is a well known method to explore design alternatives before implementation and is used to find new concepts.This thesis investigates if DSE can be used to facilitate the design process of structural aircraft components and if it can support the flow of information between different disciplines.To find a suitable discipline to connect with design a prestudy is conducted, investigating what information affect structural design and how it is managed.The information flow is concluded in a schematic diagram where structural analysis is chosen as additional discipline. By using topology optimization in a DSE, design and structural analysis are connected.The design space can be explored with regards to structural constraints.The thesis highlights the possibilities of using DSE with topology optimization for developing structural components and proposes a method for including it in the design process.

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Ramirez, Alvarez Dennis André. "The Condor UAV System : A Concept Study." Thesis, KTH, Maskinkonstruktion (Inst.), 2016. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-192262.

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In this degree project in aerospace engineering, a preliminary design of a UAV (Unmanned Aerial Vehicle) was performed. The UAV was intended to be used as a complement to the Swedish maritime administration’s helicopters, which cannot operate under limited visibility conditions. Its main mission would consist of surveillance. The UAV was therefore designed for some series criteria that were based on the customers’ requirements. The primary literature that was used was John D. Andersons Aircraft performance and design. Otherwise, historical statistical data from other aircraft was used and numerous assumptions were made. The result was a relatively small UAV named The Condor, weighing 25.6 kg with a wingspan of 2.5 m and operational in an altitude of 3500 m with a cruise speed of 81 knots. The UAV’s range is 70 nautical miles and is also able to operate in up to six hours. It should be able to manage a 300 m long runway. The chosen wing profile was the NACA 1412 with a maximal thickness and camber of 12 % and 1 % of the chord length, respectively. As for the stabilizer, the symmetric wing profile NACA 0012 was chosen. A so called constraint analysis was performed in order to determine the engine choice and thewing loading. The chosen engine was a 3.1 horsepower piston engine provided by Ricardo. The dimensions of the fuselage were designed only to fit the payload and no detailed analysis was done. It became 2.3 m long and with a maximal diameter of 0.3 m.
I det här kandidatexamensarbetet i flygteknik gjordes en preliminär design av en drönare. Drönaren skulle användas som komplettering till sjöfartsverkets helikoptrar, som inte kan användas vid mycket begränsad sikt. Dess huvudsakliga uppdrag skulle bestå av övervakning. Drönarens utformades därför efter en rad kriterier som baserades på uppdragsgivarens krav. Den huvudsakliga litteraturen som användes var John D. Andersons Aircraft performanceand design. I övrigt användes historisk statistisk data från andra flygplan och ett flertal antaganden gjordes. Resultatet blev en relativt liten drönare som döptes till The Condor och fick en vikt på 25.6 kg, med ett vingspann på 2.5 m och som opererar på 3500 m flyghöjd med en marschfart på 81 knop. Drönarens räckvidd är 70 nautiska mil och den kan därutöver operera i upp till sex timmar. Den bör klara av en landningsbana på 300 m. Som vingprofil valdes NACA 1412 med en maximal tjocklek och camber på 12 % respektive 1 % av kordalängden. För stabilisatorn valdes den symmetriska profilen NACA 0012. En så kallad ”constraint analysis” genomfördes för fastställande av motorval och vingbelastning. Motorn som valdes blev en 3.1 hästkrafters pistongmotor från Ricardo. Flygplanskroppens dimensioner utformades endast för att få plats med nyttolasten och ingen noggrannare analys genomfördes. Den blev 2.3 m lång med en maximal diameter på0.3 m.

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Maniatis, Dimitri. "The seizure and detention of aircraft by Canadian airports and the Convention on International Interests in Mobile Equipment : a critical analysis of non-consensual rights under the Unidroit regime." Thesis, McGill University, 2001. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=33055.

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Canadian airport authorities benefit from the right to seize and detain aircraft where airport charges remain unpaid. By objective measures, this right constitutes a preferred non-consensual right or interest that takes priority under Canadian law over all competing rights and interests in the aircraft subject to seizure and detention, including, for example, the interests of an owner, lessor or secured creditor. In this manner, airport authorities may recover outstanding user fees from both the airlines themselves and from the aircraft owners or lessors.
The Unidroit Convention attempts to harmonise the law applicable to aircraft finance transactions. As such, it targets private law rights. However, its breadth and scope touch upon the statutory rights of third parties with non-consensual interests in aircraft, including those of airport authorities to seize and detain aircraft.
The interplay between the Unidroit regime and the seizure and detention rights of Canada's airport is the focus of this academic discourse. It demonstrates that even though this right, recourse and remedy is of fundamental importance to Canada's National Airports System and its transportation infrastructure generally, the Unidroit Convention could, if implemented as drafted, effectively compromise the ability of Canadian airports to seize and detain aircraft.

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Svahn, Carl. "Quantified Interactive Morphological Matrix : An automated approach to aircraft fuel system synthesis." Thesis, Linköping University, Department of Mechanical Engineering, 2006. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-7715.

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This report is one part of a masters thesis in mechanical engineeing. Is is executed at the Department of Mechanical Engineering at Linköping Insitute of Technology in cooperation with Saab Aerosystems in Linköping.

A tool for concept generation called a quantified interactive morphological matrix has been created. It is based on rules of thumb and approximations concerning aircraft fuel systems.

The tool can be used for discarding bad concepts, with regard to weight, power consumption and MTBF, during the concept phase of a fuel system design process. The tool is ready for calibration towards a future specific area of use. It is open for validation and optimization and is specifically designed to be easily modified for different future products.

Suggestions for future use has been given concerning expansion, implementation, validation and optimization.

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Palmberg, Sebastian, and Sara Westroth. "Model-based concept development of system in UAV." Thesis, Luleå tekniska universitet, Institutionen för teknikvetenskap och matematik, 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-80907.

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There is a large number of design options to consider when designing aircraft vehicle systems for fighter aircraft, and there is a lack of tool support that provides an overview of these available design options. Various design options will bring consequences in terms of weight, performance, cost, etc. which is desired to be known in an early conceptual phase. Conventional methods, such as morphological matrix and design structure matrix, lack the ability to generate an overview and map complex systems. By studying model-based tools in form of ontologies and feature models in Protégé and FeatureIDE respectively, these tools are considered to provide a higher level of detail regarding the available design options compared to the conventional methods, such as the morphological matrix and the design structure matrix. Ontologies and feature-models are therefore considered to increase the effectiveness in the conceptual design phase of aircraft vehicle systems. By combining ontologies and feature models, more thoughtful design decisions can be performed. An increased knowledge of the available design options can lead to an improved development of aircraft vehicle systems, and new solutions can be evaluated. By performing more detailed trade studies for an unmanned aerial vehicle, for different system solutions, various parameters such as engine power outtake, system weight, etc. can be analysed and provide an indication whether a concept should be evaluated further. It is however necessary to consider how different parameters affect the overall system, and fuel penalty may be implemented as an equivalent parameter. Performing power flow calculations do however not consider solution-specific limitations, which have to be implemented to be able to determine if an aircraft vehicle system concept should be considered advantageous or not.

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Murça, Mayara Condé Rocha. "An optimization approach for scheduling aircraft landings in a terminal area under the concept of alternative arrival routes." Instituto Tecnológico de Aeronáutica, 2013. http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=2836.

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This work aimed to study the impact of incorporating optimization techniques into the air traffic flow management in the terminal area, specifically in the stage of arrival sequencing to an airport. For this, a mixed integer linear programming model for aircraft sequencing and scheduling for landing was developed, which seeks to determine discrete delays and discrete time advances, associated with the use of alternative arrival routes by aircraft, in the process of minimizing unavoidable deviations from the target landing time. The model developed was applied to the Brazilian scenario in order to evaluate the potential benefit it may generate if it is incorporated in a decision support tool for this stage of air traffic control. The Sao Paulo/Guarulhos International Airport was chosen as case study. From a radar database of a typical day of operations, a trajectory analysis was developed and input data for the optimization was obtained. The performance of the model, in terms of total deviations and computational time, was then evaluated for different operating scenarios by changing the following parameters: sequencing strategy, criteria of separation between aircraft, dynamic approach and discretization of the set of delays/time advances. Finally, the model benefits assessment revealed that the optimization approach was able to generate a reduction of total deviations, in relation to the actual solutions of traffic flow management taken, with a range of 5% to 35%, depending on the discretization level adopted and on the number of alternative approach routes available. Therefore, it is emphasized the potential of such models in reducing delays, fuel consumption, emissions and controller workload.

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Ashok, Kumar Sachin Sharma. "Incorporation of graphene thin films into the carbon fiber reinforced composite via 3d composite concept against the lightning strikes on composite aircraft." Thesis, Wichita State University, 2012. http://hdl.handle.net/10057/5592.

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Research and development of graphene and graphene based materials have been increasing significantly since they were invented. This report presents the development of a highly conductive graphene thin film (GTF) to reduce the damage of lightning effects on composite aircrafts. Furthermore, there are three new developments that are presented in this research: (a) the development of a highly conductive functionalized nanosize GTF, (b) a new approach of incorporating the GTF into the carbon fiber reinforced composite panel, and (c) a new development of 3D stitching concept were introduced specifically using polyester threads instead of fiber yarns that can be useful for the applications of aircraft protections against the effects of lightning strike. In addition, graphene was chemically functionalized and oxidized to form GTF. The highest electrical conductivity measured on the GTF was approximately 1800 S/cm. Furthermore, the GTF was then incorporated into the carbon fiber reinforced composite. Delamination was observed between the GTF and the composite. To investigate this issue, the composite was mechanically tested and there was a 40% decrease in tensile strength compared to the baseline. Therefore, 3D stitching concept was then introduced to reduce the delamination. Four stitch configurations having different stitch length, thread to thread thickness, thread tension, and thread thickness respectively were used in this study. 3D stitching was initially done on six sheets of unidirectional prepreg, MTM45-1 without the incorporation of GTF. Furthermore, mechanical testing was carried out and the stitch configuration that delivered the most appropriate result was then further used on twelve sheets of unidirectional prepreg, 5320. Here, three samples which was the baseline, 5320 with and without the incorporation of GTF respectively were prepared and mechanically tested, and the strength values were observed.
Thesis (M.S.)--Wichita State University, College of Engineering, Dept. of Mechanical Engineering

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Lupták, Pavol. "Design osobní kvadrokoptéry." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2019. http://www.nusl.cz/ntk/nusl-400439.

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The subject of this master‘s thesis is the design of a passenger quadcopter, which is intended for transporting two passengers and luggage. Diploma thesis includes an analysis of the existing products and deals with further direction in the solved topic. The goal of this thesis is to create a conceptual design that respects the technical, ergonomic and aesthetic requirements. The proposal itself offers possible direction of autonomous passenger quadcopters in the future.

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Smýkal, Michal. "Koncepční studie lehkého dvoumotorového proudového letounu." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2015. http://www.nusl.cz/ntk/nusl-232053.

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Tématem diplomové práce je koncepční studie lehkého dvoumotorového letounu. Je provedeno srovnání současných letounů, jejich motorů, technický popis navrhovaného řešení, hmotový rozbor, výpočet aerostatických podkladů, výpočet obálky zatížení, nákladů na vývoj a základní konstrukce hlavních součástí.

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Eklund, Adam, and Jesper Karner. "Development of a Framework for Concept Selection and Design Automation : Utilizing hybrid modeling for indirect parametric control of subdivision surfaces." Thesis, Linköpings universitet, Maskinkonstruktion, 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-147755.

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Saab Aeronautics’ section Overall Design and Survivability develops early aircraft concepts and utilizes Computer Aided Design (CAD) to ensure the feasibility of principal- and critical characteristics. Saab has over the years developed several start models of aircrafts in CAD from pre-defined aircraft configurations, which are to some extent non-generic. When new configurations are to be explored, manual- and repetitive work is required if the new configuration cannot be attained solely through parametric modifications of a start model. The complexity of these CAD models also demands great knowledge of how aircraft components interact with each other to ensure compatibility. The project covered in this thesis was thus carried out to develop a more effective way for Saab to create and explore a larger design space. This by creating a framework that consists of a product configurator coupled with a library of generic CAD models. The product configurator that was created is the Saab Tradespace Analyzer & Reconfigurator (STAR), which takes compatibility relationships into consideration to facilitate concept selection. The STAR also provides a dynamic design space calculation to indicate how close the user is to a final concept selection. Two generic CAD models were created, a fuselage model and an air inlet model. A skeleton model was also created in order to reduce model dependencies and to control the main geometry of the aircraft product. In addition to these, an already existing wing model was implemented to form the library of generic CAD models. The framework coupling the STAR with the CAD library utilizes design automation to allow automatic CAD model generation of a concept that has been selected within the STAR. It was concluded through extrapolation that the created framework would allow Saab to create and explore a larger design space in a more effective way than what is done today, provided the library of CAD models were to contain the same number of components as today’s start models.

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Podhorský, Matěj. "Návrh základní koncepce air - mobilu." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2014. http://www.nusl.cz/ntk/nusl-231440.

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The topic of the thesis is a conceptual design of a roadable aircraft. The comparison of existing concepts is made, as well as description of proposed solution, aircraft mass analysis, basic aerostatic calculations, flight and gust envelope calculation and a design of truss construction of the fuselage. The CS-VLA, alternatively ELSA-K, has been used as a certification base. The compliance to this certification specification is one of the goals of this thesis.

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Hansson, Anders, and Robert Kylander. "Flygplanstillverkning : Fixturkoncept till robotgradning." Thesis, University West, Department of Engineering Science, 2009. http://urn.kb.se/resolve?urn=urn:nbn:se:hv:diva-1610.

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Volvo Aeros flygmotortillverkning i Trollhättan har infört ett antal nya detaljvarianter i produktionen. Detta har medfört att den robotcell som är avsedd att utföra en avgradningsoperation är i behov av uppdatering av både hårdvara och mjukvara. Denna rapport följer framtagningen av fixturkoncept som möjliggör att robotcellen kan användas även till de nya detaljerna. De förslag som arbetats fram sträcker sig från enklast möjliga till mer avancerade och nytänkande funktioner. Samtliga funktioner och koncept har genomgått gallringar i ett flertal steg. Förslagen har slutligen kombinerats och poängbedömts med konceptgenereringsverktyg till grund.

Efter en objektiv poängbedömning av sex olika koncept baserad på concept scoring visar sig två huvudgrupper med tre koncept i varje. Den ena gruppen bygger på en mer avancerad konstruktion med behov av två rotationsaxlar. Dessa medför ett flertal fördelar gällande effektivitet, men även påtagliga nackdelar vad gäller ekonomiska aspekter och idrifttagandetid. Den andra gruppen av koncept baseras mer på det befintliga fixturkonceptet. Detta medför fördelar gällande idrifttagandetid och kostnader.

Ett huvudkoncept som efter poängbedömningen visat sig mest lämpligt presenteras mer ingående och slutligen förs en diskussion gällande resultatets utfall samt rekommendationer till fortsatt arbete.

Volvo Aero’s aircraft engine manufacturing in Trollhättan has introduced a number of detail models into the production. As a consequence the robot cell dedicated to executing a deburring operation is in need of upgrading of both hardware and software. This report follows the development of fixture concepts that enables the robot cell to be used also for the new details. The proposals that have been developed range from the simplest to more advanced including novel functions. All the functions and concepts have gone through selection in multiple steps. The suggestions have finally been combined and evaluated with concept generation tools.

After an objective selection based on the concept scoring of six different concepts, the result can be divided into two main groups, each consisting of three concepts. The first group is a more advanced design with a need of two axes of rotation. These three concepts have several advantages when it comes to efficiency, but also obvious disadvantages when it comes to economy and production time. The second group of concepts is based on the fixture existing today. These three concepts are advantageous concerning production time and cost.

After the scoring process one main concept, judged to be the most suitable is presented more thoroughly. Finally the results as well as recommendations for continued work are discussed.

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Johnson, Bruce. "Telemetry Receive/Record & Re-Radiation Pod." International Foundation for Telemetering, 2014. http://hdl.handle.net/10150/577391.

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ITC/USA 2014 Conference Proceedings / The Fiftieth Annual International Telemetering Conference and Technical Exhibition / October 20-23, 2014 / Town and Country Resort & Convention Center, San Diego, CA
This paper discusses the mission needs, design/development, and testing of the (L, S & C Band) Telemetry Receive/Record & Re-Radiation pod.

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Lewe, Jung-Ho. "An Integrated Decision-Making Framework for Transportation Architectures: Application to Aviation Systems Design." Diss., Available online, Georgia Institute of Technology, 2005, 2005. http://etd.gatech.edu/theses/available/etd-04132005-204114/unrestricted/Jung-Ho%5FLewe%5F200505%5Fphd.pdf.

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Thesis (Ph. D.)--Aerospace Engineering, Georgia Institute of Technology, 2005.
Amy R. Pritchett, Committee Member ; Moore, Mark D., Committee Member ; Wilhite, Alan, Committee Member ; Schrage, Daniel P., Committee Chair ; Mavris, Dimitri N., Committee Co-Chair ; DeLaurentis, Daniel A., Committee Member. Vita. Includes bibliographical references.

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Landon, Steven D. "Development of Deployable Wings for Small Unmanned Aerial Vehicles Using Compliant Mechanisms." Diss., CLICK HERE for online access, 2007. http://contentdm.lib.byu.edu/ETD/image/etd1917.pdf.

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Chaing, Yi Hui, and 江怡慧. "Study in Aircraft Leasing." Thesis, 1995. http://ndltd.ncl.edu.tw/handle/84921594360869735711.

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Huang, Shun-yu, and 黃舜宇. "The Recent Development of Aircraft Financial Leasing." Thesis, 2011. http://ndltd.ncl.edu.tw/handle/09291652022193033011.

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碩士
東吳大學
法律學系
99
The aircraft equipment is characterized as being high capital and skill-intensive, so purchasing them usually costs a great deal of financing to the airlines. How to pick out the most appropriate plan and cut down financing cost has become the primary issue of the airlines. The Cape Town Convention and its Aircraft Protocal has had a great effect upon creating a global framework as to aircraft financing and lease. Nevertheless, since Taiwan is not one of the contracting parties of the Cape Town System, one could not find any registration option of Taiwan on the International registry’s website. Therefore, it is essential to assist creditors and potential contractors in reducing their investment and operation risks through necessary warranty about rights, the international registration system instituted by the associated conventions, and institutionalized legal environment when the rights or interests of the aircraft equipments registered in Taiwan are transferred. An all of these issues will be analyzed in this article. In addition, aircraft financing in authentic situation will be analyzed in a series of cases, involving how to reduce airline costs effectively by changing nationality of aircraft registry and preferential benefits of foreign taxes. This article may servers as a reference for the operators in dealing with financing lease practice of aircraft in the future.

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Cheng, Yu-Yu, and 鄭郁于. "A Decision Making Model for Leasing/Purchasing an Aircraft for Airlines." Thesis, 2014. http://ndltd.ncl.edu.tw/handle/16145449325583657555.

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碩士
國立交通大學
管理學院運輸物流學程
102
Due to Asia’s booming aviation market, this study aims to develop a decision making model for leasing or purchasing an aircraft from airline’s point of view to meet the increased market demand based on the current operating aircraft fleet. Different from a large-scale aircraft fleet planning, this study only considers the acquisition of an additional aircraft. Therefore, the size of increased demand, the characteristics of the potential air routes to fly with, the current operating aircrafts, and the financial feasibility of the target airline company should be considered. To do so, this study uses the Analytic Hierarchy Process (AHP) method to develop the analytical framework. A total of five criteria are proposed: Financial feasibility, Demand Compatibility, Aircraft Compatibility, Performance Reputation, Environmental Protection Reputation, each of which has two to four associated sub-criteria. To obtain the weights, a total of 10 experts with rich experiences in aircraft acquisition, management and maintenance are interviewed. Results show that the summated weights of the first three criteria, i.e. Financial feasibility, Demand Compatibility, Aircraft Compatibility, exceed 0.7, explaining the importance and dominance of these criteria. To demonstrate the applicability of the proposed AHP model, a case study on an airline is conducted. A total of eight alternatives are compared, including four candidate aircraft types: Airbus 320, Airbus 330, Boeing 737, and Boeing 787 and two acquisition methods, lease or purchase. Additionally, one-stage decision (consider all criteria) and two stage decision processes (use of four criteria, except for Financial feasibility, to evaluate the type of aircraft and then use of Financial feasibility criteria to decide lease or purchase the chosen aircraft type). The evaluation results of two decision processes consistently show that to purchase the Airbus 320 is the best alternative for the target airline.

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Aleixo, José Frederico Pais. "Leasing in low-cost carriers." Master's thesis, 2014. http://hdl.handle.net/10400.14/15933.

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The aim of this paper is to explore the use of aircraft leasing as a financing instrument in the low-cost carriers’ sector. These airlines have been showing a huge growth in the customers’ preferences, while aircraft leasing plays a relevant role in the financing options of airlines. In this study we determined that lease future commitments represent on average 80% of other debt commitments in low-cost carriers. Furthermore, we discovered that the leasing rate in low-cost airlines (49%) is superior to the global average (39%), partly explained by the lower capital requirements that a lease offers comparing to a purchase. We found a high negative correlation between average fleet age and use of leasing. The reason is that leases allow the airlines to renew the fleet more easily and get younger aircraft (in fact, 67% of the leased aircraft are newly-manufactured, something unlikely to happen with purchases). Negative correlations were also found between use of leasing and the variables of fleet size, on-time performance, profit margin and debt ratio, but without statistical evidence. Use of leasing is best explained by average fleet age and fleet size, meaning that variables related to the constitution of the fleet are better in explaining the use of leasing by low-cost carriers than performance or financial measures.

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Dissertations / Theses on the topic 'Concept of aircraft leasing'

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