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1
Megas, Vasileios. "Aircraft to Aircraft Connectivity Analysis". Thesis, KTH, Skolan för elektroteknik och datavetenskap (EECS), 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-254887.
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It is very common to feel the need to be connected, especially in cases where we are idle, such as in airplanes. Aircraft connectivity has already been implemented by using direct air-to-ground communication and satellite communication. However, since the current solutions are not satisfying, more ways to provide connectivity to aircraft are being researched. One solution is to use aircraft as relay nodes and forward signals to aircraft which are out of range of the ground base stations, creating an ad-hoc network.This thesis aims in evaluating the performance of such networks over the North Atlantic ocean in terms of connectivity and achievable data rate by means of simulations. First, an aircraft mobility model is created by analyzing past flight data. Then, the topology of the network is created with the purpose of maximizing the number of connected aircraft and minimizing interference. Finally, the available bandwidth is allocated to all connected aircraft in a maxmin way. The simulations were repeated to evaluate the impact of: threshold in data rates to assume connectivity, maximum number of connections per aircraft, maximum antenna steering angle, beamwidth and bandwidth.Our results show that aircraft to aircraft connectivity is feasible if all airlines cooperate, and more than 80% of the aircraft can find a path to a base station, when the aircraft density is higher than 1 aircraft per approximately 150000 km2, which is 88% of a 24 hours period. The median data rate of the connected aircraft, achieved in the middle of the ocean is limited to 25 Mbps with a 20MHz bandwidth, which is not high enough to provide access to demanding applications, such as video streaming. Increasing the bandwidth to 200 MHz can increase the data rate to more than 184 Mbps, for 50% of the connected aircraft, which surpasses the performance of current satellite communication systems.Det är ganska vanligt att känna behovet av att sammankopplas, särskilt i fall där vi är inaktiva, exempelvis i flygplan. Flygplansanslutning har redan implementerats genom att utnyttja direkt luft till markkommunikation och satellitkommunikation. Men eftersom de befintliga lösningarna inte är tillfredsställande, undersöks fler sätt att tillhandahålla anslutning till flygplan. En lösning är att använda flygplan som relä knutpunkter och framåtsignaler till flygplan som ligger utanför markbasen, skapar ett adhocnätverk.Den här avhandlingen syftar till att utvärdera prestanda för sådana nätverk över Nordatlanten när det gäller anslutning och uppnåelig datahastighet genom simuleringar. För det första frambringas en flygplansmobilitet genom att analysera tidigare flygdata. Därefter åstadkommas nätets topologi med syftet att maximera antalet anslutna flygplan och minimera störningar. Slutligen tilldelas den tillgängliga bandbredden till alla anslutna flygplan på maximal väg. Simuleringarna upprepas för att utvärdera effekten av: tröskeln i datahastigheter för att mottaga anslutning, maximalt antal anslutningar per flygplan, max antennstyrvinkel, strålbredd och bandbredd.Våra resultat visar att flygplan till flygplansförbindelser är genomförbart om alla flygbolag samarbetar och mer än 80% av flygplanet kan sammankoppla, när flygplansdensiteten är högre än 1 flygplan per ungefär 150000 km2. Median datahastigheten uppnådd i mitten av havet är begränsad till 25 Mbps med en 20 MHz bandbredd, vilket inte är tillräckligt hög för att bringa tillgång till krävande applikationer, såsom videostreaming. Ö kning av bandbredd till 200 MHz kan öka datahastigheten mer än 184 Mbps, för 50% av de anslutna flygplanen, vilketöverträffar prestanda för de nuvarande satellitkommunikationssystemen.
2
Serrano, Ignacio. "Unmanned Aircraft System (UAS) vs. Manned Aircraft System (MAS): A Military Aircraft Study". Digital Commons at Loyola Marymount University and Loyola Law School, 2015. https://digitalcommons.lmu.edu/etd/430.
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Unmanned Aerial Vehicles (UAVs) are common place in the 21st century, whether they are small to medium sized remotely piloted vehicles (aka drones) or large advanced Unmanned Aerial Systems with a preprogrammed flight path. There is anticipation that these Unmanned Systems will, in the future assume the roles of their traditional manned aircraft counterparts. There is also the perception that these Unmanned Systems should be developed partly because they would be less expensive when compared to their manned aircraft. This integrative paper asserts that this perception is not reality with regards to developing a newly designed UAV to replace its manned counterpart, for the same mission. Through the examination of systems engineering principles between the unmanned RQ-4 Global Hawk and the manned U-2 Dragon Lady one will understand why this perception is not correct. Both aircraft perform the same mission of providing High Altitude Intelligence, Surveillance, and Reconnaissance (ISR). Through evaluation of requirements analysis both aircraft flowed down the requirements to all the various subsystems in a similar manner, creating similar subsystems for Imagery Intelligence (!MINT) and Signals Intelligence (SIGINT). However, the additional requirement for long endurance required that the Global Hawk systems engineers had additional requirements to flow down to the software, communications, data processing, and ground support subsystems in order to control an unmanned aircraft for greater than 24 hours. This one additional requirement had various derived requirements that needed to be verified, and validated during analysis, manufacturing, subsystem build and test, and final system integration. By using both System Integration Laboratories (SIL) and Flight Tests both systems requirements were verified and validated by the systems engineers. The Global Hawk since it was unmanned was required to perform more verification of subsystems and software as it was the first UAV to achieve flight airworthiness. The future of ISR missions requires that the aircraft become more adaptable to future technologies and situations. The U-2 has a modular configuration to change out to and from different subsystems depending on the mission. However, these subsystems were designed 20 to 30 years ago, and were not designed for lower level modularity or interoperability. The Global Hawk systems engineering team understood the future needs and the high level demand and data to be gathered and processed. The SE's developed modularity and interoperability requirements and flowed them down to the various subsystems. The Global Hawk system is more useful in highly contested areas of interest as there is no pilot; however resilient communications of the data and data link must be robust with anti-jamming capabilities to ensure the data is secure from cyber-attack. However,the U-2 is more survivable since it has a defense system, and can provide greater situational awareness. Taking all the general ISR requirements into consideration a trade study using a matrix was performed indicating that the Global Hawk is the most optimal solution to meeting both the current and future requirements for ISR missions. Even though the overall acquisition cost of the Global Hawk is equivalent to the U-2, systems engineering for Global Hawk had the responsibility to flow down requirements to all subsystems with consideration of the entire systems lifecycle. This is exemplified in that the Global Hawk is cost effective to fly in terms of cost per flight hour. Therefore, the Global Hawk can fulfill all the requirements of the given stakeholders with the lowest operational cost.
3
Iskender, Hani. "Aircraft Simulator". Thesis, Linköping University, Department of Electrical Engineering, 2005. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-2936.
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At Saab Bofors Dynamics there are projects running which purpose are to develop simulators for various weapon systems like RBS 70. In order to manage creating real working simulators Saab Bofors Dynamics has to do more research and this final thesis is a part of this process.
This final thesis has been performed at Saab Bofors Dynamics in the department of modelling and simulation, RTRKM, in Karlskoga. The purpose was to develop a control algorithm which makes it possible for an aircraft to behave real when controlling through a joystick.
The conclusions show that further improvements are needed before the aircraft behaves entirely by the laws of physics. Among other things it is necessary to decrease the number of delimitations that have been done.
4
Sychova, I. U., i E. I. Zolotova. "Supersonic aircraft". Thesis, Вид-во СумДУ, 2011. http://essuir.sumdu.edu.ua/handle/123456789/22211.
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Thompson, Brian G. "Aircraft agility". Thesis, This resource online, 1992. http://scholar.lib.vt.edu/theses/available/etd-09192009-040436/.
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Black, Gary Douglas. "Aircraft configuration study for experimental 2-place aircraft and RPVs". Thesis, Monterey, California : Naval Postgraduate School, 1990. http://handle.dtic.mil/100.2/ADA227604.
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Thesis (M.S. in Aeronautical Engineering)--Naval Postgraduate School, March 1990.Thesis Advisor(s): Howard, Richard M. Second Reader: Hauser, James P. "March 1990." Description based on signature page as viewed on August 25, 2009. DTIC Descriptor(s): Aerodynamic configurations, remotely piloted vehicles, military aircraft, lightweight, research aircraft, canard configurations, wings, aerodynamic drag, computer programs, scaling factor, aerodynamic stability, performance(engineering), comparison, microcomputers, trade off analysis, aeronautical engineering, theses. DTIC Identifier(s): Pusher propellers, Tandem wing aircraft, Joined wing aircraft, Three surface aircraft. Author(s) subject terms: Aircraft design, remotely piloted vehicle, RPV, configuration, experimental Includes bibliographical references (p. 121-123). Also available online.
7
Wan, Husain Wan Mohd Sufian Bin. "Maintainability prediction for aircraft mechanical components utilising aircraft feedback information". Thesis, Cranfield University, 2011. http://dspace.lib.cranfield.ac.uk/handle/1826/7272.
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The aim of this research is to propose an alternative approach to determine the
maintainability prediction for aircraft components. In this research, the author looks at
certain areas of the maintainability prediction process where missteps or
misapplications most commonly occur. The first of these is during the early stage of
the Design for Maintainability (DfMt) process. The author discovered the importance
of utilising historical information or feedback information. The second area is during
the maintainability prediction where the maintenance of components is quantified;
here, the author proposes having the maximum target for each individual
maintainability component.
This research attempts to utilise aircraft maintenance historical data and
information (i.e. feedback information systems). Aircraft feedback information
contains various types of information that could be used for future improvement
rather than just the failure elements. Literature shows that feedback information such
as Service Difficulty Reporting System (SDRS) and Air Accidents Investigation Branch,
(AAIB) reports have helped to identify the critical and sensitive components that need
more attention for further improvement.
This research consists of two elements. The first is to identity and analyse
historical data. The second is to identify existing maintainability prediction
methodologies and propose an improved methodology. The 10 years’ data from
Federal Aviation Administration (FAA) SDRS data of all aircraft were collected and
analysed in accordance with the proposed methodology before the processes of
maintainability allocation and prediction were carried out.
The maintainability was predicted to identify the potential task time for each
individual aircraft component. The predicted tasks time in this research has to be in
accordance with industrial real tasks time were possible. One of the identified
solutions is by using maintainability allocation methodology. The existing
maintainability allocation methodology was improved, tested, and validated by using
several case studies. The outcomes were found to be very successful.
Overall, this research has proposed a new methodology for maintainability
prediction by integrating two important elements: historical data information, and
maintainability allocation. The study shows that the aircraft maintenance related
feedback information systems analyses were very useful for deciding maintainabilityeffectiveness; these include planning, organising maintenance and design
improvement. There is no doubt that historical data information has the ability to
contribute an important role in design activities. The results also show that
maintainability is an importance measure that can be used as a guideline for managing
efforts made for the improvement of aircraft components.
8
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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彭遠輝 i Yuen-fai Alson Pang. "Managing aircraft noise". Thesis, The University of Hong Kong (Pokfulam, Hong Kong), 2002. http://hub.hku.hk/bib/B31255280.
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Wagner, Michael J. "AEW aircraft design". Thesis, Monterey, California. Naval Postgraduate School, 1992. http://hdl.handle.net/10945/23815.
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Brentnall, Adam Robert. "Aircraft arrival management". Thesis, University of Southampton, 2006. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.432622.
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Elsayed, M. A. N. "Aircraft trajectory optimization". Thesis, Loughborough University, 1985. https://dspace.lboro.ac.uk/2134/32873.
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A typical aircraft flight consists of three phases, namely climb, cruise and descent. The purpose of this research was to study the control schedules for a transport aircraft which would result in least fuel expenditure in each flight-segment.
13
GongZhang, Hanlin, i Eric Axtelius. "Aircraft Winglet Design". Thesis, KTH, Skolan för teknikvetenskap (SCI), 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-276586.
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Aerodynamic drag can be decreased with respect to a wing’s geometry, and wingtip devices, so called winglets, play a vital role in wing design. The focus has been laid on studying the lift and drag forces generated by merging various winglet designs with a constrained aircraft wing. By using computational fluid dynamic (CFD) simulations alongside wind tunnel testing of scaled down 3D-printed models, one can evaluate such forces and determine each respective winglet’s contribution to the total lift and drag forces of the wing. At last, the efficiency of the wing was furtherly determined by evaluating its lift-to-drag ratios with the obtained lift and drag forces. The result from this study showed that the overall efficiency of the wing varied depending on the winglet design, with some designs noticeable more efficient than others according to the CFD-simulations. The shark fin-alike winglet was overall the most efficient design, followed shortly by the famous blended design found in many mid-sized airliners. The worst performing designs were surprisingly the fenced and spiroid designs, which had efficiencies on par with the wing without winglet.Det aerodynamiska luftmotståndet kan minskas genom justeringar i vingens geometri, och vingtipsenheter så kallade virveldämpare spelar en vital roll inom vingdesign och utveckling. Projektet hade fokuset på att undersöka de lyft -och motståndskrafterna som genererades av en förutbestämd vinge vid användandet av olika varianter av virveldämpare. Genom beräkningsströmningsdynamiska simuleringar (CFD) och vindtunneltester av nerskalade 3D-utskrivna modeller kan dessa krafter beräknas. Med hjälp av dessa kan respektive virveldämparens bidrag till de sammanlagda lyft -och motståndskrafterna på vingen vidare bestämmas. Genom att beräkna förhållandet mellan de erhållna lyft -och motståndskrafterna kan vingens glidtal sist bestämmas, som är ett dimensionslöst mått på vingens effektivitet. Resultatet från denna studie visade att vingens prestanda varierade efter på valet av virveldämpare, där vissa designer gav avsevärda förbättringar över andra enligt CFD-simuleringar. Den hajfensliknande varianten (så kallad sharklet på engelska) var den mest effektiva designen, tätt följt av den ordinära uppåtriktade typen (blended på engelska) som återfinns på många av dagens medelstora flygplan. De sämst presterande designerna var förvånande nog den triangel -och spiralformade (fenced och spiroid på engelska), vilka presterade på samma nivå som den virveldämparfria vingen.
14
Pang, Yuen-fai Alson. "Managing aircraft noise /". Hong Kong : University of Hong Kong, 2002. http://sunzi.lib.hku.hk/hkuto/record.jsp?B2543598x.
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Vallone, Michael. "Parameter Estimation of Fundamental Technical Aircraft Information Applied to Aircraft Performance". DigitalCommons@CalPoly, 2010. https://digitalcommons.calpoly.edu/theses/382.
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Inverse problems can be applied to aircraft in many areas. One of the disciplines within the aerospace industry with the most openly published data is in the area of aircraft performance. Many aircraft manufacturers publish performance claims, flight manuals and Standard Aircraft Characteristics (SAC) charts without any mention of the more fundamental technical information of the drag and engine data. With accurate tools, generalized aircraft models and a few curve-fitting techniques, it is possible to evaluate vehicle performance and estimate the drag, thrust and fuel consumption (TSFC) with some accuracy. This thesis is intended to research the use of aircraft performance information to deduce these aircraft--specific drag and engine models. The proposed method incorporates models for each performance metric, modeling options for drag, thrust and TSFC, and an inverse method to match the predicted performance to the actual performance. Each of the aircraft models is parametric in nature, allowing for individual parameters to be varied to determine the optimal result. The method discussed in this work shows both the benefits and pitfalls of using performance data to deduce engine and drag characteristics. The results of this method, applied to the McDonnell Douglas DC-10 and Northrop F-5, highlight many of these benefits and pitfalls, and show varied levels of success. A groundwork has been laid to show that this concept is viable, and extension of this work to additional aircraft is possible with recommendations on how to improve this technique.
16
Miao, Zhisong. "Aircraft engine performance and integration in a flying wing aircraft conceptual design". Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/7249.
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The increasing demand of more economical and environmentally friendly aero
engines leads to the proposal of a new concept – geared turbofan. In this thesis,
the characteristics of this kind of engine and relevant considerations of
integration on a flying wing aircraft were studied.
The studies can be divided into four levels: GTF-11 engine modelling and
performance simulation; aircraft performance calculation; nacelle design and
aerodynamic performance evaluation; preliminary engine installation.
Firstly, a geared concept engine model was constructed using TURBOMATCH
software. Based on parametric analysis and SFC target, the main cycle
parameters were selected. Then, the maximum take-off thrust was verified and
corrected from 195.56kN to 212kN to meet the requirements of take-off field
length and second segment climb. Besides, the engine performance at offdesign
points was simulated for aircraft performance calculation.
Secondly, an aircraft performance model was developed and the performance
of FW-11 was calculated on the basis of GTF-11 simulation results. Then, the
effect of GTF-11 characteristics performance on aircraft performance was
evaluated. A comparison between GTF-11 and conventional turbofan, RB211-
524B4, indicated that the aircraft can achieve a 13.1% improvement in fuel
efficiency by using the new concept engine.
Thirdly, a nacelle was designed for GTF-11 based on NACA 1-series and
empirical methods while the nacelle dimensions of conventional turbofan
RB211-525B4 were obtained by measure approach. Then, the installation thrust
losses caused by nacelle drags of the two engines were evaluated using ESDU
81024a. The results showed that the nacelle drags account for about 4.08%
and 3.09% of net thrust for GTF-11 and RB211-525B4, respectively.
Finally, the considerations of engine installation on a flying wing aircraft were
discussed and a preliminary disposition of GTF-11 on FW-11 was presented.
17
Seresinhe, R. "Impact of aircraft systems within aircraft operation : a MEA trajectory optimisation study". Thesis, Cranfield University, 2014. http://dspace.lib.cranfield.ac.uk/handle/1826/9261.
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Air transport has been a key component of the socio-economic globalisation. The ever increasing demand for air travel and air transport is a testament to the success of the aircraft. But this growing demand presents many challenges. One of which is the environmental impact due to aviation. The scope of the environmental impact of aircraft can be discussed from many viewpoints. This research focuses on the environmental impact due to aircraft operation. Aircraft operation causes many environmental penalties. The most obvious is the fossil fuel based fuel burn and the consequent greenhouse gas emissions. Aircraft operations directly contribute to the CO2 and NOX emissions among others. The dependency on a limited natural resource such as fossil fuel presents the case for fuel optimised operation. The by-products of burning fossil fuel some of which are considered pollutants and greenhouse gases, presents the case for emissions optimised operations. Moreover, when considering the local impact of aircraft operation, aircraft noise is recognised as a pollutant. Hence noise optimised aircraft operation needs to be considered with regards to local impacts. It is clear whichever the objective is, optimised operation is key to improving the efficiency of the aircraft. The operational penalties have many different contributors. The most obvious of which is the way an aircraft is flown. This covers the scope of aircraft trajectory and trajectory optimisation. However, the design of the aircraft contributes to the operational penalties as well. For example the more-electric aircraft is an improvement over the conventional aircraft in terms of overall efficiency. It has been proven by many studies that the more-electric concept is more fuel efficient than a comparable conventional aircraft. The classical approach to aircraft trajectory optimisation does not account for the fuel penalties caused due to airframe systems operation. Hence the classical approach cannot define a conventional aircraft from a more-electric aircraft. With the more-electric aircraft expected to be more fuel efficient it was clear that optimal operation for the two concepts would be different. This research presents a methodology that can be used to study optimised trajectories for more-electric aircraft. The study present preliminary evidence of the environmental impact due to airframe systems operation and establishes the basis for an enhanced approach to aircraft trajectory optimisation which include airframe system penalties within the optimisation loop. It then presents a suite of models, the individual modelling approaches and the validation to conduct the study. Finally the research presents analysis and comparisons between the classical approach where the aircraft has no penalty due to systems, the conventional aircraft and the more-electric aircraft. When the case studies were optimised for the minimum fuel burn operation, the conventional airframe systems accounted for a 16.6% increase in fuel burn for a short haul flight and 6.24% increase in fuel burn for a long haul flight. Compared to the conventional aircraft, the more electric aircraft had a 9.9% lower fuel burn in the short haul flight and 5.35% lower fuel burn in the long haul flight. However, the key result was that the optimised operation for the moreelectric aircraft was significantly different than the conventional aircraft. Hence this research contributes by presenting a methodology to bridge the gap between theoretical and real aircraft-applicable trajectory optimisation.
18
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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Flodin, Linus, i 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.
20
Zhu, Zhongxi. "The aircraft rotation problem". Diss., Georgia Institute of Technology, 1994. http://hdl.handle.net/1853/21788.
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Swift, Adam. "Simulation of aircraft aeroelasticity". Thesis, University of Liverpool, 2011. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.569519.
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Aeroelastic phenomena such as flutter can have a detrimental effect on aircraft performance and can lead to severe damage or destruction. Buffet leads to a re- duced fatigue life and therefore higher operating costs and a limited performance envelope. As such the simulation of these aeroelastic phenomena is of utmost importance. Computational aeroelasticity couples computational fluid dynamics and computational structural dynamics solvers through the use of a transforma- tion method. There have been interesting developments over the years towards more efficient methods for predicting the flutter boundaries based upon the sta- bility of the system of equations. This thesis investigates the influence of transformation methods on the flutter boundary predition and considers the simulation of shock-induced buffet of a transport wing. This involves testing a number of transformation methods for their effect on flutter boundaries for two test cases and verifying the flow solver for shock-induced buffet over an aerofoil. This will be followed by static aeroelastic calculations of an aeroelastic wing. It is shown that the transformation methods have a significant effect on the predicted flutter boundary. Multiple transformation methods should be used to build confidence in the results obtained, and extrapolation should be avoided. CFD predictions are verified for buffet calculations and the mechanism behind shock-oscillation of the BGK No. 1 aerofoil is investigated. The use of steady calculations to assess if a case may be unsteady is considered. Finally the static aeroelastic response of the ARW-2 wing is calculated and compared against ex- perimental results.
22
Sonei, Arash. "Designing A Conventional Aircraft". Thesis, KTH, Skolan för teknikvetenskap (SCI), 2014. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-153225.
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This paper is explaining the important design phases of dimensioning an unmanned conventional aircraft from scratch and will also design one according to a few chosen requirements. The design phases discussed will be all from wing dimensioning to stability and spin recovery, aircraft performance requirements and how to select a motor which overcomes these. As well as the optimal rate of climb for improved efficiency is discussed. In the end an aircraft which manages the set requirements and is stable in pitch managing spin recovery with no problem will have been dimensioned.
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Hartland, A. J. "Dispersed base combat aircraft". Thesis, Cranfield University, 1989. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.237543.
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Filho, Nelson Whitaker. "Aircraft Distance Measurement System". International Foundation for Telemetering, 1994. http://hdl.handle.net/10150/611674.
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International Telemetering Conference Proceedings / October 17-20, 1994 / Town & Country Hotel and Conference Center, San Diego, CaliforniaThe Aircraft Distance Measurement System (ADMS) could be used in Flight Test application to determine the aircraft position and speed during takeoff, landing and acceleration-stop performance test within runway limits using a microwave link.
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Heffernon, Timothy James. "Aircraft noise installation effects". Thesis, University of Southampton, 2017. https://eprints.soton.ac.uk/415885/.
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Airframe noise is currently of a comparable level to engine noise for an aircraft on approach with high-lift devices and landing gears deployed. The landing gears are a large contributor to the overall airframe noise in this situation. Main landing gears are typically installed beneath a lifting wing. The wing surfaces act as scattering surfaces for the noise generated by these landing gears, and the non-uniform flow around the wing affects both the propagation and strength of the noise. This thesis focuses on investigating the propagation and scattering of installed landing gear noise sources. Boundary element methods are capable of computing acoustic scattering by large and complex geometries, such as a complete aircraft geometry. However, due to their use of Green’s functions, flow effects can only be approximated. As a result, the refraction of acoustic waves due to a non-uniform flow is not accounted for. A uniform flow formulation based on a Lorentz-type transform is typically employed with boundary element methods. The effect of neglecting refraction on the propagation and scattering of landing gear noise sources is determined in this thesis. Investigations are conducted using computational aeroacoustic methods that solve the linearised Euler equations, which account for the refraction of acoustic waves due to non-uniform flow. Using computational aeroacoustic methods, the effect of non-uniform flow due to circulation on the acoustic scattering is quantified as the difference in acoustic scattering over uniform and non-uniform base flows. These investigations are conducted using both single frequency and broadband monopole sources, and both single-element and multi-element airfoils. Increasing the angle of attack, increasing the Mach number, and deploying flaps all increase the circulation around the airfoil. The effect of varying these parameters is investigated systematically. It is shown that for a source in the approximate position of a landing gear with flow conditions similar to that of an airliner on approach, the largest difference observed is at single frequencies for an airfoil configuration with a deployed flap. Otherwise, the differences are small, and in some cases so small that they can be considered negligible. It is shown that moving the source to a position above the airfoil and using a higher Mach number gives a larger difference, although this is not representative of a landing gear source. A new method is proposed to generate a broadband input signal for use with a computational aeroacoustic solver that gives a specified power spectral density at a given radial distance from a monopole source. A signal that is equal in power across a specified range of frequencies is generated using this method. The effect on the frequency content of the scattered noise from a broadband source installed beneath a lifting wing is investigated using this generated signal. It is shown for a single-element airfoil that the major contributor to the obtained power spectral density is the distance of the source from the airfoil. Varying the angle of attack and Mach number has only a small additional effect on the power spectral density. It is then shown that flap and slat deployment has a larger effect on the computed power spectral density due to the additional reflective surfaces. Existing boundary element method formulations that estimate uniform and nonuniform flow effects are evaluated for their suitability for landing gear noise scattering predictions. It is shown that the uniform flow formulation is more suitable due to a simplifying assumption made in the derivation of the non-uniform flow formulation. An existing realistic landing gear noise model is coupled with a three-dimensional acoustic boundary element method solver. The landing gear noise model applies scaling laws to directional databases for isolated landing gear components in order to estimate the total far-field noise. The implemented coupling methodology is used to compute the sound pressure level on a ground plane beneath a realistic scattering aircraft geometry. The geometrical effect of flap deployment is investigated using sources of constant strength for each configuration. It is shown that the effect of flap deployment is to increase the sound pressure level directly below and in the region immediately surrounding the aircraft. The effect of source strength reduction due to circulation around a lifting wing is then included in the predictions. This results in a large decrease in the predicted sound pressure level on the ground plane with flap deployment.
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Yakovenko, A., Світлана Віталіївна Подолкова, Светлана Витальевна Подолкова i Svitlana Vitaliivna Podolkova. ""Green" aircraft from films". Thesis, Sumy State University, 2020. https://essuir.sumdu.edu.ua/handle/123456789/77943.
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Every year, the amount of passengers on airplanes is growing by several million people and the slogan "Everyone can fly" becomes a reality. In addition, there are different types of aircraft: wide-body aircrafts are used for transporting a large number of passengers for medium and long distances, narrowbody ones have lower passenger capacity, regional and local. But not all modern planes are environmental friendly. During flights carbon gets into the atmosphere, which causes environmental pollution. That's why some companies try their best to solve this problem.
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Sataieva i Syrotiuk. "CHOICE OF AIRCRAFT SIZE". Thesis, Київ 2018, 2018. http://er.nau.edu.ua/handle/NAU/33897.
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Tsentseris, Michail. "ARES: aircraft propulsion integration". Thesis, Cranfield University, 2013. http://dspace.lib.cranfield.ac.uk/handle/1826/12121.
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The combat aircraft and the gas turbine engine interact with one another. These
interactions have become of even greater significance than previously due to the fact
that the modern aircraft have increased requirements in terms of thrust, efficiency,
reliability and ease of maintenance. Issues that affect the performance and operational
capability of combat aircraft are the aircraft aerodynamic characteristics, propulsion
system performance and the airframe/engine matching.
This study focuses on the evaluation of the propulsion system of modern jet
powered combat aircraft and combines computations with the existing integration
methodology. The main objective of this study is the update of ARES method (aircraftengine
performance tool for combat aircraft) so as to be feasible the incorporation of
new data in the calculations of the program. The update contains:
• the establishment of a procedure that can be used for the calculation of
the additional drag that a external load (tanks, bombs, missiles, pods) contribute in the
total aircraft drag,
• the modification of ARES method in order to integrate the additional
drag of the external loads in the program calculations,
• the creation of a procedure that will be used for the calculation of the
thrust deductions due to installation effects.
The information that can be received from this study are valuable because can be
used in the evaluation of the engine performance, can give the opportunity for further
engine studies such as the structural and thermal analysis, component sizing and
geometry, life consumption and of course can make apparent if a specific aircraftengine
system is capable of accomplishing a demanded operating requirement.
The final results of the study led to the general conclusion that the total aircraft
drag and the demanded uninstalled net thrust increased with the addition of external
tanks in the aircraft. The fuel consumption was higher for the configuration with the two
tanks and was noticed an increase of the TET which is proportional to the number of the
used external tanks (max TET increases at least 0.8% per tank). Additionally was
extracted the conclusion that the addition of an external wing tank increases the amount
of the consumed fuel at least 3.5%.
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Karlsson, Albin, i Anton Lomaeus. "Transport Aircraft Conceptual Design". Thesis, KTH, Skolan för teknikvetenskap (SCI), 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-210778.
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A conceptual design for a transport aircraft has been created, tailored for human-itarian missions along the equator with its home base in the European Union while optimizing for fuel eciency and speed. An initial estimate of the empty weight was made using historical data and Breguet equations, based on a required payload of 60 tonnes and range of 5 500 nautical miles. A constraint diagram consisting of require-ments for stall speed, takeo distance, climb rate and landing distance was used to determine wing loading and thrust to weight ratio, resulting in a main wing area of 387m 2 and thrust to weight ratio of 0:224, for which two Rolls Royce Trent 1000-H engines were selected. A high aspect ratio wing was designed with blended winglets to optimize against lift induced drag. Wing placement and tail volume were decided by iterative calculations, resulting in a centre of lift located aft of the centre of gravity during all stages of the mission. The resulting aircraft model has a high wing with a span of 62 m, length of 49m with a takeo gross weight of 221 tonnes, of which 83 tonnes are fuel.
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Andersson, Henric. "Aircraft Systems Modeling : Model Based Systems Engineering in Avionics Design and Aircraft Simulation". Licentiate thesis, Linköping University, Linköping University, Machine Design, 2009. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-17573.
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Aircraft developers like other development and manufacturing companies, are experiencing increasing complexity in their products and growing competition in the global market. One way to confront the challenges is to make the development process more efficient and to shorten time to market for new products/variants by using design and development methods based on models. Model Based Systems Engineering (MBSE) is introduced to, in a structured way, support engineers with aids and rules in order to engineer systems in a new way.
In this thesis, model based strategies for aircraft and avionics development are studied. A background to avionics architectures and in particular Integrated Modular Avionics is described. The integrating discipline Systems Engineering, MBSE and applicable standards are also described. A survey on available and emerging modeling techniques and tools, such as Hosted Simulation, is presented and Modeling Domains are defined in order to analyze the engineering environment with all its vital parts to support an MBSE approach.
Time and money may be saved by using modeling techniques that enable understanding of the engineering problem, state-of-the-art analysis and team communication, with preserved or increased quality and sense of control. Dynamic simulation is an activity increasingly used in aerospace, for several reasons; to prove the product concept, to validate stated requirements, and to verify the final implementation. Simulation is also used for end-user training, with specialized training simulators, but with the same underlying models. As models grow in complexity, and the set of simulation platforms is expanded, new needs for specification, model building and configuration support arise, which requires a modeling framework to be efficient.
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Bergkvist, Erik, i Tommy Sabbagh. "Smart Future Solutions for Maintenance of Aircraft : Enhancing Aircraft Maintenance at Saab AB". Thesis, Linköpings universitet, Industriell Produktion, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-176561.
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This master thesis has the purpose to analyse and identify smart efficient future solutions within the Maintenance, Repair and Overhaul (MRO) process for aircraft. The efficiency solutions, in form of new technologies and tools, should present a foundation that MRO suppliers can continue to develop to enhance and streamline their maintenance processes. The project was performed as a case study at the aerospace and defense company Saab AB in Linköping, where the company's MRO process was investigated. Through identifying possibilities and alternative technologies available today and in the near future, one continues to have a competitive and future-proof position in the market. Through an own constructed course of action influenced from established methods, the thesis' purpose and aim was attained. The method was based on authentic approaches for case studies but also inspired by the so-called "Requirement Engineering". The combination of the methods resulted in a precise focus on the relevant subjects, together with a clear structure of the requirements on the technologies to reach a successful implementation. Through a detailed data collection comprised of study visits, interviews, literature studies, market analyses, and document reviews, multiple relevant technologies and requirement-lists for utilization were identified. To concretize the use and potential improvements with the technologies, the project had the objective to develop a demonstrator with one of the technologies presented. The demonstrator should focus on minimizing the use of paper, which is a common problem among many market actors today. The most promising technology was considered to be a tablet application with an accommodated application. The selection of the tablet solution was based on the motivation that it is a well-established technology and a favorable first step from paperwork. To conclude this master thesis, a tablet application was developed in Novacura Flow Studio, where the majority of the identified requirements were fulfilled. Beyond the demonstrator, an introduction and analysis of technologies, such as AR-glasses, voice guidance, additive manufacturing, and a digital twin, was presented.
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Thate, Timothy J. Michels Adam S. "Requirements for digitized aircraft spotting (Ouija) board for use on U.S. Navy aircraft carriers /". Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2002. http://library.nps.navy.mil/uhtbin/hyperion-image/02sep%5FThate.pdf.
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Thesis (M.S. in Information Systems Management)--Naval Postgraduate School, September 2002.Thesis advisor(s): Alex Bordetsky, Glenn Cook. Includes bibliographical references. Also available online.
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Cummins, Lane, i Tony Wilborn. "Cost-benefit analysis of the Department of the Navy's transition from C-9 Aircraft to C-40 Aircraft for logistic support aircraft". Monterey, California: Naval Postgraduate School, 2009. http://hdl.handle.net/10945/10395.
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Approved for public release, distribution unlimitedMBA Professional Report
The Navy began transitioning from the aging C-9s, which peaked at a total fleet size of 27 C-9B/DC-9 aircraft, to the C-40A. However, in response to increasing defense budget scrutiny and competing priorities, the Navy has decided to put this program on hold. Although the C-9B is an aging airframe and will require mandatory Federal Aviation Administration mandated modifications and upgrades, the DC-9/C-9B airframe has recently been determined to have significant operational service life remaining. This project provides a Cost-benefit Analysis (CBA) of the changes associated with replacing the C-9B aircraft with the C-40A. We analyze three alternatives. The first assumes that the C-40A acquisition program will remain on-hold indefinitely. The second alternative foresees the C-40A acquisition resuming as currently projected in FY2015. The third alternative involves the original C-40A acquisition program as per Naval Air Plan 2030 (NAP 2030). The objective is to compare the three alternatives, choosing the alternative, which provides the greatest net benefit and most efficient use of resources. The analysis will involve data collection of operational costs per flight hour, and total costs over the life of the program. Our cost-benefit analysis is intended to indicate the best course of action to provide continued execution of the Navy's Unique Fleet Essential Aircraft (NUFEA) mission. We intend to document all costs incurred and potential savings from a transition to the C-40 aircraft. We find that Alternative Three has lower discounted costs, as well as lower risk and better capabilities, and therefore recommend the Navy transition back to the original C-40 program as soon as practical.
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Cummins, Lane Wilborn Tony. "Cost-benefit analysis of the Department of the Navy's transition from C-9 Aircraft to C-40 Aircraft for logistic support aircraft". Monterey, California : Naval Postgraduate School, 2009. http://edocs.nps.edu/npspubs/scholarly/MBAPR/2009/Dec/09Dec%5FCummins%5FMBA.pdf.
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"Submitted in partial fulfillment of the requirements for the degree of Master of Business Administration from the Naval Postgraduate School, December 2009."Advisor(s): Franck, Raymond E. ; Hildebrandt, Gregory. "December 2009." "MBA Professional report"--Cover. Description based on title screen as viewed on January 27, 2010. Author(s) subject terms: Cost-benefit Analysis, C-9B Skytrain, C-40A Clipper, NUFEA, Fleet Logistic Support Wing, Acquisition. Includes bibliographical references (p. 85-86). Also available in print.
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Michels, Adam S., i Timothy Thate. "Requirements for digitized aircraft spotting (Ouija) board for use on U.S. Navy aircraft carriers". Thesis, Monterey California. Naval Postgraduate School, 2002. http://hdl.handle.net/10945/4447.
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Approved for public release; distribution is unlimited.This thesis will evaluate system and process elements to initiate requirements modeling necessary for the next generation Digitized Aircraft Spotting (Ouija) Board for use on U.S. Navy aircraft carriers to track and plan aircraft movement. The research will examine and evaluate the feasibility and suitability of transforming the existing two-dimensional static board to an electronic, dynamic display that will enhance situational awareness by using sensors and system information from various sources to display a comprehensive operational picture of the current flight and hangar decks aboard aircraft carriers. The authors will evaluate the current processes and make recommendations on elements the new system would display. These elements include what information is displayed, which external systems feed information to the display, and how intelligent agents could be used to transform the static display to a powerful decision support tool. Optimally, the Aircraft Handler will use this system to effectively manage the Flight and Hangar decks to support the projection of air power from U.S. aircraft carriers.
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Mirmohammadsadeghi, Navid. "Development of an Aircraft Landing Database and Models to Estimate Aircraft Runway Occupancy Times". Diss., Virginia Tech, 2020. http://hdl.handle.net/10919/99914.
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This dissertation represents the methodologies used to develop an aircraft landing database and predictive models for estimating arrival flight runway occupancy times. In the second chapter, all the algorithms developed for analyzing the airport surface radar data are explained, and detailed statistical information about various airports in the United States in terms of landing behavior is studied. In the third chapter a novel data-driven approach for modeling aircraft landing behavior is represented. The outputs of the developed approach are runway occupancy time distributions and runway exit utilizations. The represented hybrid approach in the third chapter is a combination of machine learning and Monte Carlo simulation methods. This novel approach was calibrated based on two years of airport radar data. The study's output is a computer application, which is currently being used by the Federal Aviation Administration and various airport consulting firms for analyzing and designing optimum runway exits to optimize runway occupancy times at airports. In the fourth chapter, four real-world case scenarios were analyzed to show the power of the developed model in solving real-world challenges in airport capacity. In the fifth chapter, pilot motivational behaviors were introduced, and three methodologies were used to replicate motivated pilot behaviors on the runway. Finally, in the sixth chapter, a neural network approach was used as an alternative model for estimating runway occupancy time distributions.Doctor of Philosophy
The federal aviation administration predicts ongoing growth in the aviation industry over the following 20 years. Therefore, the airports will be more crowded, and a higher number of operations will occur at those facilities. An accurate prediction of airports' capacities can help the authorities to improve the airports appropriately. Due to significant reductions in in-trail aircraft separations, runway occupancy times will become more significant in airport arrival procedures. In this study, a landing event database was developed to represent the accurate distributions of runway occupancy times. Also, it is essential to have computer applications capable of replicating runway occupancy time distributions. In this dissertation, a novel approach was developed to replicate aircraft runway occupancy times. A massive amount of airport surface radar data was utilized to create all the mentioned computer applications. The results of the final products were validated against real data. Real-world case scenarios were discussed as part of this study to showcase the strengths of the final developed product in solving challenging problems related to airport capacity. Finally, extreme cases of motivated landing behavior from airline pilots were studied, and multiple methodologies were introduced to replicate pilot motivational behavior while landing on runway.
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Hintze, Joshua. "Autonomous landing of a rotary unmanned aerial vehicle in a non-cooperative environment using machine vision /". Diss., CLICK HERE for online access, 2004. http://contentdm.lib.byu.edu/ETD/image/etd359.pdf.
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Li, Bo Lim Alvin S. "Multiple UAV simulation with multiresolution multistage models and decision support". Auburn, Ala., 2008. http://hdl.handle.net/10415/1547.
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Schauppner, Craig T. "Optimal aircraft carrier deployment scheduling". Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1996. http://handle.dtic.mil/100.2/ADA308066.
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Shu, Yan. "Future aircraft networks and schedules". Diss., Georgia Institute of Technology, 2011. http://hdl.handle.net/1853/41221.
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This thesis has focused on an aircraft schedule and network design problem that involves multiple types of aircraft and flight service. First, this thesis expands a business model for integrating on-demand flight services with the traditional scheduled flight services. Then, this thesis proposes a three-step approach to the design of aircraft schedules and networks from scratch. After developing models in the three steps and creating large-scale instances of these models, this dissertation develops iterative algorithms and subproblem approaches to solving these instances, and it presents computational results of these large-scale instances. To validate the models and solution algorithms developed, this thesis compares the daily flight schedules that it designed with the schedules of the existing airlines. In addition, it discusses the implication of using new aircraft in the future flight schedules. Finally, future research in three areas--model, computational method, and simulation for validation--is proposed.
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Kaufmann, Markus. "Cost Optimization of Aircraft Structures". Doctoral thesis, KTH, Lättkonstruktioner, 2009. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-11482.
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Composite structures can lower the weight of an airliner significantly. Due to the higher process complexity and the high material cost, however, the low weight often comes with a significant increase in production cost. The application of cost-effective design strategies is one mean to meet this challenge. In this thesis, a simplified form of direct operating cost is suggested as a comparative value that in combination with multidisciplinary optimization enables the evaluation of a design solution in terms of cost and weight. The proposed cost optimization framework takes into account the manufacturing cost, the non-destructive testing cost and the lifetime fuel consumption based on the weight of the aircraft, thus using a simplified version of the direct operating cost as the objective function. The manufacturing cost can be estimated by means of different techniques. For the proposed optimization framework, feature-based parametric cost models prove to be most suitable. Paper A contains a parametric study in which a skin/stringer panel is optimized for a series of cost/weight ratios (weight penalties) and material configurations. The weight penalty (defined as the specific lifetime fuel burn) is dependent on the fuel consumption of the aircraft, the fuel price and the viewpoint of the optimizer. It is concluded that the ideal choice of the design solution is neither low-cost nor low-weight but rather a combination thereof. Paper B proposes the inclusion of non-destructive testing cost in the design process of composite components, and the adjustment of the design strength of each laminate according to inspection parameters. Hence, the scan pitch of the ultrasonic testing is regarded as a variable, representing an index for the guaranteed material quality. It is shown that the cost for non-destructive testing can be lowered if the quality level of the laminate is assigned and adjusted in an early design stage. In Paper C and Paper D the parameters of the manufacturing processes are upgraded during the cost optimization of the component. In Paper C, the framework is extended by the cost-efficient adaptation of parameters in order to reflect the situation when machining an aluminum component. For different weight penalties, the spar thickness and stringer geometry of the provided case study vary. In addition, another cutter is chosen with regard to the modified shape of the stringer. In Paper D, the methodology is extended to the draping of composite fabrics, thus optimizing not only the stacking layup, but also the draping strategy itself. As in the previous cases, the design alters for different settings of the weight penalty. In particular, one can see a distinct change in fiber layup between the minimum weight and the minimum cost solution. Paper E summarizes the work proposed in Papers A-D and provides a case study on a C-spar component. Five material systems are used for this case study and compared in terms of cost and weight. The case study shows the impact of the weight penalty, the material cost and the labor rate on the choice of the material system. For low weight penalties, for example, the aluminum spar is the most cost-effective solution. For high weight penalties, the RTM system is favorable. The paper also discusses shortcomings with the presented methodology and thereby opens up for future method developments.QC 20100723
European Framework Program 6, project ALCAS, AIP4-CT-2003-516092
Nationella flygtekniska forskningsprogrammet (NFFP) 4, project kostnadseffektiv kompositstruktur (KEKS)
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Gray, Paula Margaret. "System tool for aircraft routing". Thesis, University of British Columbia, 1985. http://hdl.handle.net/2429/24398.
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Operations Planning at CP Air is responsible for keeping an up-to-date visual representation of the aircraft routings for the current schedule period and co-ordinating subsequent changes. Examples of changes are requests for extra usage such as charters or extra sections, changes to the maintenance schedule, and unforeseen circumstances.
The present approach is a manual charting method used in the same or similar form by many airlines as well as at CP Air. This manual process is long and tedious and even minor changes can cause much work to keep the charts up-to-date and everyone informed.
What is needed is an automated system that will present the information produced on the charts in the most useable manner plus the ability to make changes so that, the resulting information can be more effectively used than with the present manual method. The approach taken is the development of a. Decision Support tool that will allow Operations Planning to make decisions based on their knowledge and experience. This solution is a starting point in an area at CP Air that has long needed some automation.
The system has been developed on the Virtual Machine operating system using I BrA 3279 equipment for its color capabilities, and it is currently in the stages of system testing and user-training.Business, Sauder School of
Graduate
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Crowley, Christopher Keith Aerospace Civil & Mechanical Engineering Australian Defence Force Academy UNSW. "Meeting the ageing aircraft challenge". Awarded by:University of New South Wales - Australian Defence Force Academy. School of Aerospace, Civil and Mechanical Engineering, 2004. http://handle.unsw.edu.au/1959.4/38679.
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"Meeting the ageing aircraft challenge" is not just about safety, not just about effectiveness, and not just about economy of support. It is about proactive and reactive optimization of all three service goals throughout long life cycles that span 20 or 30 years, or more, and typically, beyond the originally intended design life. It is therefore about organizational attitudes towards ongoing trend analysis and condition monitoring, and pervading cost benefit assessments of all forms of human innovation across what the author describes as 'the eight sustaining disciplines for long aerospace life cycles', including scientific and technological developments, and opportunities for reliability growth or 'refresh'. Complacency is the root cause of all problems with the design, maintenance and support of all modern infrastructure, and therefore life cycle planners and minders are required to be an enthusiastic but nervous lot - always hoping for the best, but planning for the worst impact of 'Mr Murphy'. Murphy thrives on complacency, is in bed with uncertainty, and never forgets (as we do often) that imperfection (no matter how small) breeds unreliability traps that patiently wait to surprise at some stage along the life cycle journey. He has the upper hand. ...Our best weapons against Murphy are continual, total picture and longer-term situational awareness; caution, vigilance, innovation and collaboration. This research study and thesis is intended as a broad and comprehensive management philosophy, a guide and checklist - a broad scrape of everything 'so deep', rather than coverage of any one-niche aspect of the ageing aircraft challenge in great depth. It includes a brief and simple strategic setting for Australian Military Aerospace requirements, and spans a three axes management philosophy: 1. a toolbox of eight sustaining disciplines, 2. trend analysis and 3. time-cost-benefit assessment. Along with complacency, the prime ageing aircraft 'killers' are identified, as are the key ageing aircraft 'age multipliers'. The eight sustaining disciplines are explained in varying depth, according to their broad significance to the ageing aircraft condition and life cycle. The ever-ubiquitous bathtub reliability curve - the key to understanding, predicting and controlling life cycle behaviour (including costs) - is emphasized. Engineering life cycle minding and capability management are broad focus areas. The eight areas of attention identified for this broad study are: 1. Aerospace design requirements and trends, 2. Science and technology opportunities, 3. Airworthiness, engineering and maintenance philosophy, 4. Reliability behaviour, 5. Operational use and abuse patterns, 6. Logistics support and managing obsolescence, 7. Technical workforce and organizational attitudes (requirements and outlook), and 8. Life cycle costing and budgeting. This thesis primarily draws attention to the fundamental driver of life cycle behaviour - reliability. The critical dependency that life cycle control and prediction has on consistent and high quality trend data collection and analysis is emphasized throughout, and the now pressing need for better identification of ageing aircraft cost growth drivers, and their containment, is linked to reliability trend awareness, manipulation and intervention. The human dimension is included - including coverage of organizational attitudes and what it takes to be a 'high reliability organization'. There are no magic or easy answers to the ageing aircraft condition and challenge. Trend analysis has to be done from the bottom up, system by system, for each fleet type. But over time, with consistent trend data collection, patterns emerge within the sophisticated and stochastic systems behaviour that that ageing aircraft play out. These patterns enable ongoing management of the long life cycle to be more confidently predicted, more assured and with best possible cost growth containment. The best, perhaps only, path to least surprises and best cost containment is now being re-identified in some military aviation organizations as a mature and evolving RAM engineering and RCM framework. RAM-RCM may well be the only recovery from what some admit is a death spiral of ageing aircraft cost growth.
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Liu, Bilong. "Acoustical Characteristics of Aircraft Panels". Doctoral thesis, Stockholm, 2006. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-4102.
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Liu, Biong. "Sound transmission through aircraft panels /". Stockholm, 2005. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-494.
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Kuttenkeuler, Jakob. "Aircraft composites and aeroelastic tailoring /". Stockholm, 1998. http://www.lib.kth.se/abs98/kutt0520.pdf.
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Kim, Jijoong. "Automatic aircraft recognition and identification". Access electronically, 2005. http://www.library.uow.edu.au/adt-NWU/public/adt-NWU20060808.161115/index.html.
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Yildirim, Zeki. "Self-defense of large aircraft". Thesis, Monterey, Calif. : Naval Postgraduate School, 2008. http://bosun.nps.edu/uhtbin/hyperion-image.exe/08Mar%5FYildirim.pdf.
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Thesis (M.S. in Electronic Warfare Systems Engineering)--Naval Postgraduate School, March 2008.Thesis Advisor(s): Herrera, Michael. "March 2008." Description based on title screen as viewed on May 19, 2008. Includes bibliographical references (p. 131-134). Also available in print.
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Pearson, John L. "Optimizing Unmanned Aircraft System Scheduling". Thesis, Monterey, Calif. : Naval Postgraduate School, 2008. http://handle.dtic.mil/100.2/ADA483449.
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Thesis (M.S. in Operations Research)--Naval Postgraduate School, June 2008.Thesis Advisor(s): Carlyle, W. Matthew. "June 2008." Description based on title screen as viewed on August 26, 2008. Includes bibliographical references (p. 35). Also available in print.
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Gibson, William E. "Aircraft investment planning and uncertainty". Thesis, Cranfield University, 2010. http://dspace.lib.cranfield.ac.uk/handle/1826/6864.
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This research sets out to determine whether there is a best way to perform
aircraft investment analysis. The question of best practice is found to be
linked to corporate ownership: world airline shareholding patterns are
identified and linked to investment analysis practices, and to airline financial
performance over the last aviation cycle.
A key weakness identified by surveying airline practice concerns the treatment
of uncertainty in the financial analysis. This research critically examines the
state of practice regarding treatment of uncertainties embedded investment
valuation assumptions, in airline fleet planning around the world, and
proposes structured application of advanced analytical techniques to valuation
in today’s world of volatile and diverse aviation markets.
The assumptions underlying valuation are embedded in modern financial
theory, which has been developed and tested over the last century. The
validity and usefulness of financial valuation models is examined from both
theoretical and practical perspectives, and the state of practice regarding
these models in the airline industry is established, both quantitatively through
survey research, and qualitatively through aviation executive interviews in the
field. This combined approach has allowed the establishment of ‘paradigms’
characterizing the concrete application of financial theory to the question of
aircraft investment.
Regional patterns of airline shareholding are identified in a detailed analysis of
ownership structure and business models. The resulting governance typology
is analyzed in aggregate, and associated with production, and profitability by
region. The tendency of each airline ownership type to use modern financial
valuation techniques has to some extent been established by applying survey
results to the different regions.
The fleet planning process and the positioning of investment valuation within it
is discussed, and key uncertainties underlying fleet planning assumptions are
identified and mapped in a risk map framework. A method for strategic
analysis of fleet financing alternatives is derived from classical theory, and
applied to the specifics of the aircraft market.
The uncertainties surrounding several key modelling assumptions are found to
be substantial in the minds of today’s fleet planners, and the assessments of
uncertainty vary substantially between airline fleet planners and third-party
advisors. The identified practices in applying classical financial theory are
found to be strikingly inadequate in treatment of these uncertainties.A model is developed for valuing the acquisition of aircraft under uncertainty,
using extensions of the classical financial framework entailing more advanced
quantitative techniques. The model’s application to a specific analytical
situation analysis show that investment valuations under deterministic models
are contradicted when applying uncertainty to key uncertainties present in
today’s markets, and a process that yields insights beyond classical finance is
proposed.