Global ETD Search

21	Excess baggage weighing the contribution of political and corporate interests in the W.T.O. cases over commercial aircraft subsidies / Spadafore, Annemarie Michaela. January 2008 (has links) Thesis (Ph. D.)--Miami University, Dept. of Political Science, 2008. / Title from first page of PDF document. Includes bibliographical references (p.112-118).
22	Reasoning about models: detecting and isolating abnormalities in diagnostic systems Belard, Nuno 21 May 2012 (has links) (PDF) Dans le cadre du diagnostic à base de Modèle, un ensemble de règles d'inférence est typiquement exploité pour calculer des diagnostics, ceci en utilisant une théorie scientifique et mathématique sur le système à diagnostiquer, ainsi qu'un ensemble d'observations. Contrairement aux hypothèses classiques, les Modèles sont souvent anormaux vis-à-vis d'un ensemble de propriétés requises. Naturellement, cela affecte la qualité des diagnostics [à Airbus]. Une théorie sur la réalité, l'information et la cognition est créé pour redéfinir, dans une perspective basée sur la théorie des modèles, le cadre classique de diagnostic à base de Modèle. Ceci rend possible la formalisation des anomalies et de leur relation avec des propriétés des diagnostics. Avec ce travail et avec l'idée qu'un système de diagnostic implémenté peut être vu comme un objet à diagnostiquer, une théorie de méta-diagnostic est développée, permettant la détection et isolation d'anomalies dans les Modèles des systèmes de diagnostic. Cette théorie est mise en pratique à travers d'un outil, MEDITO; et est testée avec succès à travers un ensemble de problèmes industriels, à Airbus. Comme des différents systèmes de diagnostic Airbus, souffrant d'anomalies variées, peuvent calculer des diagnostics différents, un ensemble de méthodes et outils et développé pour: 1) déterminer la cohérence entre diagnostics et 2) valider et comparer la performance de ces systèmes de diagnostic. Ce travail dépend d'un pont original entre le cadre de diagnostic Airbus et son équivalent académique. Finalement, la théorie de méta-diagnostic est généralisée pour prendre en compte des métasystèmes autres que des systèmes de diagnostic implémentés. Diagnostic à base de modèles Méta-diagnostic Aéronautique Airbus Raisonnement Intelligence artificielle
23	Aircraft environmental control systems modeling for configuration selection Peng, Xiong 11 1900 (has links) According to the statistics about civil transportation aircraft Environmental Control system (ECS), the three-wheel high pressure water separation system (HPWS) and low pressure water separation system (LPWS) are the most common choices for the 150-seat airliners. Although the former has become the mainstream configuration for air conditioning pack, the latter is still used on Boeing 737-600/700. In order to compare the two configurations and choose the better one for a specific aircraft, simulation and analysis are done. The cabin heat load is calculated at first in order to calculate required engine bleed air mass flow. Then a specific aircraft is defined so that required structural dimensions and cabin comfort indexes can be obtained based on Airbus 320. Thirdly, the component models are built by Matlab/Simulink according to the fundamental knowledge of heat transfer and aerodynamics, the working principles and mechanical dimensions of the components, the ambient environmental parameters and some data from Airbus 320. Consequently, the complete system model can be assembled. After confirming the validity of the model by checking the required ram air mass flow and temperature deviation of the state points referred to Airbus 320, the simulation model is used to do analyze the specific aircraft. Finally, through comparing the different values of ram air mass flow and turbine expansion ratio, as well as the system mass, economic cost and reliability, the better configuration is selected. It can be summarized that the three-wheel LPWS requires less ram air mass flow (0.012kg/s) and a little lower expansion ratio (0.02) than the HPWS, and it also has lower weight (63% of HPWS), lower (83% of HPWS) cost and higher reliability (140% of HPWS), thus it is the suitable configuration for the specific aircraft. Airbus 320 Simulation Temperature Pressure
24	Modularisierung komplexer Produkte anhand technischer und betriebswirtchaftlicher Komponentenkopplungen / Koeppen, Birgit. January 2008 (has links) (PDF) Techn. Univ., Diss.--Hamburg-Harburg, 2007.
25	Addressing Adaptive Structure Technology to Reduce the Airframe Noise(Link) / Adaptive Slat Design and Relative Stress & Damage Analysis Sahin, Hakan January 2012 (has links) ABSTRACTThe purpose of this thesis is to design and analyze the new generation leading edge slat of a commercial jet to reduce the structural noise with the application of new conceptual design approaches. Recent scientific research show that the leading edge slats account for the structural noise during the flight operation therefore, when the leading edge slat is deployed under different flight conditions, an open gap/slot is formed between the high lift device and the wing box. However, since the leading edge slat includes flexible sections, it is assumed that defining an adaptive system inside the leading edge slat may reduce the structural noise by utilizing bending properties of these flexible sections. Hence, electromechanical actuator designing gains also great importance in the whole process. In this study, we have used, finite element modelling of the slat structure to examine the required structural deformations and strengths; our work is based on the software ANSYS/Workbench. To be realistic in deciding the right geometry in the follow up steps, we have first studied a generic geometry having no aerodynamics or actuator forces application. The whole simulation was performed by defining dummy forces and dummy material properties. The simulation lead to having a global overview of the mechanical behaviour of the structure; further, once the influent parameters were tested, realistic aerodynamic forces and material properties were defined, and as a result of bending of the flexible sections the required gap closure was formed between the trailing edge of the slat and the wing box. Subsequently, the suitable actuator design and required strength analysis are also performed on the last section. This study has also proved that the use of adaptive systems on the leading edge slats improves flight comfort by reducing the structural noise and provides less fuel consumption; this is significant for the long run considerations of aeroplane manufacturers. / es Zentrum für Luft- und Raumfahrt e. V. (DLR) Adaptive Slat Composite Slat Airbus DLR Slat deformation airframe noise Other Mechanical Engineering Annan maskinteknik Aerospace Engineering Rymd- och flygteknik
26	Experiment Design for System Identification on Satellite Hardware Demonstrator Krantz, Elias January 2018 (has links) The subject of this thesis covers the process of online parameter estimation of agile satellites. Accurate knowledge of parameters such as moment of inertia and centre of mass play a crucial role in satellite attitude control and pointing performance. Typically, identification of parameters such as these is performed on-ground using post-processing algorithms. This thesis investigates the potential of performing the identification procedures in real-time on-board operating satellites, using only measurements available from typical satellite attitude sensors. The thesis covers the areas of system identification and modelling of spacecraft attitude dynamics. An algorithm based on the Unscented Kalman Filter is developed for online parameter estimation of spacecraft moment of inertia parameters. The proposed method is successfully validated, both through simulation environments, and in practice using Airbus’ satellite hardware demonstrator INTREPID, a three-axis air-bearing table equipped with CMG actuators and typical attitude sensors. LTU Airbus Attitude Guidance Control AOCS GNC Kalman Filter UKF System Identification SysId Estimation Determination CMG Control Engineering Reglerteknik Signal Processing Signalbehandling Aerospace Engineering Rymd- och flygteknik
27	Excess Baggage: Weighing the Contribution of Political and Corporate Interests in the W.T.O. Cases over Commercial Aircraft Subsidies Spadafore, Annemarie Michaela 15 August 2008 (has links) No description available. American Studies Economics International Relations Political Science Boeing Airbus W.T.O. World Trade Organization cases trade disputes commercial aircraft industry 1992 Agreement trade negotiations
28	Basic Comparison of Three Aircraft Concepts: Classic Jet Propulsion, Turbo-Electric Propulsion and Turbo-Hydraulic Propulsion Rodrigo, Clinton January 2019 (has links) (PDF) Purpose - This thesis presents a comparison of aircraft design concepts to identify the superior propulsion system model among turbo-hydraulic, turbo-electric and classic jet propulsion with respect to Direct Operating Costs (DOC), environmental impact and fuel burn. --- Approach - A simple aircraft model was designed based on the Top-Level Aircraft Requirements of the Airbus A320 passenger aircraft, and novel engine concepts were integrated to establish new models. Numerous types of propulsion system configurations were created by varying the type of gas turbine engine and number of propulsors. --- Findings - After an elaborate comparison of the aforementioned concepts, the all turbo-hydraulic propulsion system is found to be superior to the all turbo-electric propulsion system. A new propulsion system concept was developed by combining the thrust of a turbofan engine and utilizing the power produced by the turbo-hydraulic propulsion system that is delivered via propellers. The new partial turbo-hydraulic propulsion concept in which 20% of the total cruise power is coming from the (hydraulic driven) propellers is even more efficient than an all turbo-hydraulic concept in terms of DOC, environmental impact and fuel burn. --- Research Limitations - The aircraft were modelled with a spreadsheet based on handbook methods and relevant statistics. The investigation was done only for one type of reference aircraft and one route. A detailed analysis with a greater number of reference aircraft and types of routes could lead to other results. --- Practical Implications - With the provided spreadsheet, the DOC and environmental impact can be approximated for any commercial reference aircraft combined with the aforementioned propulsion system concepts. --- Social Implications - Based on the results of this thesis, the public will be able to discuss the demerits of otherwise highly lauded electric propulsion concepts. --- Value - To evaluate the viability of the hydraulic propulsion systems for passenger aircraft using simple mass models and aircraft design concept. ddc:620 info:eu-repo/classification/ddc/629.13 Luftfahrt Luftfahrzeug Flugmechanik Betriebskosten Aeronautics Airplanes Airplanes--Performance Cost accounting Ölhydraulik Flugtriebwerk Elektroantrieb Kraftstoffverbrauch Flugzeug Entwurf Dimensionierung Aeroplanes Design Airplanes--Jet propulsion Airplanes--Turbofan engines Electric propulsion Hydraulics Airplanes--Fuel consumption Environmental protection Airbus A320 aircraft aircraft design flight mechanics engines hybrid propulsion hydraulics certification DOC Direct Operating Costs Airbus A320
29	Riskanalys inom MRO-industrin / Risk Analysis in the MRO industry Brstina, Stefan, Rizkallah, Leon January 2022 (has links) MRO-industrin är en kritisk del för underhåll inom flygindustrin och arbetsprocesserna ser olika ut från företag till företag. För att kunna utföra ett så säkert och kvalitetsmässigt arbete som möjligt så är det viktigt att riskbedöma samt minimera existerande risker i operationen för att säkerställa kvalitet till kund samt säkerhet för arbetare. Uppdragsgivaren ST Engineering Aerospace Solutions (STEAS) är det ledande företaget i Sverige när det gäller MRO arbete och med den ständiga utvecklingen av utrustning upptäcks det allt fler risker som kräver analyser och minimering. Forskning har tidigare gjorts på hur fixtur design kan förbättras ergonomiskt m h a virtuell miljöteknik. Detta för att kunna minimera design och tillverkningskostnader med hänsyn till itereringsprocessen. Detta i kombination med studier gjorda på muskuloskeletala skador med kopplingar till MRO-industrin belyser behovet av riskanalys i MRO industrin. Arbetet hos STEAS går ut på att utföra riskanalyser ur ett tekniskt, ergonomiskt och ekonomiskt perspektiv på deras rörliga fixturer samt kemiska processer som behandlar diverse komponenter av motornacellet. Detta för att STEAS sedan ska kunna kolla på eventuella kostnader och implementera de rekommenderade åtgärderna. Analysmetoderna som används är en PHL (Preliminary Hazard List), FMEA (Failure Modes and Effects Analysis) och en ACHB analys (Accidental Cost & Hypothetical Benefit) / The MRO industry is a critical part of maintenance in the aviation industry where the work processes differ from company to company. In order to be able to perform as safe and high-quality work as possible, it is important to assess risks and minimize existing risks in the operation to ensure quality for customers and safety for workers. The client ST Engineering Aerospace Solutions (STEAS) is the leading company in Sweden interms of MRO work and with the constant development of equipment, more and more risks are discovered that require analysis and minimization. Research has previously been done on how fixture design can be improved ergonomically using virtual environment technology. This is to be able to minimize design and manufacturing costs with regard to the iteration process. This in combination with studies done on musculoskeletal injuries with connections to the MRO industry highlights the need for risk analysis in the MRO industry. The work at STEAS consists of performing risk analysis from a technical, ergonomic and financial perspective on their moving fixtures and chemical processes so that STEAS can then check for possible costs and implement the recommended measures. The analysis methods used are a PHL (Preliminary Hazard List), FMEA (Failure Modes and Effects Analysis) and an ACHB analysis (Accidental Cost & Hypothetical Benefit) MRO Risk Analysis Risk Identification Risk Management Maintenance Assembly Jigs Accidents Proactive Risk Analysis FMEA PHL PHA ACHB RPN SWOT OEM AFS Airbus Boeing Rolls Royce General Electrics Inlet Cowl Fan Cowl Exhaust Thrust Reverser MRO Riskanalys Riskidentifiering Riskhantering Underhåll Rörliga Fixturer Olyckor Proaktiv riskanalys FMEA PHL PHA ACHB RPN SWOT OEM AFS Airbus Boeing Rolls Royce General Electrics Inlet Cowl Fan Cowl Exhaust Thrust Reverser Engineering and Technology Teknik och teknologier
30	論美歐大型民用航空器補貼案-以歐盟補貼案為研究中心陳靜儀 Unknown Date (has links) 美國與歐盟在航空產業的補貼爭議已有數十年之久，雙方互相指控對方補貼其國內民用航空器製造業，此一爭議雖經雙方談判協商，但終究談判破裂而進入世界貿易組織（WTO）爭端解決機構，成為WTO歷史上涉案金額最大的一次貿易糾紛案。雖然美國與歐盟就航空器補貼爭議相互於WTO下提出訴訟，總計成立了四個爭端案件，在如此複雜的情況下，目前僅歐盟航空補貼案（DS316）已進入至言詞辯論程序，其他爭議案均未進入實質審理程序，尚無資料可得分析，因此僅就DS316一案而為討論。 / 在該案中，美方指控歐盟以開發補助、基礎設施、研發技術補助等措施為空中巴士進行補貼，提升空中巴士之市場競爭力，對美國波音公司產生不良影響。上述措施是否違反WTO規定，著實進一步分析探討之必要，因此本文將介紹補貼及民用航空器的相關規定，由SCM協定下之補貼構成要件－政府財務補助、利益及特定性之要件，判斷歐盟是否構成補貼，而其中尚須檢驗美國與歐盟首次書狀中論點之合理性、考量過去小組類似判斷之見解與顧及1992年美歐航空器的雙邊協定，最後嘗試預測未來小組判斷中，對補貼之構成與否及其法律效果之意見。 / Subsidy dispute of aviation between the US and EU has been lasting over the past decades. Both sides accused each other of subsidizing domestic civil aircraft industry. In spite of having made efforts to solve the trade clash through negotiations, they eventually took the subsidy dispute before Dispute Settlement Body of the World Trade Organization（WTO） after the negotiations had failed. In the biggest case ever to come before WTO, US and EU separately filed legal complaints against each other at the WTO, which set up four dispute cases. However, except the oral arguments were held in the European Communities-Measures Affecting Trade in Large Civil Aircraft（DS316）, the three other cases have not yet entered into substantial procedures. Therefore, this thesis intends to focus on the DS316 due to no related data available to analyze the rest of the cases. / In DS316, the US argued that EU subsidized Airbus by way of such measures as Launch Aid, Infrastructure & Regional Aid and Research & Technology to improve Airbus’s competitiveness in the aviation market and put its US rival Boeing at disadvantage. Given that whether the EU subsides are against the trade rules of the WTO needs further studies, this thesis would like to interpret related rules which regulate subsidy and civil aircraft industry. It would also like to decide if the EU involved in subsidizing by examining the constitutive requirements of subsidy under the Agreement on Subsidies and Countervailing Measures（SCM agreement）including financial contribution, benefit and specificity. This thesis will review the rationality of arguments in the first written submissions both by the US and EU, and then deliberate the opinions of similar decisions from the WTO panel in the past as well as take into account the Agreement between the European Economic Community and the Government of the United States of America concerning the Application of the GATT Agreement on Trade in Civil Aircraft on Trade in Large Civil Aircraft in 1992. Finally, this article tries to forecast the opinions about what is regarded as subsidy and the related legal effects in future decisions by the WTO panel. 補貼補貼及平衡措施協定波音空中巴士 1992年美歐大型民用航空器協定 Subsidy Boeing Airbus

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