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engines</title> <meta name="description" content="Search results for: aircraft engines"> <meta name="keywords" content="aircraft engines"> <meta name="viewport" content="width=device-width, initial-scale=1, minimum-scale=1, maximum-scale=1, user-scalable=no"> <meta charset="utf-8"> <link href="https://cdn.waset.org/favicon.ico" type="image/x-icon" rel="shortcut icon"> <link href="https://cdn.waset.org/static/plugins/bootstrap-4.2.1/css/bootstrap.min.css" rel="stylesheet"> <link href="https://cdn.waset.org/static/plugins/fontawesome/css/all.min.css" rel="stylesheet"> <link href="https://cdn.waset.org/static/css/site.css?v=150220211555" rel="stylesheet"> </head> <body> <header> <div class="container"> <nav class="navbar navbar-expand-lg navbar-light"> <a class="navbar-brand" href="https://waset.org"> <img src="https://cdn.waset.org/static/images/wasetc.png" alt="Open Science Research Excellence" title="Open Science Research Excellence" /> </a> <button class="d-block d-lg-none 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action="https://publications.waset.org/abstracts/search"> <div id="custom-search-input"> <div class="input-group"> <i class="fas fa-search"></i> <input type="text" class="search-query" name="q" placeholder="Author, Title, Abstract, Keywords" value="aircraft engines"> <input type="submit" class="btn_search" value="Search"> </div> </div> </form> </div> </div> <div class="row mt-3"> <div class="col-sm-3"> <div class="card"> <div class="card-body"><strong>Commenced</strong> in January 2007</div> </div> </div> <div class="col-sm-3"> <div class="card"> <div class="card-body"><strong>Frequency:</strong> Monthly</div> </div> </div> <div class="col-sm-3"> <div class="card"> <div class="card-body"><strong>Edition:</strong> International</div> </div> </div> <div class="col-sm-3"> <div class="card"> <div class="card-body"><strong>Paper Count:</strong> 781</div> </div> </div> </div> <h1 class="mt-3 mb-3 text-center" style="font-size:1.6rem;">Search results for: aircraft engines</h1> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">781</span> Applications for Additive Manufacturing Technology for Reducing the Weight of Body Parts of Gas Turbine Engines</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Liubov%20Magerramova">Liubov Magerramova</a>, <a href="https://publications.waset.org/abstracts/search?q=Mikhail%20Petrov"> Mikhail Petrov</a>, <a href="https://publications.waset.org/abstracts/search?q=Vladimir%20Isakov"> Vladimir Isakov</a>, <a href="https://publications.waset.org/abstracts/search?q=Liana%20Shcherbinina"> Liana Shcherbinina</a>, <a href="https://publications.waset.org/abstracts/search?q=Suren%20Gukasyan"> Suren Gukasyan</a>, <a href="https://publications.waset.org/abstracts/search?q=Daniil%20Povalyukhin"> Daniil Povalyukhin</a>, <a href="https://publications.waset.org/abstracts/search?q=Olga%20Klimova-Korsmik"> Olga Klimova-Korsmik</a>, <a href="https://publications.waset.org/abstracts/search?q=Darya%20Volosevich"> Darya Volosevich</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Aircraft engines are developing along the path of increasing resource, strength, reliability, and safety. The building of gas turbine engine body parts is a complex design and technological task. Particularly complex in the design and manufacturing are the casings of the input stages of helicopter gearboxes and central drives of aircraft engines. Traditional technologies, such as precision casting or isothermal forging, are characterized by significant limitations in parts production. For parts like housing, additive technologies guarantee spatial freedom and limitless or flexible design. This article presents the results of computational and experimental studies. These investigations justify the applicability of additive technologies (AT) to reduce the weight of aircraft housing gearbox parts by up to 32%. This is possible due to geometrical optimization compared to the classical, less flexible manufacturing methods and as-casted aircraft parts with over-insured values of safety factors. Using an example of the body of the input stage of an aircraft gearbox, visualization of the layer-by-layer manufacturing of a part based on thermal deformation was demonstrated. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=additive%20technologies" title="additive technologies">additive technologies</a>, <a href="https://publications.waset.org/abstracts/search?q=gas%20turbine%20engines" title=" gas turbine engines"> gas turbine engines</a>, <a href="https://publications.waset.org/abstracts/search?q=topological%20optimization" title=" topological optimization"> topological optimization</a>, <a href="https://publications.waset.org/abstracts/search?q=synthesis%20process" title=" synthesis process"> synthesis process</a> </p> <a href="https://publications.waset.org/abstracts/163290/applications-for-additive-manufacturing-technology-for-reducing-the-weight-of-body-parts-of-gas-turbine-engines" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/163290.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">116</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">780</span> Proposal of Innovative Risk Assessment of Ergonomic Factors in the Production of Jet Engines Using AHP (Analytic Hierarchy Process)</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Jose%20Cristiano%20Pereira">Jose Cristiano Pereira</a>, <a href="https://publications.waset.org/abstracts/search?q=Gilson%20Brito%20Alves%20Lima"> Gilson Brito Alves Lima</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Ergonomics is a key factor affecting the operational safety and quality in the aircraft engine manufacturing industry and evidence shows that the lack of attention to it can increase the risk of accidents. In order to emphasize the importance of ergonomics, this paper systematically reviews the critical processes used in the aircraft engine production industry with focus on the ergonomic factors. about the subject to identify key ergonomic factors. Experts validated the factors and used AHP to rank the factors in order of significance. From the six key risk factors identified, the ones with the highest weight are psychological demand followed by understanding of operational side. These factors suggest that measures must be taken to improve ergonomic factors, quality and safety in the manufacturing of aircraft engines. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=ergonomics" title="ergonomics">ergonomics</a>, <a href="https://publications.waset.org/abstracts/search?q=safety" title=" safety"> safety</a>, <a href="https://publications.waset.org/abstracts/search?q=aviation" title=" aviation"> aviation</a>, <a href="https://publications.waset.org/abstracts/search?q=aircraft%20engine%20production" title=" aircraft engine production"> aircraft engine production</a> </p> <a href="https://publications.waset.org/abstracts/53194/proposal-of-innovative-risk-assessment-of-ergonomic-factors-in-the-production-of-jet-engines-using-ahp-analytic-hierarchy-process" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/53194.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">315</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">779</span> Technical Specifications of Bombardier Challenger 605 SN 5769 Aircraft</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Rohan%20Sarker">Rohan Sarker</a>, <a href="https://publications.waset.org/abstracts/search?q=Jon%20P.%20Conlon"> Jon P. Conlon</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The Bombardier Challenger 605 SN 5769 is a versatile business jet known for its superior range, advanced avionics, and spacious cabin. Powered by two General Electric CF34-3B engines, each producing 8,729 pounds of thrust, the aircraft offers a maximum range of 4,000 nautical miles, allowing for non-stop transcontinental flights. It operates at a maximum cruising speed of Mach 0.82 (541 mph) and a service ceiling of 41,000 feet, ensuring efficient, high-altitude travel. The aircraft’s avionics suite is equipped with the Rockwell Collins Pro Line 21, offering advanced navigation, communication, and weather systems. The cockpit features dual Flight Management Systems (FMS) and GPS to enhance operational safety and precision. Inside, the Challenger 605 boasts a luxurious and customizable cabin that accommodates up to 12 passengers. The aircraft also provides ample baggage space, excellent short-field performance, and impressive fuel efficiency, making it ideal for business or personal long-range travel. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aircraft" title="aircraft">aircraft</a>, <a href="https://publications.waset.org/abstracts/search?q=airframe" title=" airframe"> airframe</a>, <a href="https://publications.waset.org/abstracts/search?q=Bombardier" title=" Bombardier"> Bombardier</a>, <a href="https://publications.waset.org/abstracts/search?q=engines" title=" engines"> engines</a> </p> <a href="https://publications.waset.org/abstracts/191255/technical-specifications-of-bombardier-challenger-605-sn-5769-aircraft" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/191255.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">28</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">778</span> Six-Phase Tooth-Coil Winding Starter-Generator Embedded in Aerospace Engine</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Flur%20R.%20Ismagilov">Flur R. Ismagilov</a>, <a href="https://publications.waset.org/abstracts/search?q=Vyacheslav%20E.%20Vavilov"> Vyacheslav E. Vavilov</a>, <a href="https://publications.waset.org/abstracts/search?q=Denis%20V.%20Gusakov"> Denis V. Gusakov</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This paper is devoted to solve the problem of increasing the electrification of aircraft engines by installing a synchronous generator at high pressure shaft. Technical solution of this problem by various research centers is discussed. A design solution of the problem was proposed. To evaluate the effectiveness of the proposed cooling system, thermal analysis was carried out in ANSYS software. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=starter-generator" title="starter-generator">starter-generator</a>, <a href="https://publications.waset.org/abstracts/search?q=more%20electrical%20engine" title=" more electrical engine"> more electrical engine</a>, <a href="https://publications.waset.org/abstracts/search?q=aircraft%20engines" title=" aircraft engines"> aircraft engines</a>, <a href="https://publications.waset.org/abstracts/search?q=high%20pressure%20shaft" title=" high pressure shaft"> high pressure shaft</a>, <a href="https://publications.waset.org/abstracts/search?q=synchronous%20generator" title=" synchronous generator"> synchronous generator</a> </p> <a href="https://publications.waset.org/abstracts/57565/six-phase-tooth-coil-winding-starter-generator-embedded-in-aerospace-engine" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/57565.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">257</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">777</span> Detectability of Malfunction in Turboprop Engine</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Tomas%20Vampola">Tomas Vampola</a>, <a href="https://publications.waset.org/abstracts/search?q=Michael%20Val%C3%A1%C5%A1ek"> Michael Valášek</a> </p> <p class="card-text"><strong>Abstract:</strong></p> On the basis of simulation-generated failure states of structural elements of a turboprop engine suitable for the busy-jet class of aircraft, an algorithm for early prediction of damage or reduction in functionality of structural elements of the engine is designed and verified with real data obtained at dynamometric testing facilities of aircraft engines. Based on an expanding database of experimentally determined data from temperature and pressure sensors during the operation of turboprop engines, this strategy is constantly modified with the aim of using the minimum number of sensors to detect an inadmissible or deteriorated operating mode of specific structural elements of an aircraft engine. The assembled algorithm for the early prediction of reduced functionality of the aircraft engine significantly contributes to the safety of air traffic and to a large extent, contributes to the economy of operation with positive effects on the reduction of the energy demand of operation and the elimination of adverse effects on the environment. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=detectability%20of%20malfunction" title="detectability of malfunction">detectability of malfunction</a>, <a href="https://publications.waset.org/abstracts/search?q=dynamometric%20testing" title=" dynamometric testing"> dynamometric testing</a>, <a href="https://publications.waset.org/abstracts/search?q=prediction%20of%20damage" title=" prediction of damage"> prediction of damage</a>, <a href="https://publications.waset.org/abstracts/search?q=turboprop%20engine" title=" turboprop engine"> turboprop engine</a> </p> <a href="https://publications.waset.org/abstracts/166484/detectability-of-malfunction-in-turboprop-engine" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/166484.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">94</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">776</span> Comprehensive Studies on the Aerodynamic Characteristics of Subsonic Scarf Inlets</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=M.%20Jegannath">M. Jegannath</a>, <a href="https://publications.waset.org/abstracts/search?q=V.%20Akshaya"> V. Akshaya</a>, <a href="https://publications.waset.org/abstracts/search?q=B.%20Arunkumar"> B. Arunkumar</a>, <a href="https://publications.waset.org/abstracts/search?q=G.%20Lakshmi%20Soundharya"> G. Lakshmi Soundharya</a>, <a href="https://publications.waset.org/abstracts/search?q=V.%20Thenmozhi"> V. Thenmozhi</a>, <a href="https://publications.waset.org/abstracts/search?q=S.%20Varun"> S. Varun</a>, <a href="https://publications.waset.org/abstracts/search?q=V.%20R.%20S.%20Kumar"> V. R. S. Kumar</a> </p> <p class="card-text"><strong>Abstract:</strong></p> For scarf inlet design, the primary variable of interest is the circumferential extent over which the extended lower lip is formed. In this paper, an attempt has been made to optimize the aerodynamic shape of a subsonic scarf inlet with aerodynamically shaped center-body with a particular value of the circumferential extent. The parametric analytical studies have been carried out using a Spalart-Allmaras turbulence model. From our preliminary studies, we concluded that for a particular value of circumferential extent, there will be an exact shape of the center-body with certain geometric orientation for the existence of an aerodynamically efficient scarf inlet for modern aircraft engines. This numerical study is a pointer towards for the design optimization of scarf inlets for modern aircraft engines. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aerodynamics%20of%20scarf%20inlets" title="aerodynamics of scarf inlets">aerodynamics of scarf inlets</a>, <a href="https://publications.waset.org/abstracts/search?q=inlet%20design" title=" inlet design"> inlet design</a>, <a href="https://publications.waset.org/abstracts/search?q=modern%20aircraft%20inlets" title=" modern aircraft inlets"> modern aircraft inlets</a>, <a href="https://publications.waset.org/abstracts/search?q=subsonic%20scarf%20inlet" title=" subsonic scarf inlet"> subsonic scarf inlet</a> </p> <a href="https://publications.waset.org/abstracts/77913/comprehensive-studies-on-the-aerodynamic-characteristics-of-subsonic-scarf-inlets" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/77913.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">317</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">775</span> Bench Tests of Two-Stroke Opposed Piston Aircraft Diesel Engine under Propeller Characteristics Conditions</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=A.%20Majczak">A. Majczak</a>, <a href="https://publications.waset.org/abstracts/search?q=G.%20Baranski"> G. Baranski</a>, <a href="https://publications.waset.org/abstracts/search?q=K.%20Pietrykowski"> K. Pietrykowski</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Due to the growing popularity of light aircraft, it has become necessary to develop aircraft engines for this type of construction. One of engine system, designed to increase efficiency and reduce weight, is the engine with opposed pistons. In such an engine, the combustion chamber is formed by two pistons moving in one cylinder. Therefore, this type of engines run in a two-stroke cycle, so they have many advantages such as high power and torque, high efficiency, or a favorable power-to-weight ratio. Tests of one of the available aircraft engines with opposing piston system fueled with diesel oil were carried out on an engine dynamometer equipped with an eddy current brake and the necessary measuring and testing equipment. In order to get to know the basic parameters of the engine, the tests were carried out under partial load conditions for the following torque values: 40, 60, 80, 100 Nm. The rotational speed was changed from 1600 to 2500 rpm. Measurements were also taken for designated points of propeller characteristics. During the tests, the engine torque, engine power, fuel consumption, intake manifold pressure, and oil pressure were recorded. On the basis of the measurements carried out for particular loads, the power curve, hourly and specific fuel consumption curves were determined. Characteristics of charge pressure as a function of rotational speed as well as power, torque, hourly and specific fuel consumption curves for propeller characteristics were also prepared. The obtained characteristics make it possible to select the optimal points of engine operation. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aircraft" title="aircraft">aircraft</a>, <a href="https://publications.waset.org/abstracts/search?q=diesel" title=" diesel"> diesel</a>, <a href="https://publications.waset.org/abstracts/search?q=engine%20testing" title=" engine testing"> engine testing</a>, <a href="https://publications.waset.org/abstracts/search?q=opposed%20piston" title=" opposed piston"> opposed piston</a> </p> <a href="https://publications.waset.org/abstracts/106614/bench-tests-of-two-stroke-opposed-piston-aircraft-diesel-engine-under-propeller-characteristics-conditions" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/106614.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">154</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">774</span> Design & Development of a Static-Thrust Test-Bench for Aviation/UAV Based Piston Engines</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Syed%20Muhammad%20Basit%20Ali">Syed Muhammad Basit Ali</a>, <a href="https://publications.waset.org/abstracts/search?q=Usama%20Saleem"> Usama Saleem</a>, <a href="https://publications.waset.org/abstracts/search?q=Irtiza%20Ali"> Irtiza Ali</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Internal combustion engines have been pioneers in the aviation industry, use of piston engines for aircraft propulsion, from propeller-driven bi-planes to turbo-prop, commercial, and cargo airliners. To provide an adequate amount of thrust piston engine rotates the propeller at a specific rpm, allowing enough mass airflow. Thrust is the only forward-acting force of an aircraft that helps heavier than air bodies to fly, depending on the mathematical model and variables included in that with the correct measurement. Test-benches have been a bench-mark in the aerospace industry to analyse the results before a flight, having paramount significance in reliability and safety engineering, depending on the mathematical model and variables included in that with the correct measurement. Calculation of thrust from a piston engine also depends on environmental changes, the diameter of the propeller, and the density of air. The project would be centered on piston engines used in the aviation industry for light aircraft and UAVs. A static thrust test bench involves various units, each performing a designed purpose to monitor and display. Static thrust tests are performed on the ground, and safety concerns hold paramount importance. The execution of this study involves research, design, manufacturing, and results based on reverse engineering initiating from virtual design, analytical analysis, and simulations. The final evaluation of results gathered from various methods such as co-relation between conventional mass-spring and digital loadcell. On average, we received 17.5kg of thrust (25+ engine run-ups – around 40 hours of engine run), only 10% deviation from analytically calculated thrust –providing 90% accuracy. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aviation" title="aviation">aviation</a>, <a href="https://publications.waset.org/abstracts/search?q=aeronautics" title=" aeronautics"> aeronautics</a>, <a href="https://publications.waset.org/abstracts/search?q=static%20thrust" title=" static thrust"> static thrust</a>, <a href="https://publications.waset.org/abstracts/search?q=test%20bench" title=" test bench"> test bench</a>, <a href="https://publications.waset.org/abstracts/search?q=aircraft%20maintenance" title=" aircraft maintenance"> aircraft maintenance</a> </p> <a href="https://publications.waset.org/abstracts/140749/design-development-of-a-static-thrust-test-bench-for-aviationuav-based-piston-engines" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/140749.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">413</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">773</span> Penetration Analysis for Composites Applicable to Military Vehicle Armors, Aircraft Engines and Nuclear Power Plant Structures</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Dong%20Wook%20Lee">Dong Wook Lee</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This paper describes a method for analyzing penetration for composite material using an explicit nonlinear Finite Element Analysis (FEA). This method may be used in the early stage of design for the protection of military vehicles, aircraft engines and nuclear power plant structures made of composite materials. This paper deals with simple ballistic penetration tests for composite materials and the FEA modeling method and results. The FEA was performed to interpret the ballistic field test phenomenon regarding the damage propagation in the structure subjected to local foreign object impact. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=computer%20aided%20engineering" title="computer aided engineering">computer aided engineering</a>, <a href="https://publications.waset.org/abstracts/search?q=finite%20element%20analysis" title=" finite element analysis"> finite element analysis</a>, <a href="https://publications.waset.org/abstracts/search?q=impact%20analysis" title=" impact analysis"> impact analysis</a>, <a href="https://publications.waset.org/abstracts/search?q=penetration%20analysis" title=" penetration analysis"> penetration analysis</a>, <a href="https://publications.waset.org/abstracts/search?q=composite%20material" title=" composite material"> composite material</a> </p> <a href="https://publications.waset.org/abstracts/133472/penetration-analysis-for-composites-applicable-to-military-vehicle-armors-aircraft-engines-and-nuclear-power-plant-structures" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/133472.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">123</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">772</span> [Keynote Speech]: Conceptual Design of a Short Take-Off and Landing (STOL) Light Sport Aircraft</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Zamri%20Omar">Zamri Omar</a>, <a href="https://publications.waset.org/abstracts/search?q=Alifi%20Zainal%20Abidin"> Alifi Zainal Abidin</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Although flying machines have made their tremendous technological advancement since the first successfully flight of the heavier-than-air aircraft, its benefits to the greater community are still belittled. One of the reasons for this drawback is due to the relatively high cost needed to fly on the typical light aircraft. A smaller and lighter plane, widely known as Light Sport Aircraft (LSA) has the potential to attract more people to actively participate in numerous flying activities, such as for recreational, business trips or other personal purposes. In this paper, we propose a new LSA design with some simple, yet important analysis required in the aircraft conceptual design stage. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=light%20sport%20aircraft" title="light sport aircraft">light sport aircraft</a>, <a href="https://publications.waset.org/abstracts/search?q=conceptual%20design" title=" conceptual design"> conceptual design</a>, <a href="https://publications.waset.org/abstracts/search?q=aircraft%20layout" title=" aircraft layout"> aircraft layout</a>, <a href="https://publications.waset.org/abstracts/search?q=aircraft" title=" aircraft"> aircraft</a> </p> <a href="https://publications.waset.org/abstracts/63570/keynote-speech-conceptual-design-of-a-short-take-off-and-landing-stol-light-sport-aircraft" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/63570.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">346</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">771</span> Design Improvement of Aircraft Turbofan Engine Following Bird Ingestion Testing</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Ahmed%20H.%20Elkholy">Ahmed H. Elkholy</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Aircraft gas turbine engines are subject to damage by airborne foreign objects such as birds and garbage dumps. In order to assess their effect on engine performance, a complete foreign object damage (FOD) test was carried out and a component failure analysis was used to verify airworthiness standards (AWS) requirements for engine certification as set by international regulations. Ingestion damage due to 1.8 Kg (4 lb.) bird strike on an engine is presented in some detail. Based on the observed damage, improvements to the engine design were suggested in two different locations: the front bearing housing and the low compressor shaft. When these improvements were implemented, the engine showed an acceptable containment capability that meets AWS requirements. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aircraft%20engine" title="aircraft engine">aircraft engine</a>, <a href="https://publications.waset.org/abstracts/search?q=airworthiness%20standards" title=" airworthiness standards"> airworthiness standards</a>, <a href="https://publications.waset.org/abstracts/search?q=bird%20ingestion" title=" bird ingestion"> bird ingestion</a>, <a href="https://publications.waset.org/abstracts/search?q=foreign%20object%20damage" title=" foreign object damage"> foreign object damage</a> </p> <a href="https://publications.waset.org/abstracts/31666/design-improvement-of-aircraft-turbofan-engine-following-bird-ingestion-testing" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/31666.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">421</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">770</span> Computational Analysis of Adaptable Winglets for Improved Morphing Aircraft Performance </h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Erdogan%20Kaygan">Erdogan Kaygan</a>, <a href="https://publications.waset.org/abstracts/search?q=Alvin%20Gatto"> Alvin Gatto</a> </p> <p class="card-text"><strong>Abstract:</strong></p> An investigation of adaptable winglets for enhancing morphing aircraft performance is described in this paper. The concepts investigated consist of various winglet configurations fundamentally centered on a baseline swept wing. The impetus for the work was to identify and optimize winglets to enhance the aerodynamic efficiency of a morphing aircraft. All computations were performed with Athena Vortex Lattice modelling with varying degrees of twist and cant angle considered. The results from this work indicate that if adaptable winglets were employed on aircraft’s improvements in aircraft performance could be achieved. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aircraft" title="aircraft">aircraft</a>, <a href="https://publications.waset.org/abstracts/search?q=drag" title=" drag"> drag</a>, <a href="https://publications.waset.org/abstracts/search?q=twist" title=" twist"> twist</a>, <a href="https://publications.waset.org/abstracts/search?q=winglet" title=" winglet"> winglet</a> </p> <a href="https://publications.waset.org/abstracts/32680/computational-analysis-of-adaptable-winglets-for-improved-morphing-aircraft-performance" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/32680.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">584</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">769</span> Reducing Weight and Fuel Consumption of Civil Aircraft by EML</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Luca%20Bertola">Luca Bertola</a>, <a href="https://publications.waset.org/abstracts/search?q=Tom%20Cox"> Tom Cox</a>, <a href="https://publications.waset.org/abstracts/search?q=Pat%20Wheeler"> Pat Wheeler</a>, <a href="https://publications.waset.org/abstracts/search?q=Seamus%20Garvey"> Seamus Garvey</a>, <a href="https://publications.waset.org/abstracts/search?q=Herve%20Morvan"> Herve Morvan</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Electromagnetic launch systems have been proposed for military applications to accelerate jet planes on aircraft carriers. This paper proposes the implementation of similar technology to aid civil aircraft take-off, which can provide significant economic, environmental and technical benefits. Assisted launch has the potential of reducing ground noise and emissions near airports and improving overall aircraft efficiency through reducing engine thrust requirements. This paper presents a take-off performance analysis for an Airbus A320-200 taking off with and without the assistance of the electromagnetic catapult. Assisted take-off allows for a significant reduction in take-off field length, giving more capacity with existing airport footprints and reducing the necessary footprint of new airports, which will both reduce costs and increase the number of suitable sites. The electromagnetic catapult may allow the installation of smaller engines with lower rated thrust. The consequent fuel consumption and operational cost reduction are estimated. The potential of reducing the aircraft operational costs and the runway length required making electromagnetic launch system an attractive solution to the air traffic growth in busy airports. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=electromagnetic%20launch" title="electromagnetic launch">electromagnetic launch</a>, <a href="https://publications.waset.org/abstracts/search?q=fuel%20consumption" title=" fuel consumption"> fuel consumption</a>, <a href="https://publications.waset.org/abstracts/search?q=take-off%20analysis" title=" take-off analysis"> take-off analysis</a>, <a href="https://publications.waset.org/abstracts/search?q=weight%20reduction" title=" weight reduction"> weight reduction</a> </p> <a href="https://publications.waset.org/abstracts/56488/reducing-weight-and-fuel-consumption-of-civil-aircraft-by-eml" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/56488.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">332</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">768</span> Simulation Research of Innovative Ignition System of ASz62IR Radial Aircraft Engine</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Miroslaw%20Wendeker">Miroslaw Wendeker</a>, <a href="https://publications.waset.org/abstracts/search?q=Piotr%20Kacejko"> Piotr Kacejko</a>, <a href="https://publications.waset.org/abstracts/search?q=Mariusz%20Duk"> Mariusz Duk</a>, <a href="https://publications.waset.org/abstracts/search?q=Pawel%20Karpinski"> Pawel Karpinski</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The research in the field of aircraft internal combustion engines is currently driven by the needs of decreasing fuel consumption and CO2 emissions, while fulfilling the level of safety. Currently, reciprocating aircraft engines are found in sports, emergency, agricultural and recreation aviation. Technically, they are most at a pre-war knowledge of the theory of operation, design and manufacturing technology, especially if compared to that high level of development of automotive engines. Typically, these engines are driven by carburetors of a quite primitive construction. At present, due to environmental requirements and dealing with a climate change, it is beneficial to develop aircraft piston engines and adopt the achievements of automotive engineering such as computer-controlled low-pressure injection, electronic ignition control and biofuels. The paper describes simulation research of the innovative power and control systems for the aircraft radial engine of high power. Installing an electronic ignition system in the radial aircraft engine is a fundamental innovative idea of this solution. Consequently, the required level of safety and better functionality as compared to the today’s plug system can be guaranteed. In this framework, this research work focuses on describing a methodology for optimizing the electronically controlled ignition system. This attempt can reduce emissions of toxic compounds as a result of lowered fuel consumption, optimized combustion and engine capability of efficient combustion of ecological fuels. New, redundant elements of the control system can improve the safety of aircraft. Consequently, the required level of safety and better functionality as compared to the today’s plug system can be guaranteed. The simulation research aimed to determine the vulnerability of the values measured (they were planned as the quantities measured by the measurement systems) to determining the optimal ignition angle (the angle of maximum torque at a given operating point). The described results covered: a) research in steady states; b) velocity ranging from 1500 to 2200 rpm (every 100 rpm); c) loading ranging from propeller power to maximum power; d) altitude ranging according to the International Standard Atmosphere from 0 to 8000 m (every 1000 m); e) fuel: automotive gasoline ES95. The three models of different types of ignition coil (different energy discharge) were studied. The analysis aimed at the optimization of the design of the innovative ignition system for an aircraft engine. The optimization involved: a) the optimization of the measurement systems; b) the optimization of actuator systems. The studies enabled the research on the vulnerability of the signals to the control of the ignition timing. Accordingly, the number and type of sensors were determined for the ignition system to achieve its optimal performance. The results confirmed the limited benefits, in terms of fuel consumption. Thus, including spark management in the optimization is mandatory to significantly decrease the fuel consumption. This work has been financed by the Polish National Centre for Research and Development, INNOLOT, under Grant Agreement No. INNOLOT/I/1/NCBR/2013. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=piston%20engine" title="piston engine">piston engine</a>, <a href="https://publications.waset.org/abstracts/search?q=radial%20engine" title=" radial engine"> radial engine</a>, <a href="https://publications.waset.org/abstracts/search?q=ignition%20system" title=" ignition system"> ignition system</a>, <a href="https://publications.waset.org/abstracts/search?q=CFD%20model" title=" CFD model"> CFD model</a>, <a href="https://publications.waset.org/abstracts/search?q=engine%20optimization" title=" engine optimization"> engine optimization</a> </p> <a href="https://publications.waset.org/abstracts/50112/simulation-research-of-innovative-ignition-system-of-asz62ir-radial-aircraft-engine" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/50112.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">386</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">767</span> Survivability of Maneuvering Aircraft against Air to Air Infrared Missile</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Ji-Yeul%20Bae">Ji-Yeul Bae</a>, <a href="https://publications.waset.org/abstracts/search?q=Hyung%20Mo%20Bae"> Hyung Mo Bae</a>, <a href="https://publications.waset.org/abstracts/search?q=Jihyuk%20Kim"> Jihyuk Kim</a>, <a href="https://publications.waset.org/abstracts/search?q=Hyung%20Hee%20Cho"> Hyung Hee Cho</a> </p> <p class="card-text"><strong>Abstract:</strong></p> An air to air infrared missile poses a significant threat to the survivability of an aircraft due to an advanced sensitivity of sensor and maneuverability of the missile. Therefore, recent military aircraft is equipped with MAW (Missile Approach Warning) to take an evasive maneuver and to deploy countermeasures like chaff and flare. In this research, an effect of MAW sensitivity and resulting evasive maneuver on the survivability of the fighter aircraft is studied. A single engine fighter jet with Mach 0.9 flying at an altitude of 5 km is modeled in the research and infrared signature of the aircraft is calculated by numerical simulation. The survivability is assessed in terms of lethal range. The MAW sensitivity and maneuverability of an aircraft is used as variables. The result showed that improvement in survivability mainly achieved when the missile approach from the side of the aircraft. And maximum 30% increase in survivability of the aircraft is achieved when existence of the missile is noticed at 7 km distance. As a conclusion, sensitivity of the MAW seems to be more important factor than the maneuverability of the aircraft in terms of the survivability. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=air%20to%20air%20missile" title="air to air missile">air to air missile</a>, <a href="https://publications.waset.org/abstracts/search?q=missile%20approach%20warning" title=" missile approach warning"> missile approach warning</a>, <a href="https://publications.waset.org/abstracts/search?q=lethal%20range" title=" lethal range"> lethal range</a>, <a href="https://publications.waset.org/abstracts/search?q=survivability" title=" survivability"> survivability</a> </p> <a href="https://publications.waset.org/abstracts/89381/survivability-of-maneuvering-aircraft-against-air-to-air-infrared-missile" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/89381.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">568</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">766</span> Double Layer Security Model for Identification Friend or Foe</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Buse%20T.%20Ayd%C4%B1n">Buse T. Aydın</a>, <a href="https://publications.waset.org/abstracts/search?q=Enver%20Ozdemir"> Enver Ozdemir</a> </p> <p class="card-text"><strong>Abstract:</strong></p> In this study, a double layer authentication scheme between the aircraft and the Air Traffic Control (ATC) tower is designed to prevent any unauthorized aircraft from introducing themselves as friends. The method is a combination of classical cryptographic methods and new generation physical layers. The first layer has employed the embedded key of the aircraft. The embedded key is assumed to installed during the construction of the utility. The other layer is a physical attribute (flight path, distance, etc.) between the aircraft and the ATC tower. We create a mathematical model so that two layers’ information is employed and an aircraft is authenticated as a friend or foe according to the accuracy of the results of the model. The results of the aircraft are compared with the results of the ATC tower and if the values found by the aircraft and ATC tower match within a certain error margin, we mark the aircraft as a friend. In this method, even if embedded key is captured by the enemy aircraft, without the information of the second layer, the enemy can easily be determined. Overall, in this work, we present a more reliable system by adding a physical layer in the authentication process. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=ADS-B" title="ADS-B">ADS-B</a>, <a href="https://publications.waset.org/abstracts/search?q=communication%20with%20physical%20layer%20security" title=" communication with physical layer security"> communication with physical layer security</a>, <a href="https://publications.waset.org/abstracts/search?q=cryptography" title=" cryptography"> cryptography</a>, <a href="https://publications.waset.org/abstracts/search?q=identification%20friend%20or%20foe" title=" identification friend or foe"> identification friend or foe</a> </p> <a href="https://publications.waset.org/abstracts/105521/double-layer-security-model-for-identification-friend-or-foe" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/105521.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">161</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">765</span> Simulations of NACA 65-415 and NACA 64-206 Airfoils Using Computational Fluid Dynamics</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=David%20Nagy">David Nagy</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This paper exemplifies the influence of the purpose of an aircraft on the aerodynamic properties of its airfoil. In particular, the research takes into consideration two types of aircraft, namely cargo aircraft and military high-speed aircraft and compares their airfoil characteristics using their NACA airfoils as well as computational fluid dynamics. The results show that airfoils of aircraft designed for cargo have a heavier focus on maintaining a large lift force whereas speed-oriented airplanes focus on minimizing the drag force. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aerodynamic%20simulation" title="aerodynamic simulation">aerodynamic simulation</a>, <a href="https://publications.waset.org/abstracts/search?q=aircraft" title=" aircraft"> aircraft</a>, <a href="https://publications.waset.org/abstracts/search?q=airfoil" title=" airfoil"> airfoil</a>, <a href="https://publications.waset.org/abstracts/search?q=computational%20fluid%20dynamics" title=" computational fluid dynamics"> computational fluid dynamics</a>, <a href="https://publications.waset.org/abstracts/search?q=lift%20to%20drag%20ratio" title=" lift to drag ratio"> lift to drag ratio</a>, <a href="https://publications.waset.org/abstracts/search?q=NACA%2064-206" title=" NACA 64-206"> NACA 64-206</a>, <a href="https://publications.waset.org/abstracts/search?q=NACA%2065-415" title=" NACA 65-415"> NACA 65-415</a> </p> <a href="https://publications.waset.org/abstracts/137836/simulations-of-naca-65-415-and-naca-64-206-airfoils-using-computational-fluid-dynamics" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/137836.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">388</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">764</span> Effects of Inlet Distorted Flows on the Performance of an Axial Compressor</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Asad%20Islam">Asad Islam</a>, <a href="https://publications.waset.org/abstracts/search?q=Khalid%20Parvez"> Khalid Parvez</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Compressor fans in modern aircraft engines are of considerate importance, as they provide majority of thrust required by the aircraft. Their challenging environment is frequently subjected to non-uniform inflow conditions. These conditions could be either due to the flight operating requirements such as take-off and landing, wake interference from aircraft fuselage or cross-flow wind conditions. So, in highly maneuverable flights regimes of fighter aircrafts affects the overall performance of an engine. Since the flow in compressor of an aircraft application is highly sensitive because of adverse pressure gradient due to different flow orientations of the aircraft. Therefore, it is prone to unstable operations. This paper presents the study that focuses on axial compressor response to inlet flow orientations for the range of angles as 0 to 15 degrees. For this purpose, NASA Rotor-37 was taken and CFD mesh was developed. The compressor characteristics map was generated for the design conditions of pressure ratio of 2.106 with the rotor operating at rotational velocity of 17188.7 rpm using CFD simulating environment of ANSYS-CFX®. The grid study was done to see the effects of mesh upon computational solution. Then, the mesh giving the best results, (when validated with the available experimental NASA’s results); was used for further distortion analysis. The flow in the inlet nozzle was given angle orientations ranging from 0 to 15 degrees. The CFD results are analyzed and discussed with respect to stall margin and flow separations due to induced distortions. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=axial%20compressor" title="axial compressor">axial compressor</a>, <a href="https://publications.waset.org/abstracts/search?q=distortions" title=" distortions"> distortions</a>, <a href="https://publications.waset.org/abstracts/search?q=angle" title=" angle"> angle</a>, <a href="https://publications.waset.org/abstracts/search?q=CFD" title=" CFD"> CFD</a>, <a href="https://publications.waset.org/abstracts/search?q=ANSYS-CFX%C2%AE" title=" ANSYS-CFX®"> ANSYS-CFX®</a>, <a href="https://publications.waset.org/abstracts/search?q=bladegen%C2%AE" title=" bladegen®"> bladegen®</a> </p> <a href="https://publications.waset.org/abstracts/46801/effects-of-inlet-distorted-flows-on-the-performance-of-an-axial-compressor" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/46801.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">456</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">763</span> Multi-Disciplinary Optimisation Methodology for Aircraft Load Prediction </h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Sudhir%20Kumar%20Tiwari">Sudhir Kumar Tiwari</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The paper demonstrates a methodology that can be used at an early design stage of any conventional aircraft. This research activity assesses the feasibility derivation of methodology for aircraft loads estimation during the various phases of design for a transport category aircraft by utilizing potential of using commercial finite element analysis software, which may drive significant time saving. Early Design phase have limited data and quick changing configuration results in handling of large number of load cases. It is useful to idealize the aircraft as a connection of beams, which can be very accurately modelled using finite element analysis (beam elements). This research explores the correct approach towards idealizing an aircraft using beam elements. FEM Techniques like inertia relief were studied for implementation during course of work. The correct boundary condition technique envisaged for generation of shear force, bending moment and torque diagrams for the aircraft. The possible applications of this approach are the aircraft design process, which have been investigated. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=multi-disciplinary%20optimization" title="multi-disciplinary optimization">multi-disciplinary optimization</a>, <a href="https://publications.waset.org/abstracts/search?q=aircraft%20load" title=" aircraft load"> aircraft load</a>, <a href="https://publications.waset.org/abstracts/search?q=finite%20element%20analysis" title=" finite element analysis"> finite element analysis</a>, <a href="https://publications.waset.org/abstracts/search?q=stick%20model" title=" stick model"> stick model</a> </p> <a href="https://publications.waset.org/abstracts/70989/multi-disciplinary-optimisation-methodology-for-aircraft-load-prediction" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/70989.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">352</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">762</span> Dynamic Determination of Spare Engine Requirements for Air Fighters Integrating Feedback of Operational Information </h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Tae%20Bo%20Jeon">Tae Bo Jeon</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Korean air force is undertaking a big project to replace prevailing hundreds of old air fighters such as F-4, F-5, KF-16 etc. The task is to develop and produce domestic fighters equipped with 2 complete-type engines each. A large number of engines, however, will be purchased as products from a foreign engine maker. In addition to the fighters themselves, secure the proper number of spare engines serves a significant role in maintaining combat readiness and effectively managing the national defense budget due to high cost. In this paper, we presented a model dynamically updating spare engine requirements. Currently, the military administration purchases all the fighters, engines, and spare engines at acquisition stage and does not have additional procurement processes during the life cycle, 30-40 years. With the assumption that procurement procedure during the operational stage is established, our model starts from the initial estimate of spare engine requirements based on limited information. The model then performs military missions and repair/maintenance works when necessary. During operation, detailed field information - aircraft repair and test, engine repair, planned maintenance, administration time, transportation pipeline between base, field, and depot etc., - should be considered for actual engine requirements. At the end of each year, the performance measure is recorded and proceeds to next year when it shows higher the threshold set. Otherwise, additional engine(s) will be bought and added to the current system. We repeat the process for the life cycle period and compare the results. The proposed model is seen to generate far better results appropriately adding spare engines thus avoiding possible undesirable situations. Our model may well be applied to future air force military operations. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=DMSMS" title="DMSMS">DMSMS</a>, <a href="https://publications.waset.org/abstracts/search?q=operational%20availability" title=" operational availability"> operational availability</a>, <a href="https://publications.waset.org/abstracts/search?q=METRIC" title=" METRIC"> METRIC</a>, <a href="https://publications.waset.org/abstracts/search?q=PRS" title=" PRS "> PRS </a> </p> <a href="https://publications.waset.org/abstracts/90277/dynamic-determination-of-spare-engine-requirements-for-air-fighters-integrating-feedback-of-operational-information" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/90277.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">172</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">761</span> Double Layer Security Authentication Model for Automatic Dependent Surveillance-Broadcast </h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Buse%20T.%20Aydin">Buse T. Aydin</a>, <a href="https://publications.waset.org/abstracts/search?q=Enver%20Ozdemir"> Enver Ozdemir</a> </p> <p class="card-text"><strong>Abstract:</strong></p> An automatic dependent surveillance-broadcast (ADS-B) system has serious security problems. In this study, a double layer authentication scheme between the aircraft and ground station, aircraft to aircraft, ground station to ATC tower is designed to prevent any unauthorized aircrafts from introducing themselves as friends. This method can be used as a solution to the problem of authentication. The method is a combination of classical cryptographic methods and new generation physical layers. The first layer has employed the embedded key of the aircraft. The embedded key is assumed to installed during the construction of the utility. The other layer is a physical attribute (flight path, distance, etc.) between the aircraft and the ATC tower. We create a mathematical model so that two layers’ information is employed and an aircraft is authenticated as a friend or unknown according to the accuracy of the results of the model. The results of the aircraft are compared with the results of the ATC tower and if the values found by the aircraft and ATC tower match within a certain error margin, we mark the aircraft as friend. As a result, the ADS-B messages coming from this authenticated friendly aircraft will be processed. In this method, even if the embedded key is captured by the unknown aircraft, without the information of the second layer, the unknown aircraft can easily be determined. Overall, in this work, we present a reliable system by adding physical layer in the authentication process. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=ADS-B" title="ADS-B">ADS-B</a>, <a href="https://publications.waset.org/abstracts/search?q=authentication" title=" authentication"> authentication</a>, <a href="https://publications.waset.org/abstracts/search?q=communication%20with%20physical%20layer%20security" title=" communication with physical layer security"> communication with physical layer security</a>, <a href="https://publications.waset.org/abstracts/search?q=cryptography" title=" cryptography"> cryptography</a>, <a href="https://publications.waset.org/abstracts/search?q=identification%20friend%20or%20foe" title=" identification friend or foe"> identification friend or foe</a> </p> <a href="https://publications.waset.org/abstracts/105990/double-layer-security-authentication-model-for-automatic-dependent-surveillance-broadcast" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/105990.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">179</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">760</span> Research of Stalled Operational Modes of Axial-Flow Compressor for Diagnostics of Pre-Surge State</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=F.%20Mohammadsadeghi">F. Mohammadsadeghi </a> </p> <p class="card-text"><strong>Abstract:</strong></p> Relevance of research: Axial compressors are used in both aircraft engine construction and ground-based gas turbine engines. The compressor is considered to be one of the main gas turbine engine units, which define absolute and relative indicators of engine in general. Failure of compressor often leads to drastic consequences. Therefore, safe (stable) operation must be maintained when using axial compressor. Currently, we can observe a tendency of increase of power unit, productivity, circumferential velocity and compression ratio of axial compressors in gas turbine engines of aircraft and ground-based application whereas metal consumption of their structure tends to fall. This causes the increase of dynamic loads as well as danger of damage of high load compressor or engine structure elements in general due to transient processes. In operating practices of aeronautical engineering and ground units with gas turbine drive the operational stability failure of gas turbine engines is one of relatively often failure causes what can lead to emergency situations. Surge occurrence is considered to be an absolute buckling failure. This is one of the most dangerous and often occurring types of instability. However detailed were the researches of this phenomenon the development of measures for surge before-the-fact prevention is still relevant. This is why the research of transient processes for axial compressors is necessary in order to provide efficient, stable and secure operation. The paper addresses the problem of automatic control system improvement by integrating the anti-surge algorithms for axial compressor of aircraft gas turbine engine. Paper considers dynamic exhaustion of gas dynamic stability of compressor stage, results of numerical simulation of airflow flowing through the airfoil at design and stalling modes, experimental researches to form the criteria that identify the compressor state at pre-surge mode detection. Authors formulated basic ways for developing surge preventing systems, i.e. forming the algorithms that allow detecting the surge origination and the systems that implement the proposed algorithms. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=axial%20compressor" title="axial compressor">axial compressor</a>, <a href="https://publications.waset.org/abstracts/search?q=rotation%20stall" title=" rotation stall"> rotation stall</a>, <a href="https://publications.waset.org/abstracts/search?q=Surg" title=" Surg"> Surg</a>, <a href="https://publications.waset.org/abstracts/search?q=unstable%20operation%20of%20gas%20turbine%20engine" title=" unstable operation of gas turbine engine"> unstable operation of gas turbine engine</a> </p> <a href="https://publications.waset.org/abstracts/18711/research-of-stalled-operational-modes-of-axial-flow-compressor-for-diagnostics-of-pre-surge-state" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/18711.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">410</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">759</span> Hybrid Finite Element Analysis of Expansion Joints for Piping Systems in Aircraft Engine External Configurations and Nuclear Power Plants</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Dong%20Wook%20Lee">Dong Wook Lee</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This paper presents a method to analyze the stiffness of the expansion joint with structural support using a hybrid method combining computational and analytical methods. Many expansion joints found in tubes and ducts of mechanical structures are designed to absorb thermal expansion mismatch between their structural members and deal with misalignments introduced from the assembly/manufacturing processes. One of the important design perspectives is the system’s vibrational characteristics. We calculate the stiffness as a characterization parameter for structural joint systems using a combined Finite Element Analysis (FEA) and an analytical method. We apply the methods to two sample applications: external configurations of aircraft engines and nuclear power plant structures. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=expansion%20joint" title="expansion joint">expansion joint</a>, <a href="https://publications.waset.org/abstracts/search?q=expansion%20joint%20stiffness" title=" expansion joint stiffness"> expansion joint stiffness</a>, <a href="https://publications.waset.org/abstracts/search?q=finite%20element%20analysis" title=" finite element analysis"> finite element analysis</a>, <a href="https://publications.waset.org/abstracts/search?q=nuclear%20power%20plants" title=" nuclear power plants"> nuclear power plants</a>, <a href="https://publications.waset.org/abstracts/search?q=aircraft%20engine%20external%20configurations" title=" aircraft engine external configurations"> aircraft engine external configurations</a> </p> <a href="https://publications.waset.org/abstracts/133496/hybrid-finite-element-analysis-of-expansion-joints-for-piping-systems-in-aircraft-engine-external-configurations-and-nuclear-power-plants" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/133496.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">111</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">758</span> Vibration Energy Harvesting from Aircraft Structure Using Piezoelectric Transduction </h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=M.%20Saifudin%20Ahmed%20Atique">M. Saifudin Ahmed Atique</a>, <a href="https://publications.waset.org/abstracts/search?q=Santosh%20Paudyal"> Santosh Paudyal</a>, <a href="https://publications.waset.org/abstracts/search?q=Caixia%20Yang"> Caixia Yang</a> </p> <p class="card-text"><strong>Abstract:</strong></p> In an aircraft, a great portion of energy is wasted due to its inflight structural vibration. Structural components vibrate due to aeroelastic instabilities, gust perturbations and engine rotation at very high rpm. Energy losses due to mechanical vibration can be utilized by harvesting energy from aircraft structure as electrical energy. This harvested energy can be stored in battery panels built into aircraft fuselage and can be used to power inflight auxiliary accessories i.e., lighting and entertainment systems. Moreover, this power can be used for wireless Structural Health Monitoring System (SHM) for aircraft and as an excellent replacement of aircraft Ground Power Unit (GPU)/Auxiliary Power Unit (APU) during passenger onboard time to power aircraft cabin accessories to reduce aircraft ground operation cost significantly. In this paper, we propose the design of a noble aircraft wing in which Piezoelectric panels placed under the composite skin of aircraft wing will generate electrical charges from any inflight aerodynamics or mechanical vibration and store it into battery to power auxiliary inflight systems/accessories as per requirement. Experimental results show that a well-engineered piezoelectric energy harvester based aircraft wing can produce adequate energy to support in-flight lighting and auxiliary cabin accessories. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=vibration%20energy" title="vibration energy">vibration energy</a>, <a href="https://publications.waset.org/abstracts/search?q=aircraft%20wing" title=" aircraft wing"> aircraft wing</a>, <a href="https://publications.waset.org/abstracts/search?q=piezoelectric%20material" title=" piezoelectric material"> piezoelectric material</a>, <a href="https://publications.waset.org/abstracts/search?q=inflight%20accessories" title=" inflight accessories"> inflight accessories</a> </p> <a href="https://publications.waset.org/abstracts/111023/vibration-energy-harvesting-from-aircraft-structure-using-piezoelectric-transduction" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/111023.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">159</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">757</span> An A-Star Approach for the Quickest Path Problem with Time Windows</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Christofas%20Stergianos">Christofas Stergianos</a>, <a href="https://publications.waset.org/abstracts/search?q=Jason%20Atkin"> Jason Atkin</a>, <a href="https://publications.waset.org/abstracts/search?q=Herve%20Morvan"> Herve Morvan</a> </p> <p class="card-text"><strong>Abstract:</strong></p> As air traffic increases, more airports are interested in utilizing optimization methods. Many processes happen in parallel at an airport, and complex models are needed in order to have a reliable solution that can be implemented for ground movement operations. The ground movement for aircraft in an airport, allocating a path to each aircraft to follow in order to reach their destination (e.g. runway or gate), is one process that could be optimized. The Quickest Path Problem with Time Windows (QPPTW) algorithm has been developed to provide a conflict-free routing of vehicles and has been applied to routing aircraft around an airport. It was subsequently modified to increase the accuracy for airport applications. These modifications take into consideration specific characteristics of the problem, such as: the pushback process, which considers the extra time that is needed for pushing back an aircraft and turning its engines on; stand holding where any waiting should be allocated to the stand; and runway sequencing, where the sequence of the aircraft that take off is optimized and has to be respected. QPPTW involves searching for the quickest path by expanding the search in all directions, similarly to Dijkstra’s algorithm. Finding a way to direct the expansion can potentially assist the search and achieve a better performance. We have further modified the QPPTW algorithm to use a heuristic approach in order to guide the search. This new algorithm is based on the A-star search method but estimates the remaining time (instead of distance) in order to assess how far the target is. It is important to consider the remaining time that it is needed to reach the target, so that delays that are caused by other aircraft can be part of the optimization method. All of the other characteristics are still considered and time windows are still used in order to route multiple aircraft rather than a single aircraft. In this way the quickest path is found for each aircraft while taking into account the movements of the previously routed aircraft. After running experiments using a week of real aircraft data from Zurich Airport, the new algorithm (A-star QPPTW) was found to route aircraft much more quickly, being especially fast in routing the departing aircraft where pushback delays are significant. On average A-star QPPTW could route a full day (755 to 837 aircraft movements) 56% faster than the original algorithm. In total the routing of a full week of aircraft took only 12 seconds with the new algorithm, 15 seconds faster than the original algorithm. For real time application, the algorithm needs to be very fast, and this speed increase will allow us to add additional features and complexity, allowing further integration with other processes in airports and leading to more optimized and environmentally friendly airports. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=a-star%20search" title="a-star search">a-star search</a>, <a href="https://publications.waset.org/abstracts/search?q=airport%20operations" title=" airport operations"> airport operations</a>, <a href="https://publications.waset.org/abstracts/search?q=ground%20movement%20optimization" title=" ground movement optimization"> ground movement optimization</a>, <a href="https://publications.waset.org/abstracts/search?q=routing%20and%20scheduling" title=" routing and scheduling"> routing and scheduling</a> </p> <a href="https://publications.waset.org/abstracts/55803/an-a-star-approach-for-the-quickest-path-problem-with-time-windows" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/55803.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">231</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">756</span> Understanding Student Pilot Mental Workload in Recreational Aircraft Training</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Ron%20Bishop">Ron Bishop</a>, <a href="https://publications.waset.org/abstracts/search?q=Jim%20Mitchell"> Jim Mitchell</a>, <a href="https://publications.waset.org/abstracts/search?q=Talitha%20Best"> Talitha Best</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The increase in air travel worldwide has resulted in a pilot shortage. To increase student pilot capacity and lower costs, flight schools have increased the use of recreational aircraft (RA) with technological advanced cockpits in flight schools. The impact of RA based training compared to general aviation (GA) aircraft training on student mental workload is not well understood. This research investigated student pilot (N = 17) awareness of mental workload between technologically advanced cockpit equipped RA training with analogue gauge equipped GA training. The results showed a significantly higher rating of mental workload across subscales of mental and physical demand on the NASA-TLX in recreational aviation aircraft training compared to GA aircraft. Similarly, thematic content analysis of follow-up questions identified that mental workload of the student pilots flying the RA was perceived to be more than the GA aircraft. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=mental%20workload" title="mental workload">mental workload</a>, <a href="https://publications.waset.org/abstracts/search?q=recreational%20aircraft" title=" recreational aircraft"> recreational aircraft</a>, <a href="https://publications.waset.org/abstracts/search?q=student%20pilot" title=" student pilot"> student pilot</a>, <a href="https://publications.waset.org/abstracts/search?q=training" title=" training"> training</a> </p> <a href="https://publications.waset.org/abstracts/116045/understanding-student-pilot-mental-workload-in-recreational-aircraft-training" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/116045.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">156</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">755</span> Minimize Wear and Tear in Y12 Aircraft Tyres</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=N.%20D.%20Hiripitiya">N. D. Hiripitiya</a>, <a href="https://publications.waset.org/abstracts/search?q=H.%20V.%20H.%20De%20Soysa"> H. V. H. De Soysa</a>, <a href="https://publications.waset.org/abstracts/search?q=H.%20S.%20U.%20Thrimavithana"> H. S. U. Thrimavithana</a>, <a href="https://publications.waset.org/abstracts/search?q=B.%20R.%20Epitawala"> B. R. Epitawala</a>, <a href="https://publications.waset.org/abstracts/search?q=K.%20A.%20D.%20D.%20Kuruppu"> K. A. D. D. Kuruppu</a>, <a href="https://publications.waset.org/abstracts/search?q=D.%20J.%20K.%20Lokupathirage"> D. J. K. Lokupathirage</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This research was related to identify the reasons which lead for early wear and tear of aircraft tyres. Further this research focused to rectify those issues in tyres with some modifications. The aircraft tyres of Y12 aircraft was selected for the study as due to Y12 aircraft fly frequently. Self-structured questionnaire was prepared and it was distributed among Y12 aircraft technicians. Based on their feedback several issues were identified related to tyre wear and tear. One of the reasons was uneven tyre wearing. But it could rectify after interchanging the tyre sides after completion of 50 landings. Several modifications were done in order to rectify all the identified issues. Several devices were constructed in order to enhance the life time of the Y12 aircraft tyre. Mechanical properties were measured for the worn-out tyres. The properties were compared with the control tyre sample. It was found that there was an average increment of tensile strength by 38.14 % of control tyre, when compared with the worn-out tyres which were completed 50 number of landings. The suggested modifications are in the process of implementation. It is confident that above mentioned solutions will lead to increase the life span of tyres in Y12 aircraft. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aircraft" title="aircraft">aircraft</a>, <a href="https://publications.waset.org/abstracts/search?q=devices" title=" devices"> devices</a>, <a href="https://publications.waset.org/abstracts/search?q=enhance%20life%20span" title=" enhance life span"> enhance life span</a>, <a href="https://publications.waset.org/abstracts/search?q=modifications%20for%20tyre%20wear" title=" modifications for tyre wear"> modifications for tyre wear</a> </p> <a href="https://publications.waset.org/abstracts/57455/minimize-wear-and-tear-in-y12-aircraft-tyres" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/57455.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">291</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">754</span> Containment/Penetration Analysis for the Protection of Aircraft Engine External Configuration and Nuclear Power Plant Structures</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Dong%20Wook%20Lee">Dong Wook Lee</a>, <a href="https://publications.waset.org/abstracts/search?q=Adrian%20Mistreanu"> Adrian Mistreanu</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The authors have studied a method for analyzing containment and penetration using an explicit nonlinear Finite Element Analysis. This method may be used in the stage of concept design for the protection of external configurations or components of aircraft engines and nuclear power plant structures. This paper consists of the modeling method, the results obtained from the method and the comparison of the results with those calculated from simple analytical method. It shows that the containment capability obtained by proposed method matches well with analytically calculated containment capability. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=computer%20aided%20engineering" title="computer aided engineering">computer aided engineering</a>, <a href="https://publications.waset.org/abstracts/search?q=containment%20analysis" title=" containment analysis"> containment analysis</a>, <a href="https://publications.waset.org/abstracts/search?q=finite%20element%20analysis" title=" finite element analysis"> finite element analysis</a>, <a href="https://publications.waset.org/abstracts/search?q=impact%20analysis" title=" impact analysis"> impact analysis</a>, <a href="https://publications.waset.org/abstracts/search?q=penetration%20analysis" title=" penetration analysis"> penetration analysis</a> </p> <a href="https://publications.waset.org/abstracts/133421/containmentpenetration-analysis-for-the-protection-of-aircraft-engine-external-configuration-and-nuclear-power-plant-structures" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/133421.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">138</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">753</span> Operation Cycle Model of ASz62IR Radial Aircraft Engine</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=M.%20Duk">M. Duk</a>, <a href="https://publications.waset.org/abstracts/search?q=L.%20Grabowski"> L. Grabowski</a>, <a href="https://publications.waset.org/abstracts/search?q=P.%20Magryta"> P. Magryta</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Today's very important element relating to air transport is the environment impact issues. Nowadays there are no emissions standards for turbine and piston engines used in air transport. However, it should be noticed that the environmental effect in the form of exhaust gases from aircraft engines should be as small as possible. For this purpose, R&D centers often use special software to simulate and to estimate the negative effect of engine working process. For cooperation between the Lublin University of Technology and the Polish aviation company WSK "PZL-KALISZ" S.A., to achieve more effective operation of the ASz62IR engine, one of such tools have been used. The AVL Boost software allows to perform 1D simulations of combustion process of piston engines. ASz62IR is a nine-cylinder aircraft engine in a radial configuration. In order to analyze the impact of its working process on the environment, the mathematical model in the AVL Boost software have been made. This model contains, among others, model of the operation cycle of the cylinders. This model was based on a volume change in combustion chamber according to the reciprocating movement of a piston. The simplifications that all of the pistons move identically was assumed. The changes in cylinder volume during an operating cycle were specified. Those changes were important to determine the energy balance of a cylinder in an internal combustion engine which is fundamental for a model of the operating cycle. The calculations for cylinder thermodynamic state were based on the first law of thermodynamics. The change in the mass in the cylinder was calculated from the sum of inflowing and outflowing masses including: cylinder internal energy, heat from the fuel, heat losses, mass in cylinder, cylinder pressure and volume, blowdown enthalpy, evaporation heat etc. The model assumed that the amount of heat released in combustion process was calculated from the pace of combustion, using Vibe model. For gas exchange, it was also important to consider heat transfer in inlet and outlet channels because of much higher values there than for flow in a straight pipe. This results from high values of heat exchange coefficients and temperature coefficients near valves and valve seats. A Zapf modified model of heat exchange was used. To use the model with the flight scenarios, the impact of flight altitude on engine performance has been analyze. It was assumed that the pressure and temperature at the inlet and outlet correspond to the values resulting from the model for International Standard Atmosphere (ISA). Comparing this model of operation cycle with the others submodels of the ASz62IR engine, it could be noticed, that a full analysis of the performance of the engine, according to the ISA conditions, can be made. This work has been financed by the Polish National Centre for Research and Development, INNOLOT, under <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aviation%20propulsion" title="aviation propulsion">aviation propulsion</a>, <a href="https://publications.waset.org/abstracts/search?q=AVL%20Boost" title=" AVL Boost"> AVL Boost</a>, <a href="https://publications.waset.org/abstracts/search?q=engine%20model" title=" engine model"> engine model</a>, <a href="https://publications.waset.org/abstracts/search?q=operation%20cycle" title=" operation cycle"> operation cycle</a>, <a href="https://publications.waset.org/abstracts/search?q=aircraft%20engine" title=" aircraft engine"> aircraft engine</a> </p> <a href="https://publications.waset.org/abstracts/50178/operation-cycle-model-of-asz62ir-radial-aircraft-engine" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/50178.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">292</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">752</span> Review, Analysis and Simulation of Advanced Technology Solutions of Selected Components in Power Electronics Systems (PES) of More Electric Aircraft</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Lucjan%20Setlak">Lucjan Setlak</a>, <a href="https://publications.waset.org/abstracts/search?q=Emil%20Ruda"> Emil Ruda</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The subject of this paper is to review, comparative analysis and simulation of selected components of power electronic systems (PES), consistent with the concept of a more electric aircraft (MEA). Comparative analysis and simulation in software environment MATLAB / Simulink were carried out based on a group of representatives of civil aircraft (B-787, A-380) and military (F-22 Raptor, F-35) in the context of multi-pulse converters used in them (6- and 12-pulse, and 18- and 24-pulse), which are key components of high-tech electronics on-board power systems of autonomous power systems (ASE) of modern aircraft (airplanes of the future). <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=converters" title="converters">converters</a>, <a href="https://publications.waset.org/abstracts/search?q=electric%20machines" title=" electric machines"> electric machines</a>, <a href="https://publications.waset.org/abstracts/search?q=MEA%20%28more%20electric%20aircraft%29" title=" MEA (more electric aircraft)"> MEA (more electric aircraft)</a>, <a href="https://publications.waset.org/abstracts/search?q=PES%20%28power%20electronics%20systems%29" title=" PES (power electronics systems)"> PES (power electronics systems)</a> </p> <a href="https://publications.waset.org/abstracts/31446/review-analysis-and-simulation-of-advanced-technology-solutions-of-selected-components-in-power-electronics-systems-pes-of-more-electric-aircraft" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/31446.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">494</span> </span> </div> </div> <ul class="pagination"> <li class="page-item disabled"><span class="page-link">&lsaquo;</span></li> <li class="page-item active"><span class="page-link">1</span></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=aircraft%20engines&page=2">2</a></li> <li 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