CINXE.COM

<!DOCTYPE html> <html lang="en" dir="ltr"> <head>  <script async src="https://www.googletagmanager.com/gtag/js?id=G-P63WKM1TM1"></script> <script> window.dataLayer = window.dataLayer || []; function gtag(){dataLayer.push(arguments);} gtag('js', new Date()); gtag('config', 'G-P63WKM1TM1'); </script>  <script type="text/javascript" > (function(m,e,t,r,i,k,a){m[i]=m[i]||function(){(m[i].a=m[i].a||[]).push(arguments)}; m[i].l=1*new Date(); for (var j = 0; j < document.scripts.length; j++) {if (document.scripts[j].src === r) { return; }} k=e.createElement(t),a=e.getElementsByTagName(t)[0],k.async=1,k.src=r,a.parentNode.insertBefore(k,a)}) (window, document, "script", "https://mc.yandex.ru/metrika/tag.js", "ym"); ym(55165297, "init", { clickmap:false, trackLinks:true, accurateTrackBounce:true, webvisor:false }); </script> <noscript><div><img src="https://mc.yandex.ru/watch/55165297" style="position:absolute; left:-9999px;" alt="" /></div></noscript>    <title>Search results for: aircraft modeling</title> <meta name="description" content="Search results for: aircraft modeling"> <meta name="keywords" content="aircraft modeling"> <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 navbar-toggler ml-auto" type="button" data-toggle="collapse" data-target="#navbarMenu" aria-controls="navbarMenu" aria-expanded="false" aria-label="Toggle navigation"> <span class="navbar-toggler-icon"></span> </button> <div class="w-100"> <div class="d-none d-lg-flex flex-row-reverse"> <form method="get" action="https://waset.org/search" class="form-inline my-2 my-lg-0"> <input class="form-control mr-sm-2" type="search" placeholder="Search Conferences" value="aircraft modeling" name="q" aria-label="Search"> <button class="btn btn-light my-2 my-sm-0" type="submit"><i class="fas fa-search"></i></button> </form> </div> <div class="collapse navbar-collapse mt-1" id="navbarMenu"> <ul class="navbar-nav ml-auto align-items-center" id="mainNavMenu"> <li class="nav-item"> <a class="nav-link" href="https://waset.org/conferences" title="Conferences in 2024/2025/2026">Conferences</a> </li> <li class="nav-item"> <a class="nav-link" href="https://waset.org/disciplines" title="Disciplines">Disciplines</a> </li> <li class="nav-item"> <a class="nav-link" href="https://waset.org/committees" rel="nofollow">Committees</a> </li> <li class="nav-item dropdown"> <a class="nav-link dropdown-toggle" href="#" id="navbarDropdownPublications" role="button" data-toggle="dropdown" aria-haspopup="true" aria-expanded="false"> Publications </a> <div class="dropdown-menu" aria-labelledby="navbarDropdownPublications"> <a class="dropdown-item" href="https://publications.waset.org/abstracts">Abstracts</a> <a class="dropdown-item" href="https://publications.waset.org">Periodicals</a> <a class="dropdown-item" href="https://publications.waset.org/archive">Archive</a> </div> </li> <li class="nav-item"> <a class="nav-link" href="https://waset.org/page/support" title="Support">Support</a> </li> </ul> </div> </div> </nav> </div> </header> <main> <div class="container mt-4"> <div class="row"> <div class="col-md-9 mx-auto"> <form method="get" 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 modeling"> <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> 4371</div> </div> </div> </div> <h1 class="mt-3 mb-3 text-center" style="font-size:1.6rem;">Search results for: aircraft modeling</h1> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">4371</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">4370</span> Solid-Liquid-Solid Interface of Yakam Matrix: Mathematical Modeling of the Contact Between an Aircraft Landing Gear and a Wet Pavement</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Trudon%20Kabangu%20Mpinga">Trudon Kabangu Mpinga</a>, <a href="https://publications.waset.org/abstracts/search?q=Ruth%20Mutala"> Ruth Mutala</a>, <a href="https://publications.waset.org/abstracts/search?q=Shaloom%20Mbambu"> Shaloom Mbambu</a>, <a href="https://publications.waset.org/abstracts/search?q=Yvette%20Kalubi%20Kashama"> Yvette Kalubi Kashama</a>, <a href="https://publications.waset.org/abstracts/search?q=Kabeya%20Mukeba%20Yakasham"> Kabeya Mukeba Yakasham</a> </p> <p class="card-text"><strong>Abstract:</strong></p> A mathematical model is developed to describe the contact dynamics between the landing gear wheels of an aircraft and a wet pavement during landing. The model is based on nonlinear partial differential equations, using the Yakam Matrix to account for the interaction between solid, liquid, and solid phases. This framework incorporates the influence of environmental factors, particularly water or rain on the runway, on braking performance and aircraft stability. Given the absence of exact analytical solutions, our approach enhances the understanding of key physical phenomena, including Coulomb friction forces, hydrodynamic effects, and the deformation of the pavement under the aircraft's load. Additionally, the dynamics of aquaplaning are simulated numerically to estimate the braking performance limits on wet surfaces, thereby contributing to strategies aimed at minimizing risk during landing on wet runways. <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=modeling" title=" modeling"> modeling</a>, <a href="https://publications.waset.org/abstracts/search?q=simulation" title=" simulation"> simulation</a>, <a href="https://publications.waset.org/abstracts/search?q=yakam%20matrix" title=" yakam matrix"> yakam matrix</a>, <a href="https://publications.waset.org/abstracts/search?q=contact" title=" contact"> contact</a>, <a href="https://publications.waset.org/abstracts/search?q=wet%20runway" title=" wet runway"> wet runway</a> </p> <a href="https://publications.waset.org/abstracts/194905/solid-liquid-solid-interface-of-yakam-matrix-mathematical-modeling-of-the-contact-between-an-aircraft-landing-gear-and-a-wet-pavement" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/194905.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">10</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">4369</span> Modeling of a UAV Longitudinal Dynamics through System Identification Technique</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Asadullah%20I.%20Qazi">Asadullah I. Qazi</a>, <a href="https://publications.waset.org/abstracts/search?q=Mansoor%20Ahsan"> Mansoor Ahsan</a>, <a href="https://publications.waset.org/abstracts/search?q=Zahir%20Ashraf"> Zahir Ashraf</a>, <a href="https://publications.waset.org/abstracts/search?q=Uzair%20Ahmad"> Uzair Ahmad </a> </p> <p class="card-text"><strong>Abstract:</strong></p> System identification of an Unmanned Aerial Vehicle (UAV), to acquire its mathematical model, is a significant step in the process of aircraft flight automation. The need for reliable mathematical model is an established requirement for autopilot design, flight simulator development, aircraft performance appraisal, analysis of aircraft modifications, preflight testing of prototype aircraft and investigation of fatigue life and stress distribution etc.  This research is aimed at system identification of a fixed wing UAV by means of specifically designed flight experiment. The purposely designed flight maneuvers were performed on the UAV and aircraft states were recorded during these flights. Acquired data were preprocessed for noise filtering and bias removal followed by parameter estimation of longitudinal dynamics transfer functions using MATLAB system identification toolbox. Black box identification based transfer function models, in response to elevator and throttle inputs, were estimated using least square error   technique. The identification results show a high confidence level and goodness of fit between the estimated model and actual aircraft response. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=fixed%20wing%20UAV" title="fixed wing UAV">fixed wing UAV</a>, <a href="https://publications.waset.org/abstracts/search?q=system%20identification" title=" system identification"> system identification</a>, <a href="https://publications.waset.org/abstracts/search?q=black%20box%20modeling" title=" black box modeling"> black box modeling</a>, <a href="https://publications.waset.org/abstracts/search?q=longitudinal%20dynamics" title=" longitudinal dynamics"> longitudinal dynamics</a>, <a href="https://publications.waset.org/abstracts/search?q=least%20square%20error" title=" least square error"> least square error</a> </p> <a href="https://publications.waset.org/abstracts/70091/modeling-of-a-uav-longitudinal-dynamics-through-system-identification-technique" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/70091.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">325</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">4368</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">4367</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">4366</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">4365</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">4364</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">353</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">4363</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">4362</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">4361</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">4360</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">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">4359</span> Model Based Design of Fly-by-Wire Flight Controls System of a Fighter Aircraft</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Nauman%20Idrees">Nauman Idrees</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Modeling and simulation during the conceptual design phase are the most effective means of system testing resulting in time and cost savings as compared to the testing of hardware prototypes, which are mostly not available during the conceptual design phase. This paper uses the model-based design (MBD) method in designing the fly-by-wire flight controls system of a fighter aircraft using Simulink. The process begins with system definition and layout where modeling requirements and system components were identified, followed by hierarchical system layout to identify the sequence of operation and interfaces of system with external environment as well as the internal interface between the components. In the second step, each component within the system architecture was modeled along with its physical and functional behavior. Finally, all modeled components were combined to form the fly-by-wire flight controls system of a fighter aircraft as per system architecture developed. The system model developed using this method can be simulated using any simulation software to ensure that desired requirements are met even without the development of a physical prototype resulting in time and cost savings. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=fly-by-wire" title="fly-by-wire">fly-by-wire</a>, <a href="https://publications.waset.org/abstracts/search?q=flight%20controls%20system" title=" flight controls system"> flight controls system</a>, <a href="https://publications.waset.org/abstracts/search?q=model%20based%20design" title=" model based design"> model based design</a>, <a href="https://publications.waset.org/abstracts/search?q=Simulink" title=" Simulink"> Simulink</a> </p> <a href="https://publications.waset.org/abstracts/130892/model-based-design-of-fly-by-wire-flight-controls-system-of-a-fighter-aircraft" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/130892.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">118</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">4358</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> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">4357</span> Modeling of Combustion Process in the Piston Aircraft Engine Using a MCFM-3Z Model</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Marcin%20Szlachetka">Marcin Szlachetka</a>, <a href="https://publications.waset.org/abstracts/search?q=Konrad%20Pietrykowski"> Konrad Pietrykowski</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Modeling of a combustion process in a 9-cylinder aircraft engine is presented. The simulations of the combustion process in the IC engine have provided the information on the spatial and time distributions of selected quantities within the combustion chamber of the engine. The numerical analysis results have been compared with the results of indication process of the engine on the test stand. Modeling of combustion process an auto-ignited IC engine in the AVL Fire was carried out within the study. For the calculations, a ECFM-3Z model was used. Verification of simulation results was carried out by comparison of the pressure in the cylinder. The courses of indicated pressure, obtained from the simulations and during the engine tests mounted on a test stand were compared. The engine was braked by the propeller, which results in an adequate external power characteristics. The test object is a modified ASz-62IR engine with the injection system. The engine was running at take-off power. To check the optimum ignition timing regarding power, calculations, tests were performed for 7 different moments of ignition. The analyses of temperature distribution in the cylinder depending on the moments of ignition were carried out. Additional the course of pressure in the cylinder at different angles of ignition delays of the second spark plug were examined. The swirling of the mixture in the combustion chamber was also analysed. It has been shown that the largest vortexes occur in the middle of the chamber, and gets smaller, closer to the combustion chamber walls. 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=CFD" title="CFD">CFD</a>, <a href="https://publications.waset.org/abstracts/search?q=combustion" title=" combustion"> combustion</a>, <a href="https://publications.waset.org/abstracts/search?q=internal%20combustion%20engine" title=" internal combustion engine"> internal combustion engine</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/50210/modeling-of-combustion-process-in-the-piston-aircraft-engine-using-a-mcfm-3z-model" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/50210.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">372</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">4356</span> Aerodynamic Analysis of Dimple Effect on Aircraft Wing</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=E.%20Livya">E. Livya</a>, <a href="https://publications.waset.org/abstracts/search?q=G.%20Anitha"> G. Anitha</a>, <a href="https://publications.waset.org/abstracts/search?q=P.%20Valli"> P. Valli</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The main objective of aircraft aerodynamics is to enhance the aerodynamic characteristics and maneuverability of the aircraft. This enhancement includes the reduction in drag and stall phenomenon. The airfoil which contains dimples will have comparatively less drag than the plain airfoil. Introducing dimples on the aircraft wing will create turbulence by creating vortices which delays the boundary layer separation resulting in decrease of pressure drag and also increase in the angle of stall. In addition, wake reduction leads to reduction in acoustic emission. The overall objective of this paper is to improve the aircraft maneuverability by delaying the flow separation point at stall and thereby reducing the drag by applying the dimple effect over the aircraft wing. This project includes both computational and experimental analysis of dimple effect on aircraft wing, using NACA 0018 airfoil. Dimple shapes of Semi-sphere, hexagon, cylinder, square are selected for the analysis; airfoil is tested under the inlet velocity of 30m/s at different angle of attack (5˚, 10˚, 15˚, 20˚, and 25˚). This analysis favours the dimple effect by increasing L/D ratio and thereby providing the maximum aerodynamic efficiency, which provides the enhanced performance for the aircraft. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=airfoil" title="airfoil">airfoil</a>, <a href="https://publications.waset.org/abstracts/search?q=dimple%20effect" title=" dimple effect"> dimple effect</a>, <a href="https://publications.waset.org/abstracts/search?q=turbulence" title=" turbulence"> turbulence</a>, <a href="https://publications.waset.org/abstracts/search?q=boundary%20layer%20separation" title=" boundary layer separation"> boundary layer separation</a> </p> <a href="https://publications.waset.org/abstracts/24631/aerodynamic-analysis-of-dimple-effect-on-aircraft-wing" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/24631.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">533</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">4355</span> Application of the Total Least Squares Estimation Method for an Aircraft Aerodynamic Model Identification</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Zaouche%20Mohamed">Zaouche Mohamed</a>, <a href="https://publications.waset.org/abstracts/search?q=Amini%20Mohamed"> Amini Mohamed</a>, <a href="https://publications.waset.org/abstracts/search?q=Foughali%20Khaled"> Foughali Khaled</a>, <a href="https://publications.waset.org/abstracts/search?q=Aitkaid%20Souhila"> Aitkaid Souhila</a>, <a href="https://publications.waset.org/abstracts/search?q=Bouchiha%20Nihad%20Sarah"> Bouchiha Nihad Sarah</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The aerodynamic coefficients are important in the evaluation of an aircraft performance and stability-control characteristics. These coefficients also can be used in the automatic flight control systems and mathematical model of flight simulator. The study of the aerodynamic aspect of flying systems is a reserved domain and inaccessible for the developers. Doing tests in a wind tunnel to extract aerodynamic forces and moments requires a specific and expensive means. Besides, the glaring lack of published documentation in this field of study makes the aerodynamic coefficients determination complicated. This work is devoted to the identification of an aerodynamic model, by using an aircraft in virtual simulated environment. We deal with the identification of the system, we present an environment framework based on Software In the Loop (SIL) methodology and we use Microsoft<sup>TM</sup> Flight Simulator (FS-2004) as the environment for plane simulation. We propose The Total Least Squares Estimation technique (TLSE) to identify the aerodynamic parameters, which are unknown, variable, classified and used in the expression of the piloting law. In this paper, we define each aerodynamic coefficient as the mean of its numerical values. All other variations are considered as modeling uncertainties that will be compensated by the robustness of the piloting control. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aircraft%20aerodynamic%20model" title="aircraft aerodynamic model">aircraft aerodynamic model</a>, <a href="https://publications.waset.org/abstracts/search?q=total%20least%20squares%20estimation" title=" total least squares estimation"> total least squares estimation</a>, <a href="https://publications.waset.org/abstracts/search?q=piloting%20the%20aircraft" title=" piloting the aircraft"> piloting the aircraft</a>, <a href="https://publications.waset.org/abstracts/search?q=robust%20control" title=" robust control"> robust control</a>, <a href="https://publications.waset.org/abstracts/search?q=Microsoft%20Flight%20Simulator" title=" Microsoft Flight Simulator"> Microsoft Flight Simulator</a>, <a href="https://publications.waset.org/abstracts/search?q=MQ-1%20predator" title=" MQ-1 predator"> MQ-1 predator</a> </p> <a href="https://publications.waset.org/abstracts/44416/application-of-the-total-least-squares-estimation-method-for-an-aircraft-aerodynamic-model-identification" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/44416.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">287</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">4354</span> Noise Reduction by Energising the Boundary Layer</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Kiran%20P.%20Kumar">Kiran P. Kumar</a>, <a href="https://publications.waset.org/abstracts/search?q=H.%20M.%20Nayana"> H. M. Nayana</a>, <a href="https://publications.waset.org/abstracts/search?q=R.%20Rakshitha"> R. Rakshitha</a>, <a href="https://publications.waset.org/abstracts/search?q=S.%20Sushmitha"> S. Sushmitha</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Aircraft noise is a highly concerned problem in the field of the aviation industry. It is necessary to reduce the noise in order to be environment-friendly. Air-frame noise is caused because of the quick separation of the boundary layer over an aircraft body. So, we have to delay the boundary layer separation of an air-frame and engine nacelle. By following a certain procedure boundary layer separation can be reduced by converting laminar into turbulent and hence early separation can be prevented that leads to the noise reduction. This method has a tendency to reduce the noise of the aircraft hence it can prove efficient and environment-friendly than the present Aircraft. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=airframe" title="airframe">airframe</a>, <a href="https://publications.waset.org/abstracts/search?q=boundary%20layer" title=" boundary layer"> boundary layer</a>, <a href="https://publications.waset.org/abstracts/search?q=noise" title=" noise"> noise</a>, <a href="https://publications.waset.org/abstracts/search?q=reduction" title=" reduction"> reduction</a> </p> <a href="https://publications.waset.org/abstracts/53714/noise-reduction-by-energising-the-boundary-layer" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/53714.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">481</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">4353</span> Aircraft Pitch Attitude Control Using Backstepping </h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Labane%20Chrif">Labane Chrif</a> </p> <p class="card-text"><strong>Abstract:</strong></p> A nonlinear approach to the automatic pitch attitude control problem for aircraft transportation is presented. A nonlinear model describing the longitudinal equations of motion in strict feedback form is derived. Backstepping is utilized for the construction of a globally stabilizing controller with a number of free design parameters. The controller is evaluated using the aircraft transportation. The adaptation scheme proposed allowed us to design an explicit controller with a minimal knowledge of the aircraft aerodynamics. Finally, the simulation results will show that backstepping controller have better dynamic performance, simpler design, higher precision, easier implement, etc. At the same time, the control effect will be significantly improved. In addition, backstepping control is superior in short transition, good stability, anti-disturbance and good control. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=nonlinear%20control" title="nonlinear control">nonlinear control</a>, <a href="https://publications.waset.org/abstracts/search?q=backstepping" title=" backstepping"> backstepping</a>, <a href="https://publications.waset.org/abstracts/search?q=aircraft%20control" title=" aircraft control"> aircraft control</a>, <a href="https://publications.waset.org/abstracts/search?q=Lyapunov%20function" title=" Lyapunov function"> Lyapunov function</a>, <a href="https://publications.waset.org/abstracts/search?q=longitudinal%20model" title=" longitudinal model"> longitudinal model</a> </p> <a href="https://publications.waset.org/abstracts/23396/aircraft-pitch-attitude-control-using-backstepping" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/23396.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">581</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">4352</span> Effects of Aircraft Wing Configuration on Aerodynamic Efficiency</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Aderet%20Pantierer">Aderet Pantierer</a>, <a href="https://publications.waset.org/abstracts/search?q=Shmuel%20Pantierer"> Shmuel Pantierer</a>, <a href="https://publications.waset.org/abstracts/search?q=Atif%20Saeed"> Atif Saeed</a>, <a href="https://publications.waset.org/abstracts/search?q=Amir%20Elzawawy"> Amir Elzawawy</a> </p> <p class="card-text"><strong>Abstract:</strong></p> In recent years, air travel has seen volatile growth. Due to this growth, the maximization of efficiency and space utilization has been a major issue for aircraft manufacturers. Elongation of the wingspan of aircraft has resulted in increased lift; and, thereby, efficiency. However, increasing the wingspan of aircraft has been detrimental to the manufacturing process and has led to airport congestion and required airport reconfiguration to accommodate the extended wingspans of aircraft. This project outlines differing wing configurations of a commercial aircraft and the effects on the aerodynamic loads produced. Multiple wing configurations are analyzed using Finite Element Models. These models are then validated by testing one wing configuration in a wind tunnel under laminar flow and turbulent flow conditions. The wing configurations to be tested include high and low wing aircraft, as well as various combinations of the two, including a unique model hereon referred to as an infinity wing. The infinity wing configuration consists of both a high and low wing, with the two wings connected by a vertical airfoil. This project seeks to determine if a wing configuration consisting of multiple airfoils produces more lift than the standard wing configurations and is able to provide a solution to manufacturing limitations as well as airport congestion. If the analysis confirms the hypothesis, a trade study will be performed to determine if and when an arrangement of multiple wings would be cost-effective. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aerodynamics" title="aerodynamics">aerodynamics</a>, <a href="https://publications.waset.org/abstracts/search?q=aircraft%20design" title=" aircraft design"> aircraft design</a>, <a href="https://publications.waset.org/abstracts/search?q=aircraft%20efficiency" title=" aircraft efficiency"> aircraft efficiency</a>, <a href="https://publications.waset.org/abstracts/search?q=wing%20configuration" title=" wing configuration"> wing configuration</a>, <a href="https://publications.waset.org/abstracts/search?q=wing%20design" title=" wing design"> wing design</a> </p> <a href="https://publications.waset.org/abstracts/115909/effects-of-aircraft-wing-configuration-on-aerodynamic-efficiency" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/115909.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">264</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">4351</span> Factors Associated with Fatal and Non-Fatal Accidents of Commercial Aviation Fixed-Wing Aircraft in Indonesia (2007-2018)</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Adre%20Dwi%20Wiratama">Adre Dwi Wiratama</a>, <a href="https://publications.waset.org/abstracts/search?q=Budi%20Sampurna"> Budi Sampurna</a>, <a href="https://publications.waset.org/abstracts/search?q=Syougie%20Ali"> Syougie Ali</a>, <a href="https://publications.waset.org/abstracts/search?q=Djunadi"> Djunadi</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Background: Even though safety is a priority in Commercial Aviation (CA) operations, fatal fixed-wing aircraft accidents still occur frequently in Indonesia. Objective: This research aims to determine factors associated with fatal and non-fatal CA fixed-wing aircraft accidents in Indonesia. Methods: The research used a cross-sectional design, which was carried out in July 2023. It included all final reports on fixed-wing aircraft accidents published by the Indonesian National Transportation Safety Committee (KNKT). Analysis was conducted using chi-square and Fisher’s exact test methods using IBM SPSS software version 29.0. Results: Out of 52 final reports, 25 were fatal. The study found that factors associated with a higher risk of fatal accidents are pilots in command with CPL, unpressurized aircraft, single-engine aircraft, aircraft with MTOW less than 5,700kg, accidents occurring at weekends, accidents occurring outside of airport premises, CFIT occurrences, and the cruise phase of flight. The factor associated with non-fatal accidents is the landing phase. Conclusion: Efforts such as enhancing pilot training and certification processes, implementing stricter safety regulations for small, unpressurized, single-engine aircraft, and increasing safety measures during weekends and specific phases of flight can reduce future fatal accidents. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=fatal%20accident" title="fatal accident">fatal accident</a>, <a href="https://publications.waset.org/abstracts/search?q=fixed-wing%20aircraft" title=" fixed-wing aircraft"> fixed-wing aircraft</a>, <a href="https://publications.waset.org/abstracts/search?q=commercial%20aviation" title=" commercial aviation"> commercial aviation</a> </p> <a href="https://publications.waset.org/abstracts/193251/factors-associated-with-fatal-and-non-fatal-accidents-of-commercial-aviation-fixed-wing-aircraft-in-indonesia-2007-2018" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/193251.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">8</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">4350</span> Calculation of the Supersonic Air Intake with the Optimization of the Shock Wave System </h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Elena%20Vinogradova">Elena Vinogradova</a>, <a href="https://publications.waset.org/abstracts/search?q=Aleksei%20Pleshakov"> Aleksei Pleshakov</a>, <a href="https://publications.waset.org/abstracts/search?q=Aleksei%20Yakovlev"> Aleksei Yakovlev</a> </p> <p class="card-text"><strong>Abstract:</strong></p> During the flight of a supersonic aircraft under various conditions (altitude, Mach, etc.), it becomes necessary to coordinate the operating modes of the air intake and engine. On the supersonic aircraft, it’s been done by changing various control factors (the angle of rotation of the wedge panels and etc.). This paper investigates the possibility of using modern optimization methods to determine the optimal position of the supersonic air intake wedge panels in order to maximize the total pressure recovery coefficient. Modern software allows us to conduct auto-optimization, which determines the optimal position of the control elements of the investigated product to achieve its maximum efficiency. In this work, the flow in the supersonic aircraft inlet has investigated and optimized the operation of the flaps of the supersonic inlet in an aircraft in a 2-D setting. This work has done using ANSYS CFX software. The supersonic aircraft inlet is a flat adjustable external compression inlet. The braking surface is made in the form of a three-stage wedge. The IOSO NM software package was chosen for optimization. Change in the position of the panels of the input device is carried out by changing the angle between the first and second steps of the three-stage wedge. The position of the rest of the panels is changed automatically. Within the framework of the presented work, the position of the moving air intake panel was optimized under fixed flight conditions of the aircraft under a certain engine operating mode. As a result of the numerical modeling, the distribution of total pressure losses was obtained for various cases of the engine operation, depending on the incoming flow velocity and the flight altitude of the aircraft. The results make it possible to obtain the maximum total pressure recovery coefficient under given conditions. Also, the initial geometry was set with a certain angle between the first and second wedge panels. Having performed all the calculations, as well as the subsequent optimization of the aircraft input device, it can be concluded that the initial angle was set sufficiently close to the optimal angle. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=optimal%20angle" title="optimal angle">optimal angle</a>, <a href="https://publications.waset.org/abstracts/search?q=optimization" title=" optimization"> optimization</a>, <a href="https://publications.waset.org/abstracts/search?q=supersonic%20air%20intake" title=" supersonic air intake"> supersonic air intake</a>, <a href="https://publications.waset.org/abstracts/search?q=total%20pressure%20recovery%20coefficient" title=" total pressure recovery coefficient"> total pressure recovery coefficient</a> </p> <a href="https://publications.waset.org/abstracts/135524/calculation-of-the-supersonic-air-intake-with-the-optimization-of-the-shock-wave-system" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/135524.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">244</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">4349</span> Robust Control of a Dynamic Model of an F-16 Aircraft with Improved Damping through Linear Matrix Inequalities</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=J.%20P.%20P.%20Andrade">J. P. P. Andrade</a>, <a href="https://publications.waset.org/abstracts/search?q=V.%20A.%20F.%20Campos"> V. A. F. Campos</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This work presents an application of Linear Matrix Inequalities (LMI) for the robust control of an F-16 aircraft through an algorithm ensuring the damping factor to the closed loop system. The results show that the zero and gain settings are sufficient to ensure robust performance and stability with respect to various operating points. The technique used is the pole placement, which aims to put the system in closed loop poles in a specific region of the complex plane. Test results using a dynamic model of the F-16 aircraft are presented and discussed. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=F-16%20aircraft" title="F-16 aircraft">F-16 aircraft</a>, <a href="https://publications.waset.org/abstracts/search?q=linear%20matrix%20inequalities" title=" linear matrix inequalities"> linear matrix inequalities</a>, <a href="https://publications.waset.org/abstracts/search?q=pole%20placement" title=" pole placement"> pole placement</a>, <a href="https://publications.waset.org/abstracts/search?q=robust%20control" title=" robust control"> robust control</a> </p> <a href="https://publications.waset.org/abstracts/58790/robust-control-of-a-dynamic-model-of-an-f-16-aircraft-with-improved-damping-through-linear-matrix-inequalities" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/58790.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">306</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">4348</span> Construction of Large Scale UAVs Using Homebuilt Composite Techniques </h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Brian%20J.%20Kozak">Brian J. Kozak</a>, <a href="https://publications.waset.org/abstracts/search?q=Joshua%20D.%20Shipman"> Joshua D. Shipman</a>, <a href="https://publications.waset.org/abstracts/search?q=Peng%20Hao%20Wang"> Peng Hao Wang</a>, <a href="https://publications.waset.org/abstracts/search?q=Blake%20Shipp"> Blake Shipp</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The unmanned aerial system (UAS) industry is growing at a rapid pace. This growth has increased the demand for low cost, custom made and high strength unmanned aerial vehicles (UAV). The area of most growth is in the area of 25 kg to 200 kg vehicles. Vehicles this size are beyond the size and scope of simple wood and fabric designs commonly found in hobbyist aircraft. These high end vehicles require stronger materials to complete their mission. Traditional aircraft construction materials such as aluminum are difficult to use without machining or advanced computer controlled tooling. However, by using general aviation composite aircraft homebuilding techniques and materials, a large scale UAV can be constructed cheaply and easily. Furthermore, these techniques could be used to easily manufacture cost made composite shapes and airfoils that would be cost prohibitive when using metals. These homebuilt aircraft techniques are being demonstrated by the researchers in the construction of a 75 kg aircraft. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=composite%20aircraft" title="composite aircraft">composite aircraft</a>, <a href="https://publications.waset.org/abstracts/search?q=homebuilding" title=" homebuilding"> homebuilding</a>, <a href="https://publications.waset.org/abstracts/search?q=unmanned%20aerial%20system%20industry" title=" unmanned aerial system industry"> unmanned aerial system industry</a>, <a href="https://publications.waset.org/abstracts/search?q=UAS" title=" UAS"> UAS</a>, <a href="https://publications.waset.org/abstracts/search?q=unmanned%20aerial%20vehicles" title=" unmanned aerial vehicles"> unmanned aerial vehicles</a>, <a href="https://publications.waset.org/abstracts/search?q=UAV" title=" UAV"> UAV</a> </p> <a href="https://publications.waset.org/abstracts/113067/construction-of-large-scale-uavs-using-homebuilt-composite-techniques" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/113067.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">4347</span> In-Flight Aircraft Performance Model Enhancement Using Adaptive Lookup Tables</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Georges%20Ghazi">Georges Ghazi</a>, <a href="https://publications.waset.org/abstracts/search?q=Magali%20Gelhaye"> Magali Gelhaye</a>, <a href="https://publications.waset.org/abstracts/search?q=Ruxandra%20Botez"> Ruxandra Botez</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Over the years, the Flight Management System (FMS) has experienced a continuous improvement of its many features, to the point of becoming the pilot’s primary interface for flight planning operation on the airplane. With the assistance of the FMS, the concept of distance and time has been completely revolutionized, providing the crew members with the determination of the optimized route (or flight plan) from the departure airport to the arrival airport. To accomplish this function, the FMS needs an accurate Aircraft Performance Model (APM) of the aircraft. In general, APMs that equipped most modern FMSs are established before the entry into service of an individual aircraft, and results from the combination of a set of ordinary differential equations and a set of performance databases. Unfortunately, an aircraft in service is constantly exposed to dynamic loads that degrade its flight characteristics. These degradations endow two main origins: airframe deterioration (control surfaces rigging, seals missing or damaged, etc.) and engine performance degradation (fuel consumption increase for a given thrust). Thus, after several years of service, the performance databases and the APM associated to a specific aircraft are no longer representative enough of the actual aircraft performance. It is important to monitor the trend of the performance deterioration and correct the uncertainties of the aircraft model in order to improve the accuracy the flight management system predictions. The basis of this research lies in the new ability to continuously update an Aircraft Performance Model (APM) during flight using an adaptive lookup table technique. This methodology was developed and applied to the well-known Cessna Citation X business aircraft. For the purpose of this study, a level D Research Aircraft Flight Simulator (RAFS) was used as a test aircraft. According to Federal Aviation Administration the level D is the highest certification level for the flight dynamics modeling. Basically, using data available in the Flight Crew Operating Manual (FCOM), a first APM describing the variation of the engine fan speed and aircraft fuel flow w.r.t flight conditions was derived. This model was next improved using the proposed methodology. To do that, several cruise flights were performed using the RAFS. An algorithm was developed to frequently sample the aircraft sensors measurements during the flight and compare the model prediction with the actual measurements. Based on these comparisons, a correction was performed on the actual APM in order to minimize the error between the predicted data and the measured data. In this way, as the aircraft flies, the APM will be continuously enhanced, making the FMS more and more precise and the prediction of trajectories more realistic and more reliable. The results obtained are very encouraging. Indeed, using the tables initialized with the FCOM data, only a few iterations were needed to reduce the fuel flow prediction error from an average relative error of 12% to 0.3%. Similarly, the FCOM prediction regarding the engine fan speed was reduced from a maximum error deviation of 5.0% to 0.2% after only ten flights. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aircraft%20performance" title="aircraft performance">aircraft performance</a>, <a href="https://publications.waset.org/abstracts/search?q=cruise" title=" cruise"> cruise</a>, <a href="https://publications.waset.org/abstracts/search?q=trajectory%20optimization" title=" trajectory optimization"> trajectory optimization</a>, <a href="https://publications.waset.org/abstracts/search?q=adaptive%20lookup%20tables" title=" adaptive lookup tables"> adaptive lookup tables</a>, <a href="https://publications.waset.org/abstracts/search?q=Cessna%20Citation%20X" title=" Cessna Citation X"> Cessna Citation X</a> </p> <a href="https://publications.waset.org/abstracts/87528/in-flight-aircraft-performance-model-enhancement-using-adaptive-lookup-tables" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/87528.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">264</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">4346</span> Aerodynamic Design and Optimization of Vertical Take-Off and Landing Type Unmanned Aerial Vehicles</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Enes%20Gunaltili">Enes Gunaltili</a>, <a href="https://publications.waset.org/abstracts/search?q=Burak%20Dam"> Burak Dam</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The airplane history started with the Wright brothers' aircraft and improved day by day. With the help of this advancements, big aircrafts replace with small and unmanned air vehicles, so in this study we design this type of air vehicles. First of all, aircrafts mainly divided into two main parts in our day as a rotary and fixed wing aircrafts. The fixed wing aircraft generally use for transport, cargo, military and etc. The rotary wing aircrafts use for same area but there are some superiorities from each other. The rotary wing aircraft can take off vertically from the ground, and it can use restricted area. On the other hand, rotary wing aircrafts generally can fly lower range than fixed wing aircraft. There are one kind of aircraft consist of this two types specifications. It is named as VTOL (vertical take-off and landing) type aircraft. VTOLs are able to takeoff and land vertically and fly horizontally. The VTOL aircrafts generally can fly higher range from the rotary wings but can fly lower range from the fixed wing aircraft but it gives beneficial range between them. There are many other advantages of VTOL aircraft from the rotary and fixed wing aircraft. Because of that, VTOLs began to use for generally military, cargo, search, rescue and mapping areas. Within this framework, this study answers the question that how can we design VTOL as a small unmanned aircraft systems for search and rescue application for benefiting the advantages of fixed wing and rotary wing aircrafts by eliminating the disadvantages of them. To answer that question and design VTOL aircraft, multidisciplinary design optimizations (MDO), some theoretical terminologies, formulations, simulations and modelling systems based on CFD (Computational Fluid Dynamics) is used in same time as design methodology to determine design parameters and steps. As a conclusion, based on tests and simulations depend on design steps, suggestions on how the VTOL aircraft designed and advantages, disadvantages, and observations for design parameters are listed, then VTOL is designed and presented with the design parameters, advantages, and usage areas. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=airplane" title="airplane">airplane</a>, <a href="https://publications.waset.org/abstracts/search?q=rotary" title=" rotary"> rotary</a>, <a href="https://publications.waset.org/abstracts/search?q=fixed" title=" fixed"> fixed</a>, <a href="https://publications.waset.org/abstracts/search?q=VTOL" title=" VTOL"> VTOL</a>, <a href="https://publications.waset.org/abstracts/search?q=CFD" title=" CFD"> CFD</a> </p> <a href="https://publications.waset.org/abstracts/92083/aerodynamic-design-and-optimization-of-vertical-take-off-and-landing-type-unmanned-aerial-vehicles" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/92083.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">282</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">4345</span> Aerodynamic Analysis and Design of Banners for Remote-Controlled Aircraft</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Peyman%20Honarmandi">Peyman Honarmandi</a>, <a href="https://publications.waset.org/abstracts/search?q=Mazen%20Alhirsh"> Mazen Alhirsh</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Banner towing is a major form of advertisement. It consists of a banner showing a logo or a selection of words or letters being towed by an aircraft. Traditionally bush planes have been used to tow banners given their high thrust capabilities; however, with the development of remote-controlled (RC) aircraft, they could be a good replacement as RC planes mitigate the risk of human life and can be easier to operate. This paper studies the best banner design to be towed by an RC aircraft. This is done by conducting wind tunnel testing on an array of banners with different materials and designs. A pull gauge is used to record the drag force during testing, which is then used to calculate the coefficient of drag, Cd. The testing results show that the best banner design would be a hybrid design with a solid and mesh material. The design with the lowest Cd of 0.082 was a half ripstop nylon half polyester mesh design. On the other hand, the design with the highest Cd of 0.305 involved incorporating a tail chute to decrease fluttering. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aerodynamics%20of%20banner" title="aerodynamics of banner">aerodynamics of banner</a>, <a href="https://publications.waset.org/abstracts/search?q=banner%20design" title=" banner design"> banner design</a>, <a href="https://publications.waset.org/abstracts/search?q=banner%20towing" title=" banner towing"> banner towing</a>, <a href="https://publications.waset.org/abstracts/search?q=drag%20coefficients%20of%20banner" title=" drag coefficients of banner"> drag coefficients of banner</a>, <a href="https://publications.waset.org/abstracts/search?q=RC%20aircraft%20banner" title=" RC aircraft banner"> RC aircraft banner</a> </p> <a href="https://publications.waset.org/abstracts/141485/aerodynamic-analysis-and-design-of-banners-for-remote-controlled-aircraft" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/141485.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">242</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">4344</span> Enhanced Method of Conceptual Sizing of Aircraft Electro-Thermal De-Icing System</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Ahmed%20Shinkafi">Ahmed Shinkafi</a>, <a href="https://publications.waset.org/abstracts/search?q=Craig%20Lawson"> Craig Lawson</a> </p> <p class="card-text"><strong>Abstract:</strong></p> There is a great advancement towards the All-Electric Aircraft (AEA) technology. The AEA concept assumes that all aircraft systems will be integrated into one electrical power source in the future. The principle of the electro-thermal system is to transfer the energy required for anti/de-icing to the protected areas in electrical form. However, powering a large aircraft anti-icing system electrically could be quite excessive in cost and system weight. Hence, maximising the anti/de-icing efficiency of the electro-thermal system in order to minimise its power demand has become crucial to electro-thermal de-icing system sizing. In this work, an enhanced methodology has been developed for conceptual sizing of aircraft electro-thermal de-icing System. The work factored those critical terms overlooked in previous studies which were critical to de-icing energy consumption. A case study of a typical large aircraft wing de-icing was used to test and validate the model. The model was used to optimise the system performance by a trade-off between the de-icing peak power and system energy consumption. The optimum melting surface temperatures and energy flux predicted enabled the reduction in the power required for de-icing. The weight penalty associated with electro-thermal anti-icing/de-icing method could be eliminated using this method without under estimating the de-icing power requirement. <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=de-icing%20system" title=" de-icing system"> de-icing system</a>, <a href="https://publications.waset.org/abstracts/search?q=electro-thermal" title=" electro-thermal"> electro-thermal</a>, <a href="https://publications.waset.org/abstracts/search?q=in-flight%20icing" title=" in-flight icing"> in-flight icing</a> </p> <a href="https://publications.waset.org/abstracts/9616/enhanced-method-of-conceptual-sizing-of-aircraft-electro-thermal-de-icing-system" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/9616.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">517</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">4343</span> Intelligent Diagnostic System of the Onboard Measuring Devices</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Kyaw%20Zin%20Htut">Kyaw Zin Htut</a> </p> <p class="card-text"><strong>Abstract:</strong></p> In this article, the synthesis of the efficiency of intelligent diagnostic system in the aircraft measuring devices is described. The technology developments of the diagnostic system are considered based on the model errors of the gyro instruments, which are used to measure the parameters of the aircraft. The synthesis of the diagnostic intelligent system is considered on the example of the problem of assessment and forecasting errors of the gyroscope devices on the onboard aircraft. The result of the system is to detect of faults of the aircraft measuring devices as well as the analysis of the measuring equipment to improve the efficiency of its work. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=diagnostic" title="diagnostic">diagnostic</a>, <a href="https://publications.waset.org/abstracts/search?q=dynamic%20system" title=" dynamic system"> dynamic system</a>, <a href="https://publications.waset.org/abstracts/search?q=errors%20of%20gyro%20instruments" title=" errors of gyro instruments"> errors of gyro instruments</a>, <a href="https://publications.waset.org/abstracts/search?q=model%20errors" title=" model errors"> model errors</a>, <a href="https://publications.waset.org/abstracts/search?q=assessment" title=" assessment"> assessment</a>, <a href="https://publications.waset.org/abstracts/search?q=prognosis" title=" prognosis"> prognosis</a> </p> <a href="https://publications.waset.org/abstracts/47000/intelligent-diagnostic-system-of-the-onboard-measuring-devices" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/47000.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">400</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">4342</span> Theoretical Calculation of Wingtip Devices for Agricultural Aircraft</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Hashim%20Bashir">Hashim Bashir</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The Vortex generated at the edges of the wing of an Aircraft are called the Wing Tip Vortex. The Wing Tip Vortices are associated with induced drag. The induced drag is responsible for nearly 50% of aircraft total drag and can be reduced through modifications to the wing tip. Some models displace wingtips vortices outwards diminishing the induced drag. Concerning agricultural aircrafts, wing tip vortex position is really important, while spreading products over a plantation. In this work, theoretical calculations were made in order to study the influence in aerodynamic characteristics and vortex position, over Sudanese agricultural aircraft, by the following types of wing tips: delta tip, winglet and down curved. The down curved tip was better for total drag reduction, but not good referring to vortex position. The delta tip gave moderate improvement on aerodynamic characteristic and on vortex position. The winglet had a better vortex position and lift increment, but caused an undesirable result referring to the wing root bending moment. However, winglet showed better development potential for agricultural aircraft. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=wing%20tip%20device" title="wing tip device">wing tip device</a>, <a href="https://publications.waset.org/abstracts/search?q=wing%20tip%20vortice" title=" wing tip vortice"> wing tip vortice</a>, <a href="https://publications.waset.org/abstracts/search?q=agricultural%20aircaft" title=" agricultural aircaft"> agricultural aircaft</a>, <a href="https://publications.waset.org/abstracts/search?q=winglet" title=" winglet"> winglet</a> </p> <a href="https://publications.waset.org/abstracts/57169/theoretical-calculation-of-wingtip-devices-for-agricultural-aircraft" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/57169.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">314</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%20modeling&page=2">2</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=aircraft%20modeling&page=3">3</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=aircraft%20modeling&page=4">4</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=aircraft%20modeling&page=5">5</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=aircraft%20modeling&page=6">6</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=aircraft%20modeling&page=7">7</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=aircraft%20modeling&page=8">8</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=aircraft%20modeling&page=9">9</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=aircraft%20modeling&page=10">10</a></li> <li class="page-item disabled"><span class="page-link">...</span></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=aircraft%20modeling&page=145">145</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=aircraft%20modeling&page=146">146</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=aircraft%20modeling&page=2" rel="next">&rsaquo;</a></li> </ul> </div> </main> <footer> <div id="infolinks" class="pt-3 pb-2"> <div class="container"> <div style="background-color:#f5f5f5;" class="p-3"> <div class="row"> <div class="col-md-2"> <ul class="list-unstyled"> About <li><a href="https://waset.org/page/support">About Us</a></li> <li><a href="https://waset.org/page/support#legal-information">Legal</a></li> <li><a target="_blank" rel="nofollow" href="https://publications.waset.org/static/files/WASET-16th-foundational-anniversary.pdf">WASET celebrates its 16th foundational anniversary</a></li> </ul> </div> <div class="col-md-2"> <ul class="list-unstyled"> Account <li><a href="https://waset.org/profile">My Account</a></li> </ul> </div> <div class="col-md-2"> <ul class="list-unstyled"> Explore <li><a href="https://waset.org/disciplines">Disciplines</a></li> <li><a href="https://waset.org/conferences">Conferences</a></li> <li><a href="https://waset.org/conference-programs">Conference Program</a></li> <li><a href="https://waset.org/committees">Committees</a></li> <li><a href="https://publications.waset.org">Publications</a></li> </ul> </div> <div class="col-md-2"> <ul class="list-unstyled"> Research <li><a href="https://publications.waset.org/abstracts">Abstracts</a></li> <li><a href="https://publications.waset.org">Periodicals</a></li> <li><a href="https://publications.waset.org/archive">Archive</a></li> </ul> </div> <div class="col-md-2"> <ul class="list-unstyled"> Open Science <li><a target="_blank" rel="nofollow" href="https://publications.waset.org/static/files/Open-Science-Philosophy.pdf">Open Science Philosophy</a></li> <li><a target="_blank" rel="nofollow" href="https://publications.waset.org/static/files/Open-Science-Award.pdf">Open Science Award</a></li> <li><a target="_blank" rel="nofollow" href="https://publications.waset.org/static/files/Open-Society-Open-Science-and-Open-Innovation.pdf">Open Innovation</a></li> <li><a target="_blank" rel="nofollow" href="https://publications.waset.org/static/files/Postdoctoral-Fellowship-Award.pdf">Postdoctoral Fellowship Award</a></li> <li><a target="_blank" rel="nofollow" href="https://publications.waset.org/static/files/Scholarly-Research-Review.pdf">Scholarly Research Review</a></li> </ul> </div> <div class="col-md-2"> <ul class="list-unstyled"> Support <li><a href="https://waset.org/page/support">Support</a></li> <li><a href="https://waset.org/profile/messages/create">Contact Us</a></li> <li><a href="https://waset.org/profile/messages/create">Report Abuse</a></li> </ul> </div> </div> </div> </div> </div> <div class="container text-center"> <hr style="margin-top:0;margin-bottom:.3rem;"> <a href="https://creativecommons.org/licenses/by/4.0/" target="_blank" class="text-muted small">Creative Commons Attribution 4.0 International License</a> <div id="copy" class="mt-2">© 2024 World Academy of Science, Engineering and Technology</div> </div> </footer> <a href="javascript:" id="return-to-top"><i class="fas fa-arrow-up"></i></a> <div class="modal" id="modal-template"> <div class="modal-dialog"> <div class="modal-content"> <div class="row m-0 mt-1"> <div class="col-md-12"> <button type="button" class="close" data-dismiss="modal" aria-label="Close"><span aria-hidden="true">×</span></button> </div> </div> <div class="modal-body"></div> </div> </div> </div> <script src="https://cdn.waset.org/static/plugins/jquery-3.3.1.min.js"></script> <script src="https://cdn.waset.org/static/plugins/bootstrap-4.2.1/js/bootstrap.bundle.min.js"></script> <script src="https://cdn.waset.org/static/js/site.js?v=150220211556"></script> <script> jQuery(document).ready(function() { /*jQuery.get("https://publications.waset.org/xhr/user-menu", function (response) { jQuery('#mainNavMenu').append(response); });*/ jQuery.get({ url: "https://publications.waset.org/xhr/user-menu", cache: false }).then(function(response){ jQuery('#mainNavMenu').append(response); }); }); </script> </body> </html>