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 components</title> <meta name="description" content="Search results for: aircraft components"> <meta name="keywords" content="aircraft components"> <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 components" 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 components"> <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> 4408</div> </div> </div> </div> <h1 class="mt-3 mb-3 text-center" style="font-size:1.6rem;">Search results for: aircraft components</h1> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">4408</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">4407</span> Packaging in the Design Synthesis of Novel Aircraft Configuration</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Paul%20Okonkwo">Paul Okonkwo</a>, <a href="https://publications.waset.org/abstracts/search?q=Howard%20Smith"> Howard Smith</a> </p> <p class="card-text"><strong>Abstract:</strong></p> A study to estimate the size of the cabin and major aircraft components as well as detect and avoid interference between internally placed components and the external surface, during the conceptual design synthesis and optimisation to explore the design space of a BWB, was conducted. Sizing of components follows the Bradley cabin sizing and rubber engine scaling procedures to size the cabin and engine respectively. The interference detection and avoidance algorithm relies on the ability of the Class Shape Transform parameterisation technique to generate polynomial functions of the surfaces of a BWB aircraft configuration from the sizes of the cabin and internal objects using few variables. Interference detection is essential in packaging of non-conventional configuration like the BWB because of the non-uniform airfoil-shaped sections and resultant varying internal space. The unique configuration increases the need for a methodology to prevent objects from being placed in locations that do not sufficiently enclose them within the geometry. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=packaging" title="packaging">packaging</a>, <a href="https://publications.waset.org/abstracts/search?q=optimisation" title=" optimisation"> optimisation</a>, <a href="https://publications.waset.org/abstracts/search?q=BWB" title=" BWB"> BWB</a>, <a href="https://publications.waset.org/abstracts/search?q=parameterisation" title=" parameterisation"> parameterisation</a>, <a href="https://publications.waset.org/abstracts/search?q=aircraft%20conceptual%20design" title=" aircraft conceptual design"> aircraft conceptual design</a> </p> <a href="https://publications.waset.org/abstracts/33498/packaging-in-the-design-synthesis-of-novel-aircraft-configuration" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/33498.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">463</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">4406</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">4405</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">4404</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">4403</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">4402</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">4401</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">4400</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">4399</span> Multi-Disciplinary Optimisation Methodology for Aircraft Load Prediction </h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Sudhir%20Kumar%20Tiwari">Sudhir Kumar Tiwari</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The paper demonstrates a methodology that can be used at an early design stage of any conventional aircraft. This research activity assesses the feasibility derivation of methodology for aircraft loads estimation during the various phases of design for a transport category aircraft by utilizing potential of using commercial finite element analysis software, which may drive significant time saving. Early Design phase have limited data and quick changing configuration results in handling of large number of load cases. It is useful to idealize the aircraft as a connection of beams, which can be very accurately modelled using finite element analysis (beam elements). This research explores the correct approach towards idealizing an aircraft using beam elements. FEM Techniques like inertia relief were studied for implementation during course of work. The correct boundary condition technique envisaged for generation of shear force, bending moment and torque diagrams for the aircraft. The possible applications of this approach are the aircraft design process, which have been investigated. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=multi-disciplinary%20optimization" title="multi-disciplinary optimization">multi-disciplinary optimization</a>, <a href="https://publications.waset.org/abstracts/search?q=aircraft%20load" title=" aircraft load"> aircraft load</a>, <a href="https://publications.waset.org/abstracts/search?q=finite%20element%20analysis" title=" finite element analysis"> finite element analysis</a>, <a href="https://publications.waset.org/abstracts/search?q=stick%20model" title=" stick model"> stick model</a> </p> <a href="https://publications.waset.org/abstracts/70989/multi-disciplinary-optimisation-methodology-for-aircraft-load-prediction" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/70989.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">352</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">4398</span> Aircraft Components, Manufacturing and Design: Opportunities, Bottlenecks, and Challenges</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Ionel%20Botef">Ionel Botef</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Aerospace products operate in very aggressive environments characterized by high temperature, high pressure, large stresses on individual components, the presence of oxidizing and corroding atmosphere, as well as internally created or externally ingested particulate materials that induce erosion and impact damage. Consequently, during operation, the materials of individual components degrade. In addition, the impact of maintenance costs for both civil and military aircraft was estimated at least two to three times greater than initial purchase values, and this trend is expected to increase. As a result, for viable product realisation and maintenance, a spectrum of issues regarding novel processing technologies, innovation of new materials, performance, costs, and environmental impact must constantly be addressed. One of these technologies, namely the cold-gas dynamic-spray process has enabled a broad range of coatings and applications, including many that have not been previously possible or commercially practical, hence its potential for new aerospace applications. Therefore, the purpose of this paper is to summarise the state of the art of this technology alongside its theoretical and experimental studies, and explore how the cold-gas dynamic-spray process could be integrated within a framework that finally could lead to more efficient aircraft maintenance. Based on the paper's qualitative findings supported by authorities, evidence, and logic essentially it is argued that the cold-gas dynamic-spray manufacturing process should not be viewed in isolation, but should be viewed as a component of a broad framework that finally leads to more efficient aerospace operations. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aerospace" title="aerospace">aerospace</a>, <a href="https://publications.waset.org/abstracts/search?q=aging%20aircraft" title=" aging aircraft"> aging aircraft</a>, <a href="https://publications.waset.org/abstracts/search?q=cold%20spray" title=" cold spray"> cold spray</a>, <a href="https://publications.waset.org/abstracts/search?q=materials" title=" materials"> materials</a> </p> <a href="https://publications.waset.org/abstracts/98936/aircraft-components-manufacturing-and-design-opportunities-bottlenecks-and-challenges" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/98936.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">121</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">4397</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">4396</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">4395</span> Minimize Wear and Tear in Y12 Aircraft Tyres</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=N.%20D.%20Hiripitiya">N. D. Hiripitiya</a>, <a href="https://publications.waset.org/abstracts/search?q=H.%20V.%20H.%20De%20Soysa"> H. V. H. De Soysa</a>, <a href="https://publications.waset.org/abstracts/search?q=H.%20S.%20U.%20Thrimavithana"> H. S. U. Thrimavithana</a>, <a href="https://publications.waset.org/abstracts/search?q=B.%20R.%20Epitawala"> B. R. Epitawala</a>, <a href="https://publications.waset.org/abstracts/search?q=K.%20A.%20D.%20D.%20Kuruppu"> K. A. D. D. Kuruppu</a>, <a href="https://publications.waset.org/abstracts/search?q=D.%20J.%20K.%20Lokupathirage"> D. J. K. Lokupathirage</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This research was related to identify the reasons which lead for early wear and tear of aircraft tyres. Further this research focused to rectify those issues in tyres with some modifications. The aircraft tyres of Y12 aircraft was selected for the study as due to Y12 aircraft fly frequently. Self-structured questionnaire was prepared and it was distributed among Y12 aircraft technicians. Based on their feedback several issues were identified related to tyre wear and tear. One of the reasons was uneven tyre wearing. But it could rectify after interchanging the tyre sides after completion of 50 landings. Several modifications were done in order to rectify all the identified issues. Several devices were constructed in order to enhance the life time of the Y12 aircraft tyre. Mechanical properties were measured for the worn-out tyres. The properties were compared with the control tyre sample. It was found that there was an average increment of tensile strength by 38.14 % of control tyre, when compared with the worn-out tyres which were completed 50 number of landings. The suggested modifications are in the process of implementation. It is confident that above mentioned solutions will lead to increase the life span of tyres in Y12 aircraft. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aircraft" title="aircraft">aircraft</a>, <a href="https://publications.waset.org/abstracts/search?q=devices" title=" devices"> devices</a>, <a href="https://publications.waset.org/abstracts/search?q=enhance%20life%20span" title=" enhance life span"> enhance life span</a>, <a href="https://publications.waset.org/abstracts/search?q=modifications%20for%20tyre%20wear" title=" modifications for tyre wear"> modifications for tyre wear</a> </p> <a href="https://publications.waset.org/abstracts/57455/minimize-wear-and-tear-in-y12-aircraft-tyres" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/57455.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">291</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">4394</span> Reliability and Maintainability Optimization for Aircraft’s Repairable Components Based on Cost Modeling Approach</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Adel%20A.%20Ghobbar">Adel A. Ghobbar</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The airline industry is continuously challenging how to safely increase the service life of the aircraft with limited maintenance budgets. Operators are looking for the most qualified maintenance providers of aircraft components, offering the finest customer service. Component owner and maintenance provider is offering an Abacus agreement (Aircraft Component Leasing) to increase the efficiency and productivity of the customer service. To increase the customer service, the current focus on No Fault Found (NFF) units must change into the focus on Early Failure (EF) units. Since the effect of EF units has a significant impact on customer satisfaction, this needs to increase the reliability of EF units at minimal cost, which leads to the goal of this paper. By identifying the reliability of early failure (EF) units with regards to No Fault Found (NFF) units, in particular, the root cause analysis with an integrated cost analysis of EF units with the use of a failure mode analysis tool and a cost model, there will be a set of EF maintenance improvements. The data used for the investigation of the EF units will be obtained from the Pentagon system, an Enterprise Resource Planning (ERP) system used by Fokker Services. The Pentagon system monitors components, which needs to be repaired from Fokker aircraft owners, Abacus exchange pool, and commercial customers. The data will be selected on several criteria’s: time span, failure rate, and cost driver. When the selected data has been acquired, the failure mode and root cause analysis of EF units are initiated. The failure analysis approach tool was implemented, resulting in the proposed failure solution of EF. This will lead to specific EF maintenance improvements, which can be set-up to decrease the EF units and, as a result of this, increasing the reliability. The investigated EFs, between the time period over ten years, showed to have a significant reliability impact of 32% on the total of 23339 unscheduled failures. Since the EFs encloses almost one-third of the entire population. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=supportability" title="supportability">supportability</a>, <a href="https://publications.waset.org/abstracts/search?q=no%20fault%20found" title=" no fault found"> no fault found</a>, <a href="https://publications.waset.org/abstracts/search?q=FMEA" title=" FMEA"> FMEA</a>, <a href="https://publications.waset.org/abstracts/search?q=early%20failure" title=" early failure"> early failure</a>, <a href="https://publications.waset.org/abstracts/search?q=availability" title=" availability"> availability</a>, <a href="https://publications.waset.org/abstracts/search?q=operational%20reliability" title=" operational reliability"> operational reliability</a>, <a href="https://publications.waset.org/abstracts/search?q=predictive%20model" title=" predictive model"> predictive model</a> </p> <a href="https://publications.waset.org/abstracts/108910/reliability-and-maintainability-optimization-for-aircrafts-repairable-components-based-on-cost-modeling-approach" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/108910.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">127</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">4393</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">4392</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">4391</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">4390</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">4389</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">7</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">4388</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">4387</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">4386</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">4385</span> An Analysis of Different Essential Components of Flight Plan Operations at Low Altitude</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Apisit%20Nawapanpong">Apisit Nawapanpong</a>, <a href="https://publications.waset.org/abstracts/search?q=Natthapat%20Boonjerm"> Natthapat Boonjerm</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This project aims to analyze and identify the flight plan of low-altitude aviation in Thailand and other countries. The development of UAV technology has led the innovation and revolution in the aviation industry; this includes the development of new modes of passenger or freight transportation, and it has also affected other industries widely. At present, this technology is being developed rapidly and has been tested all over the world to make the most efficient for technology or innovation, and it is likely to grow more extensively. However, no flight plan for low-altitude operation has been published by the government organization; when compared with high-altitude aviation with manned aircraft, various unique factors are different, whether mission, operation, altitude range or airspace restrictions. In the study of the essential components of low-altitude operation measures to be practical and tangible, there were major problems, so the main consideration of this project is to analyze the components of low-altitude operations which are conducted up to the altitudes of 400 ft or 120 meters above ground level referring to the terrain, for example, air traffic management, classification of aircraft, basic necessity and safety, and control area. This research will focus on confirming the theory through qualitative and quantitative research combined with theoretical modeling and regulatory framework and by gaining insights from various positions in aviation industries, including aviation experts, government officials, air traffic controllers, pilots, and airline operators to identify the critical essential components of low-altitude flight operation. This project analyzes by using computer programs for science and statistics research to prove that the result is equivalent to the theory and be beneficial for regulating the flight plan for low-altitude operation by different essential components from this project and can be further developed for future studies and research in aviation industries. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=low-altitude%20aviation" title="low-altitude aviation">low-altitude aviation</a>, <a href="https://publications.waset.org/abstracts/search?q=UAV%20technology" title=" UAV technology"> UAV technology</a>, <a href="https://publications.waset.org/abstracts/search?q=flight%20plan" title=" flight plan"> flight plan</a>, <a href="https://publications.waset.org/abstracts/search?q=air%20traffic%20management" title=" air traffic management"> air traffic management</a>, <a href="https://publications.waset.org/abstracts/search?q=safety%20measures" title=" safety measures"> safety measures</a> </p> <a href="https://publications.waset.org/abstracts/184542/an-analysis-of-different-essential-components-of-flight-plan-operations-at-low-altitude" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/184542.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">68</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">4384</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">4383</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">4382</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">4381</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> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">4380</span> Technical Specifications of Bombardier Challenger 605 SN 5769 Aircraft</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Rohan%20Sarker">Rohan Sarker</a>, <a href="https://publications.waset.org/abstracts/search?q=Jon%20P.%20Conlon"> Jon P. Conlon</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The Bombardier Challenger 605 SN 5769 is a versatile business jet known for its superior range, advanced avionics, and spacious cabin. Powered by two General Electric CF34-3B engines, each producing 8,729 pounds of thrust, the aircraft offers a maximum range of 4,000 nautical miles, allowing for non-stop transcontinental flights. It operates at a maximum cruising speed of Mach 0.82 (541 mph) and a service ceiling of 41,000 feet, ensuring efficient, high-altitude travel. The aircraft’s avionics suite is equipped with the Rockwell Collins Pro Line 21, offering advanced navigation, communication, and weather systems. The cockpit features dual Flight Management Systems (FMS) and GPS to enhance operational safety and precision. Inside, the Challenger 605 boasts a luxurious and customizable cabin that accommodates up to 12 passengers. The aircraft also provides ample baggage space, excellent short-field performance, and impressive fuel efficiency, making it ideal for business or personal long-range travel. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aircraft" title="aircraft">aircraft</a>, <a href="https://publications.waset.org/abstracts/search?q=airframe" title=" airframe"> airframe</a>, <a href="https://publications.waset.org/abstracts/search?q=Bombardier" title=" Bombardier"> Bombardier</a>, <a href="https://publications.waset.org/abstracts/search?q=engines" title=" engines"> engines</a> </p> <a href="https://publications.waset.org/abstracts/191255/technical-specifications-of-bombardier-challenger-605-sn-5769-aircraft" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/191255.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">28</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">4379</span> GIS for Simulating Air Traffic by Applying Different Multi-radar Positioning Techniques</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Amara%20Rafik">Amara Rafik</a>, <a href="https://publications.waset.org/abstracts/search?q=Bougherara%20Maamar"> Bougherara Maamar</a>, <a href="https://publications.waset.org/abstracts/search?q=Belhadj%20Aissa%20Mostefa"> Belhadj Aissa Mostefa</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Radar data is one of the many data sources used by ATM Air Traffic Management systems. These data come from air navigation radar antennas. These radars intercept signals emitted by the various aircraft crossing the controlled airspace and calculate the position of these aircraft and retransmit their positions to the Air Traffic Management System. For greater reliability, these radars are positioned in such a way as to allow their coverage areas to overlap. An aircraft will therefore be detected by at least one of these radars. However, the position coordinates of the same aircraft and sent by these different radars are not necessarily identical. Therefore, the ATM system must calculate a single position (radar track) which will ultimately be sent to the control position and displayed on the air traffic controller's monitor. There are several techniques for calculating the radar track. Furthermore, the geographical nature of the problem requires the use of a Geographic Information System (GIS), i.e. a geographical database on the one hand and geographical processing. The objective of this work is to propose a GIS for traffic simulation which reconstructs the evolution over time of aircraft positions from a multi-source radar data set and by applying these different techniques. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=ATM" title="ATM">ATM</a>, <a href="https://publications.waset.org/abstracts/search?q=GIS" title=" GIS"> GIS</a>, <a href="https://publications.waset.org/abstracts/search?q=radar%20data" title=" radar data"> radar data</a>, <a href="https://publications.waset.org/abstracts/search?q=air%20traffic%20simulation" title=" air traffic simulation"> air traffic simulation</a> </p> <a href="https://publications.waset.org/abstracts/168613/gis-for-simulating-air-traffic-by-applying-different-multi-radar-positioning-techniques" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/168613.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">85</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%20components&page=2">2</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=aircraft%20components&page=3">3</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=aircraft%20components&page=4">4</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=aircraft%20components&page=5">5</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=aircraft%20components&page=6">6</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=aircraft%20components&page=7">7</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=aircraft%20components&page=8">8</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=aircraft%20components&page=9">9</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=aircraft%20components&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%20components&page=146">146</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=aircraft%20components&page=147">147</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=aircraft%20components&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>