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aircraft</title> <meta name="description" content="Search results for: commercial aircraft"> <meta name="keywords" content="commercial aircraft"> <meta name="viewport" content="width=device-width, initial-scale=1, minimum-scale=1, maximum-scale=1, user-scalable=no"> <meta charset="utf-8"> <link href="https://cdn.waset.org/favicon.ico" type="image/x-icon" rel="shortcut icon"> <link href="https://cdn.waset.org/static/plugins/bootstrap-4.2.1/css/bootstrap.min.css" rel="stylesheet"> <link href="https://cdn.waset.org/static/plugins/fontawesome/css/all.min.css" rel="stylesheet"> <link href="https://cdn.waset.org/static/css/site.css?v=150220211555" rel="stylesheet"> </head> <body> <header> <div class="container"> <nav class="navbar navbar-expand-lg navbar-light"> <a class="navbar-brand" href="https://waset.org"> <img src="https://cdn.waset.org/static/images/wasetc.png" alt="Open Science Research Excellence" title="Open Science Research Excellence" /> </a> <button class="d-block d-lg-none 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action="https://publications.waset.org/abstracts/search"> <div id="custom-search-input"> <div class="input-group"> <i class="fas fa-search"></i> <input type="text" class="search-query" name="q" placeholder="Author, Title, Abstract, Keywords" value="commercial aircraft"> <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> 2784</div> </div> </div> </div> <h1 class="mt-3 mb-3 text-center" style="font-size:1.6rem;">Search results for: commercial aircraft</h1> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">2784</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">2783</span> Feasibility of Deployable Encasing for a CVDR (Cockpit Voice and Data Recorder) in Commercial Aircraft</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Vishnu%20Nair">Vishnu Nair</a>, <a href="https://publications.waset.org/abstracts/search?q=Rohan%20Kapoor"> Rohan Kapoor</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Recent commercial aircraft crashes demand a paradigm shift in how the CVDRs are located and recovered, particularly if the aircraft crashes in the sea. CVDR (Cockpit Voice and Data Recorder) is most vital component out of the entire wreckage that can be obtained in order to investigate the sequence of events leading to the crash. It has been a taxing and exorbitantly expensive process locating and retrieving the same in the massive water bodies as it was seen in the air crashes in the recent past, taking the unfortunate Malaysia airlines MH-370 crash into account. The study aims to provide an aid to the persisting problem by improving the buoyant as-well-as the aerodynamic properties of the proposed CVDR encasing. Alongside this the placement of the deployable CVDR on the surface of the aircraft and floatability in case of water submersion are key factors which are taken into consideration for a better resolution to the problem. All of which results into the Deployable-CVDR emerging to the surface of the water-body. Also the whole system is designed such that it can be seamlessly integrated with the current crop of commercial aircraft. The work is supported by carrying out a computational study with the help Ansys-Fluent combination. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=encasing" title="encasing">encasing</a>, <a href="https://publications.waset.org/abstracts/search?q=buoyancy" title=" buoyancy"> buoyancy</a>, <a href="https://publications.waset.org/abstracts/search?q=deployable%20CVDR" title=" deployable CVDR"> deployable CVDR</a>, <a href="https://publications.waset.org/abstracts/search?q=floatability" title=" floatability"> floatability</a>, <a href="https://publications.waset.org/abstracts/search?q=water%20submersion" title=" water submersion"> water submersion</a> </p> <a href="https://publications.waset.org/abstracts/31436/feasibility-of-deployable-encasing-for-a-cvdr-cockpit-voice-and-data-recorder-in-commercial-aircraft" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/31436.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">299</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">2782</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">2781</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">2780</span> The Influence of Variable Geometrical Modifications of the Trailing Edge of Supercritical Airfoil on the Characteristics of Aerodynamics</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=P.%20Lauk">P. Lauk</a>, <a href="https://publications.waset.org/abstracts/search?q=K.%20E.%20Seegel"> K. E. Seegel</a>, <a href="https://publications.waset.org/abstracts/search?q=T.%20T%C3%A4hemaa"> T. Tähemaa</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The fuel consumption of modern, high wing loading, commercial aircraft in the first stage of flight is high because the usable flight level is lower and the weather conditions (jet stream) have great impact on aircraft performance. To reduce the fuel consumption, it is necessary to raise during first stage of flight the L/D ratio value within Cl 0.55-0.65. Different variable geometrical wing trailing edge modifications of SC(2)-410 airfoil were compared at M 0.78 using the CFD software STAR-CCM+ simulation based Reynolds-averaged Navier-Stokes (RANS) equations. The numerical results obtained show that by increasing the width of the airfoil by 4% and by modifying the trailing edge airfoil, it is possible to decrease airfoil drag at Cl 0.70 for up to 26.6% and at the same time to increase commercial aircraft L/D ratio for up to 5.0%. Fuel consumption can be reduced in proportion to the increase in L/D ratio. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=L%2FD%20ratio" title="L/D ratio">L/D ratio</a>, <a href="https://publications.waset.org/abstracts/search?q=miniflaps" title=" miniflaps"> miniflaps</a>, <a href="https://publications.waset.org/abstracts/search?q=mini-TED" title=" mini-TED"> mini-TED</a>, <a href="https://publications.waset.org/abstracts/search?q=supercritical%20airfoil" title=" supercritical airfoil"> supercritical airfoil</a> </p> <a href="https://publications.waset.org/abstracts/85202/the-influence-of-variable-geometrical-modifications-of-the-trailing-edge-of-supercritical-airfoil-on-the-characteristics-of-aerodynamics" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/85202.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">207</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">2779</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">2778</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">263</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">2777</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">567</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">2776</span> Aircraft Landing Process Simulation Using Multi-Body Multi-Dynamics Software</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Ahmad%20Kavousi">Ahmad Kavousi</a>, <a href="https://publications.waset.org/abstracts/search?q=Ali%20Delaviz"> Ali Delaviz</a> </p> <p class="card-text"><strong>Abstract:</strong></p> In this project, the landing process is simulated by using of multi-body dynamics commercial software. Various factors, including landing situations, aircraft structures and climate are used in this simulation. The purpose of this project is to determine the forces exerted on the aircraft landing gears in landing process in various landing conditions. For this purpose, the ADAMS multi-body dynamics software is used. Different scenarios based on FAR-25, including level landing, tail-down landing, crab landing are simulated. Results of dynamic simulation software with landing load factor obtained from the analytical solution are compared. The effect of fuselage elasticity on the landing load is studied. For this purpose, both of elastic and rigid body assumptions are used in the simulation process, and the results are compared and some conclusions are made. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=landing%20gear" title="landing gear">landing gear</a>, <a href="https://publications.waset.org/abstracts/search?q=landing%20process" title=" landing process"> landing process</a>, <a href="https://publications.waset.org/abstracts/search?q=aircraft" title=" aircraft"> aircraft</a>, <a href="https://publications.waset.org/abstracts/search?q=multi-body%20dynamics" title=" multi-body dynamics"> multi-body dynamics</a> </p> <a href="https://publications.waset.org/abstracts/37773/aircraft-landing-process-simulation-using-multi-body-multi-dynamics-software" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/37773.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">497</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">2775</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">2774</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">2773</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">2772</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">2771</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">2770</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">290</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">2769</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">2768</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">532</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">2767</span> Lifting Body Concepts for Unmanned Fixed-Wing Transport Aircrafts</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Anand%20R.%20Nair">Anand R. Nair</a>, <a href="https://publications.waset.org/abstracts/search?q=Markus%20Trenker"> Markus Trenker</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Lifting body concepts were conceived as early as 1917 and patented by Roy Scroggs. It was an idea of using the fuselage as a lift producing body with no or small wings. Many of these designs were developed and even flight tested between 1920’s to 1970’s, but it was not pursued further for commercial flight as at lower airspeeds, such a configuration was incapable to produce sufficient lift for the entire aircraft. The concept presented in this contribution is combining the lifting body design along with a fixed wing to maximise the lift produced by the aircraft. Conventional aircraft fuselages are designed to be aerodynamically efficient, which is to minimise the drag; however, these fuselages produce very minimal or negligible lift. For the design of an unmanned fixed wing transport aircraft, many of the restrictions which are present for commercial aircraft in terms of fuselage design can be excluded, such as windows for the passengers/pilots, cabin-environment systems, emergency exits, and pressurization systems. This gives new flexibility to design fuselages which are unconventionally shaped to contribute to the lift of the aircraft. The two lifting body concepts presented in this contribution are targeting different applications: For a fast cargo delivery drone, the fuselage is based on a scaled airfoil shape with a cargo capacity of 500 kg for euro pallets. The aircraft has a span of 14 m and reaches 1500 km at a cruising speed of 90 m/s. The aircraft could also easily be adapted to accommodate pilot and passengers with modifications to the internal structures, but pressurization is not included as the service ceiling envisioned for this type of aircraft is limited to 10,000 ft. The next concept to be investigated is called a multi-purpose drone, which incorporates a different type of lifting body and is a much more versatile aircraft as it will have a VTOL capability. The aircraft will have a wingspan of approximately 6 m and flight speeds of 60 m/s within the same service ceiling as the fast cargo delivery drone. The multi-purpose drone can be easily adapted for various applications such as firefighting, agricultural purposes, surveillance, and even passenger transport. Lifting body designs are not a new concept, but their effectiveness in terms of cargo transportation has not been widely investigated. Due to their enhanced lift producing capability, lifting body designs enable the reduction of the wing area and the overall weight of the aircraft. This will, in turn, reduce the thrust requirement and ultimately the fuel consumption. The various designs proposed in this contribution will be based on the general aviation category of aircrafts and will be focussed on unmanned methods of operation. These unmanned fixed-wing transport drones will feature appropriate cargo loading/unloading concepts which can accommodate large size cargo for efficient time management and ease of operation. The various designs will be compared in performance to their conventional counterpart to understand their benefits/shortcomings in terms of design, performance, complexity, and ease of operation. The majority of the performance analysis will be carried out using industry relevant standards in computational fluid dynamics software packages. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=lifting%20body%20concept" title="lifting body concept">lifting body concept</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=unmanned%20fixed-wing%20aircraft" title=" unmanned fixed-wing aircraft"> unmanned fixed-wing aircraft</a>, <a href="https://publications.waset.org/abstracts/search?q=cargo%20drone" title=" cargo drone"> cargo drone</a> </p> <a href="https://publications.waset.org/abstracts/140026/lifting-body-concepts-for-unmanned-fixed-wing-transport-aircrafts" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/140026.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">246</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">2766</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">480</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">2765</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">2764</span> Physicochemical-Mechanical, Thermal and Rheological Properties Analysis of Pili Tree (Canarium Ovatum) Resin as Aircraft Integral Fuel Tank Sealant</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Mark%20Kennedy">Mark Kennedy</a>, <a href="https://publications.waset.org/abstracts/search?q=E.%20Bantugon"> E. Bantugon</a>, <a href="https://publications.waset.org/abstracts/search?q=Noruane%20A.%20Daileg"> Noruane A. Daileg</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Leaks arising from aircraft fuel tanks is a protracted problem for the aircraft manufacturers, operators, and maintenance crews. It principally arises from stress, structural defects, or degraded sealants as the aircraft age. It can be ignited by different sources, which can result in catastrophic flight and consequences, exhibiting a major drain both on time and budget. In order to mitigate and eliminate this kind of problem, the researcher produced an experimental sealant having a base material of natural tree resin, the Pili Tree Resin. Aside from producing an experimental sealant, the main objective of this research is to analyze its physical, chemical, mechanical, thermal, and rheological properties, which is beneficial and effective for specific aircraft parts, particularly the integral fuel tank. The experimental method of research was utilized in this study since it is a product invention. This study comprises two parts, specifically the Optimization Process and the Characterization Process. In the Optimization Process, the experimental sealant was subjected to the Flammability Test, an important test and consideration according to 14 Code of Federal Regulation Appendix N, Part 25 - Fuel Tank Flammability Exposure and Reliability Analysis, to get the most suitable formulation. Followed by the Characterization Process, where the formulated experimental sealant has undergone thirty-eight (38) different standard testing including Organoleptic, Instrumental Color Measurement Test, Smoothness of Appearance Test, Miscibility Test, Boiling Point Test, Flash Point Test, Curing Time, Adhesive Test, Toxicity Test, Shore A Hardness Test, Compressive Strength, Shear Strength, Static Bending Strength, Tensile Strength, Peel Strength Test, Knife Test, Adhesion by Tape Test, Leakage Test), Drip Test, Thermogravimetry-Differential Thermal Analysis (TG-DTA), Differential Scanning Calorimetry, Calorific Value, Viscosity Test, Creep Test, and Anti-Sag Resistance Test to determine and analyze the five (5) material properties of the sealant. The numerical values of the mentioned tests are determined using product application, testing, and calculation. These values are then used to calculate the efficiency of the experimental sealant. Accordingly, this efficiency is the means of comparison between the experimental and commercial sealant. Based on the results of the different standard testing conducted, the experimental sealant exceeded all the data results of the commercial sealant. This result shows that the physicochemical-mechanical, thermal, and rheological properties of the experimental sealant are far more effective as an aircraft integral fuel tank sealant alternative in comparison to the commercial sealant. Therefore, Pili Tree possesses a new role and function: a source of ingredients in sealant production. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=Aircraft%20Integral%20Fuel%20Tank" title="Aircraft Integral Fuel Tank">Aircraft Integral Fuel Tank</a>, <a href="https://publications.waset.org/abstracts/search?q=Physicochemi-mechanical" title=" Physicochemi-mechanical"> Physicochemi-mechanical</a>, <a href="https://publications.waset.org/abstracts/search?q=Pili%20Tree%20Resin" title=" Pili Tree Resin"> Pili Tree Resin</a>, <a href="https://publications.waset.org/abstracts/search?q=Properties" title=" Properties"> Properties</a>, <a href="https://publications.waset.org/abstracts/search?q=Rheological" title=" Rheological"> Rheological</a>, <a href="https://publications.waset.org/abstracts/search?q=Sealant" title=" Sealant"> Sealant</a>, <a href="https://publications.waset.org/abstracts/search?q=Thermal" title=" Thermal"> Thermal</a> </p> <a href="https://publications.waset.org/abstracts/126149/physicochemical-mechanical-thermal-and-rheological-properties-analysis-of-pili-tree-canarium-ovatum-resin-as-aircraft-integral-fuel-tank-sealant" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/126149.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">294</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">2763</span> Optimum Flight Altitude</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Ravi%20Nandu">Ravi Nandu</a>, <a href="https://publications.waset.org/abstracts/search?q=Anmol%20Taploo"> Anmol Taploo</a> </p> <p class="card-text"><strong>Abstract:</strong></p> As per current scenario, commercial aircrafts have been very well functioning with higher efficiency, but there is something that affects it. Every aircraft runs with the combustion produced by mixture of fuel and air. For example: A flight to travel from Mumbai to Kolkata it takes 2h: 30 min and from Kolkata to Mumbai it takes 2h: 45 min. It happens due to head and tail wind. Due to head wind air craft travels faster than its usual velocity and it takes 2h: 30 min to reach to Kolkata, while it takes 2h;45min vis versa. This lag in time is caused due to head wind that increases the drag and reduces the relative velocity of the plane. So in order to reduce this wastage of fuel there is an optimal flight altitude at which the head and tail wind action is reduced compared to the present scenario. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=drag" title="drag">drag</a>, <a href="https://publications.waset.org/abstracts/search?q=head%20wind" title=" head wind"> head wind</a>, <a href="https://publications.waset.org/abstracts/search?q=tail%20wind" title=" tail wind"> tail wind</a>, <a href="https://publications.waset.org/abstracts/search?q=aircraft" title=" aircraft"> aircraft</a> </p> <a href="https://publications.waset.org/abstracts/16394/optimum-flight-altitude" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/16394.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">468</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">2762</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">2761</span> Adaptive Environmental Control System Strategy for Cabin Air Quality in Commercial Aircrafts</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Paolo%20Grasso">Paolo Grasso</a>, <a href="https://publications.waset.org/abstracts/search?q=Sai%20Kalyan%20Yelike"> Sai Kalyan Yelike</a>, <a href="https://publications.waset.org/abstracts/search?q=Federico%20Benzi"> Federico Benzi</a>, <a href="https://publications.waset.org/abstracts/search?q=Mathieu%20Le%20Cam"> Mathieu Le Cam</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The cabin air quality (CAQ) in commercial aircraft is of prime interest, especially in the context of the COVID-19 pandemic. Current Environmental Control Systems (ECS) rely on a prescribed fresh airflow per passenger to dilute contaminants. An adaptive ECS strategy is proposed, leveraging air sensing and filtration technologies to ensure a better CAQ. This paper investigates the CAQ level achieved in commercial aircraft’s cabin during various flight scenarios. The modeling and simulation analysis is performed in a Modelica-based environment describing the dynamic behavior of the system. The model includes the following three main systems: cabin, recirculation loop and air-conditioning pack. The cabin model evaluates the thermo-hygrometric conditions and the air quality in the cabin depending on the number of passengers and crew members, the outdoor conditions and the conditions of the air supplied to the cabin. The recirculation loop includes models of the recirculation fan, ordinary and novel filtration technology, mixing chamber and outflow valve. The air-conditioning pack includes models of heat exchangers and turbomachinery needed to condition the hot pressurized air bled from the engine, as well as selected contaminants originated from the outside or bled from the engine. Different ventilation control strategies are modeled and simulated. Currently, a limited understanding of contaminant concentrations in the cabin and the lack of standardized and systematic methods to collect and record data constitute a challenge in establishing a causal relationship between CAQ and passengers' comfort. As a result, contaminants are neither measured nor filtered during flight, and the current sub-optimal way to avoid their accumulation is their dilution with the fresh air flow. However, the use of a prescribed amount of fresh air comes with a cost, making the ECS the most energy-demanding non-propulsive system within an aircraft. In such a context, this study shows that an ECS based on a reduced and adaptive fresh air flow, and relying on air sensing and filtration technologies, provides promising results in terms of CAQ control. The comparative simulation results demonstrate that the proposed adaptive ECS brings substantial improvements to the CAQ in terms of both controlling the asymptotic values of the concentration of the contaminant and in mitigating hazardous scenarios, such as fume events. Original architectures allowing for adaptive control of the inlet air flow rate based on monitored CAQ will change the requirements for filtration systems and redefine the ECS operation. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=cabin%20air%20quality" title="cabin air quality">cabin air quality</a>, <a href="https://publications.waset.org/abstracts/search?q=commercial%20aircraft" title=" commercial aircraft"> commercial aircraft</a>, <a href="https://publications.waset.org/abstracts/search?q=environmental%20control%20system" title=" environmental control system"> environmental control system</a>, <a href="https://publications.waset.org/abstracts/search?q=ventilation" title=" ventilation"> ventilation</a> </p> <a href="https://publications.waset.org/abstracts/152286/adaptive-environmental-control-system-strategy-for-cabin-air-quality-in-commercial-aircrafts" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/152286.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">100</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">2760</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">137</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">2759</span> Image Based Landing Solutions for Large Passenger Aircraft</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Thierry%20Sammour%20Sawaya">Thierry Sammour Sawaya</a>, <a href="https://publications.waset.org/abstracts/search?q=Heikki%20Deschacht"> Heikki Deschacht</a> </p> <p class="card-text"><strong>Abstract:</strong></p> In commercial aircraft operations, almost half of the accidents happen during approach or landing phases. Automatic guidance and automatic landings have proven to bring significant safety value added for this challenging landing phase. This is why Airbus and ScioTeq have decided to work together to explore the capability of image-based landing solutions as additional landing aids to further expand the possibility to perform automatic approach and landing to runways where the current guiding systems are either not fitted or not optimum. Current systems for automated landing often depend on radio signals provided by airport ground infrastructure on the airport or satellite coverage. In addition, these radio signals may not always be available with the integrity and performance required for safe automatic landing. Being independent from these radio signals would widen the operations possibilities and increase the number of automated landings. Airbus and ScioTeq are joining their expertise in the field of Computer Vision in the European Program called Clean Sky 2 Large Passenger Aircraft, in which they are leading the IMBALS (IMage BAsed Landing Solutions) project. The ultimate goal of this project is to demonstrate, develop, validate and verify a certifiable automatic landing system guiding an airplane during the approach and landing phases based on an onboard camera system capturing images, enabling automatic landing independent from radio signals and without precision instrument for landing. In the frame of this project, ScioTeq is responsible for the development of the Image Processing Platform (IPP), while Airbus is responsible for defining the functional and system requirements as well as the testing and integration of the developed equipment in a Large Passenger Aircraft representative environment. The aim of this paper will be to describe the system as well as the associated methods and tools developed for validation and verification. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aircraft%20landing%20system" title="aircraft landing system">aircraft landing system</a>, <a href="https://publications.waset.org/abstracts/search?q=aircraft%20safety" title=" aircraft safety"> aircraft safety</a>, <a href="https://publications.waset.org/abstracts/search?q=autoland" title=" autoland"> autoland</a>, <a href="https://publications.waset.org/abstracts/search?q=avionic%20system" title=" avionic system"> avionic system</a>, <a href="https://publications.waset.org/abstracts/search?q=computer%20vision" title=" computer vision"> computer vision</a>, <a href="https://publications.waset.org/abstracts/search?q=image%20processing" title=" image processing"> image processing</a> </p> <a href="https://publications.waset.org/abstracts/157558/image-based-landing-solutions-for-large-passenger-aircraft" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/157558.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">101</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">2758</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">2757</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">2756</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">2755</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> <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=commercial%20aircraft&page=2">2</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=commercial%20aircraft&page=3">3</a></li> <li class="page-item"><a class="page-link" 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