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pitch angle</title> <meta name="description" content="Search results for: minimum pitch angle"> <meta name="keywords" content="minimum pitch angle"> <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="minimum pitch angle"> <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> 3488</div> </div> </div> </div> <h1 class="mt-3 mb-3 text-center" style="font-size:1.6rem;">Search results for: minimum pitch angle</h1> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">3488</span> Prediction of the Aerodynamic Stall of a Helicopter鈥檚 Main Rotor Using a Computational Fluid Dynamics Analysis</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Assel%20Thami%20Lahlou">Assel Thami Lahlou</a>, <a href="https://publications.waset.org/abstracts/search?q=Soufiane%20Stouti"> Soufiane Stouti</a>, <a href="https://publications.waset.org/abstracts/search?q=Ismail%20Lagrat"> Ismail Lagrat</a>, <a href="https://publications.waset.org/abstracts/search?q=Hamid%20Mounir"> Hamid Mounir</a>, <a href="https://publications.waset.org/abstracts/search?q=Oussama%20Bouazaoui"> Oussama Bouazaoui</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The purpose of this research work is to predict the helicopter from stalling by finding the minimum and maximum values that the pitch angle can take in order to fly in a hover state condition. The stall of a helicopter in hover occurs when the pitch angle is too small to generate the thrust required to support its weight or when the critical angle of attack that gives maximum lift is reached or exceeded. In order to find the minimum pitch angle, a 3D CFD simulation was done in this work using ANSYS FLUENT as the CFD solver. We started with a small value of the pitch angle 胃, and we kept increasing its value until we found the thrust coefficient required to fly in a hover state and support the weight of the helicopter. For the CFD analysis, the Multiple Reference Frame (MRF) method with k-蔚 turbulent model was used to study the 3D flow around the rotor for 胃min. On the other hand, a 2D simulation of the airfoil NACA 0012 was executed with a velocity inlet Vin=惟R/2 to visualize the flow at the location span R/2 of the disk rotor using the Spallart-Allmaras turbulent model. Finding the critical angle of attack at this position will give us the ability to predict the stall in hover flight. The results obtained will be exposed later in the article. This study was so useful in analyzing the limitations of the helicopter鈥檚 main rotor and thus, in predicting accidents that can lead to a lot of damage. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aerodynamic" title="aerodynamic">aerodynamic</a>, <a href="https://publications.waset.org/abstracts/search?q=CFD" title=" CFD"> CFD</a>, <a href="https://publications.waset.org/abstracts/search?q=helicopter" title=" helicopter"> helicopter</a>, <a href="https://publications.waset.org/abstracts/search?q=stall" title=" stall"> stall</a>, <a href="https://publications.waset.org/abstracts/search?q=blades" title=" blades"> blades</a>, <a href="https://publications.waset.org/abstracts/search?q=main%20rotor" title=" main rotor"> main rotor</a>, <a href="https://publications.waset.org/abstracts/search?q=minimum%20pitch%20angle" title=" minimum pitch angle"> minimum pitch angle</a>, <a href="https://publications.waset.org/abstracts/search?q=maximum%20pitch%20angle" title=" maximum pitch angle"> maximum pitch angle</a> </p> <a href="https://publications.waset.org/abstracts/186086/prediction-of-the-aerodynamic-stall-of-a-helicopters-main-rotor-using-a-computational-fluid-dynamics-analysis" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/186086.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">81</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">3487</span> Hybrid GA-PSO Based Pitch Controller Design for Aircraft Control System </h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Vaibhav%20Singh%20%20Rajput">Vaibhav Singh Rajput</a>, <a href="https://publications.waset.org/abstracts/search?q=Ravi%20Kumar%20Jatoth"> Ravi Kumar Jatoth</a>, <a href="https://publications.waset.org/abstracts/search?q=Nagu%20Bhookya"> Nagu Bhookya</a>, <a href="https://publications.waset.org/abstracts/search?q=Bhasker%20Boda"> Bhasker Boda</a> </p> <p class="card-text"><strong>Abstract:</strong></p> In this paper proportional, integral, derivative (PID) controller is used to control the pitch angle of the aircraft when the elevation angle is changed or modified. The pitch angle is dependent on elevation angle; a change in one corresponds to a change in the other. The PID controller helps in restricted change of pitch rate in response to the elevation angle. The PID controller is dependent on different parameters like Kp, Ki, Kd which change the pitch rate as they change. Various methodologies are used for changing those parameters for getting a perfect time response pitch angle, as desired or wished by a concerned person. While reckoning the values of those parameters, trial and guessing may prove to be futile in order to provide comfort to passengers. So, using some metaheuristic techniques can be useful in handling these errors. Hybrid GA-PSO is one such powerful algorithm which can improve transient and steady state response and can give us more reliable results for PID gain scheduling problem. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=pitch%20rate" title="pitch rate">pitch rate</a>, <a href="https://publications.waset.org/abstracts/search?q=elevation%20angle" title=" elevation angle"> elevation angle</a>, <a href="https://publications.waset.org/abstracts/search?q=PID%20controller" title=" PID controller"> PID controller</a>, <a href="https://publications.waset.org/abstracts/search?q=genetic%20algorithm" title=" genetic algorithm"> genetic algorithm</a>, <a href="https://publications.waset.org/abstracts/search?q=particle%20swarm%20optimization" title=" particle swarm optimization"> particle swarm optimization</a>, <a href="https://publications.waset.org/abstracts/search?q=phugoid" title=" phugoid"> phugoid</a> </p> <a href="https://publications.waset.org/abstracts/64457/hybrid-ga-pso-based-pitch-controller-design-for-aircraft-control-system" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/64457.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">328</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">3486</span> Study on Angle Measurement Interferometer around Any Axis Direction Selected by Transmissive Liquid Crystal Device </h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=R.%20Furutani">R. Furutani</a>, <a href="https://publications.waset.org/abstracts/search?q=G.%20Kikuchi"> G. Kikuchi</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Generally, the optical interferometer system is too complicated and difficult to change the measurement items, pitch, yaw, and row, etc. In this article, the optical interferometer system using the transmissive Liquid Crystal Device (LCD) as the switch of the optical path was proposed. At first, the normal optical interferometer, Michelson interferometer, was constructed to measure the pitch angle and the yaw angle. In this optical interferometer, the ball lenses with the refractive indices of 2.0 were used as the retroreflectors. After that, the transmissive LCD was introduced as the switch to select the adequate optical path. In this article, these optical systems were constructed. Pitch measurement interferometer and yaw measurement interferometer were switched by the transmissive LCD. When the LCD was open for the yaw measurement, the yaw was sufficiently measured and optical path for the pitch measurement was blocked. On the other hand, when the LCD was open for the pitch measurement, the pitch was measured and the optical path for the yaw measurement was also blocked. In this article, the results of both of pitch measurement and yaw measurement were shown, and the result of blocked yaw measurement and pitch measurement were shown. As this measurement system was based on Michelson interferometer, the other measuring items, the deviation along the optical axis, the vertical deviation to the optical axis and row angle, could be measured by the additional ball lenses and the additional switching in future work. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=any%20direction%20angle" title="any direction angle">any direction angle</a>, <a href="https://publications.waset.org/abstracts/search?q=ball%20lens" title=" ball lens"> ball lens</a>, <a href="https://publications.waset.org/abstracts/search?q=laser%20interferometer" title=" laser interferometer"> laser interferometer</a>, <a href="https://publications.waset.org/abstracts/search?q=transmissive%20liquid%20crystal%20device" title=" transmissive liquid crystal device"> transmissive liquid crystal device</a> </p> <a href="https://publications.waset.org/abstracts/106989/study-on-angle-measurement-interferometer-around-any-axis-direction-selected-by-transmissive-liquid-crystal-device" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/106989.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">3485</span> Dynamic Modeling of Wind Farms in the Jeju Power System</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Dae-Hee%20Son">Dae-Hee Son</a>, <a href="https://publications.waset.org/abstracts/search?q=Sang-Hee%20Kang"> Sang-Hee Kang</a>, <a href="https://publications.waset.org/abstracts/search?q=Soon-Ryul%20Nam"> Soon-Ryul Nam</a> </p> <p class="card-text"><strong>Abstract:</strong></p> In this paper, we develop a dynamic modeling of wind farms in the Jeju power system. The dynamic model of wind farms is developed to study their dynamic effects on the Jeju power system. PSS/E is used to develop the dynamic model of a wind farm composed of 1.5-MW doubly fed induction generators. The output of a wind farm is regulated based on pitch angle control, in which the two controllable parameters are speed and power references. The simulation results confirm that the pitch angle is successfully controlled, regardless of the variation in wind speed and output regulation. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=dynamic%20model" title="dynamic model">dynamic model</a>, <a href="https://publications.waset.org/abstracts/search?q=Jeju%20power%20system" title=" Jeju power system"> Jeju power system</a>, <a href="https://publications.waset.org/abstracts/search?q=online%20limitation" title=" online limitation"> online limitation</a>, <a href="https://publications.waset.org/abstracts/search?q=pitch%20angle%20control" title=" pitch angle control"> pitch angle control</a>, <a href="https://publications.waset.org/abstracts/search?q=wind%20farm" title=" wind farm"> wind farm</a> </p> <a href="https://publications.waset.org/abstracts/47581/dynamic-modeling-of-wind-farms-in-the-jeju-power-system" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/47581.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">327</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">3484</span> Power Performance Improvement of 500W Vertical Axis Wind Turbine with Salient Design Parameters</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Young-Tae%20Lee">Young-Tae Lee</a>, <a href="https://publications.waset.org/abstracts/search?q=Hee-Chang%20Lim"> Hee-Chang Lim</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This paper presents the performance characteristics of Darrieus-type vertical axis wind turbine (VAWT) with NACA airfoil blades. The performance of Darrieus-type VAWT can be characterized by torque and power. There are various parameters affecting the performance such as chord length, helical angle, pitch angle and rotor diameter. To estimate the optimum shape of Darrieustype wind turbine in accordance with various design parameters, we examined aerodynamic characteristics and separated flow occurring in the vicinity of blade, interaction between flow and blade, and torque and power characteristics derived from it. For flow analysis, flow variations were investigated based on the unsteady RANS (Reynolds-averaged Navier-Stokes) equation. Sliding mesh algorithm was employed in order to consider rotational effect of blade. To obtain more realistic results we conducted experiment and numerical analysis at the same time for three-dimensional shape. In addition, several parameters (chord length, rotor diameter, pitch angle, and helical angle) were considered to find out optimum shape design and characteristics of interaction with ambient flow. Since the NACA airfoil used in this study showed significant changes in magnitude of lift and drag depending on an angle of attack, the rotor with low drag, long cord length and short diameter shows high power coefficient in low tip speed ratio (TSR) range. On the contrary, in high TSR range, drag becomes high. Hence, the short-chord and long-diameter rotor produces high power coefficient. When a pitch angle at which airfoil directs toward inside equals to -2° and helical angle equals to 0°, Darrieus-type VAWT generates maximum power. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=darrieus%20wind%20turbine" title="darrieus wind turbine">darrieus wind turbine</a>, <a href="https://publications.waset.org/abstracts/search?q=VAWT" title=" VAWT"> VAWT</a>, <a href="https://publications.waset.org/abstracts/search?q=NACA%20airfoil" title=" NACA airfoil"> NACA airfoil</a>, <a href="https://publications.waset.org/abstracts/search?q=performance" title=" performance"> performance</a> </p> <a href="https://publications.waset.org/abstracts/40354/power-performance-improvement-of-500w-vertical-axis-wind-turbine-with-salient-design-parameters" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/40354.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">373</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">3483</span> A Novel Approach to 3D Thrust Vectoring CFD via Mesh Morphing</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Umut%20Y%C4%B1ld%C4%B1z">Umut Y谋ld谋z</a>, <a href="https://publications.waset.org/abstracts/search?q=Berkin%20Kurtulu%C5%9F"> Berkin Kurtulu艧</a>, <a href="https://publications.waset.org/abstracts/search?q=Yunus%20Emre%20Musluba%C5%9F"> Yunus Emre Musluba艧</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Thrust vectoring, especially in military aviation, is a concept that sees much use to improve maneuverability in already agile aircraft. As this concept is fairly new and cost intensive to design and test, computational methods are useful in easing the preliminary design process. Computational Fluid Dynamics (CFD) can be utilized in many forms to simulate nozzle flow, and there exist various CFD studies in both 2D mechanical and 3D injection based thrust vectoring, and yet, 3D mechanical thrust vectoring analyses, at this point in time, are lacking variety. Additionally, the freely available test data is constrained to limited pitch angles and geometries. In this study, based on a test case provided by NASA, both steady and unsteady 3D CFD simulations are conducted to examine the aerodynamic performance of a mechanical thrust vectoring nozzle model and to validate the utilized numerical model. Steady analyses are performed to verify the flow characteristics of the nozzle at pitch angles of 0, 10 and 20 degrees, and the results are compared with experimental data. It is observed that the pressure data obtained on the inner surface of the nozzle at each specified pitch angle and under different flow conditions with pressure ratios of 1.5, 2 and 4, as well as at azimuthal angle of 0, 45, 90, 135, and 180 degrees exhibited a high level of agreement with the corresponding experimental results. To validate the CFD model, the insights from the steady analyses are utilized, followed by unsteady analyses covering a wide range of pitch angles from 0 to 20 degrees. Throughout the simulations, a mesh morphing method using a carefully calculated mathematical shape deformation model that simulates the vectored nozzle shape exactly at each point of its travel is employed to dynamically alter the divergent part of the nozzle over time within this pitch angle range. The mesh morphing based vectored nozzle shapes were compared with the drawings provided by NASA, ensuring a complete match was achieved. This computational approach allowed for the creation of a comprehensive database of results without the need to generate separate solution domains. The database contains results at every 0.01掳 increment of nozzle pitch angle. The unsteady analyses, generated using the morphing method, are found to be in excellent agreement with experimental data, further confirming the accuracy of the CFD model. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=thrust%20vectoring" title="thrust vectoring">thrust vectoring</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=3d%20mesh%20morphing" title=" 3d mesh morphing"> 3d mesh morphing</a>, <a href="https://publications.waset.org/abstracts/search?q=mathematical%20shape%20deformation%20model" title=" mathematical shape deformation model"> mathematical shape deformation model</a> </p> <a href="https://publications.waset.org/abstracts/170764/a-novel-approach-to-3d-thrust-vectoring-cfd-via-mesh-morphing" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/170764.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">83</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">3482</span> Influence of High-Resolution Satellites Attitude Parameters on Image Quality</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Walid%20Wahballah">Walid Wahballah</a>, <a href="https://publications.waset.org/abstracts/search?q=Taher%20Bazan"> Taher Bazan</a>, <a href="https://publications.waset.org/abstracts/search?q=Fawzy%20Eltohamy"> Fawzy Eltohamy</a> </p> <p class="card-text"><strong>Abstract:</strong></p> One of the important functions of the satellite attitude control system is to provide the required pointing accuracy and attitude stability for optical remote sensing satellites to achieve good image quality. Although offering noise reduction and increased sensitivity, time delay and integration (TDI) charge coupled devices (CCDs) utilized in high-resolution satellites (HRS) are prone to introduce large amounts of pixel smear due to the instability of the line of sight. During on-orbit imaging, as a result of the Earth鈥檚 rotation and the satellite platform instability, the moving direction of the TDI-CCD linear array and the imaging direction of the camera become different. The speed of the image moving on the image plane (focal plane) represents the image motion velocity whereas the angle between the two directions is known as the drift angle (尾). The drift angle occurs due to the rotation of the earth around its axis during satellite imaging; affecting the geometric accuracy and, consequently, causing image quality degradation. Therefore, the image motion velocity vector and the drift angle are two important factors used in the assessment of the image quality of TDI-CCD based optical remote sensing satellites. A model for estimating the image motion velocity and the drift angle in HRS is derived. The six satellite attitude control parameters represented in the derived model are the (roll angle 蠁, pitch angle 胃, yaw angle 蠄, roll angular velocity 蠁謼, pitch angular velocity 胃謼 and yaw angular velocity 蠄謼 ). The influence of these attitude parameters on the image quality is analyzed by establishing a relationship between the image motion velocity vector, drift angle and the six satellite attitude parameters. The influence of the satellite attitude parameters on the image quality is assessed by the presented model in terms of modulation transfer function (MTF) in both cross- and along-track directions. Three different cases representing the effect of pointing accuracy (蠁, 胃, 蠄) bias are considered using four different sets of pointing accuracy typical values, while the satellite attitude stability parameters are ideal. In the same manner, the influence of satellite attitude stability (蠁謼, 胃謼, 蠄謼) on image quality is also analysed for ideal pointing accuracy parameters. The results reveal that cross-track image quality is influenced seriously by the yaw angle bias and the roll angular velocity bias, while along-track image quality is influenced only by the pitch angular velocity bias. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=high-resolution%20satellites" title="high-resolution satellites">high-resolution satellites</a>, <a href="https://publications.waset.org/abstracts/search?q=pointing%20accuracy" title=" pointing accuracy"> pointing accuracy</a>, <a href="https://publications.waset.org/abstracts/search?q=attitude%20stability" title=" attitude stability"> attitude stability</a>, <a href="https://publications.waset.org/abstracts/search?q=TDI-CCD" title=" TDI-CCD"> TDI-CCD</a>, <a href="https://publications.waset.org/abstracts/search?q=smear" title=" smear"> smear</a>, <a href="https://publications.waset.org/abstracts/search?q=MTF" title=" MTF"> MTF</a> </p> <a href="https://publications.waset.org/abstracts/79548/influence-of-high-resolution-satellites-attitude-parameters-on-image-quality" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/79548.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">402</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">3481</span> Improved Pitch Detection Using Fourier Approximation Method</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Balachandra%20Kumaraswamy">Balachandra Kumaraswamy</a>, <a href="https://publications.waset.org/abstracts/search?q=P.%20G.%20Poonacha"> P. G. Poonacha</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Automatic Music Information Retrieval has been one of the challenging topics of research for a few decades now with several interesting approaches reported in the literature. In this paper we have developed a pitch extraction method based on a finite Fourier series approximation to the given window of samples. We then estimate pitch as the fundamental period of the finite Fourier series approximation to the given window of samples. This method uses analysis of the strength of harmonics present in the signal to reduce octave as well as harmonic errors. The performance of our method is compared with three best known methods for pitch extraction, namely, Yin, Windowed Special Normalization of the Auto-Correlation Function and Harmonic Product Spectrum methods of pitch extraction. Our study with artificially created signals as well as music files show that Fourier Approximation method gives much better estimate of pitch with less octave and harmonic errors. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=pitch" title="pitch">pitch</a>, <a href="https://publications.waset.org/abstracts/search?q=fourier%20series" title=" fourier series"> fourier series</a>, <a href="https://publications.waset.org/abstracts/search?q=yin" title=" yin"> yin</a>, <a href="https://publications.waset.org/abstracts/search?q=normalization%20of%20the%20auto-%20correlation%20function" title=" normalization of the auto- correlation function"> normalization of the auto- correlation function</a>, <a href="https://publications.waset.org/abstracts/search?q=harmonic%20product" title=" harmonic product"> harmonic product</a>, <a href="https://publications.waset.org/abstracts/search?q=mean%20square%20error" title=" mean square error"> mean square error</a> </p> <a href="https://publications.waset.org/abstracts/36472/improved-pitch-detection-using-fourier-approximation-method" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/36472.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">412</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">3480</span> Performance Analysis of Solar Air Heater with Fins and Perforated Twisted Tape Insert</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Rajesh%20Kumar">Rajesh Kumar</a>, <a href="https://publications.waset.org/abstracts/search?q=Prabha%20Chand"> Prabha Chand</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The present paper deals with the analytical investigation on the thermal and thermo-hydraulic performance of the solar air collector fitted with fins and perforated twisted tapes (PTT) of twist ratio 2 with different axial pitch ratio. The mathematical models are presented, and the effect of mass flow rate and axial pitch ratios on the thermal and effective efficiency has been discussed. The results obtained are compared with the results of the solar air heater without fins and twisted tapes. Results conveyed that the collectors with fins and perforated twisted tape perform better but at the expense of increased pressure drop. Also, twisted tape with minimum axial pitch ratio is found to be more efficient than others. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=solar%20air%20heater" title="solar air heater">solar air heater</a>, <a href="https://publications.waset.org/abstracts/search?q=thermal%20efficiency" title=" thermal efficiency"> thermal efficiency</a>, <a href="https://publications.waset.org/abstracts/search?q=twisted%20tape" title=" twisted tape"> twisted tape</a>, <a href="https://publications.waset.org/abstracts/search?q=twist%20ratio" title=" twist ratio"> twist ratio</a> </p> <a href="https://publications.waset.org/abstracts/70391/performance-analysis-of-solar-air-heater-with-fins-and-perforated-twisted-tape-insert" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/70391.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">266</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">3479</span> Statistical Modeling of Mandarin Tone Sandhi: Neutralization of Underlying Pitch Targets</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Si%20Chen">Si Chen</a>, <a href="https://publications.waset.org/abstracts/search?q=Caroline%20Wiltshire"> Caroline Wiltshire</a>, <a href="https://publications.waset.org/abstracts/search?q=Bin%20Li"> Bin Li</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This study statistically models the surface f0 contour and the underlying pitch target of a well-studied third sandhi tone of Mandarin Chinese. Although the growth curve analysis on the surface f0 contours indicates non-neutralization of this sandhi tone (T3) and the base T2, their underlying pitch targets do show neutralization. These results in Mandarin are also consistent with the perception of native speakers, where they cannot distinguish the third T3 from the base T2, compensating contextual variation. It is possible to use the proposed statistical procedure of testing underlying pitch targets to verify tone sandhi processes in other tonal languages. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=growth%20curve%20analysis" title="growth curve analysis">growth curve analysis</a>, <a href="https://publications.waset.org/abstracts/search?q=Mandarin%20Chinese" title=" Mandarin Chinese"> Mandarin Chinese</a>, <a href="https://publications.waset.org/abstracts/search?q=tone%20sandhi" title=" tone sandhi"> tone sandhi</a>, <a href="https://publications.waset.org/abstracts/search?q=underlying%20pitch%20target" title=" underlying pitch target"> underlying pitch target</a> </p> <a href="https://publications.waset.org/abstracts/55068/statistical-modeling-of-mandarin-tone-sandhi-neutralization-of-underlying-pitch-targets" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/55068.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">336</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">3478</span> Combined Tarsal Coalition Resection and Arthroereisis in Treatment of Symptomatic Rigid Flat Foot in Pediatric Population</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Michael%20Zaidman">Michael Zaidman</a>, <a href="https://publications.waset.org/abstracts/search?q=Naum%20Simanovsky"> Naum Simanovsky</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Introduction. Symptomatic tarsal coalition with rigid flat foot often demands operative solution. An isolated coalition resection does not guarantee pain relief; correction of co-existing foot deformity may be required. The objective of the study was to analyze the results of combination of tarsal coalition resection and arthroereisis. Patients and methods. We retrospectively reviewed medical records and radiographs of children operatively treated in our institution for symptomatic calcaneonavicular or talocalcaneal coalition between the years 2019 and 2022. Eight patients (twelve feet), 4 boys and 4 girls with mean age 11.2 years, were included in the study. In six patients (10 feet) calcaneonavicular coalition was diagnosed, two patients (two feet) sustained talonavicular coalition. To quantify degrees of foot deformity, we used calcaneal pitch angle, lateral talar-first metatarsal (Meary's) angle, and talonavicular coverage angle. The clinical results were assessed using the American Orthopaedic Foot and Ankle Society (AOFAS) Ankle Hindfoot Score. Results. The mean follow-up was 28 month. The preoperative mean talonavicular coverage angle was 17,75潞 as compared with postoperative mean angle of 5.4潞. The calcaneal pitch angle improved from mean 6,8潞 to 16,4潞. The mean preoperative Meary鈥檚 angle of -11.3潞 improved to mean 2.8潞. The preoperative mean AOFAS score improved from 54.7 to 93.1 points post-operatively. In nine of twelve feet, overall clinical outcome judged by AOFAS scale was excellent (90-100 points), in three feet was good (80-90 points). Six patients (ten feet) obviously improved their subtalar range of motion. Conclusion. For symptomatic stiff or rigid flat feet associated with tarsal coalition, the combination of coalition resection and arthroereisis leads to normalization of radiographic parameters, clinical and functional improvement with good patient鈥檚 satisfaction and likely to be more effective than the isolated procedures. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=rigid%20flat%20foot" title="rigid flat foot">rigid flat foot</a>, <a href="https://publications.waset.org/abstracts/search?q=tarsal%20coalition%20resection" title=" tarsal coalition resection"> tarsal coalition resection</a>, <a href="https://publications.waset.org/abstracts/search?q=arthroereisis" title=" arthroereisis"> arthroereisis</a>, <a href="https://publications.waset.org/abstracts/search?q=outcome" title=" outcome"> outcome</a> </p> <a href="https://publications.waset.org/abstracts/174910/combined-tarsal-coalition-resection-and-arthroereisis-in-treatment-of-symptomatic-rigid-flat-foot-in-pediatric-population" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/174910.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">64</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">3477</span> A Cross-Gender Statistical Analysis of Tuvinian Intonation Features in Comparison With Uzbek and Azerbaijani</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Daria%20Beziakina">Daria Beziakina</a>, <a href="https://publications.waset.org/abstracts/search?q=Elena%20Bulgakova"> Elena Bulgakova</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The paper deals with cross-gender and cross-linguistic comparison of pitch characteristics for Tuvinian with two other Turkic languages - Uzbek and Azerbaijani, based on the results of statistical analysis of pitch parameter values and intonation patterns used by male and female speakers. The main goal of our work is to obtain the ranges of pitch parameter values typical for Tuvinian speakers for the purpose of automatic language identification. We also propose a cross-gender analysis of declarative intonation in the poorly studied Tuvinian language. The ranges of pitch parameter values were obtained by means of specially developed software that deals with the distribution of pitch values and allows us to obtain statistical language-specific pitch intervals. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=speech%20analysis" title="speech analysis">speech analysis</a>, <a href="https://publications.waset.org/abstracts/search?q=statistical%20analysis" title=" statistical analysis"> statistical analysis</a>, <a href="https://publications.waset.org/abstracts/search?q=speaker%20recognition" title=" speaker recognition"> speaker recognition</a>, <a href="https://publications.waset.org/abstracts/search?q=identification%20of%20person" title=" identification of person"> identification of person</a> </p> <a href="https://publications.waset.org/abstracts/8047/a-cross-gender-statistical-analysis-of-tuvinian-intonation-features-in-comparison-with-uzbek-and-azerbaijani" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/8047.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">347</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">3476</span> Advancing in Cricket Analytics: Novel Approaches for Pitch and Ball Detection Employing OpenCV and YOLOV8</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Pratham%20Madnur">Pratham Madnur</a>, <a href="https://publications.waset.org/abstracts/search?q=Prathamkumar%20Shetty"> Prathamkumar Shetty</a>, <a href="https://publications.waset.org/abstracts/search?q=Sneha%20Varur"> Sneha Varur</a>, <a href="https://publications.waset.org/abstracts/search?q=Gouri%20Parashetti"> Gouri Parashetti</a> </p> <p class="card-text"><strong>Abstract:</strong></p> In order to overcome conventional obstacles, this research paper investigates novel approaches for cricket pitch and ball detection that make use of cutting-edge technologies. The research integrates OpenCV for pitch inspection and modifies the YOLOv8 model for cricket ball detection in order to overcome the shortcomings of manual pitch assessment and traditional ball detection techniques. To ensure flexibility in a range of pitch environments, the pitch detection method leverages OpenCV鈥檚 color space transformation, contour extraction, and accurate color range defining features. Regarding ball detection, the YOLOv8 model emphasizes the preservation of minor object details to improve accuracy and is specifically trained to the unique properties of cricket balls. The methods are more reliable because of the careful preparation of the datasets, which include novel ball and pitch information. These cutting-edge methods not only improve cricket analytics but also set the stage for flexible methods in more general sports technology applications. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=OpenCV" title="OpenCV">OpenCV</a>, <a href="https://publications.waset.org/abstracts/search?q=YOLOv8" title=" YOLOv8"> YOLOv8</a>, <a href="https://publications.waset.org/abstracts/search?q=cricket" title=" cricket"> cricket</a>, <a href="https://publications.waset.org/abstracts/search?q=custom%20dataset" title=" custom dataset"> custom dataset</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=sports" title=" sports"> sports</a> </p> <a href="https://publications.waset.org/abstracts/182020/advancing-in-cricket-analytics-novel-approaches-for-pitch-and-ball-detection-employing-opencv-and-yolov8" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/182020.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">80</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">3475</span> Implementation and Modeling of a Quadrotor</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Ersan%20Aktas">Ersan Aktas</a>, <a href="https://publications.waset.org/abstracts/search?q=Eren%20Turano%C4%9Fuz"> Eren Turano臒uz</a> </p> <p class="card-text"><strong>Abstract:</strong></p> In this study, the quad-electrical rotor driven unmanned aerial vehicle system is designed and modeled using fundamental dynamic equations. After that, mechanical, electronical and control system of the air vehicle are designed and implemented. Brushless motor speeds are altered via electronic speed controllers in order to achieve desired controllability. The vehicle's fundamental Euler angles (i.e., roll angle, pitch angle, and yaw angle) are obtained via AHRS sensor. These angles are provided as an input to the control algorithm that run on soft the processor on the electronic card. The vehicle control algorithm is implemented in the electronic card. Controller is designed and improved for each Euler angles. Finally, flight tests have been performed to observe and improve the flight characteristics. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=quadrotor" title="quadrotor">quadrotor</a>, <a href="https://publications.waset.org/abstracts/search?q=UAS%20applications" title=" UAS applications"> UAS applications</a>, <a href="https://publications.waset.org/abstracts/search?q=control%20architectures" title=" control architectures"> control architectures</a>, <a href="https://publications.waset.org/abstracts/search?q=PID" title=" PID"> PID</a> </p> <a href="https://publications.waset.org/abstracts/48615/implementation-and-modeling-of-a-quadrotor" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/48615.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">365</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">3474</span> Aerodynamic Investigation of Baseline-IV Bird-Inspired BWB Aircraft Design: Improvements over Baseline-III BWB </h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=C.%20M.%20Nur%20Syazwani">C. M. Nur Syazwani</a>, <a href="https://publications.waset.org/abstracts/search?q=M.%20K.%20Ahmad%20Imran"> M. K. Ahmad Imran</a>, <a href="https://publications.waset.org/abstracts/search?q=Rizal%20E.%20M.%20Nasir"> Rizal E. M. Nasir</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The study on BWB UV begins in UiTM since 2005 and three designs have been studied and published. The latest designs are Baseline-III and inspired by birds that have features and aerodynamics behaviour of cruising birds without flapping capability. The aircraft featuring planform and configuration are similar to the bird. Baseline-III has major flaws particularly in its low lift-to-drag ratio, stability and issues regarding limited controllability. New design known as Baseline-IV replaces straight, swept wing to delta wing and have a broader tail compares to the Baseline-III鈥檚. The objective of the study is to investigate aerodynamics of Baseline-IV bird-inspired BWB aircraft. This will be achieved by theoretical calculation and wind tunnel experiments. The result shows that both theoretical and wind tunnel experiments of Baseline-IV graph of CL and CD versus alpha are quite similar to each other in term of pattern of graph slopes and values. Baseline-IV has higher lift coefficient values at wide range of angle of attack compares to Baseline-III. Baseline-IV also has higher maximum lift coefficient, higher maximum lift-to-drag and lower parasite drag. It has stable pitch moment versus lift slope but negative moment at zero lift for zero angle-of-attack tail setting. At high angle of attack, Baseline-IV does not have stability reversal as shown in Baseline-III. Baseline-IV is proven to have improvements over Baseline-III in terms of lift, lift-to-drag ratio and pitch moment stability at high angle-of-attack. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=blended%20wing-body" title="blended wing-body">blended wing-body</a>, <a href="https://publications.waset.org/abstracts/search?q=bird-inspired%20blended%20wing-body" title=" bird-inspired blended wing-body"> bird-inspired blended wing-body</a>, <a href="https://publications.waset.org/abstracts/search?q=aerodynamic" title=" aerodynamic"> aerodynamic</a>, <a href="https://publications.waset.org/abstracts/search?q=stability" title=" stability"> stability</a> </p> <a href="https://publications.waset.org/abstracts/24050/aerodynamic-investigation-of-baseline-iv-bird-inspired-bwb-aircraft-design-improvements-over-baseline-iii-bwb" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/24050.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">508</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">3473</span> Numerical Study of 5kW Vertical Axis Wind Turbine Using DOE Method</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Yan-Ting%20Lin">Yan-Ting Lin</a>, <a href="https://publications.waset.org/abstracts/search?q=Wei-Nian%20Su"> Wei-Nian Su</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The purpose of this paper is to demonstrate the design of 5kW vertical axis wind turbine (VAWT) using DOE method. The NACA0015 airfoil was implemented for the design and 3D simulation. The critical design parameters are chord length, tip speed ratio (TSR), aspect ratio (AR) and pitch angle in this investigation. The RNG k-蔚 turbulent model and the sliding mesh method are adopted in the CFD simulation. The results show that the model with zero pitch, 0.3 m in chord length, TSR of 3, and AR of 10 demonstrated the optimum aerodynamic power under the uniform 10m/s inlet velocity. The aerodynamic power is 3.61kW and 3.89kW under TSR of 3 and 4 respectively. The aerodynamic power decreased dramatically while TSR increased to 5. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=vertical%20axis%20wind%20turbine" title="vertical axis wind turbine">vertical axis wind turbine</a>, <a href="https://publications.waset.org/abstracts/search?q=CFD" title=" CFD"> CFD</a>, <a href="https://publications.waset.org/abstracts/search?q=DOE" title=" DOE"> DOE</a>, <a href="https://publications.waset.org/abstracts/search?q=VAWT" title=" VAWT"> VAWT</a> </p> <a href="https://publications.waset.org/abstracts/16847/numerical-study-of-5kw-vertical-axis-wind-turbine-using-doe-method" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/16847.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">440</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">3472</span> Aural Skills Pedagogy for Students with Absolute Pitch</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Rika%20Uchida">Rika Uchida</a> </p> <p class="card-text"><strong>Abstract:</strong></p> In teaching sophomore level aural skills, I have dealt with students with absolute pitch do poorly in my courses, particularly in harmonic dictation. They can identify triads; however, identifying quality of seventh chords or chromatic chords poses serious challenges. Most often, they need to spell all the pitches before identifying the chord qualities and Roman Numerals. Growing up in a country where acquiring absolute pitch is considered essential, I started my early music training with fixed do system at age three and learned all my music with solfege. When I was assigned as a TA in aural skills courses at graduate school in US, I had to learn relative pitch quickly. My survival method was listening to music with absolute pitch first, then quickly "translate" to relative pitch. In teaching my courses, I have been using chord progressions (5-8 chords total), in which students are asked to sing chord arpeggiation with movable do solfege. I use same progressions for harmonic dictation; I hoped that students learn to incorporate singing and listening skills by overlapping same materials. This method has proven to be successful for most students; in particular, it has helped students with absolute pitch to hear chord quality and function. Although original progressions are written in C as a tonic, they can identify chords in harmonic dictation in other keys as well. In short, I believe singing chord progression with movable do arpeggiation helps students with absolute pitch to improve hearing function and quality of chords in harmonic dictation. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aural%20skills%20pedagogy" title="aural skills pedagogy">aural skills pedagogy</a>, <a href="https://publications.waset.org/abstracts/search?q=music%20theory" title=" music theory"> music theory</a>, <a href="https://publications.waset.org/abstracts/search?q=absolute%20pitch" title=" absolute pitch"> absolute pitch</a>, <a href="https://publications.waset.org/abstracts/search?q=harmonic%20dictation" title=" harmonic dictation"> harmonic dictation</a> </p> <a href="https://publications.waset.org/abstracts/119257/aural-skills-pedagogy-for-students-with-absolute-pitch" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/119257.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">144</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">3471</span> Design and Implementation of Control System in Underwater Glider of Ganeshblue</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Imam%20Taufiqurrahman">Imam Taufiqurrahman</a>, <a href="https://publications.waset.org/abstracts/search?q=Anugrah%20Adiwilaga"> Anugrah Adiwilaga</a>, <a href="https://publications.waset.org/abstracts/search?q=Egi%20Hidayat"> Egi Hidayat</a>, <a href="https://publications.waset.org/abstracts/search?q=Bambang%20Riyanto%20Trilaksono"> Bambang Riyanto Trilaksono</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Autonomous Underwater Vehicle glider is one of the renewal of underwater vehicles. This vehicle is one of the autonomous underwater vehicles that are being developed in Indonesia. Glide ability is obtained by controlling the buoyancy and attitude of the vehicle using the movers within the vehicle. The glider motion mechanism is expected to provide energy resistance from autonomous underwater vehicles so as to increase the cruising range of rides while performing missions. The control system on the vehicle consists of three parts: controlling the attitude of the pitch, the buoyancy engine controller and the yaw controller. The buoyancy and pitch controls on the vehicle are sequentially referring to the finite state machine with pitch angle and depth of diving inputs to obtain a gliding cycle. While the yaw control is done through the rudder for the needs of the guide system. This research is focused on design and implementation of control system of Autonomous Underwater Vehicle glider based on PID anti-windup. The control system is implemented on an ARM TS-7250-V2 device along with a mathematical model of the vehicle in MATLAB using the hardware-in-the-loop simulation (HILS) method. The TS-7250-V2 is chosen because it complies industry standards, has high computing capability, minimal power consumption. The results show that the control system in HILS process can form glide cycle with depth and angle of operation as desired. In the implementation using half control and full control mode, from the experiment can be concluded in full control mode more precision when tracking the reference. While half control mode is considered more efficient in carrying out the mission. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=control%20system" title="control system">control system</a>, <a href="https://publications.waset.org/abstracts/search?q=PID" title=" PID"> PID</a>, <a href="https://publications.waset.org/abstracts/search?q=underwater%20glider" title=" underwater glider"> underwater glider</a>, <a href="https://publications.waset.org/abstracts/search?q=marine%20robotics" title=" marine robotics"> marine robotics</a> </p> <a href="https://publications.waset.org/abstracts/80520/design-and-implementation-of-control-system-in-underwater-glider-of-ganeshblue" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/80520.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">374</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">3470</span> Design and Numerical Study on Aerodynamics Performance for F16 Leading Edge Extension</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=San-Yih%20Lin">San-Yih Lin</a>, <a href="https://publications.waset.org/abstracts/search?q=Hsien-Hao%20Teng"> Hsien-Hao Teng</a> </p> <p class="card-text"><strong>Abstract:</strong></p> In this research, we use commercial software, ANSYS CFX, to carry on the simulation the F16 aerodynamics performance flow field. The flight with a modified Leading Edge Extension (LEX) is proposed to increase the lift/drag ratio. The Shear Stress Transport turbulent model is used. The unstructured grid system is generated by the ICEM CFD. The prism grid around the wall surface is generated to simulate boundary layer viscosity flow field and Tetrahedron Mesh is used for the other computation domain. The lift, drag, and pitch moment are computed. The strong vortex structures upper the wing and vortex bursts under different sweep angle of LEX are investigated. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=LEX" title="LEX">LEX</a>, <a href="https://publications.waset.org/abstracts/search?q=lift%2Fdrag%20ratio" title=" lift/drag ratio"> lift/drag ratio</a>, <a href="https://publications.waset.org/abstracts/search?q=pitch%20moment" title=" pitch moment"> pitch moment</a>, <a href="https://publications.waset.org/abstracts/search?q=vortex%20burst" title=" vortex burst"> vortex burst</a> </p> <a href="https://publications.waset.org/abstracts/85534/design-and-numerical-study-on-aerodynamics-performance-for-f16-leading-edge-extension" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/85534.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">326</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">3469</span> Emulation of a Wind Turbine Using Induction Motor Driven by Field Oriented Control</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=L.%20Benaaouinate">L. Benaaouinate</a>, <a href="https://publications.waset.org/abstracts/search?q=M.%20Khafallah"> M. Khafallah</a>, <a href="https://publications.waset.org/abstracts/search?q=A.%20Martinez"> A. Martinez</a>, <a href="https://publications.waset.org/abstracts/search?q=A.%20Mesbahi"> A. Mesbahi</a>, <a href="https://publications.waset.org/abstracts/search?q=T.%20Bouragba"> T. Bouragba</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This paper concerns with the modeling, simulation, and emulation of a wind turbine emulator for standalone wind energy conversion systems. By using emulation system, we aim to reproduce the dynamic behavior of the wind turbine torque on the generator shaft: it provides the testing facilities to optimize generator control strategies in a controlled environment, without reliance on natural resources. The aerodynamic, mechanical, electrical models have been detailed as well as the control of pitch angle using Fuzzy Logic for horizontal axis wind turbines. The wind turbine emulator consists mainly of an induction motor with AC power drive with torque control. The control of the induction motor and the mathematical models of the wind turbine are designed with MATLAB/Simulink environment. The simulation results confirm the effectiveness of the induction motor control system and the functionality of the wind turbine emulator for providing all necessary parameters of the wind turbine system such as wind speed, output torque, power coefficient and tip speed ratio. The findings are of direct practical relevance. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=electrical%20generator" title="electrical generator">electrical generator</a>, <a href="https://publications.waset.org/abstracts/search?q=induction%20motor%20drive" title=" induction motor drive"> induction motor drive</a>, <a href="https://publications.waset.org/abstracts/search?q=modeling" title=" modeling"> modeling</a>, <a href="https://publications.waset.org/abstracts/search?q=pitch%20angle%20control" title=" pitch angle control"> pitch angle control</a>, <a href="https://publications.waset.org/abstracts/search?q=real%20time%20control" title=" real time control"> real time control</a>, <a href="https://publications.waset.org/abstracts/search?q=renewable%20energy" title=" renewable energy"> renewable energy</a>, <a href="https://publications.waset.org/abstracts/search?q=wind%20turbine" title=" wind turbine"> wind turbine</a>, <a href="https://publications.waset.org/abstracts/search?q=wind%20turbine%20emulator" title=" wind turbine emulator"> wind turbine emulator</a> </p> <a href="https://publications.waset.org/abstracts/80827/emulation-of-a-wind-turbine-using-induction-motor-driven-by-field-oriented-control" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/80827.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">234</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">3468</span> Biotransformation of Glycerine Pitch as Renewable Carbon Resource into P(3HB-co-4HB) Biopolymer</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Amirul%20Al-Ashraf%20Abdullah">Amirul Al-Ashraf Abdullah</a>, <a href="https://publications.waset.org/abstracts/search?q=Hema%20Ramachandran"> Hema Ramachandran</a>, <a href="https://publications.waset.org/abstracts/search?q=Iszatty%20Ismail"> Iszatty Ismail</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Oleochemical industry in Malaysia has been diversifying significantly due to the abundant supply of both palm and kernel oils as raw materials as well as the high demand for downstream products such as fatty acids, fatty alcohols and glycerine. However, environmental awareness is growing rapidly in Malaysia because oleochemical industry is one of the palm-oil based industries that possess risk to the environment. Glycerine pitch is one of the scheduled wastes generated from the fatty acid plants in Malaysia and its discharge may cause a serious environmental problem. Therefore, it is imperative to find alternative applications for this waste glycerine. Consequently, the aim of this research is to explore the application of glycerine pitch as direct fermentation substrate in the biosynthesis of poly(3-hydroxybutyrate-co-4-hydroxybutyrate) [P(3HB-co-4HB)] copolymer, aiming to contribute toward the sustainable production of biopolymer in the world. Utilization of glycerine pitch (10 g/l) together with 1,4-butanediol (5 g/l) had resulted in the achievement of 40 mol% 4HB monomer with the highest PHA concentration of 2.91 g/l. Synthesis of yellow pigment which exhibited antimicrobial properties occurred simultaneously with the production of P(3HB-co-4HB) through the use of glycerine pitch as renewable carbon resource. Utilization of glycerine pitch in the biosynthesis of P(3HB-co-4HB) will not only contribute to reducing society鈥檚 dependence on non-renewable resources but also will promote the development of cost efficiency microbial fermentation towards biosustainability and green technology. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=biopolymer" title="biopolymer">biopolymer</a>, <a href="https://publications.waset.org/abstracts/search?q=glycerine%20pitch" title=" glycerine pitch"> glycerine pitch</a>, <a href="https://publications.waset.org/abstracts/search?q=natural%20pigment" title=" natural pigment"> natural pigment</a>, <a href="https://publications.waset.org/abstracts/search?q=P%283HB-co-4HB%29" title=" P(3HB-co-4HB)"> P(3HB-co-4HB)</a> </p> <a href="https://publications.waset.org/abstracts/11284/biotransformation-of-glycerine-pitch-as-renewable-carbon-resource-into-p3hb-co-4hb-biopolymer" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/11284.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">469</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">3467</span> Performance Comparisons between PID and Adaptive PID Controllers for Travel Angle Control of a Bench-Top Helicopter</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=H.%20Mansor">H. Mansor</a>, <a href="https://publications.waset.org/abstracts/search?q=S.%20B.%20Mohd-Noor"> S. B. Mohd-Noor</a>, <a href="https://publications.waset.org/abstracts/search?q=T.%20S.%20Gunawan"> T. S. Gunawan</a>, <a href="https://publications.waset.org/abstracts/search?q=S.%20Khan"> S. Khan</a>, <a href="https://publications.waset.org/abstracts/search?q=N.%20I.%20Othman"> N. I. Othman</a>, <a href="https://publications.waset.org/abstracts/search?q=N.%20Tazali"> N. Tazali</a>, <a href="https://publications.waset.org/abstracts/search?q=R.%20B.%20Islam"> R. B. Islam</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This paper provides a comparative study on the performances of standard PID and adaptive PID controllers tested on travel angle of a 3-Degree-of-Freedom (3-DOF) Quanser bench-top helicopter. Quanser, a well-known manufacturer of educational bench-top helicopter has developed Proportional Integration Derivative (PID) controller with Linear Quadratic Regulator (LQR) for all travel, pitch and yaw angle of the bench-top helicopter. The performance of the PID controller is relatively good; however its performance could also be improved if the controller is combined with adaptive element. The objective of this research is to design adaptive PID controller and then compare the performances of the adaptive PID with the standard PID. The controller design and test is focused on travel angle control only. Adaptive method used in this project is self-tuning controller, which controller鈥檚 parameters are updated online. Two adaptive algorithms those are pole-placement and deadbeat have been chosen as the method to achieve optimal controller鈥檚 parameters. Performance comparisons have shown that the adaptive (deadbeat) PID controller has produced more desirable performance compared to standard PID and adaptive (pole-placement). The adaptive (deadbeat) PID controller attained very fast settling time (5 seconds) and very small percentage of overshoot (5% to 7.5%) for 10掳 to 30掳 step change of travel angle. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=adaptive%20control" title="adaptive control">adaptive control</a>, <a href="https://publications.waset.org/abstracts/search?q=deadbeat" title=" deadbeat"> deadbeat</a>, <a href="https://publications.waset.org/abstracts/search?q=pole-placement" title=" pole-placement"> pole-placement</a>, <a href="https://publications.waset.org/abstracts/search?q=bench-top%20helicopter" title=" bench-top helicopter"> bench-top helicopter</a>, <a href="https://publications.waset.org/abstracts/search?q=self-tuning%20control" title=" self-tuning control"> self-tuning control</a> </p> <a href="https://publications.waset.org/abstracts/15094/performance-comparisons-between-pid-and-adaptive-pid-controllers-for-travel-angle-control-of-a-bench-top-helicopter" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/15094.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">501</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">3466</span> Starting Torque Study of Darrieus Wind Turbine</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=M.%20Douak">M. Douak</a>, <a href="https://publications.waset.org/abstracts/search?q=Z.%20Aouachria"> Z. Aouachria</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The aim of our study is to project an optimized wind turbine of Darrieus type. This type of wind turbine is characterized by a low starting torque in comparison with the Savonius rotor allowing them to operate for a period greater than wind speed. This led us to reconsider the Darrieus rotor to optimize a design which will increase its starting torque. The study of a system of monitoring and control of the angle of attack of blade profile, which allows an auto start to wind speeds as low as possible is presented for the straight blade of Darrieus turbine. The study continues to extend to other configurations namely those of parabolic type. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=Darrieus%20turbine" title="Darrieus turbine">Darrieus turbine</a>, <a href="https://publications.waset.org/abstracts/search?q=pitch%20angle" title=" pitch angle"> pitch angle</a>, <a href="https://publications.waset.org/abstracts/search?q=self%20stating" title=" self stating"> self stating</a>, <a href="https://publications.waset.org/abstracts/search?q=wind%20energy" title=" wind energy "> wind energy </a> </p> <a href="https://publications.waset.org/abstracts/26727/starting-torque-study-of-darrieus-wind-turbine" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/26727.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">348</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">3465</span> Wind Turbine Control Performance Evaluation Based on Minimum-Variance Principles</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Zheming%20Cao">Zheming Cao</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Control loops are the most important components in the wind turbine system. Product quality, operation safety, and the economic performance are directly or indirectly connected to the performance of control systems. This paper proposed a performance evaluation method based on minimum-variance for wind turbine control system. This method can be applied on PID controller for pitch control system in the wind turbine. The good performance result demonstrated in the paper was achieved by retuning and optimizing the controller settings based on the evaluation result. The concepts presented in this paper are illustrated with the actual data of the industrial wind farm. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=control%20performance" title="control performance">control performance</a>, <a href="https://publications.waset.org/abstracts/search?q=evaluation" title=" evaluation"> evaluation</a>, <a href="https://publications.waset.org/abstracts/search?q=minimum-variance" title=" minimum-variance"> minimum-variance</a>, <a href="https://publications.waset.org/abstracts/search?q=wind%20turbine" title=" wind turbine"> wind turbine</a> </p> <a href="https://publications.waset.org/abstracts/65020/wind-turbine-control-performance-evaluation-based-on-minimum-variance-principles" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/65020.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">370</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">3464</span> Numerical Investigations on Dynamic Stall of a Pitching-Plunging Helicopter Blade Airfoil </h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Xie%20Kai">Xie Kai</a>, <a href="https://publications.waset.org/abstracts/search?q=Laith%20K.%20Abbas"> Laith K. Abbas</a>, <a href="https://publications.waset.org/abstracts/search?q=Chen%20Dongyang"> Chen Dongyang</a>, <a href="https://publications.waset.org/abstracts/search?q=Yang%20Fufeng"> Yang Fufeng</a>, <a href="https://publications.waset.org/abstracts/search?q=Rui%20Xiaoting"> Rui Xiaoting</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Effect of plunging motion on the pitch oscillating NACA0012 airfoil is investigated using computational fluid dynamics (CFD). A simulation model based on overset grid technology and <em>k - ω</em> shear stress transport (SST) turbulence model is established, and the numerical simulation results are compared with available experimental data and other simulations. Two cases of phase angle <em>φ = 0, μ </em>which represents the phase difference between the pitching and plunging motions of an airfoil are performed. Airfoil vortex generation, moving, and shedding are discussed in detail. Good agreements have been achieved with the available literature. The upward plunging motion made the equivalent angle of attack less than the actual one during pitching analysis. It is observed that the formation of the stall vortex is suppressed, resulting in a decrease in the lift coefficient and a delay of the stall angle. However, the downward plunging motion made the equivalent angle of attack higher the actual one. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=dynamic%20stall" title="dynamic stall">dynamic stall</a>, <a href="https://publications.waset.org/abstracts/search?q=pitching-plunging" title=" pitching-plunging"> pitching-plunging</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=helicopter%20blade%20rotor" title=" helicopter blade rotor"> helicopter blade rotor</a>, <a href="https://publications.waset.org/abstracts/search?q=airfoil" title=" airfoil"> airfoil</a> </p> <a href="https://publications.waset.org/abstracts/75693/numerical-investigations-on-dynamic-stall-of-a-pitching-plunging-helicopter-blade-airfoil" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/75693.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">226</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">3463</span> A Short-Baseline Dual-Antenna BDS/MEMS-IMU Integrated Navigation System</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Tijing%20Cai">Tijing Cai</a>, <a href="https://publications.waset.org/abstracts/search?q=Qimeng%20Xu"> Qimeng Xu</a>, <a href="https://publications.waset.org/abstracts/search?q=Daijin%20Zhou"> Daijin Zhou</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This paper puts forward a short-baseline dual-antenna BDS/MEMS-IMU integrated navigation, constructs the carrier phase double difference model of BDS (BeiDou Navigation Satellite System), and presents a 2-position initial orientation method on BDS. The Extended Kalman-filter has been introduced for the integrated navigation system. The differences between MEMS-IMU and BDS position, velocity and carrier phase indications are used as measurements. To show the performance of the short-baseline dual-antenna BDS/MEMS-IMU integrated navigation system, the experiment results show that the position error is less than 1m, the pitch angle error and roll angle error are less than 0.1掳, and the heading angle error is about 1掳. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=MEMS-IMU%20%28Micro-Electro-Mechanical%20System%20Inertial%20Measurement%20Unit%29" title="MEMS-IMU (Micro-Electro-Mechanical System Inertial Measurement Unit)">MEMS-IMU (Micro-Electro-Mechanical System Inertial Measurement Unit)</a>, <a href="https://publications.waset.org/abstracts/search?q=BDS%20%28BeiDou%20Navigation%20Satellite%20System%29" title=" BDS (BeiDou Navigation Satellite System)"> BDS (BeiDou Navigation Satellite System)</a>, <a href="https://publications.waset.org/abstracts/search?q=dual-antenna" title=" dual-antenna"> dual-antenna</a>, <a href="https://publications.waset.org/abstracts/search?q=integrated%20navigation" title=" integrated navigation"> integrated navigation</a> </p> <a href="https://publications.waset.org/abstracts/97626/a-short-baseline-dual-antenna-bdsmems-imu-integrated-navigation-system" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/97626.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">193</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">3462</span> Optimization of Tooth Root Profile and Drive Side Pressure Angle to Minimize Bending Stress at Root of Asymmetric Spur Gear Tooth</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Priyakant%20Vaghela">Priyakant Vaghela</a>, <a href="https://publications.waset.org/abstracts/search?q=Jagdish%20Prajapati"> Jagdish Prajapati</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Bending stress at the root of the gear tooth is the very important criteria in gear design and it should be kept the minimum. Minimization of bending stress at the root of the gear tooth is a recent demand from industry. This paper presents an innovative approach to obtain minimum bending stress at the root of a tooth by optimizing tooth root profile and drive side pressure angle. Circular-filleted at the root of the tooth is widely used in the design. Circular fillet creates discontinuity at the root of the tooth. So, at root stress concentration occurs. In order to minimize stress concentration, an important criterion is a G2 continuity at the blending of the gear tooth. A Bezier curve is used with G2 continuity at the root of asymmetric spur gear tooth. The comparison has been done between normal and modified tooth using ANSYS simulation. Tooth root profile and drive side pressure angle are optimized to minimize bending stress at the root of the tooth of the asymmetric involute spur gear. Von Mises stress of optimized profile is analyzed and compared with normal profile symmetric gear. Von Mises stress is reducing by 31.27% by optimization of drive side pressure angle and root profile. Stress concentration of modified gear was significantly reduced. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=asymmetric%20spur%20gear%20tooth" title="asymmetric spur gear tooth">asymmetric spur gear tooth</a>, <a href="https://publications.waset.org/abstracts/search?q=G2%20continuity" title=" G2 continuity"> G2 continuity</a>, <a href="https://publications.waset.org/abstracts/search?q=pressure%20angle" title=" pressure angle"> pressure angle</a>, <a href="https://publications.waset.org/abstracts/search?q=stress%20concentration%20at%20the%20root%20of%20tooth" title=" stress concentration at the root of tooth"> stress concentration at the root of tooth</a>, <a href="https://publications.waset.org/abstracts/search?q=tooth%20root%20stress" title=" tooth root stress"> tooth root stress</a> </p> <a href="https://publications.waset.org/abstracts/95043/optimization-of-tooth-root-profile-and-drive-side-pressure-angle-to-minimize-bending-stress-at-root-of-asymmetric-spur-gear-tooth" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/95043.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">186</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">3461</span> Self-Tuning Dead-Beat PD Controller for Pitch Angle Control of a Bench-Top Helicopter</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=H.%20Mansor">H. Mansor</a>, <a href="https://publications.waset.org/abstracts/search?q=S.B.%20Mohd-Noor"> S.B. Mohd-Noor</a>, <a href="https://publications.waset.org/abstracts/search?q=N.%20I.%20Othman"> N. I. Othman</a>, <a href="https://publications.waset.org/abstracts/search?q=N.%20Tazali"> N. Tazali</a>, <a href="https://publications.waset.org/abstracts/search?q=R.%20I.%20Boby"> R. I. Boby</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This paper presents an improved robust Proportional Derivative controller for a 3-Degree-of-Freedom (3-DOF) bench-top helicopter by using adaptive methodology. Bench-top helicopter is a laboratory scale helicopter used for experimental purposes which is widely used in teaching laboratory and research. Proportional Derivative controller has been developed for a 3-DOF bench-top helicopter by Quanser. Experiments showed that the transient response of designed PD controller has very large steady state error i.e., 50%, which is very serious. The objective of this research is to improve the performance of existing pitch angle control of PD controller on the bench-top helicopter by integration of PD controller with adaptive controller. Usually standard adaptive controller will produce zero steady state error; however response time to reach desired set point is large. Therefore, this paper proposed an adaptive with deadbeat algorithm to overcome the limitations. The output response that is fast, robust and updated online is expected. Performance comparisons have been performed between the proposed self-tuning deadbeat PD controller and standard PD controller. The efficiency of the self-tuning dead beat controller has been proven from the tests results in terms of faster settling time, zero steady state error and capability of the controller to be updated online. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=adaptive%20control" title="adaptive control">adaptive control</a>, <a href="https://publications.waset.org/abstracts/search?q=deadbeat%20control" title=" deadbeat control"> deadbeat control</a>, <a href="https://publications.waset.org/abstracts/search?q=bench-top%20helicopter" title=" bench-top helicopter"> bench-top helicopter</a>, <a href="https://publications.waset.org/abstracts/search?q=self-tuning%20control" title=" self-tuning control"> self-tuning control</a> </p> <a href="https://publications.waset.org/abstracts/10581/self-tuning-dead-beat-pd-controller-for-pitch-angle-control-of-a-bench-top-helicopter" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/10581.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">325</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">3460</span> Design and Performance Evaluation of Synchronous Reluctance Machine (SynRM)</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Hadi%20Aghazadeh">Hadi Aghazadeh</a>, <a href="https://publications.waset.org/abstracts/search?q=Mohammadreza%20Naeimi"> Mohammadreza Naeimi</a>, <a href="https://publications.waset.org/abstracts/search?q=Seyed%20Ebrahim%20Afjei"> Seyed Ebrahim Afjei</a>, <a href="https://publications.waset.org/abstracts/search?q=Alireza%20Siadatan"> Alireza Siadatan</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Torque ripple, maximum torque and high efficiency are important issues in synchronous reluctance machine (SynRM). This paper presents a view on design of a high efficiency, low torque ripple and high torque density SynRM. To achieve this goal SynRM parameters is calculated (such as insulation ratios in the d-and q-axes and the rotor slot pitch), while the torque ripple can be minimized by determining the best rotor slot pitch in the d-axis. The presented analytical-finite element method (FEM) approach gives the optimum distribution of air gap and iron portion for the maximizing torque density with minimum torque ripple. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=torque%20ripple" title="torque ripple">torque ripple</a>, <a href="https://publications.waset.org/abstracts/search?q=efficiency" title=" efficiency"> efficiency</a>, <a href="https://publications.waset.org/abstracts/search?q=insulation%20ratio" title=" insulation ratio"> insulation ratio</a>, <a href="https://publications.waset.org/abstracts/search?q=FEM" title=" FEM"> FEM</a>, <a href="https://publications.waset.org/abstracts/search?q=synchronous%20reluctance%20machine%20%28SynRM%29" title=" synchronous reluctance machine (SynRM)"> synchronous reluctance machine (SynRM)</a>, <a href="https://publications.waset.org/abstracts/search?q=induction%20motor%20%28IM%29" title=" induction motor (IM)"> induction motor (IM)</a> </p> <a href="https://publications.waset.org/abstracts/85364/design-and-performance-evaluation-of-synchronous-reluctance-machine-synrm" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/85364.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">227</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">3459</span> Leadership Effectiveness Compared among Three Cultures Using Voice Pitches</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Asena%20Biber">Asena Biber</a>, <a href="https://publications.waset.org/abstracts/search?q=Ates%20Gul%20Ergun"> Ates Gul Ergun</a>, <a href="https://publications.waset.org/abstracts/search?q=Seda%20Bulut"> Seda Bulut</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Based on the literature, there are large numbers of studies investigating the relationship between culture and leadership effectiveness. Although giving effective speeches is vital characteristic for a leader to be perceived as effective, to our knowledge, there is no research study the determinants of perceived effective leader speech. The aim of this study is to find the effects of both culture and voice pitch on perceptions of leader's speech effectiveness. Our hypothesis is that people from high power distance countries will perceive leaders' speech effective when the leader's voice pitch is high, comparing with people from relatively low power distance countries. The participants of the study were 36 undergraduate students (12 Pakistanis, 12 Nigerians, and 12 Turks) who are studying in Turkey. National power distance scores of Nigerians ranked as first, Turks ranked as second and Pakistanis ranked as third. There are two independent variables in this study; three nationality groups that representing three levels of power distance and voice pitch of the leader which is manipulated as high and low levels. Researchers prepared an audio to manipulate high and low conditions of voice pitch. A professional whose native language is English read the predetermined speech in high and low voice pitch conditions. Voice pitch was measured using Hertz (Hz) and Decibel (dB). Each nationality group (Pakistan, Nigeria, and Turkey) were divided into groups of six students who listened to either the low or high pitch conditions in the cubicles of the laboratory. It was expected from participants to listen to the audio and fill in the questionnaire which was measuring the leadership effectiveness on a response scale ranging from 1 to 5. To determine the effects of nationality and voice pitch on perceived effectiveness of leader' voice pitch, 3 (Pakistani, Nigerian, and Turk) x 2 (low voice pitch and high voice pitch) two way between subjects analysis of variances was carried out. The results indicated that there was no significant main effect of voice pitch and interaction effect on perceived effectiveness of the leader鈥檚 voice pitch. However, there was a significant main effect of nationality on perceived effectiveness of the leader's voice pitch. Based on the results of Turkey鈥檚 HSD post-hoc test, only the perceived effectiveness of the leader's speech difference between Pakistanis and Nigerians was statistically significant. The results show that the hypothesis of this study was not supported. As limitations of the study, it is of importance to mention that the sample size should be bigger. Also, the language of the questionnaire and speech should be in the participant鈥檚 native language in further studies. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=culture" title="culture">culture</a>, <a href="https://publications.waset.org/abstracts/search?q=leadership%20effectiveness" title=" leadership effectiveness"> leadership effectiveness</a>, <a href="https://publications.waset.org/abstracts/search?q=power%20distance" title=" power distance"> power distance</a>, <a href="https://publications.waset.org/abstracts/search?q=voice%20pitch" title=" voice pitch"> voice pitch</a> </p> <a href="https://publications.waset.org/abstracts/83488/leadership-effectiveness-compared-among-three-cultures-using-voice-pitches" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/83488.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right 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