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Relevant bibliographies by topics / Cycloidal propellers

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Academic literature on the topic 'Cycloidal propellers'

Author: Grafiati

Published: 4 June 2021

Last updated: 16 February 2022

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Journal articles on the topic "Cycloidal propellers"

1

Bakhtiari, Mohammad, and Hassan Ghassemi. "Numerical analysis on effects of blade number on hydrodynamic performance of low-pitch marine cycloidal propeller." Proceedings of the Institution of Mechanical Engineers, Part M: Journal of Engineering for the Maritime Environment 234, no. 2 (2019): 490–501. http://dx.doi.org/10.1177/1475090219876508.

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Marine cycloidal propeller, as a special type of marine propulsion system, is used for ships that require high maneuverability, such as tugs and ferries. In a marine cycloidal propeller, the thrust force is generated by rotation of a circular disk with a number of lifting blades fitted on the periphery of the disk, so that the propeller axis of rotation is perpendicular to the direction of thrust force. Each blade pitches about its own axis, and the thrust magnitude and direction can be adjusted by controlling the pitching angle of the blades. Therefore, the propulsion and maneuvering units are combined together and no separate rudder is needed to maneuver the ship. Two configurations of marine cycloidal propeller have been studied and developed based on propeller pitch: low-pitch propeller (designed for advance coefficient less than one, means λ < 1) and high-pitch propeller (designed for λ > 1). Low-pitch marine cycloidal propellers are used in applications with low-speed maneuvering requirements, such as tugboats and minesweepers. In this study, the effects of blade number on hydrodynamic performance of low-pitch marine cycloidal propeller with pure cycloidal motion of the blades are investigated. The turbulent flow around marine cycloidal propeller is solved using a 2.5D numerical method based on unsteady Reynolds-averaged Navier–Stokes equations with shear-stress transport k–ω turbulent model. The presented numerical method was validated against experimental data and showed good agreement. The results showed that the thrust coefficient of marine cycloidal propeller generally decreases by increasing the blade number, whereas the torque coefficient increases. Consequently, the hydrodynamic efficiency of marine cycloidal propeller drops as the blade number increases.

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2

Roesler, Bernard T., Malia L. Kawamura, Eric Miller, et al. "Experimental Performance of a Novel Trochoidal Propeller." Journal of Ship Research 60, no. 01 (2016): 48–60. http://dx.doi.org/10.5957/jsr.2016.60.1.48.

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In the quest for higher energy efficiency in marine transportation, a promising alternative marine propulsor concept is the trochoidal propeller. The authors have 1) designed and tested a novel trochoidal propeller using a sinusoidal blade pitch function and 2) created a theoretical model to describe the principal physics governing the operation of such propellers. The main results presented herein are measurements of thrust and torque, as well as the calculated hydrodynamic efficiency, for a range of absolute advance coefficients. The performance of the present sinusoidal-pitch trochoidal propeller is compared with prior cross-flow propellers, as well as a representative screw propeller. Although the efficiency of the present sinusoidal-pitch propeller exceeds that of prior cycloidal-pitch trochoidal propellers, it is slightly lower than the efficiencies of the other propellers considered. Model predictions show excellent agreement with the experimental data, which opens possibilities for future investigation and optimization of novel blade pitch motions.

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Zhang, Hailang, Yu Hu, and Gengqi Wang. "The effect of aerofoil camber on cycloidal propellers." Aircraft Engineering and Aerospace Technology 90, no. 8 (2018): 1156–67. http://dx.doi.org/10.1108/aeat-08-2016-0128.

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Purpose This paper aims to investigate the impact of aerofoil camber on the performance of micro-air-vehicle-scale cycloidal propellers. Design/methodology/approach First, experiments were conducted to validate the numerical methodology. After that, three turbulent models were compared to select the most accurate one. Then, 2D numerical simulation was carried out on 11 aerofoils with different cambers, including five cambered aerofoils, one symmetrical aerofoil and five inverse cambered aerofoils. The inverse cambered aerofoils are symmetrical about the chord line to the corresponding cambered ones. Findings The cycloidal propeller with large cambered aerofoil gives the lowest hovering efficiency, but with symmetrical aerofoil or small inverse cambered aerofoil shows the highest. Also, blades with large cambered aerofoil display high performance at the upper part of its trajectory, while with symmetrical aerofoil or the inverse cambered aerofoil have their best at the lower part. In addition, intensified downwash can be observed in the rotor cage for all cases. When a blade runs through the top-left part of its circle path, all cases display the feature of deep dynamic stall. When the blade travels through the nadir of its path, the actual angle of attack is close to zero due to the strong downwash. Furthermore, there exits intensified blade-vortex interaction induced by the preceding blade for large cambered aerofoils at the lower-right part of its trajectory. Practical implications This paper develops a new cycloidal propeller which is more efficient than the one already present. Originality/value This paper discovers that the aerofoil camber is a vital design parameter in the performance of cycloidal propeller, and the authors expect that the rotor with deformable aerofoil on camber would achieve much higher efficiency.

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Hu, Y., H. L. Zhang, and C. Tan. "The effect of the aerofoil thickness on the performance of the MAV scale cycloidal rotor." Aeronautical Journal 119, no. 1213 (2015): 343–64. http://dx.doi.org/10.1017/s0001924000010502.

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AbstractThe numerical simulations for cycloidal propellers based on five aerofoils with different thickness are presented in this paper. The CFD simulation is based on sliding mesh and URANS. The results of CFD simulation indicates that all test cases share similar flow pattern. There are leading edge vortex and trailing-edge vortex due to blade dynamic stall. Interaction between the vortices shed from upstream blade and the downstream blade can be observed. There is variation of blade relative inflow velocity due to downwash in the cycloidal rotor cage. These factors result in large fluctuations of the aerodynamics forces on the blade. The comparison of the forces and flow pattern indicates that the thickness and leading edge radius of the aerofoil can significantly influent the flow pattern and hence the performance of the cycloidal propeller.

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Bakhtiari, Mohammad, and Hassan Ghassemi. "A 2.5D numerical study on open water hydrodynamic performance of a Voith-Schneider propeller." Mechanics & Industry 20, no. 6 (2019): 617. http://dx.doi.org/10.1051/meca/2019049.

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Marine cycloidal propeller (MCP) is a special type of marine propulsors that provides high maneuverability for marine vessels. In a MCP, the propeller axis of rotation is perpendicular to the direction of thrust force. It consists of a number of lifting blade. Each blade rotates about the propeller axis and simultaneously pitches about its own axis. The magnitude and direction of thrust force can be adjusted by controlling the propeller pitch. Voith-Schneider propeller (VSP) is a low-pitch MCP with pure cycloidal blade motion allowing fast, accurate, and stepless control of thrust magnitude and direction. Generally, low-pitch cycloidal propellers are used in applications with low speed maneuvering requirements, such as tugboats, minesweepers, etc. In this study, a 2.5D numerical method based on unsteady RANS equations with SST k-ω turbulent model was implemented to predict the open water hydrodynamic performance of a VSP for different propeller pitches and blade thicknesses. The numerical method was validated against the experimental data before applying to VSP. The results showed that maximum open water efficiency of a VSP is enhanced by increasing the propeller pitch. Furthermore, the effect of blade thickness on open water efficiency is different at various advance coefficients, so that the maximum efficiency produced by the VSP decreases with increasing blade thickness at different propeller pitches.

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Hu, Y., F. Du, and H. L. Zhang. "Investigation of unsteady aerodynamics effects in cycloidal rotor using RANS solver." Aeronautical Journal 120, no. 1228 (2016): 956–70. http://dx.doi.org/10.1017/aer.2016.38.

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ABSTRACTThe cycloidal propeller for a Micro-Aerial Vehicle (MAV)-scale cyclogyro in hover was studied using a 2D Reynolds-averaged Navier-Stokes equations solver. The effects of the blade dynamic stall, parallel Blade Vortex Interaction (BVI), inflow variation and flow curvature were discussed, based on the results of numerical simulation. The results from the 2D Computational Fluid Dynamics simulation indicated that the blade of the cycloidal rotor is actually performing a pitching oscillation, if observed in a moving reference frame. The dynamic stall vortices shed from the upstream blade cause intense parallel BVI on the downstream blade. The interaction will induce upwash and downwash on the downstream blade. This changes the effective reduced frequency and actually delays the stall of the blade, which is beneficial to the thrust generation. There is also strong downwash in the rotor cage and it changes the inflow velocity experienced by the blade. The downwash and flow curvature can either be beneficial or harmful to the thrust generation. The combined effects of dynamic stall, parallel BVI, inflow variation and flow curvature cause large aerodynamic force peaks and ensure the cycloidal rotors work at very low rotation speeds with high thrust. This guarantees that the cycloidal rotors possess at least the same level of hover efficiency as screw propellers.

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Yu, Hu, Zhang Hai Lang, and Wang Geng Qi. "Two-dimensional and three-dimensional numerical simulations of cycloidal propellers in hover." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 7 (2016): 1223–34. http://dx.doi.org/10.1177/0954410016660218.

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The cycloidal propellers for micro aerial vehicle scale cyclocopter in hovering status were studied in this paper based on the URANs solver using 2D, 2.5D, 3D half blade and 3D full blade model. The results from all numerical models were validated with the experimental results. It was found that 2.5D model cannot produce more accurate results than 2D model, hence results from 2D model were employed to discuss cycloidal rotor with infinite blade span. It was also indicated that the 3D half blade model produced the same results as 3D full blade model, but was more efficient than 3D model. The numerical simulation results of cycloidal rotor with finite (3D model) and infinite span (2D model) were compared. The results indicated that for the 2D cycloidal rotor with large blade pitching amplitude, there were leading edge and trailing edge vortices due to dynamic stall, which resulted in parallel blade vortex interactions. The parallel blade vortex interactions will also induce the fluctuation of aerodynamic forces. For the 3D blade with small aspect ratio, the flow was dominated by 3D dynamic stall and blade vortex interactions. The 3D flow due to finite blade span resulted in smooth dynamic stall and can weaken the parallel blade vortex interactions induced by dynamic stall vortices, hence no strong aerodynamic force fluctuation was observed. The perpendicular blade vortex interactions caused by blade tip vortices can induce cross flow when the azimuth angle of the rotor is between 270° and 360°, which reduces the strength of downwash in the region where the rotor azimuth angle is between 180° and 360°. This results in much smaller side force. Although sometimes the time-averaged aerodynamic forces obtained by 2D and 3D model were quite close to each other, the physics lying behind is quite different. Hence, it was not correct to use the 2D models to discuss the principles of cycloidal rotors with finite blade span.

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Tang, Jiwei, Yu Hu, Bifeng Song, and Hui Yang. "An unsteady free wake model for aerodynamic performance of cycloidal propellers." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 2 (2016): 290–307. http://dx.doi.org/10.1177/0954410016678431.

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9

Tang, Jiwei, Yu Hu, Bifeng Song, and Hui Yang. "Unsteady Aerodynamic Optimization of Airfoil for Cycloidal Propellers Based on Surrogate Model." Journal of Aircraft 54, no. 4 (2017): 1241–56. http://dx.doi.org/10.2514/1.c033649.

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10

YOSHITAKE, Kunihiko, and Hidenobu SHOJI. "912 The Analysis on the Characteristics of Cycloidal Propellers with Unsteady Airfoil Theory." Proceedings of Ibaraki District Conference 2007 (2007): 229–30. http://dx.doi.org/10.1299/jsmeibaraki.2007.229.

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Dissertations / Theses on the topic "Cycloidal propellers"

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McNabb, Michael Lynn. "Development of a cycloidal propulsion computer model and comparison with experiment." Master's thesis, Mississippi State : Mississippi State University, 2001. http://library.msstate.edu/etd/show.asp?etd=etd-08032001-111940.

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Books on the topic "Cycloidal propellers"

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Li, Jin. Theoretical and experimental study of cycloidal propellers. National Library of Canada, 1992.

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Conference papers on the topic "Cycloidal propellers"

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Hasegawa, Daisuke, Kazuo Matsuuchi, Masahiko Onda, and Yuya Sekiguchi. "Thrust Characteristics of Cycloidal Propeller and Flow Measurement." In ASME-JSME-KSME 2011 Joint Fluids Engineering Conference. ASMEDC, 2011. http://dx.doi.org/10.1115/ajk2011-15023.

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Now airships are expected to be used as drones for support services at disasters and global environment monitors. However, such applications have not been successfully attained due to the vehicle’s poor kinetic performances. Our team, then, tries to improve the kinetic performances of airships by installing cycloidal propellers which can instantly change thrusts toward arbitrarily directions by controlling attack angles of the rotor blades. In this study, we report results of static thrust measurement experiment of a cycloidal propeller for 10-meter class airships, and wind tunnel tests and flow measurements around a rotor by the particle image velocimetry (PIV) applying to a miniature cycloidal propeller. The radius of rotor, the chord and the span of blades, the number of blade of the cycloidal propeller for 10-meter class airships are respectively 0.4m, 0.3m, 0.5m, and 3, and those values for the miniature cycloidal propeller are respectively 0.16m, 0.12m, 0.2m, and 3. Firstly it was found that the cycloidal propeller for 10-meter class airships can generate 50N as the maximum thrust at a rotational speed of 8 rps and with attack angle of 25 degrees. Moreover, thrust directions deviate from instructed directions toward the rotational direction by 25 degrees at the maximum. Secondly, from the wind tunnel test, thrust coefficients were found to be decreasing as advance ratios increase, which corresponds to a tendency of general type propellers. In addition, it was clarified that the propeller intakes the air not only from the rotating surface of the propeller but also from the rotor axial direction of the propeller by visualizing the air flow around the rotor by PIV.

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2

Onda, Masahiko, Masaaki Sano, Kakuya Iwata, et al. "Airship-Type Crane Robot with Cycloidal Propellers." In 6th AIAA Aviation Technology, Integration and Operations Conference (ATIO). American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-7718.

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Nozaki, Hirohito, Yuya Sekiguchi, Kazuo Matsuuchi, et al. "Research and Development on Cycloidal Propellers for Airships." In 18th AIAA Lighter-Than-Air Systems Technology Conference. American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-2850.

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Leger, J., J. Páscoa, and C. Xisto. "3D Effects in Cyclorotor Propulsion Systems." In ASME 2015 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/imece2015-52173.

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A cycloidal propeller is an aircraft propulsion system that is composed by several blades rotating about a horizontal axis perpendicular to the flight direction. The rotor blades prescribe a periodic change on their pitch angle over a cycle of rotation. Many experimental, analytical and numerical studies have been developed in order to calculate force production and power required as well as the real simulation of the blades motion and the cyclorotor mechanical system operation. An important aspect of cycloidal propellers is the study of their efficiency both in hovering state and in forward motion considering 3D effects. For this purpose, it is developed a two-dimensional and three-dimensional CFD model of a cyclorotor whose blades describe the cycloidal path imposed by the pitch mechanical system control. Then, it is taken into account the experimental data for the proper validation. With the validated model, it presented and analyzed the 3D flow field around the cyclorotor under different operating conditions.

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Hu, Yu, Hailang Zhang, and Gengqi Wang. "Two dimensional and three dimensional numerical simulation of cycloidal propellers in hovering status." In 54th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-1350.

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6

Li Daizong. "Design of a new VTOL UAV by combining cycloidal blades and FanWing propellers." In 2013 IEEE Aerospace Conference. IEEE, 2013. http://dx.doi.org/10.1109/aero.2013.6496836.

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7

Hu, Yu. "Two dimensional numerical simulation of cycloidal propellers with flat plate airfoil in hovering status." In 2013 International Powered Lift Conference. American Institute of Aeronautics and Astronautics, 2013. http://dx.doi.org/10.2514/6.2013-4244.

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8

Rodrigues, F. F., M. Habibnia, and J. Pascoa. "Novel Propulsion System for VTOL Aircraft Based on Cycloidal Rotors Coupled With Wings." In ASME 2020 Fluids Engineering Division Summer Meeting collocated with the ASME 2020 Heat Transfer Summer Conference and the ASME 2020 18th International Conference on Nanochannels, Microchannels, and Minichannels. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/fedsm2020-20292.

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Abstract Aircraft being capable of Vertical Take-off and Landing (VTOL) and hover are increasingly emerging in various critical and routine applications. Rescue missions in roads and environmental disasters, observance and monitoring-based carriers, surveillance and payload carriage in environments that require high maneuverability and controllability are just a few examples in which this type of aircraft is essential. Helicopters are the most typical aircraft in this kind, but concerning the thrusting mechanism, several alternatives are yet in hand. The tendency to equip aircraft with cycloidal rotors (shortly say, cyclorotors) as means of Vertical Take-Off and Landing thrusters has increased in recent years. These devices present several advantages such as considerably lower noise production and more stable hover and vertical displacements in comparison with conventional screw propellers as used in helicopters. In the present work a novel concept of propulsion system combining two cycloidal rotors with a pair-wing system is presented. A double wing assembly is designed to place in between the two cyclorotors on each side of the aircraft. The bottom wing is intended to divide the flow in two separate portions through the downwash region of the front cycloidal rotor. To improve the efficiency of this propulsion system, the implementation of plasma actuators in the pair-wing system will be experimentally studied. The concept behind this novel propulsion system is explained and numerical and experimental results, that support its operation concept, are presented.

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Siegel, Stefan, Jürgen Seidel, Kelly Cohen, and Thomas McLaughlin. "A Cycloidal Propeller Using Dynamic Lift." In 37th AIAA Fluid Dynamics Conference and Exhibit. American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/6.2007-4232.

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Prabhu, J. Joseph, V. Nagarajan, and O. P. Sha. "Unsteady Flow Analysis of Marine Cycloidal Propeller." In ICSOT India 2015. RINA, 2015. http://dx.doi.org/10.3940/rina.icsotin15.2015.15.

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