Browsing by Subject "Aircraft Design"
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ItemA conceptual design methodology for rotorcraft maneuverability( 2013) Patterson, F. ; Lamour, R. ; Schrage, D.
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ItemA new concept of the main rotor for a high-speed single-rotor helicopter( 2007) Pavlenko, N.S.
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ItemA new tail rotor for the S-61( 2010) Curtiss, H.C.
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ItemA study in helicopter fuselage drag( 2013) Batrakov, A.S. ; Kusyumov, A.N. ; Mikhailov, S.A. ; Pakhov, V. ; Sungatullin, A.R. ; Zherekhov, V.V. ; Barakos, G.N.
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ItemA system framework for design robustness analysis of helicopter mid-life upgrades( 2002) Kusumo, R. ; Sinha, A.K.
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ItemAdvanced technologies for a future heavy transport helicopter( 2007) Burgmair, R. ; Koletzko, W. ; Kreitmar-Steck, W. ; Weimer, C.
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ItemAerodynamic design optimization of helicopter rotor blades in hover performance using advanced configuration generation method( 2009) Vu, N.A. ; Kang, H.J. ; Azamatov, A.I. ; Lee, J.W. ; Byun, Y.H.
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ItemAerodynamic shape optimization of tiltrotor blades equipped with continuous morphing aerofoils( 2015) Pagano, A.This document explores the adoption of morphing blades on tiltrotors with the aim of improving the rotor aerodynamic performance. Rotors for such aircrafts are designed to simultaneously address the peculiarities of both axial flights (hover, vertical ascent/descent and cruise) and edge flights (flyover). Some of the current aerofoil morphing technologies are investigated from the aerodynamic point of view so that the blade can modify its shape to meet the best rotor performance for the examined flight conditions. The potential benefits are discussed through the application of numerical procedures on a realistic tiltrotor geometry.
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ItemAnalysis and conceptual design of a novel MAV rotorcraft( 2008) Hall, A. ; Wong, K.C. ; Auld, D.
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ItemArtificial icing flight trials on the EH101( 2004) Ramage, A.I.
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ItemBevel gear pattern optmisation( 2004) Thomassey, L. ; Icard, Y.
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ItemBeyond Clean Sky: Cartercopter slowed rotor / compound exceeds efficiency and emission goals( 2015) Carter, J. ; Lewis, J.R.Carter Aviation has its footing in environmental efforts with roots in the wind industry. Leveraging its very lightweight high inertia wind turbine blades for application as a rotor blade, Carter has developed its Slowed Rotor/Compound (SR/C™) technology as an alternative to conventional vertical lift. The benefits of slowing a rotor in cruise flight from both a drag and acoustic perspective are well understood, but doing so safely is another matter. Carter overcame 10 challenges to make the SR/C aircraft a reality, and with it, a new era of aviation is now possible. Runway independent aircraft (to include full hovering configurations) that possess efficiencies more akin to fixed-wing aircraft promise to deliver a cleaner, greener, and safer VTOL capability that exceeds environmental goals of Clean Sky 2. CO2 emission reductions of 80% for the jump takeoff CarterCopters have been demonstrated and a 66% reduction for a full hovering heavy twin is predicted. And, all of this is accomplished with 15-20 EPNdB less noise than helicopters.
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ItemBlade shape optimization for HSI noise reduction and performance improvement of helicopter( 2008) Chae, S. ; Yee, K. ; Yang, C. ; Aoyama, T. ; Jeong, S. ; Obayashi, S.
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ItemBluecopter demonstrator – an approach to eco-efficient helicopter design( 2015) Bebesel, M. ; D'Alascio, A. ; Schneider, S. ; Guenther, S. ; Vogel, F. ; Wehle, C. ; Schimke, D.The "BLUECOPTER DEMONSTRATOR" presented in this paper has been developed to prove the feasibility of future eco-friendly helicopter concepts and to demonstrate "green" technologies in-flight. The main objectives are: • Significant reduction in CO2 emission and fuel consumption up to 40%; • Noise reduction of around 10 EPNdB below ICAO §8.4.1 noise certification limits; • Development of "transversal" technologies allowing for serial applications to all helicopter classes. A major contribution to the improved efficiency and reduced acoustic emission of the BLUECOPTER DEMONSTRATOR is provided by the newly developed rotor system. It includes an innovative five-bladed bearingless main rotor with increased diameter, BlueEdge™ style blade shape, new twist distribution and low tip speed design. Moreover it features an advanced Fenestron® with an optimized blade and stator design. Several measures were applied to reduce the drag of the aircraft including fairings for the main rotor and landing skids, a special design of the aft-body and a low-drag empennage including a "T-Tail" horizontal stabilizer. Additional features like the active fin rudder and the "acoustic liner" for the Fenestron shroud have been applied to further improve the acoustic footprint of the demonstrator. The BLUECOPTER DEMONSTRATOR has been successfully flight tested in 2014 and will be further improved and tested in 2015. This paper gives an overview on the technologies proven in-flight and summarizes the benefits achieved in terms of performance and acoustic emissions.
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ItemCLEANSKY green rotorcraft new technologies – Maximizing noise and emissions benefits( 2016) Stevens, J. ; Smith, C. ; Thevenot, L. ; D'Ippolito, R. ; Gires, E. ; Castillo Pardo, A. ; Pachidis, V.
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ItemComanche technology status( 2004) Lewis, W.D. ; Richey, J.M.
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ItemComparative study of optimal active twists for helicopter rotor blades with C and D-spars( 2007) Kovalov, A.O. ; Barkanov, E.N. ; Gluhih, S.A.