Numerical optimization of helicopter rotor aerodynamic performance in hover

Pape, Arnaud Le; Beaumier, Philippe

doi:10.1016/j.ast.2004.09.004

Cited by 77 publications

(49 citation statements)

References 13 publications

(17 reference statements)

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“…Indeed, the drag torque presents the flight main issue caused by the reaction of the air on the propeller blades. Le Pape and Beaumier (2005) confirm that there are two parameters characterising any kind of propeller: its diameter is called length and the pitch defines the vertical travelled gap after full rotation. This parameter is crucial to establish the relationship between aerodynamic forces and the propeller velocity and the following expression is given:…”

Section: Flight Methodologymentioning

confidence: 93%

“…In contrast to Kulhare et al (2012) who presented a model with highly coupled aerodynamic forces, this paper proposed a reduced dynamic model. Compared to all previous works in Rys et al (2014) and Le Pape and Beaumier (2005), we got to extract some relationships between forces. Thus it has been shown that we can reduce the dynamic presentation of our system.…”

Section: Introductionmentioning

confidence: 99%

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Trirotor mechatronic design and reduction of dynamic model inputs by aerodynamic forces identification

Chabir

Bouteraa

Boucetta

2017

IJMIC

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This paper outlines a mechatronic design and a remote measurement system of a trirotor unmanned aerial vehicle (UAV). Furthermore, with particular emphasis on the experimental aspect, this study presents also a real dynamic model with reduced inputs made by experimental aerodynamic forces/torques identification. The trirotor presents a real control challenge compared with the quadrotor system. Indeed, in contrast to the quadrotor, the trirotor presents a non-symmetric structure and it has an odd number of rotors which causes a yaw moment issue. The developed mechanical design and the actuators characteristics are then presented. Experimental tests show that we can have a reduced dynamic model. Indeed, with empirical manipulations we deduce some relations between drag torque and thrust forces. Such result allows us to reduce the trirotor developed model inputs. Finally, this study is a preliminary phase before the real-time control implementation.Keywords: trirotor UAV; mechatronic design; aerodynamic forces identification.Reference to this paper should be made as follows: Chabir, A., Bouteraa, Y. and Boucetta, R. (2017) 'Trirotor mechatronic design and reduction of dynamic model inputs by aerodynamic forces identification', Int.

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Section: Flight Methodologymentioning

confidence: 93%

Section: Introductionmentioning

confidence: 99%

Trirotor mechatronic design and reduction of dynamic model inputs by aerodynamic forces identification

Chabir

Bouteraa

Boucetta

2017

IJMIC

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“…Recently, state-of-the-art computational techniques and numerical methods have been extensively used to simulate the aerodynamic performance of advanced rotor blades [8][9][10]. However, an accurate prediction of the flow field around a rotorcraft still remains as one of the most challenging problems, even for modern computational fluid dynamics This is an Open Access article distributed under the terms of the Creative Commons Attribution Non-Commercial License (http://creativecommons.org/licenses/bync/3.0/) which permits unrestricted non-commercial use, distribution, and reproduction in any medium, provided the original work is properly cited.…”

Section: Introductionmentioning

confidence: 99%

Assessment of Tip Shape Effect on Rotor Aerodynamic Performance in Hover

Hwang¹,

Kwon²

2015

International Journal of Aeronautical and Space Sciences

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In the present study, an unstructured mixed mesh flow solver was used to conduct a numerical prediction of the aerodynamic performance of the S-76 rotor in hover. For the present mixed mesh methodology, the near-body flow domain was modeled by using body-fitted prismatic/tetrahedral cells while Cartesian mesh cells were filled in the off-body region. A high-order accurate weighted essentially non-oscillatory (WENO) scheme was employed to better resolve the flow characteristics in the off-body flow region. An overset mesh technique was adopted to transfer the flow variables between the two different mesh regions, and computations were carried out for three different blade configurations including swept-taper, rectangular, and swept-taper-anhedral tip shapes. The results of the simulation were compared against experimental data, and the computations were also made to investigate the effect of the blade tip Mach number. The detailed flow characteristics were also examined, including the tip-vortex trajectory, vortex core size, and first-passing tip vortex position that depended on the tip shape.

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“…The aerodynamic shape optimization of a rotorcraft has been carried out using different aerodynamic modelling of the main rotor. Thus non-linear frequency domain method to solve the unsteady viscous flow is applied in reference [4] and a 3D Navier-Stokes solver is used in reference [5]. Other authors used simpler models, for instance a combined lifting-line blade with a prescribed wake and a free-wake models are applied in reference [6].…”

Section: Introductionmentioning

confidence: 99%

Use of calculus of variations to determine the shape of hovering rotors of minimum power and its application to micro air vehicles

López-García

Cuerva

Esteban

2011

Proceedings of the Institution of Mechanical Engineers, Part G:

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Abstract:In this paper, calculus of variations and combined blade element and momentum theory (BEMT) are used to demonstrate that, in hover, when neither root nor tip losses are considered; the rotor, which minimizes the total power (MPR), generates an induced velocity that varies linearly along the blade span. The angle of attack of every blade element is constant and equal to its optimum value. The traditional ideal twist (ITR) and optimum (OR) rotors are revisited in the context of this variational framework. Two more optimum rotors are obtained considering root and tip losses, the ORL, and the MPRL. A comparison between these five rotors is presented and discussed. The MPR and MPRL present a remarkable saving of power for low values of both thrust coefficient and maximum aerodynamic efficiency. The result obtained can be exploited to improve the aerodynamic behaviour of rotary wing micro air vehicles (MAV). A comparison with experimental results obtained from the literature is presented.

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Numerical optimization of helicopter rotor aerodynamic performance in hover

Cited by 77 publications

References 13 publications

Trirotor mechatronic design and reduction of dynamic model inputs by aerodynamic forces identification

Trirotor mechatronic design and reduction of dynamic model inputs by aerodynamic forces identification

Assessment of Tip Shape Effect on Rotor Aerodynamic Performance in Hover

Use of calculus of variations to determine the shape of hovering rotors of minimum power and its application to micro air vehicles

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