Minimum-Induced Power Loss of a Helicopter Rotor via Circulation Optimization

Rand, Omri; Khromov, Vladimir; Peyran, R. J.

doi:10.2514/1.9085

Cited by 7 publications

(2 citation statements)

References 3 publications

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“…Through reconfiguration, or active control, during operation performance, improvement may be realized over diverse operating conditions. Several researchers (Hall et al, 1994;Kroninger, 2008;Moffitt and Bissell, 1982;Rand et al, 2004;Wachspress et al, 2005) have examined the optimal airload distribution over the rotor disk that would produce the required rotor forces and moments for trim at the lowest power requirement. But how these optimal airload distributions can be practically achieved remains a question.…”

Section: Introductionmentioning

confidence: 99%

Design, fabrication, and benchtop testing of a helicopter rotor blade section with warp-induced spanwise camber variation

Mistry

Gandhi

2014

Journal of Intelligent Material Systems and Structures

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This article focuses on the design, fabrication, testing, modeling, and validation of a spanwise variable camber section of a helicopter rotor blade. The lower surface skin was slit aft of the trailing edge spar and subjected to a spanwise warping actuation input. A kinematic linkage facilitates a corresponding chordwise motion of the skin along the span length (from zero at the no-camber end to maximum at the maximum camber end). Input warping actuation of 0.18 in length produced an 18°camber variation over a 45 in span section of a modified CH-46 blade. Finite element model predictions of the active camber section showed good agreement with benchtop test data for both the output camber for a given warping actuation input and the corresponding actuation force required. Finite element results suggest that some geometry distortions in the active camber section could be experienced due to the presence of centrifugal and aerodynamic loads, but these distortions could be alleviated with the introduction of a shear-flexible (but stiff through the thickness) core.

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Section: Introductionmentioning

confidence: 99%

Design, fabrication, and benchtop testing of a helicopter rotor blade section with warp-induced spanwise camber variation

Mistry

Gandhi

2014

Journal of Intelligent Material Systems and Structures

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“…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]. In some cases, even the classic combined blade element and momentum theory (BEMT) is used to perform an aerodynamic shape optimization of a coaxial rotor, see reference [7], or to evaluate new rotor control mechanisms in MAV, see reference [8].…”

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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Minimum Induced Power for a Rotor with a Finite Number of Blades

Hong

Peters

2018

Journal of Aircraft

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Minimum-Induced Power Loss of a Helicopter Rotor via Circulation Optimization

Cited by 7 publications

References 3 publications

Design, fabrication, and benchtop testing of a helicopter rotor blade section with warp-induced spanwise camber variation

Design, fabrication, and benchtop testing of a helicopter rotor blade section with warp-induced spanwise camber variation

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

Minimum Induced Power for a Rotor with a Finite Number of Blades

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