Analysis of a structural-aerodynamic fully-coupled formulation for aeroelastic response of rotorcraft

Bernardini, Giovanni; Serafini, Jacopo; Colella, Marco Molica; Gennaretti, Massimo

doi:10.1016/j.ast.2013.03.002

Cited by 47 publications

(43 citation statements)

References 16 publications

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“…Specifically, once the velocity potential, φ , is provided by BEM formulation , wake inflow is determined as follows:

{\overset{v}{true}}_{i} (\overset{x}{true}, t) = \nabla_{x} φ (\overset{x}{true}) = - \int_{S_{W}} normalΔ φ^{TE} ({\overset{y}{true}}_{TE}, t - τ) \nabla_{x} ((), \frac{∂G}{∂n}) dS (\overset{y}{true})

where

\overset{x}{true}

denotes a field point, S W the rotor wake surface (a zero‐thickness layer of vorticity released from the trailing edge of lifting bodies), and

\overset{y}{true}

a point on S W . Furthermore, G is the unit source solution of Laplace equation, whereas ∇ x denotes gradient operator with respect to

\overset{x}{true}

.…”

Section: Aeroelastic Modellingmentioning

confidence: 99%

“…Furthermore, G is the unit source solution of Laplace equation, whereas ∇ x denotes gradient operator with respect to

\overset{x}{true}

. In addition,

normalΔ φ^{TE} ({\overset{y}{true}}_{TE}, t - τ)

indicates the potential jump at trailing edge position,

{\overset{y}{true}}_{TE}

, where the wake material point currently in

\overset{y}{true}

emanated at time t − τ . The evaluation of

{\overset{v}{true}}_{i}

near the blade tip is critical because of the presence of concentrated wake singularities: in order to assure a stable and regular numerical solution, a finite‐thickness vortex model yielding a finite distribution of velocity within the vortex core is introduced .…”

Section: Aeroelastic Modellingmentioning

confidence: 99%

“…Steady‐periodic responses to arbitrary wind conditions (like, for instance, axial wind, yawed wind and vertical shear layer conditions) are evaluated by a harmonic balance approach applied to the proposed solution schemes .…”

Section: Aeroelastic Modellingmentioning

confidence: 99%

“…The resulting aeroelastic differential system is integrated through the Galerkin approach, with introduction of a novel, and computationally efficient, technique for spatial integration of additional aerodynamic states related to wake vorticity and dynamic stall. Steady‐periodic rotor response is evaluated by a harmonic‐balance technique at reduced computational costs, whilst a time‐marching solution algorithm is applied for evaluating responses to arbitrary inputs.…”

Section: Introductionmentioning

confidence: 99%

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Assessment of a comprehensive aeroelastic tool for horizontal‐axis wind turbine rotor analysis

et al. 2016

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This paper presents the development of a computational aeroelastic tool for the analysis of performance, response and stability of horizontal-axis wind turbines. A nonlinear beam model for blades structural dynamics is coupled with a state-space model for unsteady sectional aerodynamic loads, including dynamic stall effects. Several computational fluid dynamics structural dynamics coupling approaches are investigated to take into account rotor wake inflow influence on downwash, all based on a Boundary Element Method for the solution of incompressible, potential, attached flows. Sectional steady aerodynamic coefficients are extended to high angles of attack in order to characterize wind turbine operations in deep stall regimes. The Galerkin method is applied to the resulting aeroelastic differential system. In this context, a novel approach for the spatial integration of additional aerodynamic states, related to wake vorticity and dynamic stall, is introduced and assessed. Steady-periodic blade responses are evaluated by a harmonic balance approach, whilst a standard eigenproblem is solved for aeroelastic stability analyses. Drawbacks and potentialities of the proposed model are investigated through numerical and experimental comparisons, with particular attention to rotor blades unsteady aerodynamic modelling issues.

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“…Specifically, once the velocity potential, φ , is provided by BEM formulation , wake inflow is determined as follows:

{\overset{v}{true}}_{i} (\overset{x}{true}, t) = \nabla_{x} φ (\overset{x}{true}) = - \int_{S_{W}} normalΔ φ^{TE} ({\overset{y}{true}}_{TE}, t - τ) \nabla_{x} ((), \frac{∂G}{∂n}) dS (\overset{y}{true})

where

\overset{x}{true}

denotes a field point, S W the rotor wake surface (a zero‐thickness layer of vorticity released from the trailing edge of lifting bodies), and

\overset{y}{true}

a point on S W . Furthermore, G is the unit source solution of Laplace equation, whereas ∇ x denotes gradient operator with respect to

\overset{x}{true}

.…”

Section: Aeroelastic Modellingmentioning

confidence: 99%

“…Furthermore, G is the unit source solution of Laplace equation, whereas ∇ x denotes gradient operator with respect to

\overset{x}{true}

. In addition,

normalΔ φ^{TE} ({\overset{y}{true}}_{TE}, t - τ)

indicates the potential jump at trailing edge position,

{\overset{y}{true}}_{TE}

, where the wake material point currently in

\overset{y}{true}

emanated at time t − τ . The evaluation of

{\overset{v}{true}}_{i}

Section: Aeroelastic Modellingmentioning

confidence: 99%

Section: Aeroelastic Modellingmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Assessment of a comprehensive aeroelastic tool for horizontal‐axis wind turbine rotor analysis

et al. 2016

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“…16 Once the potential field is known, the Bernoulli theorem yields the pressure distribution to be provided to the aeroacoustic solver. 24 …”

Section: Rotor Aerodynamic Solvermentioning

confidence: 99%

Investigation on a High-Frequency Controller for Rotor BVI Noise Alleviation

Anobile¹

2016

IJAV

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Among the several sources of acoustic annoyance produced by rotorcraft in operating conditions, blade-vortex interactions (BVIs) capture the interest of much of the current research. This paper deals with the reduction of BVI noise from helicopter main rotors by application of the active twist rotor concept (ATR), exploiting smart materials for twisting blades through higher-harmonic torque loads. An optimal, multi-cyclic, control approach is applied to identify the control law driving the ATR actuation during the occurrence of severe BVI events. Numerical predictions are obtained through a computational tool that is able to predict the aeroelastic response of the rotor blades and the emitted noise in arbitrary steady flight conditions. The approach for the control law identification is described and numerical results concerning aeroelastic and aeroacoustic performance of the controlled rotor are presented to assess the proposed methodology.

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Rotary-Wings

Gennaretti

2024

Fundamentals of Aeroelasticity

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Analysis of a structural-aerodynamic fully-coupled formulation for aeroelastic response of rotorcraft

Cited by 47 publications

References 16 publications

Assessment of a comprehensive aeroelastic tool for horizontal‐axis wind turbine rotor analysis

Assessment of a comprehensive aeroelastic tool for horizontal‐axis wind turbine rotor analysis

Investigation on a High-Frequency Controller for Rotor BVI Noise Alleviation

Rotary-Wings

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