Correlation of Aeroelastic Response and Structural Loads for a Rotor in Descent

Jung, Sung Nam; You, Young Hyun; Kim, Jee Woong; Hwan, Jeong; Park, Jae Sang; Park, Soo Hyung

doi:10.2514/1.c031287

Cited by 8 publications

(13 citation statements)

References 14 publications

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“…Many attempts have been made to use CFD-based approaches for the validation of the HART II rotor [6][7][8][9][10][11][12][13][14][15]. The CFD-based methods developed for the HART II validation can be divided into two different categories, with a view of incorporating the effects of blade elastic motions.…”

mentioning

confidence: 99%

Loose Fluid-Structure Coupled Approach for a Rotor in Descent Incorporating Fuselage Effects

Jung

Hwan

You

et al. 2013

Journal of Aircraft

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A loose coupling approach is used to combine a comprehensive structural dynamics code CAMRAD II and a computational fluid dynamics solver KFLOW to validate the data and to identify the effect of fuselage on the aeroelastic behavior of the second higher harmonic rotor acoustic test rotor. The computations are made using isolated rotor and rotor-fuselage models. To demonstrate the effect of a fuselage, the shaft tilt angles remain identical for both configurations. A good correlation has been obtained with the present computational fluid dynamics/ comprehensive structural dynamics method. It is observed that a rotor-fuselage model improves the correlation significantly in terms of magnitudes and phases of the airloads solution. All the blade-vortex interaction peaks are captured accurately, and the phase shift in the section normal forces improves significantly, with the inclusion of a fuselage. The sources of improvements are investigated, considering the vorticity distributions and induced velocity fields of a rotor. It is revealed that the upwash pattern due to a fuselage is not restricted locally but propagates to considerable portions of the disk. Numerical results indicate that the upwash is responsible to lift up vortices at the zone of interest for a reduced miss distance, which results in a stronger blade-vortex interaction for improved correlations. Nomenclature= hub-based Cartesian coordinates α s = shaft tilt angle θ 0 , θ 1c , θ 1s = control pitch angles μ = advance ratio σ = solidity ψ = rotor azimuth angle Ω = rotor rotational speed

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mentioning

confidence: 99%

Loose Fluid-Structure Coupled Approach for a Rotor in Descent Incorporating Fuselage Effects

Jung

Hwan

You

et al. 2013

Journal of Aircraft

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“…Start time of a force response in an experiment is either not available or has uncertainties. Often unprecedented procedures such as arbitrarily removing the mean from the computations is followed [7] in LC methods that results in better comparisons with experiments. On the other hand to minimize uncertainties fixed wing community historically has preferred [3,24] to compare results in frequency domain by performing Fourier transformation [25].…”

Section: Guru P Guruswamy 77mentioning

confidence: 99%

“…Figure 12 shows a snapshot of vorticity magnitude and, surface pressure on the HART II body. Wakes are modeled in the LC/DC approach [7], whereas here they are directly computed using the RANS equations. The development of tip-vortices and bladewake structure can be seen in Figure 12.…”

Section: Guru P Guruswamy 77mentioning

confidence: 99%

“…Although a formal proof of solution-convergence to a time-periodic state has not yet been obtained for the LC/DC method, it has been applied when the flow is periodic in time as in forward flight at constant speed [7]. However, in general the LC/DC is not applicable when the flow is transient, for example, accelerating and decelerating rotors or maneuver [8].…”

Section: Introductionmentioning

confidence: 97%

“…Comprehensive methods use measured parameters (such as thrust and moment forces) to compute the control angles [6] instead of using those measured in experiment. This approach of combining comprehensive methods with the Euler or RANS flow equations is known as loose coupling (LC) or delta-load coupling (DC) [7].…”

Section: Introductionmentioning

confidence: 99%

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Time-Accurate Aeroelastic Computations of a Full Helicopter Model using the Navier-Stokes Equations

Guruswamy¹

2013

International Journal of Aerospace Innovations

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A time-accurate procedure to model fluid/structure interactions of helicopter blades is presented. The Navier-Stokes equations in conjunction with the one-equation SpalartAllmaras turbulence model are used to compute the flow. Structural dynamics is modeled using the modal equations. The aerodynamic and structural dynamic equations are coupled time-accurately using the linear acceleration method of Newmark (direct integration scheme). Effects of time accuracy on the computed results are investigated. Results are compared with experimental data for a full rotor blade system.

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Optimal deployment schedule of an active twist rotor for performance enhancement and vibration reduction in high-speed flights

You

Jung

Kim

2017

Chinese Journal of Aeronautics

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Correlation of Aeroelastic Response and Structural Loads for a Rotor in Descent

Cited by 8 publications

References 14 publications

Loose Fluid-Structure Coupled Approach for a Rotor in Descent Incorporating Fuselage Effects

Loose Fluid-Structure Coupled Approach for a Rotor in Descent Incorporating Fuselage Effects

Time-Accurate Aeroelastic Computations of a Full Helicopter Model using the Navier-Stokes Equations

Optimal deployment schedule of an active twist rotor for performance enhancement and vibration reduction in high-speed flights

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