Aeroelastic analysis of helicopter rotor blade in hover using an efficient reduced-order aerodynamic model

Shahverdi, Hossein; Nobari, A.S.; Behbahani–Nejad, Morteza; Haddadpour, H.

doi:10.1016/j.jfluidstructs.2009.06.007

Cited by 16 publications

(19 citation statements)

References 26 publications

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“…1 Schematic of elastic deformation components of the blade [3] copter rotor blades with the unsteady aerodynamic model based on Greenberg theory and using the Loewy aerodynamic function. The parameters of the considered four-bladed rotor are tabulated in Table 1.…”

Section: Resultsmentioning

confidence: 99%

“…These equations which are completely nonlinear are used in this study in comparison with previous studies [2,3,9] which used the linearized format of these equatios around static deflection.…”

Section: Structural and Aerodynamic Modelsmentioning

confidence: 99%

“…Perturbation theory is another useful method which is used extensively in the nonlinear aeroelastic analysis for finding flutter boundaries. This theory is applicable for determining mode shapes and frequencies of nonlinear dynamical systems through eigenvalue analysis [2,3]. Moreover, it can be used for investigating stability of systems in the time domain about an equilibrium operating condition.…”

Section: Introductionmentioning

confidence: 99%

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Nonlinear aeroelastic stability analysis of hingeless helicopter rotor blades using FRF coupling and condition number

2015

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In this paper, aeroelastic stability analysis of hingeless helicopter blades in frequency domain is studied. In this regard, the nonlinear structural beam model of Hodges-Dowell and an unsteady aerodynamic model based on Greenberg theory and using Loewy aerodynamic function are considered to construct the aeroelastic model. Then, the concept of optimum equivalent linear frequency response function (OELF) is implemented to derive the aeroelastic FRF by coupling the aerodynamic and structural FRFs. Finally, for stability analysis, the efficient and simple criterion of condition number (CN) of aeroelastic OELF is applied. The comparison of the obtained results against those in the literature shows the capability of the OELF and condition number criterion for capturing the instability boundaries of a complex, nonlinear, aeroelastic system such as helicopter blades.

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Section: Resultsmentioning

confidence: 99%

Section: Structural and Aerodynamic Modelsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Nonlinear aeroelastic stability analysis of hingeless helicopter rotor blades using FRF coupling and condition number

2015

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“…Table 10 shows the values of the aerodynamic coefficients computed with the ROM and the CFD fields. In addition to the thrust and torque coefficients, a third indicator (i.e., the figure of merit) is also reported [27]. This coefficient is typically used in the helicopter aerodynamics to assess the performances of the rotor; it is a combination of the thrust and torque and is the analog of the aerodynamic efficiency in the case of fixed-wing aircraft.…”

Section: A Definition Of the Reduced Modelmentioning

confidence: 99%

“…In the area of helicopter aerodynamics, the use of modal ROMs is not very well documented in the literature. Some recent pertinent examples in the context of aeroelasticity for helicopter rotor blades can be found in [25,26], whereas a first attempt to address the entire aerodynamic field around a rotor via modal ROM is presented in [27].…”

Section: Introductionmentioning

confidence: 99%

Evaluation of Aerodynamic Loads via Reduced-Order Methodology

Fossati

2015

AIAA Journal

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Centroidal Voronoi tessellation, leave-one-out cross validation, proper orthogonal decomposition, and multidimensional interpolation are integrated to define a reduced-order modeling approach for the parametric evaluation of steady aerodynamic loads. The proper orthogonal decomposition-based methodology allows reducing the number of degrees of freedom of the problem while maintaining good accuracy for the solution of complex threedimensional viscous turbulent flows. As a result, it yields fairly accurate solutions at a fraction of the time required by standard computational fluid dynamics approaches. Three-dimensional examples for fixed-and rotary-wing cases of industrial relevance are used to assess the method in the cases of subsonic and transonic flow conditions.

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