Dynamic Stability of a Rotor Blade Using Finite Element Analysis

Sivaneri, N. T.; Chopra, Inderjit

doi:10.2514/3.51129

Cited by 57 publications

(16 citation statements)

References 8 publications

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“…The torsional degree of freedom <£, instead of 0, is used in the present analysis to keep the banded character of the system matrices. 19 The Hamilton's principle given in Eq. (6) is discretized as…”

Section: Finite Element Discretizationmentioning

confidence: 99%

“…The resulting flutter equations of motion, which include the information for dynamic inflow and structural damping, can be written in the following form = 0 (19) where the bars over the matrices indicate that these matrices have been evaluated using the modal coordinate transformation, C% is the modal damping matrix defined in Eq. (15), and r the modal coordinates.…”

Section: Solution Proceduresmentioning

confidence: 99%

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Aeroelastic response of composite rotor blades considering transverse shear and structural damping

Jung

Kim

1994

AIAA Journal

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The effects of transverse shear deformations and structural damping on the flutter phenomena of a composite rotor blade in hover have been investigated using the finite element method. First-order shear deformation theory with rotary inertia effects and a damped element model of composite laminates are employed for the structural formulation. A quasisteady aerodynamic theory with a dynamic inflow model is used. Torsion-related out-of-plane warping and noncirculatory aerodynamic components are also incorporated in the formulation. Using these structural and aerodynamic tools, several numerical studies are carried out, first to validate the current approach and second to show the effects of transverse shear deformations and structural damping on the aeroelastic stability of a composite rotor as a function of fiber orientation. The predictions derived by the frequency analysis of this model are found to be more accurate than those given by an alternative approach compared with experimental data. It is shown that the transverse shear flexibility tends to lower the frequency of the rotor, and generally has a destabilizing effect on the lag mode and a stabilizing effect on the flap mode. It is also presented that the magnitude of structural damping can be controlled by changing ply orientation angle.

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Section: Finite Element Discretizationmentioning

confidence: 99%

Section: Solution Proceduresmentioning

confidence: 99%

Aeroelastic response of composite rotor blades considering transverse shear and structural damping

Jung

Kim

1994

AIAA Journal

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“…Therefore, ordering schemes are introduced. [5][6][7][8][9] However, the derivation of the equation of motion with an ordering scheme is not consistent. It is very dependent on who conducts the analyses and which nonlinear effects produced by higher order terms are neglected.…”

Section: Introductionmentioning

confidence: 99%

Development of an anisotropic beam finite element for composite wind turbine blades in multibody system

2013

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Link back to DTU OrbitCitation (APA): Kim, T., Hansen, A. M., & Branner, K. (2013 ABSTRACTIn this paper a new anisotropic beam finite element for composite wind turbine blades is developed and implemented into the aeroelastic nonlinear multibody code, HAWC2, intended to be used to investigate if use of anisotropic material layups in wind turbine blades can be tailored for improved performance such as reduction of loads and/or increased power capture. The element stiffness and mass matrices are first derived based on pre-calculated anisotropic beam properties, and the beam element is subsequently put into a floating frame of reference to enable full rigid body displacement and rotation of the beam. This derivation provides the mass and stiffness properties and the fictitious forces needed for implementation into HAWC2. The implementation is subsequently validated by running three validation cases which all show good agreement with results obtained by other authors. Further, a parametric study is conducted in order to investigate if the given anisotropic effect of the composite blade, bend-twist coupling effect, is able to be examined by the developed beam element in a multibody system or not. Two different coupled examples of bend-twist coupling for the blade of a 5MW fictitious wind turbine are considered. The two cases differ in the amount of bend-twist coupling introduced into the blade so that they produce 0.3deg and 1deg twist at the blade tip (towards feather), respectively, for a 1m flapwise tip deflection towards the tower. It is examined if the current structural model is able to capture the anisotropic effects in a multibody system.

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“…Because of the blades' multi-restriction at root and configuration changing span-wisely, it is more suitable to model with a finite element approach [8][9] , which can involve all kinds of blades' nonuniformity (mass, stiffness, etc.). Based on the typical moderate deflection beam theory [10] and the Hamilton principle, the blade equation of motion is expressed as…”

Section: Blade Dynamic Equations and The Calculation Of Responsesmentioning

confidence: 99%

Nonlinear aeroelastic coupled trim and stability analysis of rotor-fuselage

Jing

2010

Appl. Math. Mech.-Engl. Ed.

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Based on the Hamilton principle and the moderate deflection beam theory, discretizing the helicopter blade into a number of beam elements with 15 degrees of freedom, and using a quasi-steady aero-model, a nonlinear coupled rotor/fuselage equation is established. A periodic solution of blades and fuselage is obtained through aeroelastic coupled trim using the temporal finite element method (TEM). The Peters dynamic inflow model is used for vehicle stability. A program for computation is developed, which produces the blade responses, hub loads, and rotor pitch controls. The correlation between the analytical results and related literature is good. The converged solution simultaneously satisfies the blade and the vehicle equilibrium equations.

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Dynamic Stability of a Rotor Blade Using Finite Element Analysis

Cited by 57 publications

References 8 publications

Aeroelastic response of composite rotor blades considering transverse shear and structural damping

Aeroelastic response of composite rotor blades considering transverse shear and structural damping

Development of an anisotropic beam finite element for composite wind turbine blades in multibody system

Nonlinear aeroelastic coupled trim and stability analysis of rotor-fuselage

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