Aeroelastic Analysis of a Hingeless Rotor Blade in Forward Flight

The aeroelastic response and stability of isotropic and composite rotor blades re investigated using a large diflection-type beam theory. The finite element equations of motion for beams undergoing arbitrary large displacements and rotations, but small strains, are obtained from Hamilton's prin...

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Bibliographic Details
Published in:AIAA journal 2000-05, Vol.38 (5), p.843-850
Main Authors: Jeon, Seong Min, Lee, In
Format: Article
Language:English
Subjects:
Aerodynamics
Composite beams and girders
Deflection (structures)
Deformation
Elastic moduli
Equations of motion
Exact sciences and technology
Finite element analysis
Finite element method
Flight dynamics
Fundamental areas of phenomenology (including applications)
Mathematical models
Natural frequencies
Physics
Rotation
Solid mechanics
Structural and continuum mechanics
Theory
Vibration, mechanical wave, dynamic stability (aeroelasticity, vibration control...)
Vibrations and mechanical waves
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Summary:The aeroelastic response and stability of isotropic and composite rotor blades re investigated using a large diflection-type beam theory. The finite element equations of motion for beams undergoing arbitrary large displacements and rotations, but small strains, are obtained from Hamilton's principle. The sectional elastic constants of a composite box beam including warping deformations are determined from the refined cross-sectional finite element method.
ISSN:0001-1452
1533-385X
DOI:10.2514/2.1038