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Dynamic stability of a rotor blade using finite element analysisThe aeroelastic stability of flap bending, lead-lag bending, and torsion of a helicopter rotor blade in hover is examined using a finite element formulation based on the principle of virtual work. Quasi-steady two-dimensional airfoil theory is used to obtain the aerodynamic loads. The rotor blade is discretized into beam elements, each with ten modal degrees of freedom. The resulting nonlinear equations of motion are solved for steady-state blade deflections through an iterative procedure. The flutter solution is calculated assuming blade motion to be a small perturbation about the steady solution. The normal mode method based on the coupled rotating natural modes about the steady deflections is used to reduce the number of equations in the flutter eigenanalysis. Results are presented for hingeless and articulated rotor blade configurations.
Document ID
19810045109
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Sivaneri, N. T.
(Stanford Univ. CA, United States)
Chopra, I.
(NASA Stanford Joint Institute for Aeronautics and Acoustics; Stanford University Stanford, Calif., United States)
Date Acquired
August 11, 2013
Publication Date
January 1, 1981
Subject Category
Structural Mechanics
Report/Patent Number
AIAA PAPER 81-0615
Meeting Information
Meeting: Conference on Structures, Structural Dynamics and Materials
Location: Atlanta, GA
Start Date: April 6, 1981
End Date: April 8, 1981
Accession Number
81A29513
Funding Number(s)
CONTRACT_GRANT: NCC2-13
Distribution Limits
Public
Copyright
Other

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