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Modeling Helicopter Rotor Blade Flapping Motion Considering Nonlinear Aerodynamicsu

Majhi, Jyoti Ranjan and Ganguli, Ranjan (2008) Modeling Helicopter Rotor Blade Flapping Motion Considering Nonlinear Aerodynamicsu. In: CMES: Computer Modeling in Engineering & Sciences, 27 (1). pp. 25-36.

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The flapping equation for a rotating rigid helicopter blade is typically derived by considering 1) small flap angle, 2) small induced angle of attack and 3) linear aerodynamics. However, the use of nonlinear aerodynamics can make the assumptions of small angles suspect. A general equation describing helicopter blade flap dynamics for large flap angle and large induced inflow angle of attack is derived in this paper with nonlinear aerodynamics . Numerical simulations are performed by solving the nonlinear flapping ordinary differential equation for steady state conditions and the validity of the small angle approximations are examined. It is shown that the small flapping assumption, and to a lesser extent, the small induced angle of attack assumption can lead to inaccurate predictions of the blade flap response in certain flight conditions for some rotors when nonlinear aerodynamics is considered.

Item Type: Journal Article
Publication: CMES: Computer Modeling in Engineering & Sciences
Publisher: Tech Science Press
Additional Information: Copyright of this article belongs to Tech Science Press.
Keywords: Helicopter;Flapping;Aerodynamics;Aeroelasticity;Nonlinear System;Fluid-Structure Interaction.
Department/Centre: Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited: 18 Jul 2008
Last Modified: 27 Aug 2008 13:36
URI: http://eprints.iisc.ac.in/id/eprint/15084

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