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Modeling Helicopter Rotor Blade Flapping Motion Considering Nonlinear Aerodynamics

Jyoti Ranjan Majhi, Ranjan Ganguli1
Department of Aerospace Engineering, Indian Institute of Science, Bangalore-560012, India

Computer Modeling in Engineering & Sciences 2008, 27(1&2), 25-36. https://doi.org/10.3970/cmes.2008.027.025

Abstract

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.

Keywords

Helicopter, Flapping, Aerodynamics, Aeroelasticity, Nonlinear System, Fluid-Structure Interaction

Cite This Article

Majhi, J. R., Ganguli, R. (2008). Modeling Helicopter Rotor Blade Flapping Motion Considering Nonlinear Aerodynamics. CMES-Computer Modeling in Engineering & Sciences, 27(1&2), 25–36.



This work is licensed under a Creative Commons Attribution 4.0 International License , which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
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