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Aeroelastic response of helicopter rotors using a 3D unsteady aerodynamic solver

Published online by Cambridge University Press:  03 February 2016

M. Gennaretti  and
G. Bernardini
M. Gennaretti
Affiliation:
University Roma Tre, Department of Mechanical and Industrial Engineering, Rome, Italy
G. Bernardini
Affiliation:
University Roma Tre, Department of Mechanical and Industrial Engineering, Rome, Italy
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Abstract

The prediction of blade deflections and vibratory hub loads concerning helicopter main rotors in forward flight is the objective of this work. They are determined by using an aeroelastic model derived through the coupling between a nonlinear blade structural model and a boundary integral equation solver for three-dimensional, unsteady, potential aerodynamics. The Galerkin method is used for the spatial integration, whereas the periodic blade response is determined by a harmonic balance approach. This aeroelastic model yields a unified approach for aeroelastic response and blade pressure prediction that may be used for aeroacoustic purposes, with the possibility of including effects from both blade-vortex interaction and multiple-body aerodynamic interaction. Quasi-steady aerodynamic models with wake-inflow from the three-dimensional aerodynamic solver are also applied, in order to perform a comparative study. Numerical results show the capability of the aeroelastic tool to evaluate blade response and vibratory hub loads for a helicopter main rotor in level flight conditions, and examine the sensitivity of the predictions on the aerodynamics model used.

Type
Research Article
Information
The Aeronautical Journal , Volume 110 , Issue 1114 , December 2006 , pp. 793 - 801
Copyright
Copyright © Royal Aeronautical Society 2006 

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