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Analysis of helicopter vibratory hub loads alleviation by cyclic trailing-edge blade flap actuation

Published online by Cambridge University Press:  03 February 2016

M. Gennaretti ,
M. Molica Colella  and
G. Bernardini
M. Gennaretti
Affiliation:
[email protected], University Roma Tre, Department of Mechanical and Industrial Engineering, Rome, Italy
M. Molica Colella
Affiliation:
[email protected]
G. Bernardini
Affiliation:
[email protected]
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Abstract

The aim of the present work is the investigation about the use of blade trailing-edge flaps for the reduction of vibratory loads arising at the hub of helicopter main rotors in forward flight. The alleviation of these loads is achieved through multicyclic higher harmonic actuation of the blade flaps, which is related to measured vibratory loads amplitude. The feedback control law is obtained by an optimal control process based on the minimisation of a cost function, under the constraint of compatibility with the nonlinear equations governing blade aeroelasticity. In the numerical investigation concerning a four-bladed rotor in level flight conditions, a computationally efficient local controller methodology is applied, with the attention focused on the effectiveness of the control algorithm, along with its robustness with respect to differences (existing in real applications) between the aeroelastic models used for control law synthesis and validation.

Type
Research Article
Information
The Aeronautical Journal , Volume 113 , Issue 1146 , August 2009 , pp. 549 - 556
Copyright
Copyright © Royal Aeronautical Society 2009 

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