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Rotorcraft-pilot coupling analysis through state-space aerodynamic modelling

Published online by Cambridge University Press:  27 January 2016

J. Serafini ,
L. Greco  and
M. Gennaretti
J. Serafini*
Affiliation:
Roma Tre University, Department of Engineering, Rome, Italy
L. Greco
Affiliation:
CNR-INSEAN, Marine Technology Research Institute, Rome, Italy
M. Gennaretti
Affiliation:
Department of Engineering, Roma Tre University, Rome, Italy
*
serafini@uniroma3.it
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Abstract

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The terminology ‘rotorcraft-pilot coupling’ denotes phenomena arising from interaction between pilot and rotorcraft. Among these, the present work deals with ‘pilot-assisted oscillations’ that derive from unintentional pilot actions on controls due to seat vibrations, and are strictly related to rotor-aeroelasticity/airframe-structural-dynamics coupling, with involvement of blade control actuator dynamics. Focusing the attention on helicopters, a comprehensive rotorcraft model is developed and applied, with main rotor unsteady aerodynamics described in state-space form. This makes it particularly suited for stability and frequency-response analysis, as well as control applications. Numerical investigations address two critical rotorcraft-pilot coupling aeroelastic issues: stability of vertical bouncing and gust response in hovering. Results from main rotor unsteady aerodynamics modelling are compared with widely-used quasi-steady aerodynamics predictions. These suggest that, for accurate RPC/PAO phenomena predictions, mathematical modelling should include the three-dimensional, unsteady-flow effects, and that the pilot-in-the-loop passive behaviour produces a beneficial effect on the load factor generated by gust encountering.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 119 , Issue 1219 , September 2015 , pp. 1105 - 1122
Copyright
Copyright © Royal Aeronautical Society 2015

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