Abstract
In this paper, an accurate structural dynamic analysis was developed for a helicopter rotor system including rotor
control components, which was coupled to various aerodynamic and wake models in order to predict an aeroelastic
response and the loads acting on the rotor. Its blade analysis was based on an intrinsic formulation of moving beams
implemented in the time domain. The rotor control system was modeled as a combination of rigid and elastic
components. A multicomponent analysis was then developed by coupling the beam finite element model with the
rotor control system model to obtain a complete rotor-blade/control-system aeroelastic analysis. The rotor blade
analysis was in good agreement and validated by comparing with DYMORE. Numerical results were obtained for a
four-bladed, small-scale, articulated rotor rotating in vacuum and in a wind tunnel to simulate forward-flight
conditions and its aerodynamic effects. The complete rotor-blade/control-system model was loosely coupled with
various inflow and wake models in order to simulate both hover and forward-flight conditions. The resulting rotor
blade response and pitch link loads are in good agreement with those predicted byCAMRADII. The present analysis
features both model compactness and robustness in its solution procedure while capturing the sophisticated behavior
of individual rotor components. The analysis is expected to be part of a framework useful in the preliminary design
phase for helicopters.
Original language | English |
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Journal | Journal of Aircraft |
Volume | 47 |
Issue number | 4 |
Pages (from-to) | 1382-1390 |
ISSN | 0021-8669 |
DOIs | |
Publication status | Published - 2010 |
Keywords
- Aeroelastic design methods
- Wind Energy