Abstract
VPM/CFD-Based Research on Rotor Performance and Loads of Individual Blade Control Rotor System
Highlights
For a helicopter, it is more difficult to maintain stability in forward flight than in hovering
This paper aims to explore the effect of individual blade control (IBC) on aerodynamic performance of helicopter rotor and explain its formation mechanism
The proposed method was proved valid; the effect of control frequency and phase on the helicopter performance was analysed under different forward flight conditions; the mechanism of IBC control was examined by comparing the lift coefficient distribution and the induced inflows of the optimal control and the worst control
Summary
It is more difficult to maintain stability in forward flight than in hovering. During the forward flight, the blades are in a periodically changing aerodynamic environment. In the near-blade region, there exist prominent nonlinear flow phenomena, such as separate flow and shock wave. The strong tip vortex in the flow field seriously disturbs the movement and induces a highly nonlinear velocity field. When the blades move close to the vortex, the blade-vortex interaction (BVI) is formed, producing nonlinear oscillations of aerodynamic loads. The ensuing vibration and noise make it difficult to optimize the aerodynamic performance of the helicopter. This calls for the reduction of the nonlinear fluctuations of rotor aerodynamic loads
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