VPM/CFD-Based Research on Rotor Performance and Loads of Individual Blade Control Rotor System

Abstract

This paper aims to explore the effect of individual blade control (IBC) on aerodynamic performance of helicopter rotor and explain its formation mechanism. For this purpose, the vortex particle method (VPM)-computational fluid dynamics (CFD) coupling method was proposed to calculate rotor aerodynamic performance under open-loop IBC active control. Specifically, the near-blade flow field was calculated by the CFD method, while the far-field flow field was solved by the VPM method. In this way, the entire flow field was computed through the information interaction between the two calculated fields. Then, the UH-60A rotor was selected as an example to verify the established VPM/CFD method. First, the proposed method was proved valid; then, the effect of control frequency and phase on the helicopter performance was analysed under different forward flight conditions; finally, 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. The results showed that proper IBC control parameters can lower the required power of the rotor to some extent, but the optimal control parameters vary with flight states. Comparatively, the lift distribution is more even and the induced flows are less fluctuating under optimal control than under worst control.