| Citation: | ZHOU Xu, ZHAO Guoqing, ZHAO Qijun, et al. Mechanism effect of circling parameters on the helicopter unsteady blade/vortex interaction[J]. Journal of Aerospace Power, 2025, 40（7）：20240110 doi: 10.13224/j.cnki.jasp.20240110
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The influences of circling flight parameters on the unsteady blade/vortex interaction characteristics were studied comprehensively. An efficient and accurate simulation method for the blade tip vortex considering flapping and circling correction was established. The airloads of the fuselage and tail rotor were calculated by the numerical fitting of wind tunnel test data. Based on this, a comprehensive trim method of balancing the efficiency and accuracy was constructed. Afterwards, under the trim condition, the distributions of the rotor wake and aerodynamic loads in different circling states were simulated, revealing the influence mechanism of circling flight parameters on the unsteady blade/vortex interaction characteristics. The results showed that the vortex was distorted under rotor disc after $ \varPsi $=60° and certain segments of the vortex rolled into the region above the rotor disc after $\varPsi $=90° on the inner side of the circling direction with low circling speed and small radius. The resulting continuous and concentrated interaction led to rapid changes in the vertical induced velocity, causing abrupt changes in local aerodynamic loads. The circling direction did not affect the influence mechanism of blade/vortex interaction. Instead, it affected the harmonic characteristics of aerodynamic load and the first order component was most sensitive to the circling direction. With the increase of circling radius, the weakening of wake distortion led to the rapid disappearance of the concentrated interaction phenomenon above rotor disc. Other interactions within the rotor disc became prominent gradually, causing the distribution of aerodynamic loads to move along the circumferential direction. As for the circling radius, the aerodynamic loads above the fifth order fell out fast, and the influence range of lower order aerodynamic loads was wider than higher order parts. The increase in circling speed stretched the wake vortex, weakening the blade/vortex interaction phenomenon in spatial distribution. The aerodynamic loads of each order showed the same changing trend.
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