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<p>In this paper, the sand movement characteristics in the hovering flow field of the UH-60 helicopter at twice the rotor radius above the ground were simulated. The UH-60 helicopter model equipped with a T700 Inertial particle separator (IPS) was simplified and integrated with the Lagrange Sand Tracking Method to simulate the spatial concentration distribution, movement trajectory of sand particles, and the brownout phenomenon induced by sand particles in the integrated flow field of the helicopter rotor/fuselage/inlet. The fuselage/rotor coupling caused interference with the flow field structure at the inlet during the research, resulting in asymmetrical flow field structures on the left and right sides. Consequently, there is an increased concentration of sand outside the right inlet. When the incoming flow velocity is 40&#xa0;m/s, the coupling flow field between the helicopter rotor and inlet differs from that in a hovering state. The ground effect on the rotor is significantly diminished, leading to the disappearance of the ground vortex and elimination of sand dust movement toward the fuselage inlet position, thereby eliminating potential hazards caused by sand dust. The dust separation efficiency of the left inlet decreases by 3–8% as the rotor speed decreases. Conversely, the sand separation efficiency of the right inlet increases by 3.6–9.2%. Additionally, an increase in Mach number at the outlet of the core channel leads to higher sand dust concentration and a greater proportion of large particle sizes at the inlet surface.</p>

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Characteristics of sand movement in helicopter flow field

  • 期刊论文

  • 发表日期：

    2025年8月18日

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  • Tianyu Zhang,
  • Zhenlong Wu,
  • Haoyu Zhou,
  • Huijun Tan,
  • Zhaoguang Wang,
  • Wei Li,
  • Maixiang Xie,
  • Yakui Liu

摘要

In this paper, the sand movement characteristics in the hovering flow field of the UH-60 helicopter at twice the rotor radius above the ground were simulated. The UH-60 helicopter model equipped with a T700 Inertial particle separator (IPS) was simplified and integrated with the Lagrange Sand Tracking Method to simulate the spatial concentration distribution, movement trajectory of sand particles, and the brownout phenomenon induced by sand particles in the integrated flow field of the helicopter rotor/fuselage/inlet. The fuselage/rotor coupling caused interference with the flow field structure at the inlet during the research, resulting in asymmetrical flow field structures on the left and right sides. Consequently, there is an increased concentration of sand outside the right inlet. When the incoming flow velocity is 40 m/s, the coupling flow field between the helicopter rotor and inlet differs from that in a hovering state. The ground effect on the rotor is significantly diminished, leading to the disappearance of the ground vortex and elimination of sand dust movement toward the fuselage inlet position, thereby eliminating potential hazards caused by sand dust. The dust separation efficiency of the left inlet decreases by 3–8% as the rotor speed decreases. Conversely, the sand separation efficiency of the right inlet increases by 3.6–9.2%. Additionally, an increase in Mach number at the outlet of the core channel leads to higher sand dust concentration and a greater proportion of large particle sizes at the inlet surface.