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To further enhance the take-off, landing, hovering, and shuttling capabilities of micro-rotor drones in complex environments and implement lightweight design for the entire aircraft, a fuselage tilting tri-rotor UAV structure is proposed, which adopts the form of twin steering engines on the tail to realize fixed-angle tilt flight and hovering. In this paper, the unsteady aerodynamic interference phenomena between rotor-rotor and rotor-fuselage at different fuselage tilt angles (0° ~ 20°) are numerically investigated by using the sliding mesh model. The results demonstrate that this configuration allows the fuselage to be tilted and hovered from 0° to 20°. The fuselage tilts from 0° to 15° and 20°, resulting in respective increases of individual rotor input power by 16.7% and 46.6%. Furthermore, the hover efficiency decreases from 0.6262 to 0.5422 as the fuselage tilts from 0° to 20°. The fuselage should not be tilted at an angle greater than 15°, combining the effects of aerodynamic disturbances. Relevant conclusions can provide a reference for the design and flight control of the tri-rotor UAV with tilted fuselage.

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Research on Aerodynamic Interference of a Tri-Rotor UAV With Tilted Fuselage

  • 会议论文

  • 发表日期：

    2025年

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  • Liming Qing,
  • Ying Yuan,
  • Qing Zhang,
  • Chengchuan Yang,
  • Haoyu Zhou

摘要

To further enhance the take-off, landing, hovering, and shuttling capabilities of micro-rotor drones in complex environments and implement lightweight design for the entire aircraft, a fuselage tilting tri-rotor UAV structure is proposed, which adopts the form of twin steering engines on the tail to realize fixed-angle tilt flight and hovering. In this paper, the unsteady aerodynamic interference phenomena between rotor-rotor and rotor-fuselage at different fuselage tilt angles (0° ~ 20°) are numerically investigated by using the sliding mesh model. The results demonstrate that this configuration allows the fuselage to be tilted and hovered from 0° to 20°. The fuselage tilts from 0° to 15° and 20°, resulting in respective increases of individual rotor input power by 16.7% and 46.6%. Furthermore, the hover efficiency decreases from 0.6262 to 0.5422 as the fuselage tilts from 0° to 20°. The fuselage should not be tilted at an angle greater than 15°, combining the effects of aerodynamic disturbances. Relevant conclusions can provide a reference for the design and flight control of the tri-rotor UAV with tilted fuselage.