Abstract
The longitudinal flight stability of the ducted vertical take-off and landing fixed-wing UAV during the flight state of hovering and transition is studied. Firstly, based on the Blade-Element Momentum Theory (BEMT) and experimental data, a coaxial dual-rotor ducted aerodynamic model and a thrust ducted aerodynamic model based on characteristic cross-section calculations are established. The model parameters are identified according to the experimental data. Secondly, a UAV flight dynamics model with thrust duct deflection is established according to the six-degree-of-freedom equations. Finally, the case UAV was used to solve the longitudinal balance and stability analysis of hovering and transition state with the established model method, and compared with the hovering experimental results. The results show that the UAV flight dynamics model combined with the ducted dynamic model established in the article can accurately describe the longitudinal flight stability characteristics of this type of aircraft.
Highlights
Based on the Blade⁃Element Momentum Theory ( BEMT) and experimental data, a coaxial dual⁃rotor ducted aerodynamic model and a thrust ducted aerodynamic model based on characteristic cross⁃section calculations are established
The model parameters are identified according to the experimental data
A UAV flight dynamics model with thrust duct deflection is established according to the six⁃degree⁃of-freedom equations
Summary
Tfan + Tduct sinθ + Lwing cosθ + Dwing sinθ - mgcosθ = 0ý Mwing + Tfan lfan - Tduct lduct sinθduct = 0 þïï 同速度下的过渡平衡的升力风扇推力 Tfan, 推力涵 道推力 Tduct 和推力涵道偏转角 θ duct ,如图 9 所示。 Tfan + Tduct sinθduct - mgcosθ = 0ý
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