Deployment Modes and Aerodynamic Analysis of UAV Orthogonal Biaxial Folding Wing

Considering the deployment characteristics of the folding wing, this paper proposed three deployment modes, synchronous deployment, fixed-axis-non-fixed-axis stepwise deployment, and non-fixed-axis-fixed-axis stepwise deployment, to obtain the optimal deployment scheme of the orthogonal biaxial folding wing of Unmanned Aerial Vehicles (UAVs) at different airspeeds. On this basis, combined with the folding wing deployment action, the Lagrange method was used to establish the aerodynamic model of the folding wing, and the Fluent simulation software was used to simulate the aerodynamic simulation of multiple deployment modes of the orthogonal biaxial folding wing, which analyze the influence of the UAV deployment mode and airspeed towards the driving torque of the folding wing. Based on the driving moment of the folding wing, the optimal deployment mode at different airspeeds was obtained. The comparison of simulation results shows that when the airspeed is less than 40 m/s, the optimal deployment mode is synchronous deployment. When the airspeed is greater than or equal to 40 m/s, the optimal deployment mode is non-fixed-axis-fixed-axis stepwise deployment. The accuracy of the folding wing aerodynamics model can be proven according to the comparison of the simulation results with the theoretical results.

Automated summary

This paper proposes three deployment modes, synchronous deployment, fixed-axis-non-fixed-axis stepwise deployment, and non-fixed-axis-fixed-axis stepwise deployment, to obtain the optimal deployment scheme of the orthogonal biaxial folding wing of UAVs at different airspeeds. The aerodynamic model of the folding wing is established using the Lagrange method and the Fluent simulation software is used to analyze the influence of the UAV deployment mode and airspeed on the driving torque of the folding wing. The simulation results show that the optimal deployment mode is synchronous deployment when the airspeed is less than 40 m/s, and non-fixed-axis-fixed-axis stepwise deployment when the airspeed is greater than or equal to 40 m/s. The accuracy of the folding wing aerodynamics model is proven through comparison with theoretical results.