Dynamic Response Comparison of Low-Fidelity Six-Degree of Freedom Nonlinear Model with the Flight Test Data of Small Twin Electric Engine UAV

초록

This research conducted a six-degree of freedom simulation of a small twin electric engine UAV using a nonlinear equation of motion. The simulation employed a low-fidelity aerodynamic model based on the vortex lattice method and a thrust model derived from in-ground static testing. The resulting simulation data was compared with data obtained from flight tests. The aircraft model utilized in this study has a Maximum Take Off Weight of 10 kg, a wingspan of 2430 mm, and a wing area of 72.5 dm2. It was powered by two Electric Engine 3520 kV 500 units. The flight test maneuvers encompassed doublet input elevator, step input aileron, and rudder movements. The comparison focused on both longitudinal and lateral-directional motion. The outcomes of the comparison revealed an overall favorable agreement between the simulation and flight test data, displaying generally acceptable trends. However, it is noteworthy that the simulation's accuracy, particularly in the phugoid mode, may require further refinement due to the challenges associated with approximating drag and thrust parameters within the aerodynamic model. © 2024 Praise Worthy Prize S.r.l.-All rights reserved.

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