Dynamic Load of Urban Air Mobility Aircraft in Wake Vortex of Large Passenger Aircraft

Abstract This paper investigates the dynamic loads experienced by a UAM (Urban Air Mobility) aircraft encountering a modeled wake vortex generated by a Boeing 737-800. The modeled wake vortex follows the Barnham-Hallock vortex model, characterized by a circular velocity profile. The UAM aircraft is simulated in longitudinal motion, beginning from a trimmed-level flight condition and penetrating the wake vortex with symmetric wing loading. Two flight scenarios are explored: free flight and closed-loop controlled flight. In the controlled scenario, an LQR controller is designed to mitigate the adverse effects of the wake vortex by dynamically adjusting the control surfaces to maintain the trimmed-level flight. The study evaluates and compares bending strains on the wing and the rigid-body dynamics of the UAM aircraft under both scenarios. Simulations are conducted with a wake vortex of a circulation strength of 250 m2/s and a core radius of 1.5 m. Results indicate that while the LQG flight controller effectively attenuates perturbations in pitch angle and vertical motion, it also increases bending strains and structural loads on the aircraft’s wing.