A Total Energy Control System Design for the Transition Phase of a Tiltrotor Aerial Vehicle

This paper presents a total energy control system design to take-off and transition flight for a tiltrotor aerial vehicle. The aerodynamic effect produced by the wake of the rotors on the wing and the horizontal stabilizer is taken into consideration. The lift, drag and pitch moment coefficients are modeled for angle of attack variations between one hundred eigthy degrees and minus one hunded eighty degrees based on preliminary wing tunnel tests. Numerical simulations are provided to verify the effectiveness of the proposed control strategy.