Distributed Electric Propulsion for Yaw Control: Testbeds, Control Approach, and Flight Testing

This work presents an approach to efficient yaw control by differential thrust from distributed electric propulsion, avoiding an increase in aerodynamic drag associated with rudder deflection. Both a fully automated, scaled (1:3) version of the electric aircraft e-Genius, and the manned electric aircraft icare-2 serve as testbeds and are equipped with an additional wing-tip mounted electrical propulsion system. A control law aiming for zero side-slip is proposed, which results in a difference in the motor input signals to generate a yawing moment. The respective system design and implementation are presented, with special focus being set to a system architecture ensuring safe operation. Flight test results from either aircraft demonstrate the feasibility of the yaw control approach proposed.