Abstract: An aircraft propulsion system is provided. The system may provide improved directional control of an aircraft, eliminating the need for a tail rotor. The system may include a frame connected between a body of the aircraft and a main rotor having a torque effect on the body. The system may also include a first motor mounted to the frame and configured to spin in a first rotational direction. The system may further include a second motor mounted to the frame and configured to spin in a second rotational direction opposite the first rotational direction to create a force opposite the motion imparted to the body by the torque effect of powering the main rotor. The second motor and the first motor drive the main rotor in the first rotational direction. The aircraft is steered around a vertical axis by adjusting the speed of the first motor and the second motor.

Abstract: The disclosed propulsion apparatus according to various aspects of the subject technology may provide improved directional control of an aircraft, eliminating the need for a tail rotor. The propulsion apparatus may include a frame connected between a body of the aircraft and a main rotor having a torque effect on the body. The propulsion apparatus may also include a first motor mounted to the frame and configured to spin in a first rotational direction. The propulsion apparatus may further include a second motor mounted to the frame and configured to spin in a second rotational direction opposite the first rotational direction to create a force opposite the motion imparted to the body by the torque effect of powering the main rotor, wherein the second motor and the first motor drive the main rotor in the first rotational direction, and wherein the aircraft is steered around a vertical axis by adjusting the speed of the first motor and the second motor.