The invention discloses an unconventional yaw control system for a fixed-wing aircraft. The system is characterized in that one or more fixed wings and one or more motor saddles which can rotate around a vertical axis or an approximate vertical axis. The system is especially useful for unmanned and fixed-wing aircraft which can take off and land vertically. The angular deflection of the motor saddles relative to the vertical axis results in the corresponding angular deflection of the motor, a motor shaft and the propulsion vector. When the propulsion vector deflects, the force no longer passesthrough the center of gravity of the aircraft, and thus a non-zero yaw moment is generated. The system can realize the comprehensive three-axis control over the aircraft with only three driving devices by combining the elevons or one elevon and flaps.