A simple, safe, and inexpensive flight control system in an aircraft. An anti-torque system for a rotary-wing aircraft has an airfoil with a first surface extending from a first trailing edge and a leading edge, and a second surface extending from a second trailing edge to join the first surface at the leading edge. The airfoil has a first moveable deflector panel pivotally coupled to the first trailing edge, and a second moveable deflector panel pivotally coupled to the second trailing edge. Means are provided to pivot the deflector panels in unison about their respective pivot axes to alter the direction of travel of the airflow downstream of the pivot axes over the surfaces of the deflector panels, thereby producing a lift in a direction perpendicular to the airflow to counteract the torque applied on the aircraft. The flight control system may be arranged within a fixed-wing aircraft.

A simple, safe, and inexpensive flight control system in an aircraft. An anti-torque system for a rotary-wing aircraft has an airfoil with a first surface extending from a first trailing edge and a leading edge, and a second surface extending from a second trailing edge to join the first surface at the leading edge. The airfoil has a first moveable deflector panel pivotally coupled to the first trailing edge, and a second moveable deflector panel pivotally coupled to the second trailing edge. Means are provided to pivot the deflector panels in unison about their respective pivot axes to alter the direction of travel of the airflow downstream of the pivot axes over the surfaces of the deflector panels, thereby producing a lift in a direction perpendicular to the airflow to counteract the torque applied on the aircraft. The flight control system may be arranged within a fixed-wing aircraft.

A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight.

A dual-motor system includes a first motor rotationally coupled to a first drive shaft. The first drive shaft is coupled to a common shaft couplable to a rotationally driveable member. The dual-motor system also includes a second motor rotationally coupled to a second drive shaft. The second drive shaft is coupled to the common shaft. The first motor and the second motor are coaxially aligned with the first drive shaft passing through the second drive shaft.

A yaw control system for a helicopter having a tailboom includes one or more tail rotors rotatably coupled to the tailboom and a quiet mode controller. The quiet mode controller includes a noise monitoring module configured to monitor one or more flight parameters of the helicopter and a quiet mode command module configured to selectively switch the one or more tail rotors to a quiet mode based on the one or more flight parameters. The quiet mode command module is also configured to modify one or more operating parameters of the one or more tail rotors in the quiet mode to reduce noise emitted by the helicopter.

A yaw control system for a helicopter having a tailboom includes one or more tail rotors rotatably coupled to the tailboom and a quiet mode controller. The quiet mode controller includes a noise monitoring module configured to monitor one or more flight parameters of the helicopter and a quiet mode command module configured to selectively switch the one or more tail rotors to a quiet mode based on the one or more flight parameters. The quiet mode command module is also configured to modify one or more operating parameters of the one or more tail rotors in the quiet mode to reduce noise emitted by the helicopter.

The present disclosure is directed to a detachable connection between a pitch control unit arm and a pitch horn of a blade holder in a tail rotor head of a tail rotor of a rotary wing aircraft. The detachable connection includes a pin connecting the pitch horn, attached to a blade holder, with the pitch control unit arm of a pitch control unit, by protruding through an arm through hole and at another edge through a pitch horn through hole. By this arrangement, material wear is reduced and maintenance intervals can be reduced. This is reached because the pin is designed as a sliding pin projecting between pitch horn and pitch control unit arm, which is running in the course of its length through a spherical bearing in form of a ball with a central ball through hole.

The present disclosure is directed to a detachable connection between a pitch control unit arm and a pitch horn of a blade holder in a tail rotor head of a tail rotor of a rotary wing aircraft. The detachable connection includes a pin connecting the pitch horn, attached to a blade holder, with the pitch control unit arm of a pitch control unit, by protruding through an arm through hole and at another edge through a pitch horn through hole. By this arrangement, material wear is reduced and maintenance intervals can be reduced. This is reached because the pin is designed as a sliding pin projecting between pitch horn and pitch control unit arm, which is running in the course of its length through a spherical bearing in form of a ball with a central ball through hole.

There is disclosed a rotorcraft comprising: an array of lift devices supported at a structure; a first group of the lift devices configured to generate thrust in a first common direction; a second group of the lift devices being tilted or tiltable relative to the first group of devices so as to generate thrust in at least a second common direction; and a flight control system.

There is disclosed a rotorcraft comprising: an array of lift devices supported at a structure; a first group of the lift devices configured to generate thrust in a first common direction; a second group of the lift devices being tilted or tiltable relative to the first group of devices so as to generate thrust in at least a second common direction; and a flight control system.