An anti-torque rotor of a helicopter, having: a supporting body; a drive shaft which rotates about a first axis with respect to the supporting body; a hub connected operatively to drive shaft and angularly fixed with respect to first axis; at least one blade which is connected operatively to hub, is angularly fixed with respect to first axis, and is angularly movable with respect to a second axis to adjust the pitch angle of blade; and an actuator which can be operated to rotate blade about second axis to adjust the pitch angle of blade; actuator has an electric motor which generates torque along the first axis; and a mechanical stage interposed between the electric motor and blade, and designed to convert the torque into rotation of blade about the respective second axes; electric motor is fixed to supporting body.

Embodiments are directed to a flight control system for a helicopter comprises a pilot interface configured to receive a control input, at least one electronically controlled actuator, and a computing device configured to translate the control input to an actuator command, wherein the computing device is further configured to apply yaw rate limits to the actuator command to avoid loss of tail rotor effectiveness. The yaw rate limits are associated with a vortex ring state (VRS) envelope for a tail rotor of the helicopter. The electronically controlled actuator comprises a tail rotor actuator. The control input is a pedal input.

Embodiments are directed to a flight control system for a helicopter comprises a pilot interface configured to receive a control input, at least one electronically controlled actuator, and a computing device configured to translate the control input to an actuator command, wherein the computing device is further configured to apply yaw rate limits to the actuator command to avoid loss of tail rotor effectiveness. The yaw rate limits are associated with a vortex ring state (VRS) envelope for a tail rotor of the helicopter. The electronically controlled actuator comprises a tail rotor actuator. The control input is a pedal input.

An exemplary distributed propulsion system with thermal management includes two or more rotors individually controlled by associated motors and an input control connected to the associated motors to demand the associated motors produce a demanded thrust, wherein a motor power output of each motor of the associated motors is independently controlled to produce the demanded thrust and to control a motor temperature of one or more of the associated motors.

A pitch change link may include a shaft having a first end region and a second end region, and a bearing cartridge on at least one of the first end region and the second end region. The bearing cartridge may include a bearing and a bearing ring at least partially surrounding the bearing. The bearing ring may have a geometric symmetry and a cross section that is wider at a first end than at a second end, the first end may oppose the second end.

A pitch change link may include a shaft having a first end region and a second end region, and a bearing cartridge on at least one of the first end region and the second end region. The bearing cartridge may include a bearing and a bearing ring at least partially surrounding the bearing. The bearing ring may have a geometric symmetry and a cross section that is wider at a first end than at a second end, the first end may oppose the second end.

A joint for an actuator of a rotorcraft includes a housing configured to be coupled to an input lever of the actuator; and a rotary bearing coupled to the housing, the rotary bearing comprising an inner race and an outer race and configured to be coupled to a control rod, wherein the inner race and outer race are rotationally fixed relative to each other until a torque applied to the joint exceeds a threshold torque value, upon which there is a relative rotatability between the inner race and the outer race.

A joint for an actuator of a rotorcraft includes a housing configured to be coupled to an input lever of the actuator; and a rotary bearing coupled to the housing, the rotary bearing comprising an inner race and an outer race and configured to be coupled to a control rod, wherein the inner race and outer race are rotationally fixed relative to each other until a torque applied to the joint exceeds a threshold torque value, upon which there is a relative rotatability between the inner race and the outer race.

A yaw control system coupled to a tailboom of a helicopter includes tail rotors. The tail rotors include a clockwise tail rotor and a counterclockwise tail rotor. The clockwise tail rotor is configured to rotate in a first rotational direction. The counterclockwise tail rotor is configured to rotate in a second rotational direction, the second rotational direction opposite of the first rotational direction.

A yaw control system coupled to a tailboom of a helicopter includes tail rotors. The tail rotors include a clockwise tail rotor and a counterclockwise tail rotor. The clockwise tail rotor is configured to rotate in a first rotational direction. The counterclockwise tail rotor is configured to rotate in a second rotational direction, the second rotational direction opposite of the first rotational direction.