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 blade pitch control system includes a plurality of serially stacked swashplate assemblies, each having concentric, ring-shaped inner and outer sections, an associated output pitch link coupled to its outer section and an associated input pitch link coupled to its inner section. The inner and outer sections of each swashplate assembly includes pass through holes to accommodate input pitch links and output pitch links of adjacent ones of the stacked swashplate assemblies. The system also includes a plurality of actuators, each coupled to a respective input pitch link of a respective one of the stacked swashplate assemblies. A central static mast accommodates a rotor drive shaft and the stacked swashplate assemblies are configured to slide axially, parallel to a long axis of the static mast.

A blade pitch control system includes a plurality of serially stacked swashplate assemblies, each having concentric, ring-shaped inner and outer sections, an associated output pitch link coupled to its outer section and an associated input pitch link coupled to its inner section. The inner and outer sections of each swashplate assembly includes pass through holes to accommodate input pitch links and output pitch links of adjacent ones of the stacked swashplate assemblies. The system also includes a plurality of actuators, each coupled to a respective input pitch link of a respective one of the stacked swashplate assemblies. A central static mast accommodates a rotor drive shaft and the stacked swashplate assemblies are configured to slide axially, parallel to a long axis of the static mast.

A rotorcraft swashplate assembly includes a rotationally fixed swashplate fixed against rotating with a rotorcraft rotor. The swashplate assembly also includes a rotatable swashplate coupled to the rotor to rotate with the rotor. The swashplate assembly also includes multiple pitch change links, each pitch change link coupled to a respective rotor blade and to the rotatable swashplate to rotate with the rotor. The swashplate assembly also includes an annular track coupled to the rotationally fixed swashplate and configured to support each pitch change link riding on the annular track as each pitch change link rotates with the rotor. The track includes multiple bearings upon which a pitch change link rides, and actuators that move the bearings changing a shape of the annular track and thereby the pitch of each rotor blade as each pitch change link rides on the annular track during rotation of the rotor blades.

A rotorcraft swashplate assembly includes a rotationally fixed swashplate fixed against rotating with a rotorcraft rotor. The swashplate assembly also includes a rotatable swashplate coupled to the rotor to rotate with the rotor. The swashplate assembly also includes multiple pitch change links, each pitch change link coupled to a respective rotor blade and to the rotatable swashplate to rotate with the rotor. The swashplate assembly also includes an annular track coupled to the rotationally fixed swashplate and configured to support each pitch change link riding on the annular track as each pitch change link rotates with the rotor. The track includes multiple bearings upon which a pitch change link rides, and actuators that move the bearings changing a shape of the annular track and thereby the pitch of each rotor blade as each pitch change link rides on the annular track during rotation of the rotor blades.

A swashplate assembly, that includes an integrated electric motor. The present embodiments also relate to a multi-blade rotor for a rotary-wing aircraft with such a swashplate assembly and to a rotary-wing aircraft with such a multi-blade rotor. The swashplate assembly may include a rotating plate that is mounted to the rotor shaft and rotates in operation with the rotor shaft, a stationary plate that is coupled to the rotating plate by means of bearings, and an electric motor that generates torque for driving the rotor shaft. The electric motor comprises a stator that is mounted to one of the stationary or the rotating plates and a rotor that is mounted to the other one of the stationary or rotating plates.

A swashplate assembly, that includes an integrated electric motor. The present embodiments also relate to a multi-blade rotor for a rotary-wing aircraft with such a swashplate assembly and to a rotary-wing aircraft with such a multi-blade rotor. The swashplate assembly may include a rotating plate that is mounted to the rotor shaft and rotates in operation with the rotor shaft, a stationary plate that is coupled to the rotating plate by means of bearings, and an electric motor that generates torque for driving the rotor shaft. The electric motor comprises a stator that is mounted to one of the stationary or the rotating plates and a rotor that is mounted to the other one of the stationary or rotating plates.

The system is configured for automation of rotorcraft entry into autorotation. The system can provide a means to assist the flight crew of a rotorcraft in maintaining rotor speed following loss of engine power. The system can automatically adjust control positions, actuator positions or both to prevent excessive loss of rotor speed upon initial loss of engine power before the flight crew is able to react. The system uses model matching to provide axis decoupling and yaw anticipation; it includes pitch control initially to assist in preventing rotor deceleration; and it makes use of collective, pitch, roll and yaw trim functions to provide tactile cueing to the pilot to assist when the pilot is in the loop. The system can reduce workload by assisting the crew with controlling rotor speed and forward speed during stabilized autorotation.

The system is configured for automation of rotorcraft entry into autorotation. The system can provide a means to assist the flight crew of a rotorcraft in maintaining rotor speed following loss of engine power. The system can automatically adjust control positions, actuator positions or both to prevent excessive loss of rotor speed upon initial loss of engine power before the flight crew is able to react. The system uses model matching to provide axis decoupling and yaw anticipation; it includes pitch control initially to assist in preventing rotor deceleration; and it makes use of collective, pitch, roll and yaw trim functions to provide tactile cueing to the pilot to assist when the pilot is in the loop. The system can reduce workload by assisting the crew with controlling rotor speed and forward speed during stabilized autorotation.