An electromechanical pitch control system for modifying a collective blade pitch of a multi-blade propeller includes a pitch control rod mechanically coupled via a distal end to a plurality of blades of a propeller, a bearing assembly operatively connected to a proximal end of the pitch control rod, and an electric actuator operatively connected to the bearing assembly. The bearing assembly allows the electric actuator to remain stationary while the pitch control rod rotates with the propeller. The electric actuator is configured to translate the pitch control rod in a longitudinal direction for adjusting an incidence angle of the blades.

An electromechanical pitch control system for modifying a collective blade pitch of a multi-blade propeller includes a pitch control rod mechanically coupled via a distal end to a plurality of blades of a propeller, a bearing assembly operatively connected to a proximal end of the pitch control rod, and an electric actuator operatively connected to the bearing assembly. The bearing assembly allows the electric actuator to remain stationary while the pitch control rod rotates with the propeller. The electric actuator is configured to translate the pitch control rod in a longitudinal direction for adjusting an incidence angle of the blades.

A control system (50) for an electro-hydraulic servo-actuator (26) envisages: a controller (55), to generate a control current (I.sub.c), designed to control actuation of the electro-hydraulic servo-actuator (26), implementing a position control loop based on a position error (e.sub.p), the position error (e.sub.p) being a difference between a reference position (Pos.sub.ref) and a measured position (Pos.sub.meas) of the electro-hydraulic servo-actuator (26); and a limitation stage (58), coupled to the controller (55) to provide a limitation of the actuator speed of the electro-hydraulic servo-actuator (26); the limitation stage (58) limits a rate of change of a driving current (I.sub.d) to be supplied to the electro-hydraulic servo-actuator (26), in order to limit the actuator speed.

A control system (50) for an electro-hydraulic servo-actuator (26) envisages: a controller (55), to generate a control current (I.sub.c), designed to control actuation of the electro-hydraulic servo-actuator (26), implementing a position control loop based on a position error (e.sub.p), the position error (e.sub.p) being a difference between a reference position (Pos.sub.ref) and a measured position (Pos.sub.meas) of the electro-hydraulic servo-actuator (26); and a limitation stage (58), coupled to the controller (55) to provide a limitation of the actuator speed of the electro-hydraulic servo-actuator (26); the limitation stage (58) limits a rate of change of a driving current (I.sub.d) to be supplied to the electro-hydraulic servo-actuator (26), in order to limit the actuator speed.

There is provided a system comprising a brushless DC (“BLDC”) electric motor for a propeller engine and a motor controller. The motor comprises a rotor including one or more permanent magnets and one or more alternator windings, and a stator including one or more stator windings. The controller is configured to apply a first, transient DC voltage to the windings of the stator, wherein the first, transient DC voltage is configured to provide commutation switching for the windings of the stator so as to generate a torque on the rotor. The controller is further configured to apply a second, static DC voltage to the windings of the stator, wherein the second, static DC voltage is configured to induce an electric current in the alternator windings so as to generate an AC voltage in the alternator windings.

An electric, inductively-energized, multi-bladed, controllable-pitch propeller hub is configured with an internal battery, electronic control unit and electric internal reversible hubmotor, when energized by a voltage inducted across an air gap into an annulus of receiver coils that is mounted onto said propeller hub and when said propeller hub is attached to and operated with complementary electrical, electronic and mechanical components that enable wireless command signals, together forming a novel and versatile device whose operation can provide near-instantaneous modulation of aircraft thrust, lift and drag by the action of said propeller hub to actuate precise and equal changes to the pitch of each propeller blade through a full range of useful pitch settings, both during rotation of said propeller hub and when said propeller hub is stationary, with an innovation including a coaxial driveshaft that facilitates the removal and installation of said propeller hub from a propmotor.

An electric, inductively-energized, multi-bladed, controllable-pitch propeller hub is configured with an internal battery, electronic control unit and electric internal reversible hubmotor, when energized by a voltage inducted across an air gap into an annulus of receiver coils that is mounted onto said propeller hub and when said propeller hub is attached to and operated with complementary electrical, electronic and mechanical components that enable wireless command signals, together forming a novel and versatile device whose operation can provide near-instantaneous modulation of aircraft thrust, lift and drag by the action of said propeller hub to actuate precise and equal changes to the pitch of each propeller blade through a full range of useful pitch settings, both during rotation of said propeller hub and when said propeller hub is stationary, with an innovation including a coaxial driveshaft that facilitates the removal and installation of said propeller hub from a propmotor.

A turbine engine including: a rotor supporting a blade and guided by means of bearings; a control system for controlling the blade, which is solidly connected to the rotor and which includes an actuator driven by energy, the control system being disposed axially upstream of the bearings; and a device for transferring the energy, disposed axially between the bearings and including a stationary member and a moving member. The rotor includes a support ring supporting the blade and a shaft having a frustoconical portion and a cylindrical portion on which the bearings and the moving member are mounted, the frustoconical portion extending about the cylindrical portion.

A turbine engine including: a rotor supporting a blade and guided by means of bearings; a control system for controlling the blade, which is solidly connected to the rotor and which includes an actuator driven by energy, the control system being disposed axially upstream of the bearings; and a device for transferring the energy, disposed axially between the bearings and including a stationary member and a moving member. The rotor includes a support ring supporting the blade and a shaft having a frustoconical portion and a cylindrical portion on which the bearings and the moving member are mounted, the frustoconical portion extending about the cylindrical portion.

A system comprises a resonant coupling having a first coil and a second coil, wherein the first coil is mounted to a first body that is stationary relative to a second body that is configured to rotate relative to the first body, and wherein the second coil is mounted to the second body to rotate relative to the first coil. The first and second coils are configured so that alternating current in the first coil induces an alternating current in the second coil to transfer electrical power from the first coil to the second coil wirelessly. The first and second coils do not contact one another regardless of whether the first and second bodies rotate relative to one another.