A hybrid power system for an aircraft comprises a gas turbine connected to a generator for generating electrical power; an electrical storage device configured to output electrical power; a propulsor; a motor operable to drive the propulsor using electrical power from either or both of the generator and the electrical storage device; and a controller. The controller, to meet propulsor power demand, is configured to control an amount of electrical power generated by the generator, and an amount of electrical power outputted by the electrical storage device. In a first control mode coinciding with an increase in the propulsor power demand sufficient to cause a transient excursion of the operating point of a compressor of the gas turbine from a steady state working line, the controller is further configured to temporarily increase the amount of electrical power outputted by the electrical storage device such that the transient excursion is reduced.

One embodiment is an electric drive system including a plurality of redundant motors, wherein power generated by the plurality of motors is used to drive a rotor system comprising a rotor shaft having a plurality of rotor blades connected thereto via a swashplate; a gear box associated with the plurality of redundant motors; a cyclic actuation system for controlling an individual pitch of the rotor blades connected to the swashplate; and at least one structural element for retaining the redundant motors, the gear box, and the cyclic actuation system together as a single integrated unit.

A blade-pitch change mechanism includes a motor comprising a rotating motor shaft and a housing, a solenoid coupled to a first end of the rotating motor shaft and to the housing, and a hub coupled with a second end of the rotating motor shaft. The hub includes a cylindrical puck having formed therein a gated castellated groove and connected to the second end of the rotating motor shaft and a cylindrical blade-pitch hub selectively couplable with the cylindrical puck via a plurality of drive pins and having formed therein a blade-pitch adjustment groove.

A blade-pitch change mechanism includes a motor comprising a rotating motor shaft and a housing, a solenoid coupled to a first end of the rotating motor shaft and to the housing, and a hub coupled with a second end of the rotating motor shaft. The hub includes a cylindrical puck having formed therein a gated castellated groove and connected to the second end of the rotating motor shaft and a cylindrical blade-pitch hub selectively couplable with the cylindrical puck via a plurality of drive pins and having formed therein a blade-pitch adjustment groove.

A propulsion system for a hybrid electric vehicle comprises a traction motor having first and second stator windings; a power source having a DC power output coupled to the first windings; a battery having a DC power output coupled to the second windings; and a controller to independently control: (i) a first power level output at the first DC power output, and (ii) a second power level of motive power output by the traction motor; wherein responsive to a signal to set the second power level less than full capacity of the traction motor, the controller provides a power difference between the first and second power levels from the second windings to the battery.

A propulsion system for a hybrid electric vehicle comprises a traction motor having first and second stator windings; a power source having a DC power output coupled to the first windings; a battery having a DC power output coupled to the second windings; and a controller to independently control: (i) a first power level output at the first DC power output, and (ii) a second power level of motive power output by the traction motor; wherein responsive to a signal to set the second power level less than full capacity of the traction motor, the controller provides a power difference between the first and second power levels from the second windings to the battery.

A propellant force generator is provided having the size in the axial direction of a rotational shaft of a motor reduced while making the pitch angles of rotational blades driven by the motor variable. The propellant force generator includes a propellant-force generating motor adapted to generate a propellant force for rotational blades, a pitch varying motor adapted to generate a rotational motion for changing pitch angles of the rotational blades, a rotation-linear motion converting unit adapted to convert the rotational motion generated by the pitch varying motor into a linear motion, and a linear motion-rotation converting unit adapted to convert the linear motions converted by the rotation-linear motion converting unit into rotational motions. At least a part of the linear motion-rotation converting unit is located within the propellant-force generating motor.

A propellant force generator is provided having the size in the axial direction of a rotational shaft of a motor reduced while making the pitch angles of rotational blades driven by the motor variable. The propellant force generator includes a propellant-force generating motor adapted to generate a propellant force for rotational blades, a pitch varying motor adapted to generate a rotational motion for changing pitch angles of the rotational blades, a rotation-linear motion converting unit adapted to convert the rotational motion generated by the pitch varying motor into a linear motion, and a linear motion-rotation converting unit adapted to convert the linear motions converted by the rotation-linear motion converting unit into rotational motions. At least a part of the linear motion-rotation converting unit is located within the propellant-force generating motor.

A variable pitch propeller assembly operatively coupled with an engine and methods for controlling the pitch of a plurality of propeller blades thereof is provided. In one example aspect, the variable pitch propeller assembly includes features for combining overspeed, feathering, and reverse functionality in a single secondary control valve. The secondary control valve is operable to selectively allow a controlled amount of hydraulic fluid to flow to or from a pitch actuation assembly such that the pitch of the propeller blades can be adjusted to operate the variable pitch propeller assembly in one of a constant speed mode, a feather mode, and a reverse mode.

A linear electromechanical servocontrol comprising a power rod that is able to move in translation. The servocontrol comprises a single linear electrical actuator provided with at least one electric motor connected by a mechanical link to the power rod, the servocontrol comprising an anchor secured to the electrical actuator, the at least one electric motor being controlled by a computer, the anchor having an anchoring rod that is able to move in translation, the anchor having an anchoring brake that is configured to immobilize the anchoring rod with respect to the electrical actuator in a normal operating mode or to allow the electrical actuator to move in relation to the anchoring rod in a safe operating mode at the request of the computer.