A power system for an aircraft comprises: a motor-generator component; a shaft, wherein the motor-generator component is connectable to the shaft, the shaft connectable to an additional component of the aircraft to for torque transfer with the additional component; and a de-coupler operable to disconnect the motor-generator component from the shaft, wherein the motor-generator component is located between the de-coupler and the additional component in use.

An actuator apparatus includes a motor, an electromagnetic clutch, and an accommodation member accommodating the electromagnetic clutch, the electromagnetic clutch including an armature supported by a drive member rotated by motor drive and being adapted to rotate integrally with the drive member, a rotor being rotatable relative to the armature and being adapted to rotate integral with an output member, an electromagnet being capable of connecting the armature and the rotor to each other in accordance with an electromagnetic attractive force generated by electrification in such a manner that torque of the motor is transmittable, the actuator apparatus including a conductive member integrally provided at the accommodation member and being connected to a conductive portion of the electromagnetic clutch in such a manner that the conductive member forms a ground circuit that can connect the conductive portion with ground.

An electric actuator comprises a housing and an output shaft reciprocatingly received by the housing. There is a screw assembly disposed within the housing and coupled to the output shaft. The screw assembly includes a plurality of annular rollers and a central screw received by the annular rollers. The annular rollers are rotatable about the central screw. There is a motor which includes a stator and a rotor. The rotor has an inner bore which engages the annular rollers. Rotation of the rotor causes the central screw to translate axially relative to the rotor and the output shaft to reciprocate relative to the housing.

An electric drive for driving a motor vehicle comprises a housing assembly; an electric motor having a motor shaft provided in the form of a hollow shaft which is rotatingly drivable around a rotational axis A and which is connected to a drive gear; a transmission unit having at least one transmission shaft which is rotatingly drivable by the drive gear and having at least one output shaft, the output shaft extending through the hollow shaft; wherein between the hollow shaft and the output shaft an annular channel is formed, having a first opening facing the transmission unit and a second opening facing away from the transmission unit; wherein the housing assembly comprises a lubricant-guiding geometry that is configured to guide lubricant into a mouth region of the first opening of the annular channel, so that the lubricant can flow through the annular channel to the second opening.

An electrical machine comprising a two-part rotor formed of a first rotor part and a second rotor part. The first rotor part includes a conical section and is mounted to a shaft of the machine. The second rotor part has a bore including a complementary conical section. The second rotor part is configured to displace axially between a first state, in which it is engaged with the first rotor part to form the rotor of the electrical machine, and a second state, in which it is axially disengaged from the first rotor part. Also a clutch having an engaged state and a disengaged state. When the clutch is in one of its states the second rotor part is in its first state and switching the clutch to the other of its states axially displaces the second rotor part to its second state.

An electric actuator comprises a housing and an output shaft reciprocatingly received by the housing. There is a screw assembly disposed within the housing and coupled to the output shaft. The screw assembly includes a plurality of annular rollers and a central screw received by the annular rollers. The annular rollers are rotatable about the central screw. There is a motor which includes a stator and a rotor. The rotor has an inner bore which engages the annular rollers. Rotation of the rotor causes the central screw to translate axially relative to the rotor and the output shaft to reciprocate relative to the housing.

An integrated controller for an operator unit for powering an overhead garage roller door or roller shutter is described. The operator unit comprises a motor, an output drive assembly, a timing assembly unit, and a clutch assembly for providing selective engagement between motor powered operation and manual operation (provided by a chain rotating a chain wheel). The motor is arranged to drive a shaft which, in turn, provides drive to the roller door or shutter assembly (not shown), which includes an axle around which the roller door or shutter is wound. The integrated controller comprises an inverter for receiving a single phase power supply and supplying three phase power to drive the motor; and a drive controller in operable association with the inverter for providing active management of the operation of the motor.

An automatic and intelligent clutch-type wind turbine system clutch-type wind turbine system is revealed. A rotor-blade base is disposed with rotor blades and connected to a main shaft. A gearbox of a split gearbox is connected to the main shaft while a turbine-driven set of the split gearbox is connected to a power shaft. A plurality of sets of disc generators is connected to the power shaft and a synchronous clutch is arranged between the two adjacent disc generators. A battery is connected to each disc generator. Thereby electricity is generated by the wind turbine system without being affected by wind force from surrounding area and the electricity is not wasted on braking. During the electricity generation process, the energy stored is converted into kinetic energy for assistance in generating electricity. Thus not only the power generation efficiency is improved, the total production cost is also reduced.

An electrical generating system for an aircraft may include a first shaft connected with an engine gearbox, a second shaft connected with a generator of the aircraft, and a connection unit in which the first and second shafts are selectively engageable with one another. The connection unit may include a solenoid coil, an armature co-axial with the first and the second shafts, a plurality of balls positioned around the armature. The armature may include a first cylindrical segment and a second cylindrical segment. The armature may be selectively movable between a first axial position and a second axial position. When the armature is in a first axial position, the balls are positioned to transmit torque forces between the first shaft and the second shaft. When the armature is in a second axial position, the first shaft and the second shaft are free to rotate independently.

An electric drive module for an electrified vehicle includes an electric motor, a transmission and a multispeed actuation mechanism (MAM). The transmission is driven by a rotatable output of the electric motor and includes a first drive shaft and a second drive shaft. The transmission has a first gear set that selectively converts rotatable motion of the first drive shaft into rotatable motion of the second drive shaft in a first gear mode at a first drive ratio, and a second gear set that selectively converts rotatable motion of the first drive shaft into rotatable motion of the second drive shaft in a second gear mode at a second drive ratio, distinct from the first drive ratio. The MAM has magnetic fluid therein. Activation of the magnetic fluid causes a shift to occur within the transmission from the first gear set to the second gear set.