A starting device is used in a starting system that includes a starting electric motor unit and a rotating electrical machine; the starting electric motor unit including a motor that rotates a pinion gear, and a pushing member that pushes out the pinion gear toward a ring gear, the ring gear rotating together with a crankshaft of an engine; the rotating electrical machine being connected to the crankshaft and rotating the crankshaft; the starting system being configured to push, using the pushing member, the pinion gear toward the ring gear, and drive the motor to rotate, based on driving force of the motor, the ring gear via the pinion gear, thus starting the engine. The starting device includes a drive instruction unit that instructs the rotating electrical machine to rotate the ring gear via the crankshaft during a pre-drive period before drive of the motor.

An electric generator assembly for an aircraft is provided. The electric generator assembly includes: a main generator having a main rotor and a main stator, the main stator comprising a first three-phase winding and a second three-phase winding, the first and second three-phase windings each configured to have a voltage induced therein by the main rotor, the first three-phase winding defining a phase shift from the second three-phase winding greater than zero degrees

An electric generator assembly for an aircraft is provided. The electric generator assembly includes: a main generator having a main rotor and a main stator, the main stator comprising a first three-phase winding and a second three-phase winding, the first and second three-phase windings each configured to have a voltage induced therein by the main rotor, the first three-phase winding defining a phase shift from the second three-phase winding greater than zero degrees

A mounting system for mounting a supplemental alternator, as well as methods of assembling the same, is provided. The mounting system includes a top mounting bracket that is configured to align with a top flange aperture of the additional alternator. The mounting system also includes a bottom mounting bracket having a bracket aperture that aligns with an aperture of an existing alternator mount and also having a flange aperture that aligns with the foot flange aperture of the additional alternator. The mounting system further includes a shaft that couples to the additional alternator.

A mounting system for mounting a supplemental alternator, as well as methods of assembling the same, is provided. The mounting system includes a top mounting bracket that is configured to align with a top flange aperture of the additional alternator. The mounting system also includes a bottom mounting bracket having a bracket aperture that aligns with an aperture of an existing alternator mount and also having a flange aperture that aligns with the foot flange aperture of the additional alternator. The mounting system further includes a shaft that couples to the additional alternator.

A multi-port power converter including a housing including a plurality of ports structured to electrically interface to a plurality of loads; a plurality of solid-state components configured to provide selected electrical power outputs and to accept selected electrical power inputs; a plurality of solid-state switches configured to provide selected connectivity between the plurality of solid-state components and the plurality of ports; and a controller, the controller including: a component bank configuration circuit structured to interpret a port electrical interface description of the multi-port power converter from an external tool communicatively coupled to the controller, the port electrical interface description comprising a description of at least a portion of distinct electrical characteristics; and a component bank implementation circuit structured to provide solid switch states in response to the port electrical interface description, and wherein the plurality of solid-state switches are responsive to the solid switch states.

A computer room heat-pipe air conditioning system with an emergency cooling control method. The system comprises a phase-change energy storage module, a phase-change material packaging body, a condenser housing, a condenser, a cold releasing pump, evaporators, evaporation fans, four three-way valves, a cooling unit, standby power generators and storage batteries. The three-way valves are opened and closed based on a preset heat-pipe cooling criteria in combination with phase-change energy storage technology.

A rotor assembly includes a rotor core having winding slots, and one or more coils, which have slot-inserted segments included in the winding slots, and first and second end-turn segments external to the winding slots and located around opposite axial ends of the rotor core, respectively. The rotor assembly further includes a first containment band located around at least a portion of the first end-turn segments and configured to prevent the first end-turn segments from moving away from the rotor core radially, a second containment band located around at least a portion of the second end-turn segments and configured to prevent the second end-turn segments from moving away from the rotor core radially, and one or more sticks mounted in one or more of the winding slots, respectively. The first and second containment bands are retained via the sticks against moving away axially.

A rotor assembly includes a rotor core having winding slots, and one or more coils, which have slot-inserted segments included in the winding slots, and first and second end-turn segments external to the winding slots and located around opposite axial ends of the rotor core, respectively. The rotor assembly further includes a first containment band located around at least a portion of the first end-turn segments and configured to prevent the first end-turn segments from moving away from the rotor core radially, a second containment band located around at least a portion of the second end-turn segments and configured to prevent the second end-turn segments from moving away from the rotor core radially, and one or more sticks mounted in one or more of the winding slots, respectively. The first and second containment bands are retained via the sticks against moving away axially.

An aircraft hybrid propulsion system (5) comprises an internal combustion engine (10) comprising a main drive shaft (24), an electric machine (28) comprising an electric machine rotor (78), a propulsor (12) mounted to a propulsor shaft (62), and a clutch arrangement configured to selectively couple each of the gas turbine engine main drive shaft (24) and electric machine rotor (78) to the propulsor drive shaft (62). The electric machine rotor (78) is mounted coaxially with the main drive shaft (24) and the clutch arrangement comprises a first overrunning clutch (52) configured to couple the main drive shaft (24) to the propulsor drive shaft (62), and a second overrunning clutch (54) configured to couple the electric machine rotor (78) to the propulsor drive shaft (62).