A method for manufacturing a rotor assembly of an electric engine, comprising: loading a first and second plurality of magnets in a magnet insertion tool, loading a sleeve in the magnet insertion tool: performing an insertion movement of the first plurality of magnets with respect to the second plurality of magnets using the magnet insertion tool, wherein the insertion movement comprises: moving the first plurality of magnets in a radial direction of the sleeve; moving the second plurality of magnets in an axial direction of the sleeve; and expanding a radius of the sleeve in the radial direction using the magnet insertion tool during the insertion movement.

An inspection device includes a switching assembly including a switch array configured to allow or block power flow to at least one component among a plurality of components of an aircraft having a heterogeneous power source module and a propulsor driven by the power source module; and one or more processors configured to control the switch array to allow or block power flow to the at least one component based on an inspection mode related to at least one of the power source module and the propulsor and output diagnostic data for the at least one component by performing an inspection according to the inspection mode.

An inspection device includes a switching assembly including a switch array configured to allow or block power flow to at least one component among a plurality of components of an aircraft having a heterogeneous power source module and a propulsor driven by the power source module; and one or more processors configured to control the switch array to allow or block power flow to the at least one component based on an inspection mode related to at least one of the power source module and the propulsor and output diagnostic data for the at least one component by performing an inspection according to the inspection mode.

A drive unit for a rotary-wing aircraft has a first and second propeller, which rotates in the opposite direction to, and are axially spaced apart from, the first propeller. A first and second drive shaft are arranged coaxially with the first drive shaft, for the propellers, wherein the propellers are each rigid and mounted to be tiltable relative to the axis of rotation of their drive shafts. The tilt axis of each propeller extends in a plane perpendicular to the axis of rotation of the drive shafts and is oriented at an angle different from 90 relative to the longitudinal axis of the propeller. An electric drive module has at least two rotors which are coupled to one of the drive shafts, wherein the ratio of the diameter of the propellers to the axial distance between the propellers is between 4:1 and 12:1.

A drive unit for a rotary-wing aircraft has a first and second propeller, which rotates in the opposite direction to, and are axially spaced apart from, the first propeller. A first and second drive shaft are arranged coaxially with the first drive shaft, for the propellers, wherein the propellers are each rigid and mounted to be tiltable relative to the axis of rotation of their drive shafts. The tilt axis of each propeller extends in a plane perpendicular to the axis of rotation of the drive shafts and is oriented at an angle different from 90 relative to the longitudinal axis of the propeller. An electric drive module has at least two rotors which are coupled to one of the drive shafts, wherein the ratio of the diameter of the propellers to the axial distance between the propellers is between 4:1 and 12:1.

A configuration instruction associated with configuring a plurality of batteries which supply power to a plurality of motors in a vehicle is received. The batteries are configuring as specified by the configuration instruction, where the batteries are able to be configured in a plurality of configurations, including: a first configuration where at least some of the batteries are electrically connected together in parallel and a second configuration where at least some of the batteries are electrically connected together in series.

A configuration instruction associated with configuring a plurality of batteries which supply power to a plurality of motors in a vehicle is received. The batteries are configuring as specified by the configuration instruction, where the batteries are able to be configured in a plurality of configurations, including: a first configuration where at least some of the batteries are electrically connected together in parallel and a second configuration where at least some of the batteries are electrically connected together in series.

An assembly for an aircraft powerplant includes an engine case, a gearbox, a conduit, a first electric machine, a first controller and a first electric cable. The gearbox is offset from the engine case. The conduit extends longitudinally from a first end of the conduit to a second end of the conduit. The conduit is anchored to the engine case at the first end of the conduit by a first conduit mount. The conduit is anchored to the gearbox at the second end of the conduit by a second conduit mount. The conduit is self-supported longitudinally between the first conduit mount and the second conduit mount. The first electric machine is mounted to the gearbox. The first controller is mounted to the engine case. The first electric cable electrically couples the first electric machine to the first controller. The first electric cable extends longitudinally through a bore of the conduit.

An assembly for an aircraft powerplant includes an engine case, a gearbox, a conduit, a first electric machine, a first controller and a first electric cable. The gearbox is offset from the engine case. The conduit extends longitudinally from a first end of the conduit to a second end of the conduit. The conduit is anchored to the engine case at the first end of the conduit by a first conduit mount. The conduit is anchored to the gearbox at the second end of the conduit by a second conduit mount. The conduit is self-supported longitudinally between the first conduit mount and the second conduit mount. The first electric machine is mounted to the gearbox. The first controller is mounted to the engine case. The first electric cable electrically couples the first electric machine to the first controller. The first electric cable extends longitudinally through a bore of the conduit.