An air intake scoop intended to be fastened on a panel of an aircraft includes an air inlet mouth having a wall, a peripheral collar intended to be fastened to the panel, and a bearing element intended to support the air circulation duct. The air inlet mouth is made of a thermoplastic material and the bearing element is fastened on the peripheral collar so as to achieve a pressure barrier in case of breakage of the wall of the air inlet mouth.

A machine includes a liquid lubrication system and a shaft, the shaft being rotatable about a rotation axis, the shaft including a first part, a second part engaged coaxially with the first part, and a journal bearing between the first part and the second part, the first part being rotatable relative to the second part about the rotation axis, a helical feature disposed between the first part and the second part and configured to define a helical pump between the first part and the second part, the pump being hydraulically connected to the liquid lubrication system, the journal bearing being disposed adjacent to the helical feature.

A machine includes a liquid lubrication system and a shaft, the shaft being rotatable about a rotation axis, the shaft including a first part, a second part engaged coaxially with the first part, and a journal bearing between the first part and the second part, the first part being rotatable relative to the second part about the rotation axis, a helical feature disposed between the first part and the second part and configured to define a helical pump between the first part and the second part, the pump being hydraulically connected to the liquid lubrication system, the journal bearing being disposed adjacent to the helical feature.

An aircraft propulsion unit includes an electric motor, at least one accessory unit used for operating the electric motor, an inverter module, the inverter module including a plurality of inverters for powering the electric motor and the at least one accessory unit, and a cooling system coupled to the electric motor and the inverter module, the cooling system comprising a coolant path for circulating a coolant through or adjacent to the electric motor and the at least one accessory unit.

An aircraft propulsion unit includes an electric motor, at least one accessory unit used for operating the electric motor, an inverter module, the inverter module including a plurality of inverters for powering the electric motor and the at least one accessory unit, and a cooling system coupled to the electric motor and the inverter module, the cooling system comprising a coolant path for circulating a coolant through or adjacent to the electric motor and the at least one accessory unit.

In an aspect of the present disclosure is an electric aircraft lift motor with air cooling, the motor including a stator connected to the electric aircraft, the stator including: an inner cylindrical surface and an outer cylindrical surface, wherein each of the inner cylindrical surface and the outer cylindrical surface is coaxial about an axis of rotation; and a rotor coaxial within the stator, the rotor including a rotor cylindrical surface, wherein the rotor cylindrical surface and the inner cylindrical surface combine to form an air gap between the rotor cylindrical surface and the inner cylindrical surface; and a first fan connected to an axial end of the rotor and configured to rotate with the rotor, the first fan comprising at least a blade configured to direct air toward the air gap.

In an aspect of the present disclosure is an electric aircraft lift motor with air cooling, the motor including a stator connected to the electric aircraft, the stator including: an inner cylindrical surface and an outer cylindrical surface, wherein each of the inner cylindrical surface and the outer cylindrical surface is coaxial about an axis of rotation; and a rotor coaxial within the stator, the rotor including a rotor cylindrical surface, wherein the rotor cylindrical surface and the inner cylindrical surface combine to form an air gap between the rotor cylindrical surface and the inner cylindrical surface; and a first fan connected to an axial end of the rotor and configured to rotate with the rotor, the first fan comprising at least a blade configured to direct air toward the air gap.

A locking system for an electric propulsion system is disclosed. The system includes a propulsor configured to propel an electric vehicle and a motor operatively connected to the propulsor configured to power the propulsor. The motor includes a rotor connected to the propulsor and a stator configured to rotate the rotor. A propulsor sensor is configured to determine a motion parameter of the propulsor. A lock is configured to prevent a movement of the propulsor. A controller is configured to receive a signal from the propulsor sensor and control the motor as a function of the signal from the propulsor sensor, wherein controlling the motor includes allowing the propulsor to slow at a desired rate for parking.

The disclosure relates to a modular arrangement of a converter for the electrical supply of a multi-phase electric motor. The modular arrangement includes multiple output stage modules, each module having a separate first housing. An output stage module is provided for each phase of the electric motor, wherein the output stage module has a phase intermediate circuit and an inverter circuit, together forming a commutation cell. The phase intermediate circuit supplies DC voltage and is electrically connected to the inverter circuit. The disclosure also relates to a motor arrangement and an aircraft having a motor arrangement of this type.

The disclosure relates to a modular arrangement of a converter for the electrical supply of a multi-phase electric motor. The modular arrangement includes multiple output stage modules, each module having a separate first housing. An output stage module is provided for each phase of the electric motor, wherein the output stage module has a phase intermediate circuit and an inverter circuit, together forming a commutation cell. The phase intermediate circuit supplies DC voltage and is electrically connected to the inverter circuit. The disclosure also relates to a motor arrangement and an aircraft having a motor arrangement of this type.