The controller is disposed inside the housing and configured to control operation of the inverter and control the pitch angle of the propeller blades.Ī fault-tolerant power system architecture for aircraft electric propulsion. The inverter is disposed within the housing and connected to receive DC power for conversion into AC power. The governor is configured to adjust a pitch angle of the propeller blades by actuating axial translation of the beta rod. The propeller includes propeller blades having an adjustable pitch angle which depends on an axial position of the beta rod. The propeller is mechanically coupled to the hollow motor shaft. The beta rod is axially translatable inside the hollow motor shaft.
The AC motor is disposed within the housing and includes a plurality of bearings supported inside the housing, a hollow motor shaft rotatably coupled to the housing by the plurality of bearings, a stator which is supported by the housing, and a rotor which is mounted to the hollow motor shaft. The controller is disposed inside the housing and configured to control operation of the inverter and control the pitch angle of the propeller blades.Ībstract: An electric propulsion unit comprising a housing, an AC motor, a beta rod, a propeller, a governor, an inverter, and a controller. Publication/Patent Number: US2022119121A1Īn electric propulsion unit comprising a housing, an AC motor, a beta rod, a propeller, a governor, an inverter, and a controller. For example, in response to a short circuit in one battery string, the faulty battery string may be disconnected from the positive and negative busbars while the remaining battery strings continue to provide power. The resulting battery disconnect/protection system is configured to detect bus faults, load faults and string faults and then take appropriate action to isolate the detected fault. The methods and systems use a smart mid-point battery disconnect (14), comprising a current sensor (46) and a mid-point disconnect contactor (48), in conjunction with centralized battery management system (22). For example, in response to a short circuit in one battery string, the faulty battery string may be disconnected from the positive and negative busbars while the remaining battery strings continue to provide power.Ībstract: Methods and systems for protection/disconnect of high-power/energy high-voltage modular multi-string battery packs, such as battery packs for electric propulsion systems in all-electric or hybrid-electric aircraft. The methods and systems are based on a dissimilar/redundant distributed battery pack protection architecture and use a smart mid-point battery disconnect in conjunction with centralized battery management system. Methods and systems for protection/disconnect of airborne high-power/energy high-voltage modular multi-string battery packs (such as battery packs for airborne electric propulsion systems). Publication/Patent Number: US2022115878A1