An electric power system for a vehicle includes at least one electric machine, one or more power rectifiers, and a plurality of DC channels. The at least one electric machine includes a plurality of tooth-wound multi-phase windings that are substantially magnetically decoupled, and the at least one electric machine is mechanically balanced even if one of the plurality of windings is de-energized. The one or more power rectifiers are configured to produce rectified power from the power generated by the at least one electric machine. The plurality of DC channels are formed after the at least one power rectifier and are configured to provide DC power to one or more loads within a vehicle.

A method and system for operating a hybrid propulsion system, includes controllably providing a first power to a first bus and a first inverter, electrically coupling a first motor with a second inverter by way of a second bus, operably converting, by the second inverter, the first power received by the first inverter to a starting power adapted for starting the first motor, and increasing, by the second inverter, the starting power to match the first power received.

A system for fault detection and control in an electric aircraft including an inertial measurement unit, the inertial measurement unit including at least a sensor configured to detect a torque datum associated with at least a propulsor. The system includes an observer, the observer configured to generate a torque prediction datum associated with the at least a propulsor, compare the torque prediction datum with the torque datum, and generate a residual datum as a function of the comparison. The system includes a mixer, the mixer comprising circuitry configured to generate, as a function of the residual datum, a torque priority command datum and transmit, to the at least a propulsor, the torque priority command datum.

This aircraft is a Vertical Take Off and Landing Fighter type. The primary power source will be a low bypass jet turbine/engine. The auxiliary power source will be provided by axial flux electric motors. These motors will be housed in a moveable section, the EVTOL apparatus, that houses multiple turbines. These moveable sections will be attached to sides of the fuselage, extending into the dual wing. These moveable sections will move to a vertical position during take-off and landing; and be in a horizontal position during normal flight. These moveable sections will have an intake area aft, and vectoring thrust at the rear. This aircraft is a hybrid utilizing a gas jet turbine and electrical axial flux motors. The EVTOL apparatus is a compact self-contained unit capable of generating thrust through a turbine driven by Axial Flux electric motors.

A craft comprises at least one hull, a main wing coupled to the hull and configured to facilitate airborne operations of the craft, a plurality of propellers that include one or more electric motor propellers and one or more combustion motor propellers arranged along each of a port side and a starboard side of the main wing and configured to generate lift on the craft by blowing air over the main wing, and a control system. The control system comprises data storage having instruction code stored thereon that, when executed by one or more processors of the control system, causes the control system to: after receiving a takeoff indication, increase thrust generated by the electric motor propellers to cause the craft to transition from a hull-borne mode of operation to an airborne mode of operation, and after a thrust adjustment condition occurs, increase thrust generated by the combustion motor propellers.

A craft comprises at least one hull, a main wing coupled to the hull and configured to facilitate airborne operations of the craft, a plurality of propellers that include one or more electric motor propellers and one or more combustion motor propellers arranged along each of a port side and a starboard side of the main wing and configured to generate lift on the craft by blowing air over the main wing, and a control system. The control system comprises data storage having instruction code stored thereon that, when executed by one or more processors of the control system, causes the control system to: after receiving a takeoff indication, increase thrust generated by the electric motor propellers to cause the craft to transition from a hull-borne mode of operation to an airborne mode of operation, and after a thrust adjustment condition occurs, increase thrust generated by the combustion motor propellers.

An electric motor comprises a rotor and a stator. The rotor includes a housing having an inner surface and an outer surface, a first end, and a second end. Permanent magnets are located along the inner surface of the rotor housing. At least one groove is defined in the first end of the rotor housing. A sealing member includes at least one protrusion located in the at least one groove. A honeycomb panel may be located in a recess defined in the outer surface of the rotor housing. The electric motor may form part of a propulsions system for an aircraft, used to drive a rotor assembly including rotor blades.

An electric motor comprises a rotor and a stator. The rotor includes a housing having an inner surface and an outer surface, a first end, and a second end. Permanent magnets are located along the inner surface of the rotor housing. At least one groove is defined in the first end of the rotor housing. A sealing member includes at least one protrusion located in the at least one groove. A honeycomb panel may be located in a recess defined in the outer surface of the rotor housing. The electric motor may form part of a propulsions system for an aircraft, used to drive a rotor assembly including rotor blades.

A propulsor fan array having reduced noise emission is disclosed. The propulsor fan array includes a plurality of propulsor fans that collectively generate thrust. Each of the propulsor fans include a blade fan having a plurality of blades. The plurality of blades are tensioned at tips of the plurality of blade fans such that a pitch of the blades during thrust generation is substantially the same as a pitch of the blades at rest. By tensioning the tips of the blades, an angle of the blades is maintained during operation of the propulsor fan thereby reducing noise that may result from changes in the angle of the blades.

A propulsor fan array having reduced noise emission is disclosed. The propulsor fan array includes a plurality of propulsor fans that collectively generate thrust. Each of the propulsor fans include a blade fan having a plurality of blades. The plurality of blades are tensioned at tips of the plurality of blade fans such that a pitch of the blades during thrust generation is substantially the same as a pitch of the blades at rest. By tensioning the tips of the blades, an angle of the blades is maintained during operation of the propulsor fan thereby reducing noise that may result from changes in the angle of the blades.