A rotational slip ring assembly for an improved counter-rotating (CR) differential electric motor assembly is utilized to power an aircraft vehicle or fan for moving a gas and includes two oppositely rotating propellers that may be mounted to horizontal flight and vertical lift-off aircraft or a fan housing in spaces similar in size to mounting spaces for traditional motors having only one propeller and includes a hollow central shaft and slip ring assembly that is mounted either within, slight above, or total above oppositely rotating components and around the hollow central shaft.

The invention relates to a turbomachine of an aircraft comprising an outer casing (2) delimiting with an inner hub (3), a flow path (1) of a gas stream in which is disposed a low-pressure turbine configured to rotationally drive a low-pressure shaft; said turbomachine comprising, in the direction of flow of the gas stream, a first propeller (31); and a second propeller (32) downstream of the first propeller, the first propeller (31) being rotationally driven by said low-pressure shaft and the second propeller being rotationally driven by an electric motor (70), the second propeller (32) being further disposed at a distance between 1.5 and 4 cord lengths (LC1) from the first propeller (31) defined between the respective axes of shimming (A31, A32) of each of the first and second propellers.

The invention relates to a turbomachine of an aircraft comprising an outer casing (2) delimiting with an inner hub (3), a flow path (1) of a gas stream in which is disposed a low-pressure turbine configured to rotationally drive a low-pressure shaft; said turbomachine comprising, in the direction of flow of the gas stream, a first propeller (31); and a second propeller (32) downstream of the first propeller, the first propeller (31) being rotationally driven by said low-pressure shaft and the second propeller being rotationally driven by an electric motor (70), the second propeller (32) being further disposed at a distance between 1.5 and 4 cord lengths (LC1) from the first propeller (31) defined between the respective axes of shimming (A31, A32) of each of the first and second propellers.

The present invention discloses a ducted double-magnetic-circuit coreless motor special for electric aircraft, which is an open special motor with a hollow structure according to the technical invention and includes a housing, a main shaft, a coreless stator winding, an inner rotor structure and an outer rotor structure. The main shaft is arranged in the middle of the housing; the inner rotor structure is connected with the main shaft; the outer rotor structure is connected with the inner rotor structure; and the coreless stator winding is arranged between the inner rotor structure and the outer rotor structure. The coreless stator winding can generate an electromagnetic torque when current is applied; and the inner rotor structure and the outer rotor structure can fully induce the electromagnetic torque of the coreless stator winding and rotate about the main shaft simultaneously, thereby directly driving the electric aircraft to fly.

An unmanned rotorcraft includes an airframe, rotor blades that are coupled to the airframe for rotation therewith, a propulsion unit having a propeller, and an actuator that is coupled to the airframe and adapted to temporarily reorient the propulsion unit such that an axis of the propeller moves out of alignment with an axis of the rotor blades. Rotation of the propeller causes counter-rotation of the airframe and rotor blades. The rotor blades and blades of the propeller are adapted to deploy from collapsed positions when flight of the rotorcraft is initiated. A method of operation by the rotorcraft includes, when it is determined that a current heading does not correspond to a determined flight path, causing the actuator to temporarily reorient the propulsion unit in accordance with an angular orientation of the actuator relative to the current heading.

A multi-rotor aircraft includes a fuselage, a propulsion engine coupled to the fuselage that generates thrust to propel the aircraft along a first vector during forward flight, and rotors coupled to the fuselage, each rotor comprising blades, each rotor coupled to a motor, and each motor configured to supply power to and draw power from the coupled rotor. The aircraft includes a flight control system configured to control the motors coupled to the rotors in a power managed regime in which a net electrical power, consisting of a sum of the power being supplied to or drawn from each rotor by its motor, is maintained within a range determined by a feedback control system of the flight control system. The flight control system can also be leveraged to adjust rotor control inputs to modify at least one of thrust, roll, pitch, or yaw of the multi-rotor aircraft.

An axial flow turbomachine (102) for producing thrust to propel an aircraft is shown. The turbomachine has an inner duct (202) and an outer duct (204), both of which are annular and concentric with one another. An inner fan (206) is located in the inner duct, and is configured to produce a primary pressurised flow (P). An outer fan (207) is located in an outer duct, and is configured to produce a secondary pressurised flow (S). The outer fan has a hollow hub (208) through which the inner duct passes. The inner fan is configured to have, in operation, a rate of rotation of from 3 to 8 times that of the outer fan.

An axial flow turbomachine (102) for producing thrust to propel an aircraft is shown. The turbomachine has an inner duct (202) and an outer duct (204), both of which are annular and concentric with one another. An inner fan (206) is located in the inner duct, and is configured to produce a primary pressurised flow (P). An outer fan (207) is located in an outer duct, and is configured to produce a secondary pressurised flow (S). The outer fan has a hollow hub (208) through which the inner duct passes. The inner fan is configured to have, in operation, a tip speed of from 1 to 3 times that of the outer fan.

An aircraft rotor assembly comprises first and second rotors and a drive assembly. The first and second rotors are rotatable about a common axis synchronously and with respect to each other. The first rotor has a first blade extending radially from the common axis; the second rotor has a second blade extending radially from the common axis, longitudinally offset from the first blade along the common axis. The drive assembly is coupled to the first and second rotors and configured to controllably vary, during continuous rotation of the first and second rotors, a differential phase angle separating the first and second blades as projected onto a plane perpendicular to the common axis.

An aircraft rotor assembly comprises first and second rotors and a drive assembly. The first and second rotors are rotatable about a common axis synchronously and with respect to each other. The first rotor has a first blade extending radially from the common axis; the second rotor has a second blade extending radially from the common axis, longitudinally offset from the first blade along the common axis. The drive assembly is coupled to the first and second rotors and configured to controllably vary, during continuous rotation of the first and second rotors, a differential phase angle separating the first and second blades as projected onto a plane perpendicular to the common axis.