An aircraft propulsion system comprises a propulsor an electric motor coupled to the propulsor. The electric motor comprises a surface mounted permanent magnet electric machine comprising a rotor mounted radially inward of a stator. A Motor Diameter Ratio (MDR) is defined as an inner diameter (D.sub.stator,in) of the motor stator in metres divided by an outer diameter (D.sub.stator,out) of the motor stator in metres. The MDR of the electric motor stator is within 10% of the value given by the equation: ${\mathrm{MDR}=0.83(\frac{\mathrm{Torq}ue}{L_{active}}\frac{1}{U_{\mathrm{fan},\mathrm{tip}}})}^{0.08}$ where: T is the maximum torque rating of the electric motor in kilonewton metres; L.sub.active is the active length of the motor stator in metres; and U.sub.tip is the tip speed of the propulsor at the maximum rated torque of the electric motor in metres per second. In the described embodiments, the MDR is less than 1.

An apparatus for facilitating propulsion of a vehicle. The apparatus comprises a housing with an interior space, an inlet, and an outlet, a propulsion mechanism, and a gimbal. The propulsion mechanism is disposed in the interior space and comprises and an upper rotor and a lower rotor rotatably mounted on a first portion and a second portion of a spindle. The upper rotor rotates in a first direction and the lower rotor rotates in a second direction opposite to the first direction. Upper rotor blades have a first blade pitch and lower rotor blades have a second blade pitch opposite to the first blade pitch. The rotating of the upper rotor and the lower rotor crates a fluid flow from the inlet to the outlet for generating a directional thrust. The gimbal rotatably attaches the propulsion mechanism to the housing. The housing is rotatable for vectoring the directional thrust.

The novel wing design disclosed herein has a cambered, swept wing design for aircraft application that can achieve steady state flight via the integration of an electric motor driven lift-thrust system that can provide both vertical thrust for take-off and horizontal thrust for flight propulsion by the selective use of fan blades connected to the motor.

The novel wing design disclosed herein has a cambered, swept wing design for aircraft application that can achieve steady state flight via the integration of an electric motor driven lift-thrust system that can provide both vertical thrust for take-off and horizontal thrust for flight propulsion by the selective use of fan blades connected to the motor.

An electrical propulsion assembly that includes: a propeller that has a rotation axis, at least two electric motors offset relative to one another in a longitudinal direction parallel to the rotation axis of the propeller, a main drive shaft parallel to the rotation axis of the propeller to which the electric motor are coupled, a transmission system including an output shaft connected to the propeller and an input shaft connected to the main drive shaft. Also an aircraft including at least one such electrical propulsion assembly.

An electrical propulsion assembly that includes: a propeller that has a rotation axis, at least two electric motors offset relative to one another in a longitudinal direction parallel to the rotation axis of the propeller, a main drive shaft parallel to the rotation axis of the propeller to which the electric motor are coupled, a transmission system including an output shaft connected to the propeller and an input shaft connected to the main drive shaft. Also an aircraft including at least one such electrical propulsion assembly.

An aeronautical propulsion system (200), comprises a propeller (202) mounted to a propeller shaft (204) defining a propeller axis (214); an electric motor (208) comprising a motor output shaft defining a motor axis (216); wherein the motor output shaft and propeller shaft are connected by a linkage such that, in use, driving the motor output shaft for rotation drives rotation of the propeller via the propeller shaft and linkage; and a motor power unit configured to receive power from a power source and provide a motor drive signal to the motor; wherein the motor power unit is spaced along the motor axis from the motor.

An aeronautical propulsion system (200), comprises a propeller (202) mounted to a propeller shaft (204) defining a propeller axis (214); an electric motor (208) comprising a motor output shaft defining a motor axis (216); wherein the motor output shaft and propeller shaft are connected by a linkage such that, in use, driving the motor output shaft for rotation drives rotation of the propeller via the propeller shaft and linkage; and a motor power unit configured to receive power from a power source and provide a motor drive signal to the motor; wherein the motor power unit is spaced along the motor axis from the motor.

Provided is an electric propulsion device 106 including a propeller 131 and a motor 121 for rotating the propeller, wherein the propeller includes a rotary boss 132 secured to a rotating shaft 123 of the motor, and blades 133 protruding radially outward from the rotary boss. Further, the blades include a base end portion with an airfoil continuously changing such that a trailing edge comes to be in parallel to the rotating shaft of the motor from a radially outer side to the rotary boss, in a vicinity of the rotary boss.

Provided is an electric propulsion device 106 including a propeller 131 and a motor 121 for rotating the propeller, wherein the propeller includes a rotary boss 132 secured to a rotating shaft 123 of the motor, and blades 133 protruding radially outward from the rotary boss. Further, the blades include a base end portion with an airfoil continuously changing such that a trailing edge comes to be in parallel to the rotating shaft of the motor from a radially outer side to the rotary boss, in a vicinity of the rotary boss.