An aircraft including a fuselage with a cooling unit including a first radiator, a second radiator, a first cooling fan and a second cooling fan for taking air outside the fuselage into the fuselage and supplying air to the first radiator and the second radiator. The aircraft has an exhaust orifice for discharging air delivered into the interior of the fuselage, the cooling unit is arranged forward of the engine in the fuselage, and the exhaust orifice is positioned rearward of the engine in the fuselage.

A propulsor fan and drive system having reduced noise emission is disclosed. The propulsor fan includes a blade fan having a plurality of blades. The blade fan is tensioned at the tips of the plurality of blades. 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 and drive system having reduced noise emission is disclosed. The propulsor fan includes a blade fan having a plurality of blades. The blade fan is tensioned at the tips of the plurality of blades. 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.

An aircraft is provided including a fuselage extending between a forward end and an aft end. An aft engine is mounted to the fuselage at the aft end of the fuselage. The aft engine includes a nacelle having a forward section. An airflow duct is also provided extending at least partially through the nacelle and including an opening on the forward section of the nacelle. The opening is configured for providing an airflow to, or receiving an airflow from, the forward section of the nacelle to increase an amount of, e.g., boundary layer airflow received within the aft engine during operation of the aircraft, to guide the flow of boundary layer airflow into the engine more smoothly, or to reduce a distortion on the engine.

An aircraft includes a front tiltwing which in turn includes two non-foldable outer propellers and four foldable inner propellers. The four foldable inner propellers are rotating at least some of the time while the front tiltwing is held in a vertical takeoff and landing position. The four foldable inner propellers are stowed at least some of the time while the front tiltwing is held in a forward flight position. The aircraft also includes a back tiltwing which includes two non-foldable back propellers.

An aircraft with an electric propulsion arrangement which includes a fuselage, a wing system attached to the fuselage, and a tail unit attached to a rear part of the fuselage. The electric propulsion arrangement is arranged on each side of the fuselage, an electrical energy generator and electricity storage and supply devices are arranged substantially along a longitudinal axis of symmetry of the fuselage. The aircraft thus incorporates a hybrid motorization.

Provided are a stator, and a propeller driving device and an aircraft using the stator. The propeller driving device includes: a radial gap type BLDC motor with an inner rotor-outer stator structure where a rotor is placed in a circumferential shape with an air gap inside a stator; and a propeller installation bracket for mounting a propeller to a rotary shaft of the motor, wherein the stator includes: a stator core including an annular back yoke having a predetermined width to form a magnetic circuit and teeth extending from the back yoke in a central direction; an insulator formed to surround an outer circumferential surface on which a coil is wound in each tooth; and a stator coil wound around an outer circumferential surface of the insulator in each tooth. The insulator is formed of an insulating heat dissipation composite material having both heat dissipation performance and insulation performance.

An aircraft includes a fuselage extending between a forward end and an aft end. An aft engine is mounted to the aft end of the fuselage, the aft engine defining a centerline. The aft engine further includes a nacelle having a bottom section, the bottom section having a forward lip. The forward lip of the bottom section defines a camber line. The camber line, in turn, defines an angle relative to the centerline of the aft engine greater than or equal to at least about five degrees.

An aircraft includes a fuselage extending between a forward end and an aft end. The aircraft additionally includes a propulsor mounted to the fuselage at the aft end of the fuselage, the propulsor including an outer nacelle and the outer nacelle defining an inlet. Additionally, the aircraft includes a deployable assembly attached to at least one of the fuselage or the outer nacelle, the deployable assembly movable between a stowed position and an engaged position. The deployable assembly alters an airflow towards the propulsor or into the propulsor through the inlet defined by the outer nacelle when in the engaged position to increase an efficiency of the aft fan and/or of the aircraft.

A gas turbine engine includes a compressor section and a turbine section together defining a core air flowpath. The rotary component is rotatable with the compressor section and the turbine section. The gas turbine engine additionally includes an electric machine rotatable with the rotary component and positioned coaxially with the rotary component at least partially inward of the core air flowpath. The electric machine is flexibly mounted to a static frame member, or flexibly coupled to the rotary component, or both, such that the electric machine is mechanically isolated or insulated from various internal and external forces on the gas turbine engine.