An aircraft includes: a gas turbine for driving a generator; a first electric motor for driving a first rotor; and a second electric motor for driving a second rotor. The gas turbine is arranged in a manner so that the gas turbine overlaps a rear wing in the front-rear direction of a fuselage, and a first high-voltage harness for transmitting electric power to the first electric motor and a second high-voltage harness for transmitting electric power to the second electric motor are arranged inside the rear wing so as to be separated from each other in the front-rear direction of the fuselage.

The invention is related to a battery housing (10) for accommodating a battery device (20) with multiple battery cells (22) for an electric aircraft (100), comprising at least one inner wall (30) and at least one outer wall (40) forming together a battery volume (50) for holding the multiple battery cells (22), characterised in that the at least one outer wall (40) comprises an outside surface (42) wherein the outside surface (42) has an aerodynamical shape for completing a part of a fuselage (110) of the electric aircraft (100).

The invention is related to a battery housing (10) for accommodating a battery device (20) with multiple battery cells (22) for an electric aircraft (100), comprising at least one inner wall (30) and at least one outer wall (40) forming together a battery volume (50) for holding the multiple battery cells (22), characterised in that the at least one outer wall (40) comprises an outside surface (42) wherein the outside surface (42) has an aerodynamical shape for completing a part of a fuselage (110) of the electric aircraft (100).

An electric aircraft is capable of vertically taking off and landing. The aircraft includes a fuselage, front and rear power units, power pods, main wings, ailerons, front landing gears, a tail wing and a rear landing gear. The power units include first and second electric duct groups. The first electric duct group includes two electric duct fans symmetrically and connected to two sides of a front portion of the fuselage respectively. The second electric duct group includes two electric duct fans symmetrically provided at two sides of a rear portion of the fuselage respectively. The power pods are configured to connect the fuselage to the first electric duct group. The two main wings are symmetrically and foldably connected to two sides of the fuselage respectively. The two ailerons are symmetrically connected to front ends of the two main wings respectively.

An electric aircraft is capable of vertically taking off and landing. The aircraft includes a fuselage, front and rear power units, power pods, main wings, ailerons, front landing gears, a tail wing and a rear landing gear. The power units include first and second electric duct groups. The first electric duct group includes two electric duct fans symmetrically and connected to two sides of a front portion of the fuselage respectively. The second electric duct group includes two electric duct fans symmetrically provided at two sides of a rear portion of the fuselage respectively. The power pods are configured to connect the fuselage to the first electric duct group. The two main wings are symmetrically and foldably connected to two sides of the fuselage respectively. The two ailerons are symmetrically connected to front ends of the two main wings respectively.

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.

An electricity generation and propulsion system of an aircraft is provided. The electricity generation and propulsion system includes a fuselage, a hybrid-electric power generation system operably disposed in the fuselage and a ram air turbine (RAT) device. The RAT device is coupled with the hybrid-electric power generation system and is stowable in the fuselage and deployable to an exterior of the fuselage. The RAT device is operable as a RAT when deployed into an airstream that drives rotations of the RAT from which the hybrid-electric power generation system generates electricity, and the RAT device is operable as a propulsor when deployed and driven by the hybrid-electric power generation system.

An electrical engine mounting arrangement for providing propulsion power to a vehicle includes a mounting block, an electric motor, a power transfer shaft arranged to rotate in response to the rotation of the electric motor and aligned along a rotation axis. The rotation axis lies on a division plane. One or more first side battery compartments are fixed to the mounting block at the first side of the division plane, and one or more second side battery compartments are fixed to the mounting block at the second side. The batteries housed in the battery compartments supply power to the electric motor.

An electrical engine mounting arrangement for providing propulsion power to a vehicle includes a mounting block, an electric motor, a power transfer shaft arranged to rotate in response to the rotation of the electric motor and aligned along a rotation axis. The rotation axis lies on a division plane. One or more first side battery compartments are fixed to the mounting block at the first side of the division plane, and one or more second side battery compartments are fixed to the mounting block at the second side. The batteries housed in the battery compartments supply power to the electric motor.