An electric fan includes: an electric motor that includes an output shaft extending along an axis line and a tubular housing centered on the axis line; an inner duct provided on a downstream side of the electric motor; a plurality of blades mounted on the output shaft; and a cooling member having a plurality of fins provided on an outer peripheral surface of the housing.

An electric fan includes: an electric motor that includes an output shaft extending along an axis line and a tubular housing centered on the axis line; an inner duct provided on a downstream side of the electric motor; a plurality of blades mounted on the output shaft; and a cooling member having a plurality of fins provided on an outer peripheral surface of the housing.

The method for dimensioning a multi-pole oriented-flux magnetic ring for a rotor of a rotating electric machine, where the magnetic ring includes a predetermined number of pairs of poles, and the magnetic ring is formed by at least one oriented-flux magnet. The method includes determining a characteristic dimension of the magnet equal to the minimum value out of the outer perimeter of the ring and the axial length of the ring, determining a reference value equal to the minimum value out of a predetermined reference length and twice the value Pi, comparing the characteristic dimension of the magnet with the reference value, and if the characteristic dimension of the magnet is greater than the reference value, the method comprises circumferentially dividing the magnet into at least two sub-magnets.

The method for dimensioning a multi-pole oriented-flux magnetic ring for a rotor of a rotating electric machine, where the magnetic ring includes a predetermined number of pairs of poles, and the magnetic ring is formed by at least one oriented-flux magnet. The method includes determining a characteristic dimension of the magnet equal to the minimum value out of the outer perimeter of the ring and the axial length of the ring, determining a reference value equal to the minimum value out of a predetermined reference length and twice the value Pi, comparing the characteristic dimension of the magnet with the reference value, and if the characteristic dimension of the magnet is greater than the reference value, the method comprises circumferentially dividing the magnet into at least two sub-magnets.

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.

An aircraft compensates for asymmetry of engine failure by drawing part of the energy produced by the still-operating engine to generate thrust at the tip of the opposite wing. For example, the left engine drives its own thrust on the left wing, but a portion of the energy the left engine produces is delivered at a propeller at the tip of right wing. Similarly, the right engine drives its own thrust on the right wing, but a portion of the energy the right engine produces is delivered at a propeller at the tip of the left wing. In this way, every pair of engines and opposite tip thrust generators are intrinsically balanced. In the event of one engine failure, no yaw moment will be noticed.

A converter for an aircraft includes an intermediate circuit for providing a DC voltage between a positive line and a negative line, at least two rectifiers connected to the intermediate circuit to produce the DC voltage from input AC voltages and at least two inverters connected to the intermediate circuit to produce AC output voltages from the DC voltage. The DC voltage terminals of the rectifiers are connected to a first series circuit and the DC voltage terminals of the inverters are connected to a second series circuit. The positive line and the negative line of the intermediate circuit are connected on an input side via the first series circuit and on the output side via the second series circuit. At least one of the DC voltage terminals includes a short circuit for short-circuiting terminal contacts by which the DC voltage terminal is connected to the respective series circuit.

An electrical propulsion system for a vehicle. The electrical propulsion system includes at least one generator. The electrical propulsion system also includes at least one drive engine coupled to the at least one generator. The electrical propulsion system further includes at least one electrical device and at least one battery integrated power converter (BIC). The at least one generator and at least one of the at least one BIC and the at least one electrical device are coupled. The at least one BIC and the at least one electrical device are coupled.

A solar relay aircraft system includes a solar relay aircraft having an upper surface, and a lower surface, and equipped with a solar radiation receiver on said lower surface and capable of converting solar energy to electrical energy. An electric motor in electrical connection with said solar radiation receiver to receive the electrical energy and drives a propeller to propel the solar relay aircraft. A number of ground-based reflector arrays include a plurality of reflecting mirrors for receiving solar radiation from the sun and direct the solar radiation from the sun towards the solar relay aircraft.