AIRCRAFT

Abstract

An aircraft includes a fuselage, a wing structure and a tail assembly, and also at least one propeller having the general shape of a ring. The propeller includes a rotor formed by an annular element having blades projecting outwardly therefrom, and a likewise annular base coaxial to the annular element and on which the annular element can turn under the action of a driver. The base is coaxial to the fuselage and integrated into the shell constituting the fuselage. The blades of the rotor are arranged outside the shell.

Claims

1. An aircraft, comprising: a fuselage, a wing structure, a tail assembly, and at least one propeller having the general shape of a ring, wherein the propeller is comprised of a rotor formed by an annular element having blades projecting outwardly therefrom, and a likewise annular base being coaxial with respect to the annular element and on which said annular element can turn under the action of drive means, said base being coaxial with respect to said fuselage and being integrated into the shell constituting said fuselage, whereas the blades of said rotor are arranged outside said shell.

2. The aircraft, according to claim 1, wherein the propeller further comprises, outside the rotor, a shroud, so as to define, together with the base to which it is rigidly connected by legs, a space in which at least one rotor moves.

3. The aircraft, according to claim 1, wherein the rotor is comprised of means for regulating the angle of attack of the blades.

4. The aircraft, according to claim 1, further comprising: two contra-rotating rotors.

5. The aircraft, according to claim 1, wherein the drive means is comprised of toroidal electric motors of the brushless type, having a fixed winding and a movable peripheral rotor, the stator being incorporated in the fixed base which is rigidly connected to the fuselage and comprises coils, while said rotor bears the blades and comprises permanent magnets at the side.

6. The aircraft, according to claim 5, wherein the stator comprises a plurality of pairs of poles.

7. The aircraft, according to claim 5 wherein the toroidal electric motors are supplied by an electricity generator.

8. The aircraft, according to claim 7, wherein the electricity generator is comprised of a gas turbine.

9. The aircraft, according to claim 1, wherein the shell which forms the fuselage comprises a space which passes through the propeller and which is divided horizontally and longitudinally by a floor which defines, at the top, a space intended for transport, and underneath, a space intended to contain the drive means and/or the supply means of said drive means.

Description

BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWINGS

[0029] The advantages and the features of the aircraft according to the invention will become clearer from reading the following description, with reference to the accompanying drawings which show a non-limiting embodiment.

[0030] In the accompanying drawings:

[0031] FIG. 1 is a perspective view of an aircraft according to the invention.

[0032] FIG. 2 is a schematic partial cross section according to a longitudinal plane of the same aircraft.

[0033] FIG. 3 is a detailed schematic view of FIG. 2.

[0034] FIG. 4 is a schematic elevated view of a portion of the engine of the aircraft according to the invention.

DETAILED DESCRIPTION OF THE INVENTION

[0035] With reference to FIG. 1, an aircraft 1 according to the invention is visible, which aircraft is of a conventional general design, i.e. it comprises a fuselage 10 which is equipped, in the mid region thereof, with two wings 11, and at the rear with a tail assembly 12.

[0036] The aircraft 1 is provided with a propulsion system made up of a propeller 2 which forms a portion of the shell 13 forming the fuselage 10, inserted between standard portions of said fuselage. The propeller 2 is annular in shape, arranged in part around the fuselage 10, in this case in front of the tail assembly 12 and projecting from the fuselage.

[0037] In this embodiment, the propeller 2 comprises two rotors 3 and 4 which are contra-rotating, are provided with blades, 30 and 40, respectively, and which project from the plane defined by the outside wall of the shell 13, in order to move between the fuselage 1 and a shroud 20 which, it will be noted, it is possible to omit.

[0038] With reference now to FIG. 2, which relates to a particular non-limiting embodiment of the power system of the propeller 2, in this case an electric power system, it is possible to see that said power system is achieved by means of toroidal electric motors of the brushless type, having a fixed winding, and that the propeller 2 is made up of a fixed base 21 which is annular in shape, and a shroud 20 that is rigidly connected, at a distance, to the base 21 by means of legs 22, and two rotors 3 and 4 which move in the annular space 23 delimited by the base 21 and the shroud 20.

[0039] It can also be seen that the annular shape of the propeller 2 makes it possible to free up a significant space inside the fuselage 10, which space is divided horizontally and longitudinally by the floor 15 of the shell 13 in order to create, above, a space 24 for transport, and, below, a hold 25 portion which can be intended to house an electric generator of, in a non-limiting manner, the gas turbine or hydrogen battery type, or indeed drive means (not shown) other than electric and intended for driving the propeller 2.

[0040] With reference also to FIG. 3, it can be seen that the base 21 is incorporated into a bearing structure 14 in the form of an annular groove which forms an integral part of the shell 13 and which houses two annular stators 5 and 6, each cooperating with one of the rotors, 3 and 4, respectively.

[0041] The stators 5 and 6 comprise coils B which are arranged and distributed peripherally, while each of the rotors 3 and 4 comprises an element in the form of a ring, 31 and 41, respectively, which is mounted on the bearing structure 21 so as to be freely rotatable, by means of rolling or sliding means G, from which the blades 30 and 40 project towards the outside, and which comprises, on the inside, permanent magnets A which are arranged so as to remain at a small distance from the coils B.

[0042] The peripheral dimension of the propeller 2 makes it possible for the engine to integrate a large number of poles, which has advantages, in particular a redundancy of the engine or engines which can be easily managed, a positioning and an exchange surface which facilitate natural cooling, it being possible for a quasi linear engine to be formed by parts, each part using an angular sector of the torus in order to create the redundancy.

[0043] Thus, with reference to FIG. 4, a portion of a rotor, 3-4, i.e. the element 31-41 and its magnet A, and a portion of a stator, 5-6, i.e. its coils B, are visible. The stator 5-6 comprises an alternating succession of angular sectors S and T creating a succession of poles.