Aircraft comprising a fuselage and wings each having an outer part and a widened inner part between the fuselage and the outer part

1. An aircraft comprising:

a fuselage,

first and second wings positioned on either side of the fuselage,

the fuselage having a longitudinal axis and a fuselage height, the fuselage comprising:

a nose,

a tail, and

at least one portion positioned between the nose and the tail, such that each wing comprises:

an inner part, and

an outer part such that each inner part connects the corresponding outer part and the fuselage, each inner part comprising:

a first end connected by a first connection to the corresponding outer part, and

a second end connected by a second connection to the fuselage,

each inner part having, at the second end, a height greater than half the height of the fuselage, the second end of each inner part extending over a length greater than or equal to half of a distance separating the nose and the tail;

wherein each inner part comprises at least one cylindrical fuel tank positioned along the fuselage and having an axis of revolution parallel to the longitudinal axis,

wherein each inner part comprises multiple spars positioned in vertical planes, at least two spars being separated by a distance which increases from the first end toward the second end,

wherein each fuel tank passes through at least one of the at least two spars.

2. The aircraft as claimed in claim 1 ,

wherein each fuselage portion has a fuselage structure and an aerodynamic fuselage envelope fitted on the fuselage structure,

wherein each outer part has a wing outer part structure and an aerodynamic wing outer part envelope fitted on the wing outer part structure, and

wherein each inner part comprises at least one wing inner part structure ensuring a transmission of forces between the wing outer part structure of the corresponding outer part and the fuselage structure, and an aerodynamic wing inner part envelope ensuring that the aerodynamic wing outer part envelope of the corresponding outer part and the aerodynamic fuselage envelope are continuous.

3. The aircraft as claimed in claim 1 ,

wherein, for each inner part, the first end has a first length, and

wherein the second end has a second length at least twice the first length of the first end, the first and second ends being separated by a distance less than the second length.

4. The aircraft as claimed in claim 1 , wherein the at least one cylindrical fuel tank comprises a plurality of cylindrical fuel tanks being positioned inside each of the inner parts.

5. The aircraft as claimed in claim 2 , wherein the at least one wing inner part structure of each inner part comprises a panel, positioned in a plane parallel to the longitudinal axis and horizontal or slightly inclined with respect to a horizontal plane, which extends between the first and second ends of each inner part.

6. The aircraft as claimed in claim 1 , wherein, for each wing, the first connection comprises a first plate integral with the outer part and positioned at the first end of the outer part, a second plate integral with the inner part and positioned at the first end of the inner part, and multiple connection elements keeping the first and second plates pressed against one another.

7. The aircraft as claimed in claim 4 , wherein each cylindrical fuel tank of the plurality of cylindrical fuel tanks has a volume of greater than 5 m 3 .

8. The aircraft as claimed in claim 4 , wherein each cylindrical fuel tank is supported by the inner part of each wing and positioned such that they are not affected upon a lateral or rearward tilting of the aircraft or upon a landing on the fuselage.

9. The aircraft as claimed in claim 2 , wherein at least one of the inner parts comprises:

at least one cooling device having at least one heat exchanger positioned inside the aerodynamic wing inner part envelope,

at least one upstream duct connected to the heat exchanger and opening out via at least one forward-facing first opening positioned outside of the aerodynamic wing inner part envelope and below the inner part, and

at least one downstream duct connected to the heat exchanger and opening out via at least one rearward-facing second opening positioned outside of the aerodynamic wing inner part envelope and above the inner part.