Aircraft fuselage configured to offer the passengers a totally panoramic view of the outside

1. An aircraft fuselage comprising:

an element forming a skin; and

a load-carrying structure supporting said element forming the skin, said load-carrying structure comprising:

a plurality of elements forming a spar disposed parallel to an axial direction defined by the fuselage; and

a plurality of elements forming a frame spaced apart along said axial direction, each element forming the frame being arranged substantially perpendicularly to said elements forming the spar, wherein the element forming the skin is fastened on an external perimeter of each element forming the frame by fastening elements and wherein the element forming the skin is made of a transparent material;

wherein each element forming the frame have a substantially polygonal shape including several vertices; and

wherein each fastening element comprises a tubular body comprising:

a first end secured to one of the plurality of elements forming the frame at one of the vertices of one of said elements forming the frame; and

a second end provided with an inner thread into which a bolt provided with a threaded rod and with a head is screwed, said bolt crossing an opening formed in the element forming the skin at a level of its threaded rod and bearing on an outer face of said element forming the skin at a level of its head.

2. The aircraft fuselage according to claim 1 , wherein the load-carrying structure comprises a plurality of crown-shaped sections, each of said plurality of crown-shaped sections being formed by at least two adjacent elements forming the frame, linked together by a plurality of triangle-shaped junction elements, each junction element having two ends each secured to one of said elements forming the frame and a third end secured to an intermediate frame disposed coaxially with at least two adjacent elements forming the frame.

3. The aircraft fuselage according to claim 2 , wherein the element forming the skin comprises an envelope over which several movable portions forming access doors are linked by hinge elements.

4. The aircraft fuselage according to claim 3 , wherein each movable portion is positioned between two adjacent crown-shaped sections along the axial direction.

5. The aircraft fuselage according to claim 1 , wherein the load-carrying structure is formed by an assembly of substantially straight tubes linked together at a level of their respective ends, said assembly forming a lattice structure.

6. The aircraft fuselage according to claim 5 , wherein the assembly of substantially straight tubes of the load-carrying structure are made of a material selected from the group consisting of aluminum, titanium, and a carbon-fiber reinforced composite material.

7. The aircraft fuselage according to claim 5 , wherein the assembly of substantially straight tubes of the load-carrying structure are externally coated with a black-color varnish or paint layer, said layer preventing a reflection of light in a direction of the element forming the skin.

8. The aircraft fuselage according to claim 1 , wherein the element forming the skin is made of an acrylic material.

9. An aircraft comprising the aircraft fuselage according to claim 1 .

10. The aircraft according to claim 9 , wherein the aircraft comprises a pair of front wings and a pair of rear wings being contiguous and aligned in a plane parallel to the axial direction defined by the fuselage.

11. The aircraft according to claim 10 , wherein the front wings are disposed above a front end of the fuselage, and the pair of rear wings are disposed above an end of the fuselage.