Floor for aircraft

1. A floor for an aircraft, said floor comprising:

a plurality of spars extending substantially parallel to a longitudinal direction (X) of the aircraft;

a plurality of cross-beams assembled to said spars and extending substantially parallel to a transverse direction (Y) of the aircraft;

a plurality of attachment assemblies configured to assemble said floor to a sealed bottom of the aircraft,

wherein said plurality of attachment assemblies comprise a plurality of fasteners,

wherein each one of the plurality of fasteners comprise at least one junction element with two opposite ends, and

wherein each of said two opposite ends are configured to articulate freely about respective axes substantially parallel to said transverse direction (Y);

wherein each one of the plurality of fasteners comprises a first connection element fixed to a primary structure of the floor formed from an assembly of said spars and said cross-beams, and a second connection element configured to be fixed to said sealed bottom, and

wherein each junction element is articulated at one of its two opposite ends to the first connection element, and the other of its two opposite ends is articulated to the second connection element.

2. A floor according to claim 1 , wherein each one of the plurality of fasteners comprises two junction elements.

3. A floor according to claim 1 , wherein each junction element is a shackle.

4. A floor according to claim 3 , wherein each shackle is oriented substantially parallel to a vertical direction (Z) of the aircraft.

5. A floor according to claim 1 ,

wherein said floor is an aircraft cockpit floor, and

said sealed bottom is located in a forward part of said aircraft cockpit floor.

6. A floor according to claim 5 ,

wherein said aircraft cockpit floor comprises a plurality of secondary spars extending substantially parallel to the longitudinal direction (X), said plurality of secondary spars fixed to a forward part of a primary structure of the floor formed from an assembly of said spars and said cross-beams, and

wherein at least one of the plurality of fasteners is fixed to a forward part of each of said secondary spars.

7. A floor according to claim 1 , wherein said spars and said cross-beams include a composite material.

8. A floor according to claim 7 , wherein said spars and said cross-beams include a thermoplastic composite material.

9. A floor according to claim 8 , wherein the thermoplastic composite material includes carbon fibre plies impregnated with PEEK, PEKK or PPS resin.

10. An assembly for an aircraft, comprising:

a sealed bottom; and

a floor according to claim 1 .

11. An assembly according to claim 10 , wherein said sealed bottom is a sealed bottom located in a forward part of a fuselage of the aircraft.

12. An assembly according to claim 10 , wherein said sealed bottom is a sealed bottom located in an aft part of a fuselage of the aircraft.

13. A floor according to claim 1 , wherein said plurality of fasteners are configured to allow free relative movement substantially parallel to the longitudinal direction (X) between the sealed bottom and said floor.

14. A floor according to claim 1 , wherein said plurality of fasteners are configured to resist forces substantially parallel to a vertical direction (Z) applied to said floor, and

wherein said plurality of fasteners are not configured to resist forces substantially parallel to the longitudinal direction (X) applied to said floor.

15. A floor according to claim 1 ,

wherein each one of said plurality of fasteners further comprises a first connection element fixed to the floor and a second connection element configured to be fixed to said sealed bottom,

wherein the at least one junction element comprises two shackles, said two shackles each including a top end and a bottom end,

wherein said two shackles are respectively located on opposite sides of said second connection element,

wherein each top end of said two shackles is hinged to said second connection element and each bottom end of said two shackles is hinged to said first connection element.

16. A floor according to claim 1 ,

wherein each one of said plurality of fasteners further comprises a first connection element fixed to the floor and a second connection element configured to be fixed to said sealed bottom,

wherein the at least one junction element comprises a double shackle, said double shackle including a top end and a bottom end,

wherein the top end of said double shackle is hinged to said second connection element and the bottom end of said double shackle is hinged to said first connection element.

17. A floor according to claim 1 ,

wherein each one of the plurality of fasteners includes a first connection mechanism configured to connect the at least one junction element to said sealed bottom and a second connection mechanism configured to connect the at least one junction element to said floor,

wherein said first connection mechanism is configured to allow the at least one junction element to pivot relative to said sealed bottom about a first axis substantially parallel to the transverse axis (Y), and

wherein said second connection mechanism is configured to allow the at least one junction element to pivot relative to said floor about a second axis substantially parallel to the transverse axis (Y).

18. A floor according to claim 1 , wherein said plurality of fasteners are configured to allow the sealed bottom to deform freely under thermal stresses or during aircraft pressurization phases.

19. A floor according to claim 1 , wherein said plurality of fasteners are configured to prevent a deformation of the sealed bottom under thermal stresses or during aircraft pressurization phases from being transmitted to the floor.