AIRCRAFT FUSELAGE MADE FROM LONGITUDINAL PANELS AND METHOD OF PRODUCING SUCH A FUSELAGE
The invention relates to an aircraft fuselage comprising a nose cone, a tail section and a central section, the central section comprising longitudinal panels assembled directly with one another, at least one of these longitudinal panels having a length corresponding to the distance between the nose cone and the tail section in order to connect said nose cone with said tail section.
1 . An aircraft fuselage comprising:
a nose cone;
a tail section; and
a central section comprising longitudinal panels made of composite materials and assembled directly with one another by longitudinal joints, at least one longitudinal panel having a length corresponding to a distance between the nose cone and the tail section to couple the nose cone with the tail section.
2 . The aircraft fuselage as claimed in claim 1 , wherein direct assembly of a first longitudinal panel with a second longitudinal panel includes a partial superimposition of the first and the second longitudinal panels and fasteners passing through the first and second longitudinal panels.
3 . The aircraft fuselage as claimed in claim 1 , wherein direct assembly of a first longitudinal panel with a second longitudinal panel includes a juxtaposition of the first and second longitudinal panels with an internal lining.
4 . The aircraft fuselage as claimed in claim 1 , wherein at least one longitudinal panel has a length corresponding to a distance between the nose cone and a central wing box of an aircraft.
5 . The aircraft fuselage as claimed in claim 1 , wherein at least one longitudinal panel has a length corresponding to a distance between a central wing box and the tail section.
6 . The aircraft fuselage as claimed in claim 1 , wherein at least one longitudinal panel has a length corresponding to a width of a central wing box.
7 . The aircraft fuselage as claimed in claim 1 , wherein at least one longitudinal panel comprises at least one of a stiffening sub-structure or a floor structure.
8 . The aircraft fuselage as claimed in claim 1 , wherein at least one longitudinal panel comprises skin reinforcements.
9 . The aircraft fuselage as claimed in claim 1 , wherein at least one longitudinal panel corresponds to a single curvature area of the fuselage.
10 . The aircraft fuselage as claimed in claim 1 , wherein at least one longitudinal panel corresponds to a double curvature area of the fuselage.
11 . A method for producing an aircraft fuselage including a nose cone, a tail section and a central section of an aircraft, wherein producing the central section comprises:
producing longitudinal panels of composite materials, at least one of the longitudinal panels having a length corresponding to a distance between the nose cone and the tail section; and
assembling the longitudinal panels directly with one another by longitudinal joints.
12 . The method as claimed in claim 11 , wherein direct assembly of a first longitudinal panel with a second longitudinal panel comprises partially superimposing the first and the second longitudinal panels and attaching the first and second longitudinal panels by fasteners.
13 . The method as claimed in claim 11 , wherein direct assembly of a first longitudinal panel with a second longitudinal panel comprises juxtaposing the first and second longitudinal panels with an internal lining.
14 . An aircraft comprising:
a fuselage comprising
a nose cone;
a tail section; and
a central section comprising longitudinal panels made of composite materials and assembled directly with one another by longitudinal joints, at least one longitudinal panel having a length corresponding to a distance between the nose cone and the tail section to couple the nose cone with the tail section.
15 . An aircraft comprising:
a fuselage comprising a nose cone, a tail section, and a central section, the central section produced by producing longitudinal panels of composite materials, at least one of the longitudinal panels having a length corresponding to a distance between the nose cone and the tail section, and assembling the longitudinal panels directly with one another by longitudinal joints.