Aircraft doorway
View Patent ↗The invention concerns a doorway in an aircraft fuselage comprising a door frame in which a door is mounted, this frame comprising an outer framework, an inner framework and a core placed between the inner framework and the outer framework, capable of absorbing energy from an impact, the core being a stiffener made of composite material having an accordion shape.
1. A doorway for an aircraft fuselage comprising a door frame inside which a door is mounted, the door frame comprising:
an outer framework,
an inner framework,
a core positioned between the inner framework and the outer framework and adapted to absorb energy from an impact,
wherein the core comprises a stiffener made of composite material having an accordion shape including a succession of V-shaped and inverted V-shapes bellows.
2. The doorway as claimed in claim 1 , wherein each bellows of the accordion-shaped stiffener has a rounded top.
3. The doorway as claimed in claim 1 , wherein the accordion-shaped stiffener is made of a single piece.
4. The doorway as claimed in claim 3 , wherein the accordion-shaped stiffener comprises four accordion-shaped sides connected by crenel-shaped corners.
5. The doorway as claimed in claim 1 , wherein the accordion-shaped stiffener comprises at least two independent stiffener components positioned end to end between the inner and outer frameworks.
6. The doorway as claimed in claim 5 , wherein the accordion-shaped stiffener comprises two vertical stiffener components and two horizontal stiffener components.
7. The doorway as claimed in claim 1 , wherein the stiffener is operably coupled to at least one of the outer framework and/or the inner framework by tops of the bellows.
8. The doorway as claimed in any claim 1 , wherein the composite material contains carbon fibers.
9. An aircraft fuselage, comprising at least one doorway as claimed in claim 1 .
10. An aircraft, comprising at least one doorway as claimed in claim 1 .