Aircraft fuselage portion in composite material including ply drop-off with gentle slope
OwnerPhilippe Bernadet, Romain Delahayeinventors
Life of this patent
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Abstract
In a fuselage portion for an aircraft, in order to reduce the assembly clearance between the soleplate of a circumferential frame and a fuselage skin in composite material while limiting the mass of the fuselage portion, a ply drop-off is used comprising two portions oriented in the circumferential direction and having different respective slopes.
Claims10
A fuselage portion formed of composite material for an aircraft, comprising:
- a fuselage skin comprising at least two regions of constant thickness having different thicknesses, comprising
- a first region of greater constant thickness, and
- a second region of lesser constant thickness, said regions being connected to one another by a first ply drop-off,
- said first ply drop-off comprising at least two portions having different slopes each oriented in a circumferential direction orthogonal to a longitudinal direction of said fuselage portion, comprising
- a first portion having a greater slope and
- a second portion having a lesser slope,
- the first and second portions being arranged on one and the same circumferential side relative to the first region.
A forward section of an aircraft comprising a fuselage portion formed of composite material, comprising:
- a fuselage skin comprising at least two regions of constant thickness having different thicknesses, comprising
- a first region of greater constant thickness, and
- a second region of lesser constant thickness, said regions being connected to one another by a first ply drop-off,
- said first ply drop-off comprising at least two portions having different slopes each oriented in a circumferential direction orthogonal to a longitudinal direction of said fuselage portion, comprising
- a first portion having a greater slope and
- a second portion having a lesser slope,
- the first and second portions being arranged on one and the same circumferential side relative to the first region.
An aircraft comprising a forward section comprising a fuselage portion formed of composite material, comprising:
- a fuselage skin comprising at least two regions of constant thickness having different thicknesses, comprising
- a first region of greater constant thickness, and
- a second region of lesser constant thickness, said regions being connected to one another by a first ply drop-off,
- said first ply drop-off comprising at least two portions having different slopes each oriented in a circumferential direction orthogonal to a longitudinal direction of said fuselage portion, comprising
- a first portion having a greater slope and
- a second portion having a lesser slope,
- the first and second portions being arranged on one and the same circumferential side relative to the first region.
Dependencies are inferred from the claim text.