Aircraft panel

1 . An aircraft panel having an upper surface and a lower surface, comprising:

an inner ply of composite material having a free end,

wherein the inner ply of composite material is curved around an axis such that the free end of the ply extends more than 180 degrees around the axis defining a wall of an elongated channel opening along the axis and for receiving a hinge member of an aircraft component,

at least one continuously extending surrounding outer ply of composite material in a laminated arrangement with the inner ply of composite material,

wherein the at least one continuously extending surrounding outer ply forms

the upper surface of the panel,

a transition portion,

a curved portion that curves around the axis and continuously extends to the transition portion,

wherein the transition portion extends to the lower surface of the panel, and

wherein the outer ply extends longitudinally along an entire length of the lower surface of the panel.

2 . The aircraft panel of claim 1 , wherein the upper surface extends in a direction orthogonal to the axis.

3 . The aircraft panel of claim 1 , wherein the channel is defined at an edge of the aircraft panel.

4 . The aircraft panel of claim 1 , wherein the inner ply of composite material is curved around the axis such that the free end extends at least 270 degrees around the axis.

5 . The aircraft panel of claim 1 , wherein the free end of the at least one continuously extending surrounding outer ply extends more than 180 degrees around the axis.

6 . The aircraft panel of claim 1 , wherein the at least one continuously extending surrounding outer ply has a length in a direction orthogonal to the axis, and the ply is longer than the at least one continuously extending surrounding outer ply in the direction orthogonal to the axis.

7 . The aircraft panel of claim 1 , wherein the free end of the inner ply comprises cut-outs such that the channel comprises discrete channel elements spaced apart along the axis.

8 . The aircraft panel of claim 1 , wherein the inner ply of composite material comprises fibres aligned in a direction of curvature of the ply around the axis.

9 . An aircraft assembly comprising:

the aircraft panel of claim 1 ; and

the aircraft component comprising the hinge member,

wherein the hinge member is located in the channel to connect the aircraft component to the aircraft panel.

10 . An aircraft wing comprising the aircraft panel of claim 1 , wherein the aircraft panel forms an aerodynamic surface of the wing.

11 . An aircraft comprising the aircraft assembly of claim 9 .

12 . A method of manufacturing an aircraft panel having an upper surface and a lower surface, the method comprising;

providing a inner ply of composite material; and

curving the inner ply of composite material around an axis such that a free end of the inner ply extends more than 180 degrees around the axis and defines a wall of a channel for receiving a hinge member of an aircraft component,

providing an at least one continuously extending surrounding outer ply in a laminated arrangement with the inner ply;

curving the at least one continuously extending surrounding outer ply around the axis so that the at least one continuously extending surrounding outer ply comprises

the upper surface of the panel,

a transition portion,

a curved portion that curves around the axis and continuously extends to the transition portion,

wherein the transition portion extends to a the lower surface of the panel, and

wherein the outer ply extends longitudinally along an entire length of the lower surface of the panel.

13 . The method of claim 12 , further comprising providing a wedge to separate the at least one continuously extending surrounding inner ply from the ply as the at least one continuously extending surrounding outer ply is curved around the axis.

14 . The method of claim 12 , comprising removing material from the inner ply to form a plurality of channel elements spaced apart along the axis.

15 . An aircraft panel manufactured according to the method of claim 12 .