Rib element and composite flange for aircraft

1. A rib element for aircraft, which is an elongated support component to be arranged in a space defined by skin plates and edge spars in a wing, guide surface or stabilizer of the aircraft and which comprises:

a first flange and a third flange having outer surfaces which are arrangeable towards the skin plates of a wing, guide surface or stabilizer,

a second flange connected to the first flange and the third flange at first and second corners and at predetermined angles, the first and second corners having rounded inner corners and rounded outer corners between the flanges, the second flange having transverse ends which are arrangeable towards the edge spars of a wing, guide surface or stabilizer,

wherein the rib element is manufactured from a composite material and further comprises a reinforcing component attached to the rib element, the reinforcing component being manufactured in a separate phase with respect to the rib element and arranged in the first corner between the first and second flanges of the rib element to cover at least a part of the inner corner of the first corner and to reinforce the first corner,

wherein the reinforcing component is an elongated plate-like piece provided with a first end and a second end, the second end of the reinforcing component is curved and has a radius of curvature substantially corresponding to a radius of curvature of the inner corner, the reinforcing component is attached to the first flange and arranged such that the curved second end of the reinforcing component resides and terminates against the inner corner of the first corner, and a thickness of the reinforcing component is smaller than the radius of curvature of the inner corner of the first corner.

2. A rib element as claimed in claim 1 , wherein

the first flange comprises at least one attachment point at a distance from the inner corner of the first corner,

the reinforcing component is dimensioned such that the first end resides at a greater distance from the inner corner of the first corner than said attachment point,

and the reinforcing component is attached by an adhesive against an inner surface of the first flange, the reinforcing component being arranged to receive shear forces to which the attachment point is subjected and to support the first corner.

3. A rib element as claimed in claim 1 , wherein a thickness of the reinforcing component decreases toward the second end.

4. A rib element as claimed in claim 3 , wherein the thickness of the reinforcing component decreases to form a curved surface which substantially follows the curvature of the inner corner of the composite structure.

5. An aircraft composite structure comprising:

a first flange for supporting a load thereon and a second flange, each having one free edge and being connected to each other at a corner at an angle, the corner having a rounded inner corner and a rounded outer corner between the flanges,

and wherein the composite structure is manufactured at least mainly from at least one polymeric binder and at least one reinforcing fiber,

and further comprises a reinforcing component manufactured in a separate phase with respect to the composite structure, the reinforcing component being attached to the composite structure, and arranged to cover at least a part of the inner corner of the composite structure and to reinforce the corner of the composite structure,

wherein the reinforcing component is an elongated plate-like piece having a first end and a second end, the second end of the reinforcing component is curved and has a radius of curvature substantially corresponding to a radius of curvature of the inner corner of the composite structure, and the reinforcing component is attached to the first flange and arranged so that the second end of the reinforcing component resides and terminates against the inner corner of the composite structure.

6. A composite flange as claimed in claim 5 , wherein the reinforcing component is made of a composite comprising at least one polymeric binder and at least one reinforcing fiber.

7. A composite flange as claimed in claim 5 , wherein the reinforcing component is attached by an adhesive to the composite structure.

8. A composite flange as claimed in claim 5 , wherein the first flange comprises at least one attachment point, and the reinforcing component is dimensioned to extend from the corner at least as far as to said attachment point.

9. A composite structure as claimed in claim 5 , wherein a thickness of the reinforcing component decreases toward the second end.

10. A composite structure as claimed in claim 9 , wherein the thickness of the reinforcing component decreases to form a curved surface which substantially follows the curvature of the inner corner of the composite structure.

11. An aircraft support structure made of a composite material, the support structuring comprising:

a first flange for supporting a load thereon,

a second flange connected to the first flange at an angle forming a corner between the first and second flanges,

a reinforcing component secured to the first flange, the reinforcing component extending from the first flange to the corner between the first and second flanges,

wherein the reinforcing component has a curved end having a decreasing thickness, the curved end of the reinforcing component being shaped to follow a curvature of the corner between the first and second flanges.