Composite reinforcement structures and aircraft assemblies comprising composite reinforcement structures

1. A composite reinforcement structure comprising:

a first skin having a first end and a second end;

a second skin having a first end and a second end, wherein the first end of the first skin and the first end of the second skin are coupled;

a corrugated spar disposed between the first skin and the second skin and bonded to the first skin and the second skin; and

a forward skin having a first end, a second end, and a forward skin wall interposed between the first end and the second end, wherein the first end of the forward skin is coupled to the second end of the first skin and the second end of the forward skin is coupled to the second end of the second skin, and wherein the corrugated spar is bonded to a portion of the forward skin wall.

2. The composite reinforcement structure of claim 1 , wherein the first end of the first skin and the first end of the second skin are integral.

3. The composite reinforcement structure of claim 1 , wherein the first end of the first skin and the first end of the second skin are bonded together.

4. The composite reinforcement structure of claim 1 , wherein the corrugated spar extends from a first side of the first skin to a second side of the first skin.

5. The composite reinforcement structure of claim 1 , wherein the corrugated spar comprises:

a first wall; and

a second wall that is adjacent to and integral with the first wall.

6. The composite reinforcement structure of claim 1 , wherein the first end of the forward skin is bonded to the first skin.

7. The composite reinforcement structure of claim 1 , wherein the second end of the forward skin is bonded to the second skin.

8. A composite reinforcement structure comprising:

a first skin having a first end and a second end;

a second skin having a first end and a second end, wherein the first end of the first skin and the first end of the second skin are coupled;

a forward skin separating the second end of the first skin and the second end of the second skin;

a first wall extending between the first skin and the second skin; and

a second wall extending between the first skin and the second skin, wherein the second wall is adjacent to and integral with the first wall, wherein the forward skin has a first end, a second end, and a forward skin wall interposed between the first end and the second end, wherein the first end of the forward skin is coupled to the second end of the first skin and the second end of the forward skin is coupled to the second end of the second skin, wherein the first end of the forward skin is bonded to the first skin, wherein the second wall extends from the first skin to the forward skin wall and is integral with a third wall, and wherein the third wall is bonded to a portion of the forward skin wall and is bonded to and sandwiched between the second end of the forward skin and the second skin.

9. The composite reinforcement structure of claim 8 , wherein the first end of the first skin and the first end of the second skin are integral.

10. The composite reinforcement structure of claim 8 , wherein the first end of the first skin and the first end of the second skin are bonded together.

11. The composite reinforcement structure of claim 8 , wherein the second end of the forward skin is bonded to the second skin, wherein the second wall extends to the forward skin wall, is bonded to the first skin and is integral with a third wall, and wherein the third wall is bonded to and sandwiched between the first end of the forward skin and the first skin.

12. An aircraft assembly comprising:

a fixed lifting surface;

a composite reinforcement structure comprising:

a first skin having a first end and a second end;

a second skin having a first end and a second end, wherein the first end of the first skin and the first end of the second skin are coupled; and

a corrugated spar disposed between the first skin and the second skin and bonded to the first skin and the second skin;

a forward skin having a first end, a second end, and a forward skin wall interposed between the first end and the second end, wherein the first end of the forward skin is coupled to the second end of the first skin and the second end of the forward skin is coupled to the second end of the second skin, and wherein the corrugated spar is bonded to a portion of the forward skin wall; and

a plurality of fittings connecting the composite reinforcement structure to the fixed lifting surface.

13. The aircraft assembly of claim 12 , wherein the fixed lifting surface is a wing of an aircraft.

14. The aircraft assembly of claim 12 , wherein the composite reinforcement structure is an aileron of an aircraft.

15. The aircraft assembly of claim 12 , wherein the corrugated spar comprises:

a first wall; and

a second wall that is adjacent to and integral with the first wall.

16. The aircraft assembly of claim 12 , wherein the plurality of fittings include fittings selected from hinges, mechanical actuators, electrical actuators, and hydraulic actuators.