Composite structure with integrated hinge
A composite structure with an integrated hinge is disclosed. In various embodiments, the composite structure includes a plurality of layers of fiber reinforced polymer material; and a hinge structure comprising one or more layers of bendably flexible hinge material a first region of which is interleaved between adjacent layers of said layers of fiber reinforced polymer material comprising the composite structure and bonded to said adjacent layers by bonding material comprising said composite structure, and a second region of which extends beyond said layers of fiber reinforced polymer material comprising the composite structure.
1. A composite structure, comprising:
a first composite structure comprising a plurality of layers of fiber reinforced polymer material;
a second composite structure comprising a plurality of layers of fiber reinforced polymer material; and
a hinge structure joining the first composite structure to the second composite structure, wherein:
the hinge structure comprises two or more layers of bendably flexible hinge material, a first region of each of the two or more layers of which is interleaved between adjacent layers of said layers of fiber reinforced polymer material comprising the first composite structure, a second region of each of the two or more layers of which is interleaved between adjacent layers of said layers of fiber reinforced polymer material comprising the second composite structure, and
wherein the hinge structure includes an air gap between at least two of the two or more layers of bendably flexible hinge material.
2. The composite structure of claim 1 , wherein the hinge structure is bendable.
3. The composite structure of claim 1 , wherein the hinge structure comprises a flexible material with a tensile strength greater than the tensile strength of at least one of the first composite structure and the second composite structure.
4. The composite structure of claim 1 , wherein the hinge structure comprises one or more of Kevlar® and another aramid.
5. The composite structure of claim 1 , wherein the hinge structure comprises a material having lower rigidity than the composite structure.
6. The composite structure of claim 1 , wherein layers of fiber reinforced polymer comprise carbon fiber reinforced polymer.
7. The composite structure of claim 1 , wherein the two of more layers of the second region are bonded to the adjacent layers by bonding material comprising said second composite structure and said bonding material comprises a cured resin.
8. The composite structure of claim 1 , wherein the two of more layers of the second region are bonded to the adjacent layers by bonding material comprising said second composite structure and said bonding material comprises epoxy.
9. The composite structure of claim 1 , wherein the second composite structure comprises a flap structure having a free end opposite the hinge material.
10. The composite structure of claim 1 , wherein the number of hinge material layers is fewer than the number of first composite structure layers.
11. The composite structure of claim 1 , wherein the hinge structure is integrally attached to a hinge flap, wherein the hinge flap provides access to a space in an aircraft.
12. The composite structure of claim 11 , wherein the space in an aircraft is configured to store at least one of a servo motor, a power supply, a control circuit, and a connector.
13. The composite structure of claim 11 , wherein the hinge flap is made of the same material as at least one of the first composite structure and the second composite structure.
14. The composite structure of claim 11 , wherein the hinge structure couples the hinge flap to at least one of the first composite structure and the second composite structure.
15. The composite structure of claim 11 , wherein the hinge flap includes a segment of rigid composite material.
16. The composite structure of claim 1 , wherein at least two of the two or more layers of the hinge structure overlap by at least 0.5 inches.
17. The composite structure of claim 1 , wherein at least one layer of the two or more layers of the hinge structure is 0.004 inches thick.
18. The composite structure of claim 1 , wherein the hinged structure is configured to couple a control surface to an airfoil.
19. The composite structure of claim 1 , wherein the hinged structure is configured to flexibly couple and integrate a control surface to an airfoil.
20. The composite structure of claim 1 , wherein the hinged structure is configured to couple a control surface to a trailing edge of an airfoil.