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A composite shear tie for connecting a rib in a wing of an aircraft to a skin panel. The shear tie includes a web section having a first edge, a second edge, and a third edge. The web section is formed from a composite material. The first edge is parallel to the second edge, and the web section is c

A composite shear tie for connecting a rib in a wing of an aircraft to a skin panel. The shear tie includes a web section having a first edge, a second edge, and a third edge. The web section is formed from a composite material. The first edge is parallel to the second edge, and the web section is configured to be connected to the rib in the wing of the aircraft. The shear tie also has a first free flange extending from the first edge, wherein the first free flange is around perpendicular to the web section and wherein the first free flange is formed from the composite material. A second free flange is present in the shear tie in which the second free flange extends from the second edge, wherein the second free flange is around perpendicular to the web section and wherein the second free flange is formed from the composite material. The shear tie has a base flange section extending from the third edge, wherein the first base flange is configured for attachment to the skin panel and wherein the first base flange is formed from the composite material.

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What is claimed is: 1. A composite shear tie for connecting a rib in a wing of an aircraft to a skin panel, the composite shear tie comprising: a planar web section formed from a composite material and having first and second opposed sides, a first edge, a second edge opposed to the first edge, and

What is claimed is: 1. A composite shear tie for connecting a rib in a wing of an aircraft to a skin panel, the composite shear tie comprising: a planar web section formed from a composite material and having first and second opposed sides, a first edge, a second edge opposed to the first edge, and a third edge, wherein the first edge is around parallel to the second edge and wherein the planar web section is configured for attachment to the rib in the wing of the aircraft; a first free flange formed from the composite material and extending from the first edge, wherein the first free flange is around perpendicular to the first and second opposed sides of the planar web section and extends in first and second opposed directions from the first and second opposed sides, respectively, of the planar web section; a second free flange formed from the composite material and extending from the second edge, wherein the second free flange is around perpendicular to the first and second opposed sides of the planar web section and extends in the first and second opposed directions from the first and second opposed sides, respectively, of the planar web section; a base section formed from the composite material and extending from the third edge, wherein the base section is configured for attachment to the skin panel; and a groove extending through the planar web section between the first and second opposed edges of the planar web section and through the base section and configured for allowing a stringer to pass through the groove. 2. The composite shear tie of claim 1, wherein the base section extends in the first and second opposed directions from the first and second opposed sides, respectively, of the planar web section. 3. The composite shear tie of claim 1, wherein the planar web section is attached to the rib using a set of web section fasteners extended through the planar web section. 4. The composite shear tie of claim 1, wherein the base section is attached to the skin panel using a set of base section fasteners extended through the base section. 5. The composite shear tie of claim 4, wherein the stringer comprises portions configured to be positioned between the base section and the skin panel, and wherein the set of base section fasteners attach the composite shear tie to both the portions of the stringer and the skin panel. 6. The composite shear tie of claim 1, wherein the composite material is comprised of an epoxy resin and an intermediate modulus fiber. 7. A composite shear tie comprising: a planar section, wherein the planar section is formed from a composite material and is configured for attachment to a rib in a wing of an aircraft; a set of flanges extending from the planar section, wherein each flange of the set of flanges is around perpendicular to first and second opposed sides of the planar section, extends in first and second opposed directions from the first and second opposed sides, respectively, of the planar section, and is formed from the composite material; a base section extending from the planar section, wherein the base section is around perpendicular to the planar section, extends in the first and second opposed directions from the first and second opposed sides, respectively, of the planar section, is formed from the composite material, and is configured for attachment to a skin panel of the aircraft; and a groove extending through the planar section between first and second opposed edges of the planar section and through the base section and configured for allowing a stringer to pass through the groove. 8. The composite shear tie of claim 7, wherein the planar section is configured for attachment to the rib using a set of planar section fasteners extended through the planar section. 9. The composite shear tie of claim 7, wherein the base section is configured for attachment to the skin panel using a set of base section fasteners extended through the base section. 10. The composite shear tie of claim 9, wherein the stringer comprises portions configured to be positioned between the base section and the skin panel, and wherein the set of base section fasteners attach the composite shear tie to both the portions of the stringer and the skin panel. 11. The composite shear tie of claim 7, wherein the composite material is comprised of an epoxy resin and an intermediate modulus fiber. 12. The composite shear tie of claim 7, wherein the set of flanges strengthen the planar section against loads applied by the rib and the skin panel. 13. A method comprising: providing a shear tie comprising a planar section, a set of flanges extending from the planar section, wherein each flange of the set of flanges is around perpendicular to the planar section and extends in first and second opposed directions from first and second opposed sides, respectively, of the planar section, and a base section extending from the planar section, wherein the base section is around perpendicular to the planar section, wherein the planar section, the set of flanges and the base section are formed of a composite material; providing a groove in the shear tie that extends through the planar section between first and second opposed edges of the planar section and through the base section, wherein the groove is configured for allowing a stringer to pass through the groove; fastening the planar section of the shear tie to a rib in a wing of an aircraft; and fastening the base section of the shear tie to a skin panel of the aircraft. 14. The method of claim 13, further comprising: placing portions of the stringer between the base section of the shear tie and the skin panel, wherein fastening the base section of the shear tie to a skin panel of the aircraft comprises fastening the base section of the shear tie to both the portions of the stringer and the skin panel. 15. The method of claim 13, wherein the composite material is comprised of an epoxy resin and an intermediate modulus fiber. 16. The method of claim 13, wherein fastening the planar section of the shear tie to a rib in a wing of an aircraft comprises fastening the planar section of the shear tie to the rib with a set of planar section fasteners extended through the planar section, and wherein fastening the base section of the shear tie to a skin panel of the aircraft comprises fastening the base section of the shear tie to the skin panel with a set of base section fasteners extended through the base section.