Abstract: A splice and an associated method are provided in order to efficiently join structures, such as adjacent fuselage sections. A splice for joining fuselage sections may include a strap configured to bridge the fuselage sections, a shear tie overlying the strap and a fitting positioned between the strap and the shear tie such that the strap and the shear tie are spaced apart. At least the strap and the fitting may be formed of a composite material. The fitting may have an H-shape and may have first and second longitudinally extending sections that extend beyond opposite sides of the strap. Each longitudinally extending section is configured to overlie at least two stringers of a respective fuselage section. The fitting may also have a medial portion upon which the shear tie is seated.

Abstract: This disclosure is directed to a boron reinforced composite structural member. The concepts and technologies illustrated in this disclosure are taught within the context of a boron reinforced aircraft keel. A boron reinforced composite structural member may be constructed of a structural member core and a surrounding structural member casing. In one embodiment, the structural member core includes alternating layers of boron fiber reinforced plies and layers of interior carbon fiber reinforced plies. The boron fiber reinforced plies are oriented in a longitudinal direction, and the interior carbon fiber reinforced plies are oriented diagonally, perpendicular, and parallel to the boron fiber reinforced plies. The structural member casing includes layers of exterior carbon fiber reinforced plies that substantially surround the structural member core.

Abstract: A splice and an associated method are provided in order to efficiently join structures, such as adjacent fuselage sections. A splice for joining fuselage sections may include a strap configured to bridge the fuselage sections, a shear tie overlying the strap and a fitting positioned between the strap and the shear tie such that the strap and the shear tie are spaced apart. At least the strap and the fitting may be formed of a composite material. The fitting may have an H-shape and may have first and second longitudinally extending sections that extend beyond opposite sides of the strap. Each longitudinally extending section is configured to overlie at least two stringers of a respective fuselage section. The fitting may also have a medial portion upon which the shear tie is seated.