Abstract: Systems and methods are provided for splicing airframe components. One embodiment is a method for assembling an airframe of an aircraft. The method includes forming a first skin of a first circumferential section of fuselage, the first skin including a distal portion comprising a lip and a shoulder, aligning a second skin of a second circumferential section of fuselage with the shoulder such that the lip overlaps the second skin, and affixing the first skin and the second skin together via a circumferential splice.

Abstract: An apparatus, system, and methods for providing flowable material to a part-forming fixture. The apparatus comprising a tool manifold and a fixture manifold. The tool manifold comprises a tool-manifold base and a plurality of tool fittings extending through the tool-manifold base. The fixture manifold comprises a fixture-manifold base and a plurality of fixture fittings extending through the fixture-manifold base. An interface end of each one of the plurality of tool fittings is removably attachable to an interface end of a corresponding one of the plurality of fixture fittings such that, when attached, a seal is created between the tool fittings and the corresponding fixture fitting and flowable material is flowable from each one of the tool fittings into the corresponding one of the fixture fittings.

Abstract: An apparatus for processing a composite structure includes a mandrel that includes a tooling surface and vacuum bagging that includes an elastomeric membrane and a bagging surface. The apparatus also includes a surface interface formed between the mandrel and the elastomeric membrane. The surface interface includes a suction channel formed in at least one of the tooling surface of the mandrel and the bagging surface of the elastomeric membrane. The elastomeric membrane is configured to be sealed to the mandrel along the suction channel in response to a vacuum applied to the suction channel.

Abstract: Systems and methods are provided for splicing airframe components. One embodiment is a method for assembling an airframe of an aircraft. The method includes forming a first skin of a first circumferential section of fuselage, the first skin including a distal portion comprising a lip and a shoulder, aligning a second skin of a second circumferential section of fuselage with the shoulder such that the lip overlaps the second skin, and affixing the first skin and the second skin together via a circumferential splice.