Abstract: A system and method for fabricating large composite fuselages or other vehicle structures, in which the composite structure is fabricated and cured as on a tool, segmented and removed from the tool without disassembling the tool, and then reassembled off the tool to reform the large structure. The tool includes mandrel segments attached to a substructure. The attachments may be moveable to accommodate differential expansion and contraction during curing, and the tool may be rotatable to facilitate access. A composite material of resin and synthetic fibers is applied over the mandrel segments to fabricate the structure on the tool. Caul plates are secured over the composite material, and the composite material is cured on the tool. The resulting structure is cut into part segments which are then removed from the tool, and the part segments are joined to reassemble the large composite structure off the tool.

Abstract: A system and method for splicing multiple plies of material together during the construction of a stringer sheet. A first ply layer is laid onto a portion of a surface of a tool having a contour which defines a stringer, and the first ply layer is pressed down such that an edge of the first ply layer is located on the contour. A second ply layer is laid onto an adjacent portion of the surface, and the second ply layer is pressed down such that the edge of the second ply layer is located on the contour and overlaps the edge of the first ply layer. This process may be repeated for additional ply layers. The system may include an end-effector having a dispenser of the plies of material and a roller for pressing the plies, and a movement mechanism for moving the end-effector over the tool.

Abstract: A system and method for fabricating large composite fuselages or other vehicle structures, in which the composite structure is fabricated and cured as on a tool, segmented and removed from the tool without disassembling the tool, and then reassembled off the tool to reform the large structure. The tool includes mandrel segments attached to a substructure. The attachments may be moveable to accommodate differential expansion and contraction during curing, and the tool may be rotatable to facilitate access. A composite material of resin and synthetic fibers is applied over the mandrel segments to fabricate the structure on the tool. Caul plates are secured over the composite material, and the composite material is cured on the tool. The resulting structure is cut into part segments which are then removed from the tool, and the part segments are joined to reassemble the large composite structure off the tool.

Abstract: An aircraft panel assembly including a panel, a number of open-ended composite stringers, and a number of stringer end caps. Each stringer end cap covers an open end of one of the stringers and includes a base, a vertically extending wall, and an overlap section. The base is bonded to the panel near the open end of the stringer. The vertically extending wall is angled upward from the base and includes an upper periphery. The overlap section extends horizontally from the upper periphery and is bonded to the stringer near the open end of the stringer.

Abstract: A system and method for splicing multiple plies of material together during the construction of a stringer sheet. A first ply layer is laid onto a portion of a surface of a tool having a contour which defines a stringer, and the first ply layer is pressed down such that an edge of the first ply layer is located on the contour. A second ply layer is laid onto an adjacent portion of the surface, and the second ply layer is pressed down such that the edge of the second ply layer is located on the contour and overlaps the edge of the first ply layer. This process may be repeated for additional ply layers. The system may include an end-effector having a dispenser of the plies of material and a roller for pressing the plies, and a movement mechanism for moving the end-effector over the tool.

Abstract: A panel structure, for an aircraft fuselage or wing, including a skin component and a stringer sheet component which are independently constructed and then subsequently integrated to form the panel structure. The skin is constructed and consolidated in a first process, and the stringer sheet is constructed and consolidated in a second process which is independent of the first process. Because the skin and stringer sheet are independently constructed, they may, with less compromise, be constructed with the same or different materials, using the same or different techniques, and at the same or different times to optimize each component. The stringers form cavities, and the cavities may be unfilled or filled with material. The skin and stringer sheet are bonded together in a third process, which is independent of the first and second processes. A frame component may be attached to the panel structure in a fourth process.