Aircraft Skin Attachment System

摘要

A method for forming a structural member and a structural member produced thereby includes positioning a first composite section and a second composite section within a tool. The tool has an inner surface and a wall intersection and is supported by a tool platform. The tool platform and a pressure platform are relatively movable between an open position and a closed position. The tool has a non-planar outer surface against which the member may be pressed. A composite splice member is positioned at least partially overlapping both the first composite section and the second composite section to form a joint in the composite structural member. The composite structural member is pressed against the non-planar outer surface of the tool by applying pressure to the joint from a pressure bladder. Heat is applied to the composite structural member at the joint to cure the composite splice member to the first composite section and the second composite section.

主权项

1. A method for producing a composite structural member, comprising:
positioning a first composite section and a second composite section within a tool, the tool being supported by a tool platform and having an inner surface and a wall intersection, the tool platform and a pressure platform relatively movable between an open position and a closed position; the tool having a non-planar outer surface against which the composite structural member may be pressed; positioning a composite splice member at least partially overlapping both the first composite section and the second composite section to form a joint in the composite structural member; pressing the composite structural member against the non-planar outer surface of the tool by applying pressure to the joint from a pressure bladder; applying heat to the composite structural member at the joint to cure the composite splice member to the first composite section and the second composite section.