The Boeing Company
Internal tooling for composite parts

Abstract:

Systems and methods are provided for composite part fabrication. One embodiment is a method for fabricating a composite part. The method includes selecting a tool with sides made of a core material in a desired size and shape, disposing a preform of a fiber reinforced material that surrounds the tool, resulting in a lamina assembly comprising the preform and the tool, heating the tool and the preform, co-bonding the tool to the fiber reinforced material within the lamina assembly, and hardening the preform and the tool into a hybrid composite part.