Abstract: The present invention provides an automated mandrel clamping and indexing mechanism for a multi-piece AFP mandrel wherein a clamping mechanism is used in order to secure mandrel segments together as well as to join mandrel segments to end rings. The clamping mechanism is preferably integrated with an indexing mechanism according to embodiments of the present invention such that mandrel segments will preferably remain securely connected and aligned until air is applied to the clamping and indexing mechanism in order to unclamp the secured mandrel segments and remove the part being manufactured. The clamping and indexing mechanism preferably withstands the autoclave heat and pressure that is typically experienced during the curing part of the manufacturing process.

Abstract: The present invention is directed to the incorporation of a substructure into tooling for constructing composite structures in order to control thermal expansion of the tooling during aerospace manufacturing processes. Substructure, such as headers and/or gussets is added to the tooling to constrain the growth of the laminate expansion and/or control the diametric growth of the tool during the curing cycle. The thickness of the face-sheet of the tooling also may be reduced in order to further reduce the effective coefficient of thermal expansion (CTE) of the tooling.