The Boeing Company

Richard E Heath, Iii

Richard Alexander Prause

Andrew Elmer Modin

Allen James Halbritter

Eileen E Miller

Ivan Gilberto Ramirez

John R Nibe

An example method of forming a composite structure includes applying a laminated charge onto an expandable pallet, moving the expandable pallet in a linear motion relative to a plurality of rollers, and progressively urging the laminated charge into a continuously expanding recess defined by the expandable pallet using the plurality of rollers. The plurality of rollers are oriented in a serial configuration so as to shape the laminated charge into at least part of a shape of the composite structure.

Methods, devices, and systems for forming a composite structure using an expandable pallet

An example mandrel for processing a part is described including a plurality of elastomeric components aligned end to end and spaced apart linearly to form a segmented mandrel body, and compressible interconnections positioned within spacing between adjacent elastomeric components and abutting the adjacent elastomeric components. The compressible interconnections allow the plurality of elastomeric components to expand axially due to thermal expansion resulting in a distribution of pressure. An example method for fabricating a composite part is also described including placing a base composite layer into a cavity of a tooling surface, inserting a mandrel into the cavity of the tooling surface such that the base composite layer is between the mandrel and the tooling surface, applying a skin to the mandrel and the base composite layer forming a package, enclosing the package in a vacuum bag and curing, and removing the mandrel from the cavity of the tooling surface.

Multi-segment mandrel for processing a composite part and method for fabricating a composite part

An example mandrel for processing a part is described including an inner core having a material with first thermal properties, and an outer layer surrounding the inner core. The outer layer includes a material with second thermal properties different than the first thermal properties to enable uniform pressure distribution within the mandrel. An example method for fabricating a composite part is described including placing a base composite layer into a cavity of a tooling surface, inserting a mandrel into the cavity, applying a skin to the mandrel and the base composite layer forming a package, enclosing the package in a vacuum bag and curing the base composite layer and the skin such that during curing a pressure due to thermal expansion of one of the inner core and the outer layer is distributed by the other, and removing the mandrel from the cavity of the tooling surface following the curing.

Multi-component mandrel for processing a composite part and method for fabricating a composite part

A mandrel for processing a part is described that includes a solid mandrel body with an elastomeric material, and hollow micro-particles embedded within the solid mandrel body in a uniform distribution. The hollow micro-particles deform in response to a change in a processing environment resulting in a distribution of voids in the solid mandrel body. A method for fabricating a composite part is also described that includes placing a base composite layer into a cavity of a tooling surface, inserting the mandrel into the cavity, applying a skin to the mandrel and the base composite layer forming a package, enclosing the package in a vacuum bag and curing the base composite layer and the skin such that during curing the hollow micro-particles deform resulting in the distribution of voids in the solid mandrel body, and removing the mandrel from the cavity of the tooling surface following the curing.

Mandrel for processing a composite part and method for fabricating a composite part

An example apparatus for fabrication of a co-cured composite assembly includes a layup tool body with a cavity, a thermal expansion insert inserted into the cavity of the layup tool body and a first uncured composite part of the composite assembly is positioned onto the thermal expansion insert, and a solid internal mandrel configured for insertion onto the first uncured composite part. During curing, the first uncured composite part compacts and reduces in thickness while the solid internal mandrel and the thermal expansion insert each increase in size to apply pressure to the first uncured composite part.

Growing community of inventors

Chicago, IL, United States of America

Richard E Heath, Iii