The Boeing Company

Brian Timothy Peters

James R Kendall

Byron James Autry

Samuel James Knutson

Santiago M Mejia

Raviendra Sidath Suriyaarachchi

Paul D Shaw

Matthew S Stauffer

Steven P Wanthal

David Raines

Patrick James Macko

Sara Murphy

Samantha Eberhardt

Brian S Carpenter

David H Curry, Iii

Brian Bentley Reid

Michael J Bailey

David M Raines

David H Curry Iii

An apparatus, system, and methods for providing flowable material to a part-forming fixture. The apparatus comprising a tool manifold and a fixture manifold. The tool manifold comprises a tool-manifold base and a plurality of tool fittings extending through the tool-manifold base. The fixture manifold comprises a fixture-manifold base and a plurality of fixture fittings extending through the fixture-manifold base. An interface end of each one of the plurality of tool fittings is removably attachable to an interface end of a corresponding one of the plurality of fixture fittings such that, when attached, a seal is created between the tool fittings and the corresponding fixture fitting and flowable material is flowable from each one of the tool fittings into the corresponding one of the fixture fittings.

Quick connect manifold for flowable material delivery to a part-forming fixture and associated systems and methods

A system to adjust extension lengths of slats of a work platform relative to a workpiece includes sensors to collect first data associated with a position of an outer surface of the workpiece at a height of the slats. The system includes actuators configured to extend or retract the slats. The system also includes a controller coupled to the sensors and to the actuators. The controller is configured to receive the first data and second data associated with rotation of the workpiece. The controller is configured to provide signals to the actuators of the work platform based on the first data and the second data. The signals cause the actuators to adjust or maintain extension lengths of the slats of the work platform to maintain separation distances between ends of the slats and the outer surface of the workpiece within a separation distance range as the workpiece rotates.

System and method to adjust extension lengths of slats of a work platform relative to a workpiece

An apparatus for processing a composite structure includes a mandrel that includes a tooling surface and vacuum bagging that includes an elastomeric membrane and a bagging surface. The apparatus also includes a surface interface formed between the mandrel and the elastomeric membrane. The surface interface includes a suction channel formed in at least one of the tooling surface of the mandrel and the bagging surface of the elastomeric membrane. The elastomeric membrane is configured to be sealed to the mandrel along the suction channel in response to a vacuum applied to the suction channel.

Apparatus and method for processing a composite structure

Systems and methods are provided for splicing airframe components. One embodiment is a method for assembling an airframe of an aircraft. The method includes forming a first skin of a first circumferential section of fuselage, the first skin including a distal portion comprising a lip and a shoulder, aligning a second skin of a second circumferential section of fuselage with the shoulder such that the lip overlaps the second skin, and affixing the first skin and the second skin together via a circumferential splice.

Circumferential lap splices for sections of fuselage

A carrier film set configured to apply a number of stiffener assemblies to a layup mandrel, the carrier film set comprising: a number of alignment features configured to align the carrier film set relative to the layup mandrel; and a number of indexing features configured to index the number of stiffener assemblies onto the carrier film set.

Stiffener assembly application system with carrier film set

A method of fabricating a composite structure is presented. The method comprises laying up a plurality of composite plies over a layup mandrel; positioning a first caul plate and a second caul plate over the plurality of composite plies, leaving composite material exposed; removing at least part of the composite material exposed between the first caul plate and the second caul plate to separate a first composite section from a second composite section; curing the first composite section and the second composite section to form a first composite part and a second composite part; and removing the first composite part and the second composite part from the layup mandrel immediately following curing.

Method of fabricating a composite structure

Growing community of inventors

North Charleston, SC, United States of America

Brian Timothy Peters