The Boeing Company

David Eric Gideon

Aaron William Bartel

Edward McMurray Fisher, Jr

Mark L Younie

Michael P Kuntz

Eugene A Jackson

David A Vaughan

Marc Rollo Matsen

Randall Dow Wilkerson

Brett Ian Lyons

Bernhard Dopker

Richard R Rosman

Paul B Diep

Ian E Schroeder

Gregg Robert Bogucki

Jamie J Langabeer

Wallace C Chan

Michael H Larson

Josh M Montgomery

Greg M Reyneke

Joshua Paul Koehn

Megan C Kinney

Kin M Ng

Kristin L Hall

Kirk J Malmquist

A co-consolidation tool, including a heating assembly to receive one or more thermoplastic parts and to apply a consolidation temperature to the one or more thermoplastic parts, a pressure bladder to apply a consolidation pressure to the one or more thermoplastic parts, and a support insert shaped and configured to support and at least partially surround at least one of the one or more thermoplastic parts, wherein at least one of heating assembly and the pressure bladder is shaped to receive and support the support insert.

Method and system for co-consolidation of thermoplastic composite material parts

An assembly of thermoplastic parts for forming a final composite part is presented where the assembly includes at least two prefabricated shells fabricated of thermoplastic. Each prefabricated shell has substantially the same shape as the final composite part and where the shapes of the prefabricated shells have dimensions that allow the prefabricated shells to be assembled into a nest for placement into a mold.

Thermoplastic composite part and method of fabrication

In an embodiment of the disclosure, there is provided a method of prototyping a thermoplastic composite part. The method comprises fabricating one or more discardable freeform tooling elements via a rapid manufacturing process. The method further comprises forming thermoplastic composite materials into a thermoplastic composite prototype part using the one or more discardable freeform tooling elements. The method further comprises separating the thermoplastic composite prototype part from the one or more discardable freeform tooling elements.

Methods for forming thermoplastic parts with freeform tooling

A window frame assembly for an aircraft, includes a window frame of composite material, adapted for attachment in a window opening of an aircraft, having an outer flange with an exterior surface and an interior surface, a metal erosion shield attached to the exterior surface of the outer flange, and a polymer adapter ring, attached to the interior surface of the outer flange. The window frame has a substantially constant thickness, and the erosion shield has a substantially constant cross-sectional shape. The adapter ring has a sloped engagement surface configured for supporting a window pane assembly.

Window frame assembly for aircraft

A method of fabricating a reinforced thermoplastic composite part comprises moving a laminate of reinforcing fibers embedded in a thermoplastic matrix for sequential operations through a heating station and then a forming station. The heating station is used to soften the thermoplastic matrix in a portion of the laminate while the forming station is used to impart a geometry to a portion of the laminate whose thermoplastic matrix had just been softened. The softening and the forming are performed simultaneously on different portions of the laminate.

Fabrication of reinforced thermoplastic composite parts

A fiber reinforced part is formed from a compression molded thermoplastic resin reinforced with individual fibers of differing lengths randomly oriented substantially throughout the part.

Compression molding method and reinforced thermoplastic parts molded thereby

Concepts and technologies are disclosed herein for compression molding of composite material quasi-isotropic flakes. According to some embodiments disclosed herein, a first layer formed from a composite component material and a second layer formed from a composite component material are consolidated together to form a quasi-isotropic panel. Composite material flakes having quasi-isotropic properties ('quasi-flakes') are obtained from the quasi-isotropic panel. A compression mold is filled with the quasi-flakes, and heat is applied to the compression mold to form a part.

Compression molding of composite material quasi-isotropic flakes

To an aircraft stringer, a strap is inserted lengthwise through a stringer of an aircraft fuselage, a first end of the strap is secured to a first end of a length of insulation, and the first end of the length of insulation is drawn into a first end of the stringer in response to pulling a second end of the strap.

Tooling for insulating aircraft stringers and method

An apparatus and method for making a mold or mold face includes a container having at least one opening. The apparatus also includes a flexible membrane that is retained to the container that extends across the opening of the container. The apparatus for making a mold further includes support media that is disposed within the container along with a vacuum valve that is connected to the container.

Growing community of inventors

Edmonds, WA, United States of America

David Eric Gideon