The Boeing Company

Mark L Younie

Matthew K Lum

Michael P Kuntz

Walter Forrest Frantz

Daniel James Kovach

David Eric Gideon

Eugene A Jackson

Bryan K Bergsma

Denis J Klein

David A Vaughan

Albert E Seifert

James T Nishimura

Harvey T Jones

Thomas J Courrier

Joseph P Canavan

Jeffrey C Bower

Gary E Georgeson

Douglas Alan McCarville

Joshua M Montgomery

Salvatore L Liguore

John S Howitt, Jr

Robert G Rackl

Matthew K S Lum

Robert G Shaw, Ii

Robert G Shaw

A molding apparatus comprises an upper molding box, a lower mold box, an upper flexible membrane covering an opening of the upper mold box, a lower flexible membrane covering an opening of the lower mold box, a heating system located in the upper mold box, a set of ports located between the upper flexible membrane and the lower flexible membrane capable of being used to draw a vacuum between the upper flexible membrane and the lower flexible membrane, and a displacement system located in the lower mold box under the lower flexible membrane.

Flexible tooling method and apparatus

Methods and computer storage media provide for the installation of potted inserts and installation validation. According to embodiments described herein, an insert is placed within an insert aperture of a panel or other structure. Potting compound is injected into a potting cavity surrounding the insert through a fill hole in the insert until potting compound overflows from another fill hole. The installation is validated by applying a force to the installed insert at a determined frequency using a mechanical impedance instrument and measuring a response frequency. The response frequency is compared to an acceptable frequency range to determine whether the insert is properly installed.

Potted insert installation and validation

There are provided apparatuses and related methods for preforming sheets to form preforms for forming ducts. The preforms can be formed of a thermoplastic material, such as flat sheets of reinforced thermoplastic, which can be lightweight, strong, and perform well in flammability, smoke, and toxicity tests. The apparatus includes a heater for heating the sheet to a processing temperature and a structure for configuring the sheet to a desired shape of the duct. For example, rollers, rods, tubes, or a funnel can be used to bend the sheet.

Preforming thermoplastic ducts

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.

Molding apparatus and method

There is provided an apparatus and method for consolidation joining a thermoplastic preform to form a duct. The apparatus includes first and second longitudinally extending support structures. The first support structure at least partially defines a cavity for supporting the preform in a desired configuration of the duct. The second support structure extends in the cavity such that the preform can be supported between the first and second support structures. The second support structures can include an elastomeric device that is configured to adjust radially and urge the interface of the preform against the first support structure. A heater is configured to heat an interface of the preform to above a glass transition temperature. The resulting duct is has a longitudinal consolidation joint and defines a passage.

Consolidation joining of thermoplastic laminate ducts

In accordance with the present invention an aircraft floor panel is provided comprising a honeycomb core element having an upper core surface, a lower core surface, and a core thickness. An upper face sheet assembly is mounted to and seals the upper core surface and includes at least one upper material sheet impregnated with an upper epoxy resin. A lower damping face sheet assembly is mounted to and seals the lower core surface and includes at least one lower material sheet infused with a highly damped lower epoxy resin. The lower damping face sheet assembly dampens vibrational noise.

Integrally damped composite aircraft floor panels

An apparatus and method are provided for thermoplastically forming a contour in a thermoplastic duct defining a passage. The apparatus includes a longitudinal collar that defines a cavity and a rigid inner support structure extending longitudinally in the cavity. The collar and/or the inner support structure define a mold contour. One or more heaters are configured to heat at least a formation portion of the duct to a formation temperature. An expansion member, such as an expandable elastomer, which is disposed between an inner surface of the collar and an outer surface of the inner support structure, is configured to urge the formation portion of the duct against the mold contour to thermoplastically form the duct.

Post-forming of thermoplastic ducts

An apparatus and method are provided for circumferentially measuring cross-sectional characteristics of a tubular member. The apparatus includes first and second template members that cooperably define an aperture for receiving the tubular member. At least one of the template members is adjustable so that the aperture can be adjusted between open and closed positions. A measurement device can be configured to detect the relative position of the first and second template members, thereby measuring the relative adjustment of the members between the open and closed positions. This measurement is indicative of the cross-sectional size of the tubular member, e.g., for determining the diameter of the tubular member. Alternatively, multiple measurement devices can respond to a contact force between the measurement devices and the tubular member, e.g., to determine a variation in wall thickness of the tubular member.

Circumferential measurement of tubular members

A method and tooling concept for fabricating complex composite parts is provided. The method and tooling concept use various tooling configurations in order to produce varying magnitudes of thermal expansion at different areas within the tooling concept. The varying magnitudes of thermal expansion allow the tool concept to account for varying magnitudes of tool movement needed to debulk and consolidate varying thickness areas of the composite workpiece being cured. The tooling concept is formed of different materials having different thicknesses that allow the tooling concept to produce varying magnitudes of thermal expansion. The exterior surface of the tooling concept is covered by a compliant covering. The compliant covering helps to equalize the consolidation pressures produced by the tooling concept during curing. A composite wing box structure fabricated using the method and tooling concept is also disclosed.

Composite fabrication method and tooling to improve part consolidation

A method for fabricating composite parts having improved pulloff strengths between portions of the composite part. In one embodiment, a sine wave spar is formed from two U-shaped channels having opposing flanges and a central web. The U-shaped channels are joined along the webs. The triangular gaps between the edges of the joined U-shaped channels are filled using a titanium radius filler that is configured to fit within the gaps. After the titanium radius filler is placed within the gaps, additional layers of composite material are placed over the titanium radius filler and the flanges of the U-shaped channels to form the caps of the I-beam. The resulting composite workpiece is then placed within appropriate tooling and cured within an autoclave. In other embodiments, the method of the invention is used to form spars, ribs, stringers, or bulkheads from composite materials.

Titanium radius filler for use in composite interfaces

An method and tooling concept for fabricating complex composite parts is provided. The method and tooling concept use various tooling configurations in order to produce varying magnitudes of thermal expansion at different areas within the tooling concept. The varying magnitudes of thermal expansion allow the tool concept to account for varying magnitudes of tool movement needed to debulk and consolidate varying thickness areas of the composite workpiece being cured. The tooling concept is formed of different materials having different thicknesses that allow the tooling concept to produce varying magnitudes of thermal expansion. The exterior surface of the tooling concept is covered by a compliant covering. The compliant covering helps to equalize the consolidation pressures produced by the tooling concept during curing. A composite wing box structure fabricated using the method and tooling concept is also disclosed.

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Snohomish, WA, United States of America

Mark L Younie