The Boeing Company

Applus Servicios Tecnologicos

Applus Servicios Tecnologicos, S.l.

Brian Gregory Robins

Daniel M Rotter

Kurtis Shuldberg Willden

Darrell Darwin Jones

Brad Andrew Coxon

Joseph Daniel Brennan

William Stahl Hollensteiner

Jennifer Sue Noel

Stephen Keith Kirchmeier

Douglas Alan McCarville

Juan C Guzman

Kenneth Marvin Dull

Michael Robert Anderson

Panagiotis Emanuel George

Joseph D Anderson

Travis James Sherwood

Donald Chester Darrow

Jordi Brufau Redondo

Todd J Washburn

Maria Clemencia Corzo Rueda

Brice Aaron Johnson

Shane Edward Arthur

Stephen Lee Metschan

Bernhard Dopker

Lisa Christina Carlson

Khanh Mai Pham

Silas Lawton Studley

Steven Michael Shewchuk

Hyukbong Kwon

Mark E King

Kieran Patrick Davis

Kimberlee Madden

Henry Macias

Nika C McManus

Ethan W Hunter

Derek Willis

Wallace C H Chan

Ivan Berrios

Douglas A Mccarville

William S Hollensteiner

A method for forming a composite part includes positioning a composite ply over a forming surface of a forming tool, moving a forming feature into engagement with the composite ply to yield a formed ply, and, after the moving, securing the formed ply relative to the forming tool.

Forming apparatus, methods, and systems

A composite forming apparatus includes an end effector and a forming feature that is coupled to the end effector. The end effector moves the forming feature relative to a forming tool to form a composite ply over a forming surface of the forming tool or over previously formed composite material on the forming surface of the forming tool. The composite forming apparatus further includes a positioning member engaged with the forming feature. The engagement between the positioning member and the forming feature facilitates a position between the forming feature and the composite ply to promote uniform application of compaction force over the forming surface of the forming tool.

Composite forming apparatus, methods, and systems

A composite forming apparatus includes an end effector, a forming feature, and a non-contact heater. The forming feature is coupled to the end effector. The end effector moves the forming feature relative to a composite ply to form the composite ply over a forming tool or a prior formed composite ply. The non-contact heater heats to a portion of the composite ply before the portion of the composite ply is formed over the forming tool or the prior formed composite ply.

Composite forming apparatus, system and method

Aircraft that incorporates a rounded-hat composite stringer connected to an inner side of the skin of the aircraft to form an elongate conduit that defines a conduit axis, where the conduit axis includes at least one curving portion. The rounded-hat composite stringer can be manufactured by constructing a lower forming die and an upper forming die, each forming die having a length and defining a curve along at least a portion of the length of the die, cutting a pre-cured flat composite charge dimensioned to form the rounded-hat composite stringer, pressing the flat composite charge between the lower and upper forming dies to shape the composite charge into a pre-formed stringer having an inner side between curved fillet portions, contacting a forming member against the inner side of the pre-formed stringer, applying radius fillers to the curved fillet portions of the pre-formed stringer, curing the pre-formed stringer, and removing the forming member from the cured stringer.

Contoured composite stringers

A clamping system for securing a composite charge in position relative to a forming mandrel includes an upstream hinge clamp and a downstream hinge clamp for clamping opposing ends of the composite charge in respective position relative to a mandrel upstream end and a mandrel downstream end during forming of the composite charge onto the forming mandrel. Each one of the hinge clamps is configured to fold a corresponding end of the composite charge from a generally approximately flat configuration to an angled configuration during forming of the composite charge onto the forming mandrel. At least one of the hinge axes is oriented approximately parallel to a folding axis located proximate an intersection of a mandrel top portion with at least one of opposing mandrel side surfaces.

Clamping system for holding a composite charge during forming over a forming mandrel

A blanket assembly for forming a composite charge onto a forming mandrel includes upper and lower heating blankets configured to have a composite charge slidable therebetween during translation along the forming mandrel. The blanket assembly has a pair of wedge elements with tapered sections that are each positionable between the lower heating blanket and the mandrel side surfaces. The wedge element top sides are inclined from the tapered section forward end to the tapered section aft end. The upper heating blanket exerts a blanket forming pressure for progressively forming the composite charge into the cross-sectional shape of the forming mandrel collectively defined by the mandrel side surfaces and wedge element top sides as the composite charge passes over the tapered sections of the blanket assembly. The wedge element top sides maintain the laterally outboard portions of the composite charge in approximately parallel relation to a level tangent to the mandrel top portion.

Heat blanket assembly for forming a composite charge

A method and apparatus for forming a tool is provided. A number of members comprised of a thermoplastic material is positioned within a hollow portion of a structure. The tool is formed within the hollow portion of the structure with the number of members positioned within the hollow portion of the structure. Heat is applied within a selected range to the number of members to reduce a size of each of the number of members. The number of members is removed from the tool such that the tool is left with a number of voids.

Apparatus and system for creating mandrels with voids for expansion control during curing

A composite mandrel includes a generally elongated mandrel body comprising a resilient mandrel core and an elastomeric mandrel outer layer disposed outside the mandrel core. A method for fabricating a contoured stiffened composite panel is also disclosed.

Composite mandrel for autoclave curing applications

An apparatus for manufacturing composite parts. An expandable tool with a transfer system may be moved on a surface of the expandable tool into an outer mold line tool with a composite material laid up on the outer mold line tool. The expandable tool may be expanded in the outer mold line tool to change the surface from a retracted state to an expanded state. The transfer system may be transferred from the expandable tool with the surface in the expanded state to the outer mold line tool.

Composite stiffener positioning and vacuum bag installation device

A composite layup is formed on a tool and placed on a contoured part. The tool is contoured to substantially match the contour of the part. A set of location data is generated which represents the location of the part in space relative to the tool. An automated manipulator uses the location data to move the tool into proximity to the part and place the contoured layup on the part.

Method for forming and applying composite layups having complex geometries

A method and apparatus for compacting composite stringers. In one illustrative embodiment, an apparatus comprises a compacting structure, a compactor vacuum system, and a carrier vacuum system. The compacting structure has a shape configured to contact layers of uncured composite material for a composite stringer. The compactor vacuum system is associated with the compacting structure. The compactor vacuum system is configured to cause the compacting structure to apply a pressure to the layers of uncured composite material when a compactor vacuum is applied to the compactor vacuum system. The carrier vacuum system is associated with the compacting structure. The carrier vacuum system is configured to hold the layers of uncured composite material against the compacting structure when a carrier vacuum is applied to the carrier vacuum system.

Compaction system for composite stringers

Apparatuses and methods for forming a joggle and a longitudinal ridge in a multi-ply composite charge are disclosed. Charges may be formed in a forming press that comprises a joggled die, with a longitudinal ridge and a joggle that crosses the longitudinal ridge, and a conforming die, with a series of longitudinally-spaced die fingers. The die fingers include pairs of die members configured to move laterally between a closed position and an open position, with each die member configured to tilt longitudinally.

Forming presses and methods for forming joggled, stiffened composite structures

Method for creating mandrels with voids for expansion control during curing

A hands-free method and related apparatus are used to shape, place and compact a composite stringer on a composite skin of an aircraft. A composite charge is placed on a tool assembly that used to shape the charge into a preformed stringer. With the stringer held on the tool assembly, the tool assembly is used to move the preformed stringer into proximity with the skin and both place and compact the stringer against the skin. Following compaction of the stringer, the tool assembly is removed and the skin and the stringer are co-cured.

Apparatus for forming and installing stringers

A method and apparatus for manufacturing composite parts. An expandable tool with a transfer system may be moved on a surface of the expandable tool into an outer mold line tool with a composite material laid up on the outer mold line tool. The expandable tool may be expanded in the outer mold line tool to change the surface from a retracted state to an expanded state. The transfer system may be transferred from the expandable tool with the surface in the expanded state to the outer mold line tool.

Composite stiffener positioning and vacuum bag installation

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Renton, WA, United States of America

Brian Gregory Robins