The Boeing Company

The Beoing Company

Matthew K Lum

Mark L Younie

Darrell Darwin Jones

Walter Forrest Frantz

Peter D McCowin

Robert Arthur Kisch

Joseph Daniel Brennan

Terrence J Rowe

Hugh R Schlosstein

George D Hempstead

Paul Elfes Nelson

Robert Ray Wampler

Robert A Kramp

Bryan K Bergsma

Robert Alan Kramp, Jr

Denis J Klein

Thomas J Courrier

Harvey T Jones

Joseph P Canavan

David L Wagner

Richard B Evans

Noel A Spishak

C Warren Turner

Thomas Dee Hall

Vincent T Olson

Albert E Seifert

Joseph A Appleton

Robert G Shaw, Ii

Robert G Shaw

Method and apparatus for layup placement on a layup structure is provided. The method includes iteratively loading a layup for the layup structure on a support frame of a saddle module; aligning the saddle module with a pre-selected registration position corresponding to a predetermined application path on the layup structure; and impressing the layup into forced contact with the layup structure along the predetermined application path using a predetermined application force. The apparatus includes a plurality of saddle modules configured to operate in unison, wherein the plurality of saddle modules is configured to receive a pre-selected composite material layup.

Apparatus for layup placement

Method and apparatus for layup placement

Aspects of the present disclosure include various exemplary methods relating to composite lamination using one or more arrays of parallel material dispensing heads. In one example, a method of fabricating a high aspect ratio composite article is disclosed which may involve applying a first strip material to a work surface datum at a first angle with a first material dispenser, and applying a plurality of second strip materials to a work surface datum each at a second angle with a plurality of rotatable parallel material dispensers. The method may also involve advancing the first material dispenser and the rotatable parallel material dispensers as a unit the width of the second strip material and continuing application of the first strip material by the first material dispenser and a plurality of second strip materials by the rotatable parallel material dispensers until a desired length is reached.

Composite lamination using array of parallel material dispensing heads

A pre-patterned layup kit with layup patterned to accommodate an airframe topological feature, trimmed to fit a preselected target region of a layup structure, and conformed to the target region contour. The kit can be fabricated in advance of airframe manufacture and stored until use. The kit includes a flexible carrier upon which the layup is laid, and a release layer between the layup and the carrier. The layup has multiple laminae oriented to an carrier indexing element, and indexed to the target region thereby. A kit manufacturing method includes preparing the laminae constituent of the layup, preparing the carrier, and laying down the laminae on the carrier to make the kit. The kit can be compacted, inspected, and prepared for storage. The layup can be fabricated of a pre-patterned lamina or multiple laminae that are shaped and trimmed to accommodate an airframe topological feature.

Pre-patterned layup kit and method of manufacture

Aspects of the present disclosure include various exemplary embodiments of systems and methods relating to composite lamination using one or more arrays of parallel material dispensing heads. In one embodiment, a method of fabricating a high aspect ratio composite article generally includes applying a first strip material to a work surface datum at a first angle with a first material dispenser, and applying a plurality of second strip materials to a work surface datum each at a second angle with a plurality of rotatable parallel material dispensers. The method also includes advancing the first material dispenser and the rotatable parallel material dispensers as a unit the width of the second strip material and continuing application of the first strip material by the first material dispenser and a plurality of second strip materials by the rotatable parallel material dispensers until a desired length is reached.

To fabricate a composite item, a first end effector is selected from a plurality of end effectors to apply tows to a form. The first end effector includes an integrated creel configured to store spools of the tow on an assembly of spindles. The assembly of spindles is substantially parallel to a longitudinal axis of the first integrated creel. The first end effector is secured to a positioning device. The tows are applied to the form and the tows are compacted on the form with a compaction device. The assembly of spindles are disposed circumferentially about the compaction device.

Method of fabricating a composite item

In one embodiment, an apparatus for removing scrap from tape material on original backing paper includes a supply reel, at least one cutting member, at least one heating member and/or cooling member, and at least one removal member. The supply reel is for supplying and unrolling tape material on original backing paper. The at least one cutting member is for cutting unrolled tape material while on original backing paper. The at least one of a heating member and a cooling member are for at least one of heating and cooling cut unrolled tape material on original backing paper. The at least one removal member is for removing scrap cut unrolled tape material from original backing paper.

Controlled temperature scrap removal for tape process

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

A one-piece barrel assembly cart includes a right assembly cart base connected with a left assembly cart base and at least three stabilizer rings that are attached to the assembly cart base. The one-piece barrel assembly cart may be used to stabilize a tapered cured composite barrel, for example the large fuselage barrel of the aft section of a large new generation aircraft, such as a 7E7 Boeing airplane. A modular assembly cart includes at least two identical modules. Each of these modules includes a cart base and a stabilizer ring. The diameter of the inner surface of the stabilizer ring may vary as needed. Other modules including a fuselage support may be added. By providing modular assembly carts any shape and size of a one-piece composite barrel may be stabilized after curing of the composite material.

One-piece barrel assembly cart

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

A composite item is fabricated with a device. The device includes and end effector and a positioning device. The end effector places a tow. The end effector includes a spindle, compaction device, and a path. The spindle detachably secures a spool of tow and the path is disposed from the spool to the compaction device. The positioning device positions the end effector. The end effector is detachably secured to the positioning device.

Modular head lamination device and method

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

A hybrid composite structure is formed from layers of gore strips (12), polymeric matrix composite (71) comprising a resin impregnated slit tape or tow, and a central honeycomb layer formed from a plurality of rectangular sections (72). The first two steps include forming a plurality of the gore strips and providing a mold, or lay-up mandrel (10). Thereafter, a first set of gore strips is applied to the lay-up mandrel to form a first gore strip layer. Subsequently, the composite material in form of resin impregnated slit tape or tow is applied to the first gore strip layer to form a first composite material layer. Next, a second set of gore strips is applied to the first layer of polymeric matrix composite, opposite the first gore strip layer, to form at least one other gore strip layer. This creates a first sandwich structure having gore strips as the first and last layers of the structure. Thereafter, the layer of honeycomb material is applied to the last layer of the first sandwich structure. Finally, a second sandwich structure, substantially identical to the first sandwich structure, is formed on the side of the honeycomb layer opposite the first sandwich structure. Thus, a hybrid composite structure is formed having first and second sandwich structures separated by a central honeycomb layer.

Growing community of inventors

Mercer Island, WA, United States of America

Matthew K Lum