The Boeing Company

Other

Brett Ian Lyons

Aaron William Bartel

Matt Wallen

Jens Rossfeldt

Jeffery Lee Marcoe

Marc Rollo Matsen

Christopher Shane Huskamp

John B Moser

Trevor E Tucker

Kay Youngdahl Blohowiak

Sahrudine Apdalhaliem

Waeil M Ashmawi

Moushumi Shome

Neal A Froeschner

Lisa Christina Carlson

Stanley W Stawski

Robert Graham Albers

Darrell D Campbell, Jr

Sergio H Sanchez

Jaime C Garcia

Robert B Miller

Daniel Joseph Braley

Jonathan Blake Vance

Scott R Johnston

James William Fonda

David Eric Gideon

Eric Eldon Deck

Andrew Lawrence Bauer

Nicole Renee Williams

Christopher J Robinson

Thomas Joseph Gonze

Garrett B Peters

Janet Mary Wick

Scott Robert Johnston

James W Fonda

Nicole R Williams

Darrell Campbell

Darrell D Campbell

Janet M Wick

Thomas J Gonze

A rollable table assembly for employing a table as a cart includes a table comprising a first half that is slidably coupled to a second half. A handle is slidably integrated into the table for gripping. A plurality of first wheels and a plurality of second wheels are each rotatably coupled to the table for rolling along the support surface. A plurality of light emitters is each coupled to the table. Each of the light emitters emits light when the light emitters are turned on to illuminate an area.

Rollable table assembly

A textile product and a method of manufacturing a composite object therefrom includes interacting a granular material with a textile material, with the textile material impregnated with the elements of the granular material forming a textile product, and introducing the textile product into a molding process so as to form the composite object therefrom. The granular material includes elements including a matrix material having a plurality of reinforcing fibers received therein, the elements of the granular material having a melt viscosity of between about 5 and about 15 grams per 10 minutes and a particle size distribution with a range in particle size of between about 50 and about 595 micrometers.

Textile product and a method of manufacturing a composite object therefrom

An aged granular material and a method of manufacturing an object from the granular material include introducing a granular material into a molding process so as to form the object therefrom. The granular material includes elements including a matrix material having a plurality of reinforcing fibers received therein, the elements of the granular material having a melt viscosity of between about 5 and about 15 grams per 10 minutes and a particle size distribution with a range in particle size of between about 50 and about 595 micrometers.

Aged granular material and a method of manufacturing an object therefrom

Materials and methods is present for manufacturing fiber reinforced parts. A powder material comprising a matrix material of a size particular distribution comprising substantially oriented fiber of a predetermined length distribution and diameter (L/D). A manufactured part that has substantially randomly oriented fiber is provided using an energy delivery system and the powder material.

Method of reinforcement for additive manufacturing

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 method of fabricating a vacuum barrier system includes fabricating a soluble forming mandrel, laying up composite material over the soluble forming mandrel, and applying a forming mandrel vacuum bag over the composite material and curing the composite tooling material to form a cured composite bag carrier. The method also includes de-bagging and trimming the cured composite bag carrier.

Method of fabricating a vacuum barrier system

A tooling system may include an outer mold line (OML) tool and one or more inner mold line (IML) tools. The OML tool may have an OML tool surface. Each one of the IML tools may have an IML tool surface and may be receivable within the OML tool. Each IML tool may be formed of expandable material. Each IML tool may apply an internal compaction pressure to a composite assembly positioned between the OML tool surface and the IML tool surface when the expandable material is heated.

System for manufacturing monolithic structures using expanding internal tools

Core structures () for composite panels () of an aircraft (), composite panels () and aircraft () including the core structures (), and methods () of manufacturing the composite panels () are disclosed herein. The core structures () include a first side (), a second side (), and a connecting region () that interconnects an upper portion () of the first side () with an upper portion () of the second side (). The first side (), the second side (), and the connecting region () at least partially define an antenna housing (), which defines a housing volume () configured to contain an aircraft antenna () of the aircraft (), and an electromagnetic wave transmission region () configured to permit electromagnetic waves to pass therethrough. The electromagnetic wave transmission region () defines a plurality of kite-shaped voids () arranged in a repeating pattern and bounded by a corresponding plurality of walls (), at least 10% of which extends at least substantially perpendicular to a surface () that bounds the electromagnetic wave transmission region ().

Core structures for composite panels of an aircraft, composite panels and aircraft including the core structures, and methods of manufacturing the composite panels

Manufacturing a thermoplastic composite tubular structure embedded with a first load fitting comprising the steps of braiding a first plurality of inner layers of thermoplastic composite material around a soluble, expandable mandrel. A first load fitting is positioned on the first plurality of inner layers of thermoplastic composite material. A second plurality of outer layers of thermoplastic composite material is braided around the first load fitting and the mandrel so as to form an overbraided mandrel embedded with the first load fitting. The overbraided mandrel is installed into a matched tooling assembly and heated at a specified heating profile in order to consolidate the first plurality of inner layers of thermoplastic composite material and the second plurality of outer layers of thermoplastic composite material with the first load fitting so as to form a thermoplastic composite tubular structure embedded with the first load fitting. A second load fitting may be positioned on the first plurality of inner layers of thermoplastic composite material.

Thermoplastic composite structures embedded with at least one load fitting and methods of manufacturing same

A vacuum bagging system may include a layer assembly defining a fluid flow channel. The layer assembly may include a contact layer mounted to a composite part positionable within an outer mold line (OML) tool. The contact layer may have a contact layer width defined by opposing contact layer side edges. The layer assembly may further include an inner layer mounted to the contact layer and having inner layer side edges located between the contact layer side edges. The fluid flow channel may extend along at least a portion of the composite part to at least one part end. The vacuum bagging system may include an internal vacuum bag positionable against the inner layer. An inner mold line (IML) tool may support the internal vacuum bag. The contact layer width may be less than an IML tool width.

System for facilitating fluid movement in closed molds

A method of forming a monolithic aircraft part includes additively forming a first cavity, defined by a first wall of the part, additively forming a second cavity, defined by a second wall of the part, so that the first cavity and the second cavity are not in communication with each other and share a common wall portion so that the second cavity is partially contained within the first cavity. Additively forming the first cavity includes forming a first aperture, extending through the first wall, forming a second aperture, extending through the first wall, and forming a first inner surface of the first wall, defining a first shape, wherein a first object, permanently having the first shape, would not be able to be mechanically extracted from the first cavity via the first aperture or the second aperture.

Method of making a monolithic part

An aircraft wing tip device may include a unitized, monolithic leading edge torque box that may be formed of polymer matrix fiber-reinforced material. The leading edge torque box may include a skin that may define a continuous, uninterrupted outer mold line surface extending aftwardly from a winglet leading edge by a distance of at least approximately 60 percent of a local chord length. The leading edge torque box may further include at least one internal component extending between opposing inner surfaces of the skin and being integrally formed therewith.

Laminar flow winglet

Materials and methods are presented for manufacturing fiber reinforced parts. A powder material comprising a matrix material of a particular particle size distribution comprising substantially oriented fiber of a predetermined length distribution and diameter (L/D). A manufactured part that has substantially randomly oriented fiber is provided using an energy delivery system and the powder material.

A method and apparatus for forming objects. Layers of precursor material may be placed on top of each other. The layers of precursor material may be selectively cured as the layers of precursor material are placed on top of each other to form an object and a frame associated with the object.

Growing community of inventors

Chicago, IL, United States of America

Brett Ian Lyons