The Boeing Company

Ths Boeing Company

Raviendra Sidath Suriyaarachchi

James R Kendall

Paul D Shaw

Darrell Darwin Jones

Samuel James Knutson

Andrew Elmer Modin

Daniel R Smith

Paul Chace Wilcoxson

Kurtis Shuldberg Willden

Robert William Whiting

Byron James Autry

Jeremy Evan Justice

Richard E Heath

Santiago M Mejia

Stephen Keith Kirchmeier

Steven J Plummer

Brian Timothy Peters

Edward Heath

Jason A Medenciy

Sergio Urzainqui

Antonio Martinez

Paul T Pritchard

Michael Beerman

Dennis Ray Mathis

Richard Alexander Prause

Luis Felipe Velasquez

Andrew Michael Huckey

Megan Elizabeth Bliss

Lance O McCann

Sadie Lee Fieni

Samantha Eberhardt

Brian S Carpenter

Benjamin Rennison

Valentín Forte

Bret Rodeheaver

Brian Bentley Reid

James F Mitman

Carla G Smith

Iti Srivastava

Manuel Motilva

Steven Joseph Plummer

Valentin Forte

Darell Darwin Jones

Paul Daniel Shaw

Sergio Urzainqui Mugica

Manuel Motilva Casado

Richard E Health

Lance O Mccann

Systems are provided for fabricating a preform for a fuselage section of an aircraft. The system includes advancing a series of arcuate mandrel sections in a process direction through an assembly line, laying up fiber reinforced material onto the arcuate mandrel sections via layup stations, uniting the series of arcuate mandrel sections into a combined mandrel; and splicing the fiber reinforced material laid-up onto the arcuate mandrel sections.

Composite assembly for unhardened fuselage components

There is provided a pick-and-place system for transferring and installing a contoured composite structure onto a mandrel, in a composite manufacturing system. The pick-and-place system includes a tray station having a tray assembly to hold the contoured composite structure, prior to transfer and installation onto the mandrel. The pick-and-place system further includes an installation station having the mandrel and a pick-and-place assembly. The mandrel is designed to receive the contoured composite structure, and designed to move along a moving manufacturing line, via a conveyor assembly. The pick-and-place assembly includes a gantry assembly, a main beam suspended from the gantry assembly, the main beam having a plurality of end effector assemblies and a plurality of indexing assemblies, a vacuum system coupled to the main beam, a load balancer assembly coupling the main beam to the gantry assembly, and a control system coupled to the pick-and-place assembly, to operably control the pick-and-place-assembly.

Pick-and-place system and method for transferring and installing a contoured composite structure

A part transfer system includes a movable support, a plurality of arms coupled to the movable support, and an end effector coupled to each of the plurality of arms. The end effector includes a body and a plurality of dividers each coupled to the body. The plurality of dividers divides the body into a plurality of partitions. The end effector includes a plurality of vacuum ports each in fluid communication with one of the plurality of partitions. The part transfer system further includes a vacuum source in fluid communication with at least one of the plurality of vacuum ports. Each of the plurality of vacuum ports is configured to draw a fluid from the plurality of partitions to establish a vacuum between the end effector and a part that is engaged with the end effector, thereby securing the part to the end effector.

Part transfer system

Provided are methods and devices for supporting of variety of different pre-cured composite stringers after forming and prior to curing. A post-forming processing device comprises a base with a channel for receiving hat portions of different stringers. The device also comprises a support structure, at least partially extending within the channel. The support structure is configured to conform to different hat portions and to retain the shape of these hat portions. For example, the support structure is made from a flexible material, which conforms to any shape variations. In some examples, the support structure is made from a jamming material that is reshaped together with each of the pre-cured composite stringers. A post-forming processing device is used for supporting different pre-cured composite stringers while various operations are performed on these stringers, such as stringer trimming, inspection, installation of bladders and noodles, and the like.

Methods and devices for supporting of variety of different pre-cured composite stringers

Systems and methods are provided for fabricating a part on a mandrel. The system includes a series of stations divided into at least two groups of stations, wherein each group of stations performs fabrication operations on a particular zone of the mandrel.

Fabrication line, systems, and methods for fuselage sections

A tool is configured to form a composite charge into a stringer having a net shape with at least one out-of-place feature. The out-of-plane feature is formed by a shim removably attached to the tool. A family of the shims may be used to form a range of out-of-plane features having varying characteristics.

Net shape forming of composite stringers containing out-of-plane features

There is provided a forming apparatus for constraining a composite charge and forming the composite charge into a highly contoured composite structure. The forming apparatus includes a first die and a second die between which the composite charge is formed. The first die has pairs of first die portions spaced apart to define a die cavity into which the composite charge is formed into a contoured hat section having a cap. The forming apparatus includes a constraining assembly having a constraining device positioned in the die cavity. The constraining device is designed to constrain a cap portion, and to apply an upward resistive force against the cap portion, and against a downward compressive force applied by the second die, to provide wrinkle prevention in the cap as the contoured hat section is formed. The constraining assembly has a retaining element to retain the constraining device.

Forming apparatus and method for forming highly contoured composite structures

An example method for simultaneously manufacturing a plurality of objects is described. The method includes simultaneously cycling a plurality of pallets through a conveyor system. The conveyor system is cyclical, and the conveyor system includes an entrance point for each pallet, an exit point, and a plurality of manufacturing points corresponding to a plurality of manufacturing devices. Simultaneously cycling the plurality of pallets includes simultaneously cycling the plurality of pallets past the plurality of manufacturing points for two or more cycles, wherein each pallet is associated with a set of manufacturing instructions for a corresponding object. The method further includes, while simultaneously cycling the plurality of pallets through the conveyor system, using a different combination of the plurality of manufacturing devices to manufacture each object in accordance with the set of manufacturing instructions associated with each pallet, thereby manufacturing different objects for each pallet.

Systems and methods for simultaneously manufacturing a plurality of objects

Methods and apparatus involved in the process of hardening a composite part are disclosed herein. The methods include applying a preform to a mandrel, covering the preform with a caul plate, sealing the caul plate to the mandrel, pushing the caul plate toward the preform and the mandrel and hardening the preform into a composite part while the caul plate is held against the preform. The apparatus include a mandrel, a caul plate which defines a surface of a preform and where the caul plate may include a rigid material and seals disposed between the mandrel and the caul plate. In an additional aspect, the apparatus may include a sealed chamber with a mandrel and a caul plate and a circumferential seal between the mandrel and the caul plate.

Caul plate system for aircraft fabrication

A method of cutting an uncured composite material is presented. The uncured composite material is positioned onto a surface of a tool and over a groove in the surface, the groove having a groove filler and magnetic material within the groove. A cutter having a guide is positioned relative to the uncured composite material, the guide configured to detect the magnetic material. The uncured composite material is cut above the groove using the cutter as the cutter moves along a path defined by the groove, the cutter guided by the guide detecting the magnetic material in the groove.

Methods and tool for cutting an uncured composite material

A method for fabricating a composite structure. A first section for the composite structure is formed in which the first section has a first end with a chevron shape, wherein first composite layers in the first section has a first step pattern at the first end. A second section for the composite structure is formed in which the second section has a second end with a counterpart shape to the chevron shape and in which second composite layers in the second section have a second step pattern at the second end. The first end the second end are positioned such that a first composite layer in the first composite layers in the first step pattern overlap the second composite layers in the second step pattern at a splice location.

Composite structure splice and method

There is provided a forming system for forming a contoured composite structure having a complex curved configuration. The forming system includes a receiving station having a receiving assembly to receive a composite charge to be formed. The forming system includes a forming station having a forming assembly. The forming assembly includes a gantry assembly, an upper die assembly movably coupled to the gantry assembly, a lower die assembly coupled to a floor support beam positioned between the gantry assembly, and one or more pick-and-place devices movably coupled to the gantry assembly. The upper die assembly is separate from, and independently movable with respect to, the lower die assembly. The pick-and-place device(s) are designed to move the composite charge, and the contoured composite structure. The forming system includes a tray station having a tray assembly designed to receive the contoured composite structure from the forming station.

Forming system and method for forming a contoured composite structure

A self-threading lamination head has a material supply drum, a backing layer collection drum, and a material threading system. The material supply drum supports a material roll of layup material backed by a backing layer. The material threading system includes at least one threading belt located on one side of the lamination head. The threading belt is supported by belt rollers driven by a belt drive motor. A belt-mounted layer engagement device is coupled to the threading belt for engaging a backing layer leading edge portion. The backing layer collection drum collects the backing layer as the lamination head applies the layup material onto a substrate. The belt drive motor drives the threading belt over the belt rollers and causes the belt-mounted layer engagement device to thread the backing layer through the lamination head, and position the backing layer leading edge portion proximate the backing layer collection drum.

Lamination head having self-threading capability

There is provided a forming apparatus for forming a high contour composite structure. The forming apparatus includes an upper die and a lower die between which a composite charge is formed. The forming apparatus further includes a plurality of load cells, a control system, and an overlay tool assembly coupled to the upper die. The overlay tool assembly has scalloped sections positioned between pairs of the plurality of load cells, and positioned against portion(s) of the composite charge. The composite charge has ply discontinuity features through the one or more portions. The overlay tool assembly denies pressure and a through thickness compaction to the one or more portions of the composite charge during a forming process, to allow one or more plies in the one or more portions to move after the forming process, and to enable in-plane bending of the high contour composite structure in post-forming operations.

Apparatus and method to enable in-plane bending of high contour composite structures in post-forming operations

A system for preparing a bladder for use in manufacturing a composite stringer includes a sock application station, a film application station, and a composite ply application station. The sock application station has a sock cartridge configured to progressively apply a breather sock of breather material in tubular form onto a bladder as the bladder exits the sock cartridge to thereby result in a sock-bladder assembly. The film application station is located downstream of the sock application station and is configured to inflate a film from a flat shape into an open film tube prior to application over the sock-bladder assembly to thereby result in a film-sock-bladder assembly. The composite ply application station is located downstream of the film application station and has a wrap ply forming bed containing at least one forming bed opening and configured to receive one or more wrap plies of a wrap laminate for urging into the forming bed opening by the film-sock-bladder assembly to produce a ply-film-sock-bladder assembly.

Operator-assisted system and method for preparing a bladder for use in composite stringer manufacturing

Growing community of inventors

Daniel Island, SC, United States of America

Raviendra Sidath Suriyaarachchi