The Boeing Company

Samuel James Knutson

Raviendra Sidath Suriyaarachchi

James R Kendall

Byron James Autry

Brian Timothy Peters

Paul D Shaw

Santiago M Mejia

Gregory J Hickman

Paul Gabriel Werntges

Edward Heath

Dennis Ray Mathis

Luis Felipe Velasquez

Matthew S Stauffer

Steven P Wanthal

Patrick James Macko

Sara Murphy

Samantha Eberhardt

Alice R Arnold

Brian S Carpenter

Carla G Smith

Michael J Bailey

Brian Bentley Reid

A system for joining a first thermoplastic component of a workpiece with a second thermoplastic component of the workpiece includes a first joining plate assembly comprising a housing, a heat plate, and a thermal insulator disposed between the housing and the heat plate, wherein the heat plate defines a heating surface; a second joining plate assembly opposed from the first joining plate assembly; and a clamping assembly engaged with both the first joining plate assembly and the second joining plate assembly.

Systems and methods for joining thermoplastic components

A system to adjust extension lengths of slats of a work platform relative to a workpiece includes sensors to collect first data associated with a position of an outer surface of the workpiece at a height of the slats. The system includes actuators configured to extend or retract the slats. The system also includes a controller coupled to the sensors and to the actuators. The controller is configured to receive the first data and second data associated with rotation of the workpiece. The controller is configured to provide signals to the actuators of the work platform based on the first data and the second data. The signals cause the actuators to adjust or maintain extension lengths of the slats of the work platform to maintain separation distances between ends of the slats and the outer surface of the workpiece within a separation distance range as the workpiece rotates.

System and method to adjust extension lengths of slats of a work platform relative to a workpiece

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

A joining system includes a holding fixture assembly configured to hold a fuselage skin. The stringers are temporarily attached to the fuselage skin. The joining system includes an upper beam assembly including an upper beam and a lower beam assembly. The lower beam assembly includes a lower beam and at least one lower heating element. The holding fixture assembly is coupled to the upper beam assembly. The holding fixture assembly is coupled to the lower beam assembly. The upper beam is movable relative to the lower beam to clamp the at least one of the plurality of stringers and the fuselage skin together prior to and during welding.

Method and apparatus for bonding stringers to a fuselage skin

Systems and methods are provided for splicing airframe components. One embodiment is a method for assembling an airframe of an aircraft. The method includes forming a first skin of a first circumferential section of fuselage, the first skin including a distal portion comprising a lip and a shoulder, aligning a second skin of a second circumferential section of fuselage with the shoulder such that the lip overlaps the second skin, and affixing the first skin and the second skin together via a circumferential splice.

Circumferential lap splices for sections of fuselage

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 carrier film set configured to apply a number of stiffener assemblies to a layup mandrel, the carrier film set comprising: a number of alignment features configured to align the carrier film set relative to the layup mandrel; and a number of indexing features configured to index the number of stiffener assemblies onto the carrier film set.

Stiffener assembly application system with carrier film set

Within examples, elastomeric apparatuses for use in manufacture of a composite component, and methods for altering a surface rigidity of an elastomeric apparatus for use in manufacture of a composite component are described. In one example, an elastomeric apparatus comprises an elastomer housing, and a plurality of magnets within the elastomer housing at predetermined positions to provide surface rigidity to the elastomer housing based on one or more alignments of certain magnets of the plurality of magnets due to magnetic forces. An increase in temperature causes a loss in one or more of the magnetic forces of one or more of the plurality of magnets resulting in a reduction of stiffness of the elastomer housing at corresponding predetermined positions.

Bladder that changes stiffness based on temperature effects for manufacture of composite components

A method of fabricating a composite structure is presented. The method comprises laying up a plurality of composite plies over a layup mandrel; positioning a first caul plate and a second caul plate over the plurality of composite plies, leaving composite material exposed; removing at least part of the composite material exposed between the first caul plate and the second caul plate to separate a first composite section from a second composite section; curing the first composite section and the second composite section to form a first composite part and a second composite part; and removing the first composite part and the second composite part from the layup mandrel immediately following curing.

Method of fabricating a composite structure

A manufacturing system for laying up a stringer laminate includes a lamination surface and a plurality of lamination heads including a frame filler outer ply lamination head for laying up (e.g., laminating) frame filler bottom ply at a plurality of frame filler locations. Also included is at least one frame filler inner ply lamination head for laying up one or more frame filler inner plies over a protruding portion of the frame filler bottom ply at each frame filler location. Further included is at least one stringer body lamination head laying up one or more stringer body plies defining a stringer body portion extending along the lamination surface. A frame filler outer ply lamination head is configured to lay up a frame filler top ply at each frame filler location such that the frame filler inner plies are captured between a frame filler bottom ply and a frame filler top ply.

System and method for laying up a composite laminate having integrally laminated filler elements

A method is presented. A machine head is positioned in a desired location relative to a material on a tool using a sensor connected to the machine head and calibrated to detect magnetic material in the tool. An operation is performed on the material using the machine head starting at the desired location.

Tool having magnetic material

Systems and methods are provided for dynamically altering the shape of a forming tool for a composite part during forming. An exemplary forming tool includes a main body that holds a first portion of a multi-layer laminate, and a platform that holds a second portion of the laminate aligned with the first portion. The forming tool also includes a biasing device that repositions the second portion with respect to the first portion during forming of the laminate, causing shear stresses between the layers of the laminate.

Growing community of inventors

Ladson, SC, United States of America

Samuel James Knutson