The Boeing Company

Garrett C Hanson

Lisa Christina Carlson

Khanh Mai Pham

Kanna M Pham

Christopher R Loesche

Daniel M Levine

Steve L Patterson

Joseph L Sweetin

Silas Lawton Studley

Jeffrey F Stulc

Jake Adam Reeves

Chilip Chan

Mary LeAnn Parker

Kiet Nguyen

Jeffrey E Barnes

Darrell Darwin Jones

Daniel R Smith

John Dempsey Morris

Scott Edward Krajca

Erik Lund

Bruce S Howard

Mark C Boberg

Paul Chace Wilcoxson

Hyukbong Kwon

Mark S Bunker

Derek J Flolid

Matthew R Desjardien

Stephen Glade Holley

Michael Karas

Benjamin Bowen Lee

Steven Jay McAllister

Jose L Encinosa

Gregory A Cass

Derek Willis

John D O'Connell

Yrret Maldonado

Eric J Walker

Blake Rafferty

Joseph Sweetin

Lisa Carlson

John D O'CONNELL

Examples for low impact hat stringer fluid dams are presented herein. An aircraft structure may include a wing with a vent stringer coupled to the wing. The vent stringer may include a center portion positioned between a first section and a second section. The center portion of the vent stringer includes a slot. A vent dam may be coupled within the vent stringer proximate the slot in the center portion. The vent dam can include a sealant coupled between an integrated pair of baffles such that a combination of the sealant and the integrated pair of baffles prevents fluid communication between the first section and the second section of the vent stringer.

Low impact hat stringer fluid dam

A method of joining an interior wall and a composite channel together is disclosed. The method includes wrapping one or more first composite plies around a first end portion of a first mandrel and wrapping one or more second composite plies around a second end portion of a second mandrel. The method includes positioning the one or more first composite plies located on the first end portion of the first mandrel against the one or more second composite plies located on the second end portion of the second mandrel to create the interior wall, and inserting the first mandrel and the second mandrel into a passageway of a composite channel. The interior wall created by the one or more first composite plies and the one or more second composite plies creates a barrier to block a flow of fluid within the passageway of the composite channel.

Closed composite channel with a barrier for blocking the flow of fluid

Systems and methods are provided for utilizing stringer end caps. One embodiment is a method of forming a stringer. The method includes laying up a stringer preform comprising fiber-reinforced material, placing the stringer preform onto a skin panel preform, bonding an end cap to the stringer preform and the skin panel preform, and co-curing the stringer preform and the skin panel preform while the end cap is bonded to the stringer preform and the skin panel preform, resulting in a composite part that includes the end cap.

Method of forming flyaway stringer end caps

A method includes dispensing a first set of lanes, that each comprise a tow of fiber-reinforced material, at a first angle such that the lanes are placed side-by-side with respect to each other, forming a first layer of a multi-lane tow. The method further includes applying a film directly in contact with multi-lane tow that resists shear forces applied to the multi-lane tow, transporting the multi-lane tow to a mandrel, and compacting the multi-lane tow via a Ply-By-Ply (PBP) machine disposed at the mandrel. The method further comprises removing the film from the multi-lane tow.

Multi-lane tows for use with ply-by-ply forming machines

Systems and methods are provided for fabricating composite parts. One embodiment is a method for fabricating a composite part. The method includes forming a skin panel preform comprising fiber reinforced material, disposing rigid end caps at the skin panel preform at end locations of stringer preforms that will be placed at the skin panel, locating the stringer preforms at the skin panel preform via the rigid end caps, and anchoring the stringer preforms to the skin panel preform.

Flyaway stringer end caps

A hat-stringer assembly for an aircraft comprises a hat stringer with a first hat-stringer leg, a second hat-stringer leg, a first hat-stringer sidewall, a connecting wall, a second hat-stringer sidewall, and a ventilation opening, extending through the connecting wall. The hat stringer assembly also comprises a fitting, comprising a first channel member in contact with the first hat-stringer sidewall and the first hat-stringer leg. The fitting also comprises a second channel member in contact with the second hat-stringer sidewall and the second hat-stringer leg. The fitting further comprises a web cap, in contact with the first channel member and the second channel member. The web cap comprises a web-cap opening, which is in fluidic communication with the ventilation opening.

Hat-stringer assemblies for an aircraft and methods of forming same

A vented hat stringer for an aircraft comprises a first hat-stringer leg with a first-hat-stringer-leg surface, a second hat-stringer leg with a second-hat-stringer-leg surface, a first hat-stringer sidewall, a second hat-stringer sidewall, and a hat-stringer connecting wall, comprising a hat-stringer-connecting-wall surface and a virtual hat-stringer-connecting-wall symmetry plane, passing through hat-stringer connecting wall. The vented hat stringer further comprises a ventilation opening, extending through at least one of the first hat-stringer sidewall or the hat-stringer connecting wall, or extending through at least one of the second hat-stringer sidewall or the hat-stringer connecting wall. The ventilation opening defines a ventilation-opening centerline, wherein the ventilation-opening centerline does not coincide with the virtual hat-stringer-connecting-wall symmetry plane.

Vented hat stringers and methods of forming the same

A composite structure including a composite body having an outer surface, wherein the composite body is elongated along a span axis, and a detection layer connected to the outer surface of the composite body, the detection layer including a plurality of strips, wherein each strip comprises a plurality of glass fibers embedded in a matrix material, is elongated along a detection axis, the detection axis being substantially aligned with the span axis, and is spaced a non-zero distance apart from adjacent strips such that a discontinuity is defined between adjacent strips.

Composite structure and method for barely visible impact damage detection

An apparatus is provided for forming a pleat of a vacuum bag into position over a stringer of an uncured skin panel. The apparatus comprises a leading shoe and a trailing shoe that cooperates with the leading shoe to form the pleat of the vacuum bag. The apparatus also comprises at least one roller assembly for compacting the formed pleat into position over the stringer.

Apparatus and method for operating a vacuum bagging machine to form a pleat of a vacuum bag

An example method for forming a flat composite charge into a composite blade stiffener includes cutting a flat composite charge along a cut line into a first piece and a second piece having an angle, positioning the first piece and the second piece of the flat composite charge on a forming mandrel about a tooling plunger, activating the tooling plunger to drive the first piece and the second piece into a cavity of the forming mandrel resulting in the first piece and the second piece folding at the cut line, withdrawing the tooling plunger from the cavity of the forming mandrel, compressing the forming mandrel to apply a lateral pressure to the first piece and the second piece folded into the cavity, and applying a vertical pressure to a first flange and a second flange of the first piece and the second piece, respectively, to form the composite blade stiffener.

Methods for forming a composite blade stiffener and facilitating application of barely visible impact damage treatments

The construction of a stringer transition through a common base eliminates the need for plate fittings and their associated fasteners to connect opposing ends of a first stringer having a large cross-sectional area to a second stringer having a smaller cross-sectional area. A base of composite material is secured to a skin panel of an aircraft wing with the base aligned with and extending along the longitudinal length of the skin panel. The first stringer is secured to the base and the second stringer is secured to the base, with the first stringer and second stringer longitudinally aligned with the base and with a longitudinal spacing between the first stringer and the second stringer. The base connects the first stringer to the second stringer and only the base connects the first stringer to the second stringer.

Stringer transition through a common base charge

An apparatus for forming a material layer onto a form tool may include at least one nosepiece configured to laterally sweep a ply carrier onto a form tool contour. The apparatus may include a pair of tension arms configured to support opposing lateral sides of a ply carrier having a material layer mounted to a lower surface thereof. The apparatus may include one or more actuators configured to position the tension arms during forming of the ply carrier to the form tool contour. The one or more actuators may be configured to sense and control lateral tension in the ply carrier during forming of the ply carrier to the form tool contour.

Apparatus and method for automated layup of composite structures

A substantially rigid batten is attached to an external face of a vacuum bag to reduce wrinkling of the bag during vacuum bag compaction of a composite laminate layup.

Method, apparatus and device for preventing vacuum bag wrinkling

Growing community of inventors

Mukilteo, WA, United States of America

Garrett C Hanson