The Boeing Company

Steven P Wanthal

Joseph L Sweetin

Douglas Lewis Grose

Randy Allan Southmayd

Christopher B Mathiesen

James R Kendall

Byron James Autry

Matthew S Stauffer

Samuel James Knutson

Terry A Sewell

Santiago M Mejia

Brian Timothy Peters

Patrick James Macko

Sara Murphy

Michael J Bailey

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 metal/composite joint. An illustrative embodiment of the metal/composite joint includes a metallic component, a composite component provided in engagement with the metallic component, an engagement region defining contact between the metallic component and the composite component and a plurality of attachment projections joining the metallic component and the composite component. The attachment projections may be non-uniformly distributed along the engagement region. A method of joining a metallic component and a composite component is also included.

Metal/composite joint with selective interlaminar reinforcement

A torque tube includes a composite body and an end fitting. The composite tube includes a body having a body interior diameter, a wall thickness, an end having an edge, and a set of helically-shaped grooves. Each helically-shaped groove may pass through the wall thickness. Each helically-shaped groove may begin at the edge and end in the body. The end fitting may include a sleeve configured to mate with the body interior diameter and a set of ribs configured to mate with the set of helically-shaped groove.

Joint for composite tube

A torque tube includes a composite body and an end fitting. The composite tube includes a body having a body interior diameter, wall thickness, an end having an edge, and a set of grooves. Each groove of the set of grooves passes through the wall thickness. Each groove of the set of grooves begins at the edge and ends in the body. The end fitting includes a sleeve configured to mate with the body interior diameter and a set of ribs configured to mate with the set of grooves.

Joint for hybrid composite items

A joint is formed by joining two structures using a joint element. The joint element has a base and at least two legs extending from the base, the legs defining a slot having opposing sides and a bottom. The joint element is attached to the first structure. A second structure is positioned in the slot. An adhesive is disposed in the slot joining the second structure to the joint element. A cavity is formed between the bottom of the slot and the second structure. The cavity being substantially free of adhesive.

Joints formed by joining structures

A product including a first structure. A joint element is attached to the first structure. The joint element has a base and at least two legs extending from the base, the legs defining a slot having opposing sides and a bottom. A second structure is positioned in the slot. An adhesive is disposed in the slot joining the second structure to the joint element. A cavity is formed between the bottom of the slot and the second structure. The cavity being substantially free of adhesive.

Joining structures

A method of joining a first structure to a second structure using a joint element. The joint element has a base and at least two legs extending from the base and the legs define a slot having opposing sides and a bottom. The method comprises attaching the joint element to the first structure and inserting the second structure into the slot. The method further includes injecting an adhesive into the slot. The method also includes ensuring a cavity is formed between the bottom of the slot and the second structure and the cavity is substantially free of adhesive.

Methods of joining structures and joints formed thereby

A method for vacuum assisted resin transfer molding a composite structure including fibers at least partially surrounded by resin using a mold including a tool having a surface shaped to correspond to the composite structure and an inflatable bladder for forcing the composite structure against the tool. A resin inlet is connected to a resin source for introducing resin into a mold cavity at least partially defined by the tool surface and the bladder and a vacuum port spaced from the resin inlet. The method includes the steps of opening the mold cavity, loading fibers into the open mold cavity, closing the loaded mold cavity, introducing resin through the resin inlet into the closed mold cavity loaded with fibers, and pulling a vacuum at the resin inlet and the vacuum port to draw excess resin from the structure prior to curing thereof.

Growing community of inventors

St. Charles, MO, United States of America

Steven P Wanthal