The Boeing Company

Paul S Gregg

Marc Rollo Matsen

Jeff Dean Will

Howard E Martinson

Robert W Snyder

Lee Charles Firth

Max Urban Kismarton

Brad Lee Kirkwood

Jack J Esposito

Matthew G Kistner

David W Evans

Jeffery Lee Marcoe

Kirk Ben Kajita

Gerald D Miller

Henry John Koppelman

Kenneth Joseph Hunziker

Mark Alan Negley

Donald A Anderson

Marc Joel Piehl

Arthur C Day

David S Nansen

John R Fischer

Arvid J Berg

Gregory Alan Foltz

Rangasamy Elangovan

Brian Scott Kasperson

Eric Howard Nelson

Michael L Leggett

Yuri Tian

Avrid J Berg

Michael A Ross

John J Gurbach

Soo Y Oh

Gerry D Miller

Kirk B Kajita

Brian S Kasperson

An aerodynamic body operable to both promote laminar flow and satisfy structural requirements is disclosed. A perforated panel skin comprises an inner surface and an outer surface of the aerodynamic body. At least one hollow member is coupled to the inner surface and is operable to suction air from the outer surface and through the perforated panel skin. The at least one hollow member is oriented in a substantially chord-wise direction relative to an airflow over the aerodynamic body.

Laminar flow panel

A method and apparatus for forming a sandwich structure is presented. A sandwich structure comprises a metallic core layer and a thermoplastic layer on a first side of the metallic core layer. The thermoplastic layer is consolidated against the first side of the metallic core layer.

Thermoplastic and titanium sandwich structures

According to an embodiment a current return network assembly, for an aircraft having a predetermined potential lightning strike zone, is mounted within the predetermined potential lightning strike zone. The current return network assembly includes an electrically conductive honeycomb central core that conducts electrical current both through the assembly and through the predetermined potential lightning strike zone. The electrical current is caused by a lightning strike on the aircraft at the predetermined potential lightning strike zone. According to an embodiment, an aircraft has a predetermined potential lightning strike zone. A current return network assembly is within the zone. An electrically conductive honeycomb central core is provided for conducting electrical current through the assembly and through the zone wherein the electrical current has been caused by a lightning strike on the aircraft at the zone.

Method and apparatus for providing a current return network in an aircraft structure

Methods of manufacture include welding two or more elongate members together to define an elongate weldment, wherein the welding results in a weld region that is in tension and regions adjacent to the weld region that are in compression, and longitudinally stretching the elongate weldment. Tools and systems for manufacturing elongate weldments, as well as apparatuses, such as aircraft, that include elongate weldments, also are disclosed.

Systems for manufacturing elongate weldments

The invention relates to a mounting device in an aircraft. In one aspect of the invention, a method is disclosed for assembling a metal securement member of the mounting device. In another aspect of the invention, a mounting device is disclosed. In another aspect of the invention, a method is disclosed for installing and using a mounting device in an aircraft.

Method and apparatus to construct metal securement member for an aircraft

A test fixture for determining circumferential shear properties of an arcuate test specimen may include an outer fixture and an inner fixture. The outer fixture may be coupled to an outer side of the test specimen, and may be rotatably mounted on a central pin and may include a rocker arm. The inner fixture may be coupled to an inner side of the test specimen, and may be rotatably mounted on the central pin and may include a load arm extending in a direction opposite the rocker arm. The inner fixture and the outer fixture may be configured such that application of a test load to the rocker arm and the load arm causes rotation thereof about the central pin producing circumferential movement of the inner side relative to the outer side and inducing a circumferential shear load in the test specimen.

Circumferential shear test method and apparatus for a sandwich structure

A testing apparatus for characterizing a tension strength of a fillet bond of a test specimen may include a lower fixture and an upper fixture. The test specimen may include a skin component bonded to a stiffener component. The lower fixture may maintain the stiffener component in a fixed position. The upper fixture may engage the skin component at a pair of discrete engagement locations on opposite sides of the fillet bond. The upper fixture may be mechanically coupled to a gimbal joint and may substantially isolate the filet bond from asymmetric bending during application of a tension test load to the fillet bond.

System and method for testing a fillet bond

A hybrid contoured load-spreading washer is disclosed. An illustrative embodiment of the washer includes a washer body having a composite layer and a metal layer bonded to the composite layer and a fastener opening extending through the washer body. A floor beam seat track attachment assembly and a method of transmitting a load from a seat track to a floor beam web in a seat track attachment assembly are also disclosed.

Hybrid contoured load-spreading washer

The invention relates to a method of bonding two members together utilizing a stack of solid film adhesive and a layer of solid film adhesive, both disposed between the members. A pressure-applying device may be utilized to apply low pressure to force the members together. The pressure may force the stack to compress and expand in varying directions in order to substantially remove air-bubbles between the layer and one of the members. A heating device may be utilized to change the layer and the stack into liquid states in order to bond the members together with a void-free bond-line.

Film adhesive bonding apparatus and process

Composite structural members and methods for forming the same are disclosed. In one embodiment, a composite structural member includes a central structural portion that extends in a first direction and having a first flange portion and a second flange portion that are spaced apart in a second direction perpendicular to the first direction by a web portion, the web portion further including a periodic or a non-periodic undulation extending in the first direction. A first reinforced polymer-based substrate is fixedly coupled to the first flange portion, and a second reinforced polymer-based substrate is fixedly coupled to the second flange portion.

Composite structural member having an undulating web and method for forming same

Mounting device for an aircraft

Growing community of inventors

Seattle, WA, United States of America

Paul S Gregg