The Boeing Company

Jeffrey H Wood

Mike P Matlack

Michael Palmore Matlack

Terry A Sewell

James Patrick Dunne

Thomas R Berkel

Michael P Renieri

Steven John Miener

Robert E Bender

Kevin J Sitton

Lamvien H Ngo

John Hershey Fogarty

Joseph M Colich

Charles R Saff

Anthony Falcone

James P Dunne

James A Witte

A floor beam assembly, system, and method for supporting floor beams within a structure are provided. According to one embodiment, a floor beam assembly for installing a floor beam within a structure is provided. The assembly includes at least one floor beam, wherein at least a portion of each floor beam comprises a composite material. The assembly also includes at least one support bracket attached to a structure, wherein each support bracket is configured to support at least a portion of a floor beam thereon. In addition, the assembly includes at least one conductive element extending from the at least one support bracket and configured for electrically communicating with the at least one support bracket.

Floor beam support assembly, system, and associated method

A method for fabricating a structure to include at least a portion of a conduit retention system is described. The method includes receiving parameters for the structure and the portion of the conduit retention system associated with the structure via a user interface, providing the parameters to a machine configured to fabricate the structure and incorporate the portion of the conduit retention system, the machine using a direct manufacturing process, and operating the machine to integrally fabricate the structure and the portion of the conduit retention system.

Methods for system component installation utilizing direct manufactured components

A determinant assembly feature for a joint assembly and a method of assembly therefor. The joint assembly includes a structure and a web connected thereto. The structure includes a base, a pair of legs extending from the base to define a channel, and one or more location control receiving elements in either leg. The web includes a thickness control element and one or more location control elements correspondingly matched to the location control receiving elements. The method includes providing a structure comprising a base, a pair of legs extending from the base to define a channel and one or more location control receiving elements in either leg; providing a web comprising one or more location control elements and a thickness control element; and inserting the web into the structure, wherein the one or more location control elements is correspondingly matched to the one or more location control receiving elements.

Determinant assembly features for vehicle structures

A computer implemented method and apparatus for creating a structural joint for an aircraft. A first composite component and a second composite component are co-joined to form the structural joint for the aircraft. A hole through the first composite component and the second composite component is created. A composite shear pin is placed through the hole. A composite collar is bonded to the composite shear pin with an adhesive.

Method and apparatus for reinforcing composite structures

A method of controlling mixing of a flow exiting a downstream end of a primary nozzle associated with a jet engine. The method may involve coupling a shape memory alloy (SMA) element to a mixing structure disposed at the downstream edge of the primary nozzle. An electrical signal may be applied to the SMA element to heat the SMA element and induce a phase change in the SMA element. The phase change may cause an axial length of the SMA element to constrict, to cause movement of the mixing structure into a path of the flow exiting the primary nozzle.

Morphing structure and method

A method and apparatus for an airfoil, a flexible skin, and a shape control system. The flexible skin forms a control surface of the airfoil. The shape control system is capable of changing a shape of the control surface formed by the flexible skin between a plurality of shapes, wherein a gap does not occur during a changing of the shape of the control surface.

Shape changing airfoil system

A method of controlling mixing of a flow exiting a nozzle associated with a jet engine. The method may involve pivotally supporting a mixing structure forming a hinge device at a downstream edge of the nozzle. A shape memory alloy (SMA) element may be used to couple to the mixing structure. Heat may be generated by a flow exiting the nozzle to induce a phase change in the SMA element. The phase change may cause an axial length of the SMA element to constrict, to cause a pivoting movement of the mixing structure into a path of the flow exiting the nozzle.

A particular method includes installing a window assembly in a structure by coupling a window frame body of the window assembly to a first surface of an interior side of an outer skin of the structure. The method also includes coupling the window frame body to a second surface of an interior side of an inner skin of the structure. The method also includes coupling the window frame body to a portion of the structure between the outer skin and the inner skin.

Window installation method

A window panel adapted for installation relative to a structure. The panel includes a single piece of generally transparent injection-molded material configured to span one or more openings in the structure. The panel has panel attachment inserts for attaching the panel relative to the structure. The inserts are embedded in the material alongside at least one edge of the panel. The panel has a curvature that essentially continues a curvature of the structure surrounding the opening(s) when the panel is installed relative to the structure. This panel can be single-pane and can provide an essentially continuous window along an aircraft fuselage.

Injection-molded window panel and related methods

An airframe attachment fitting includes a fitting base having a base attachment surface and a flange attachment surface, at least one attachment post extending from the base attachment surface of the fitting base and at least one attachment flange carried by the flange attachment surface of the fitting base. An aircraft fuselage and a method of attaching a system or subsystem component to an airframe are also disclosed.

Airframe attachment fitting

A system of interconnecting structures fabricated utilizing an additive manufacturing process is described. The system includes a first component comprising a first unit of an interconnection mechanism, and a second component comprising a second unit of an interconnection mechanism. The first component and first unit are integrally formed utilizing the additive manufacturing process as are the second component and the second unit. The first unit and the second unit are operable to engage one another to attach the first component to the second component.

Methods and systems for providing direct manufactured interconnecting assemblies

A truss network for aircraft floor attachment includes an aircraft fuselage, an aircraft floor disposed in the aircraft fuselage and a three-dimensional truss network comprising at least two truss assemblies each comprising a plurality of tie rod assemblies connecting the aircraft fuselage to the aircraft floor. A method of attaching a floor structure to a honeycomb fuselage structure and an aircraft having a truss network connecting an aircraft fuselage to an aircraft floor are also disclosed.

Truss network for aircraft floor attachment

An exemplary window frame assembly includes a window frame and spring clips. The window frame includes a window frame body, and flanges extend from the window frame body. The spring clips are removably attachable to the flanges. Each flange may define at least one first locking member and each spring clip may define at least one second locking member configured to engage the first locking member. For example, the at least one first locking member may include saw tooth grooves and the at least one second locking member may include a pair of angled tabs. As another example, the at least one first locking member may include a pair of angled tabs and the at least one second locking member may include saw tooth grooves. Each spring clip may further define a release mechanism, such as a tab, that is configured to disengage the spring clip and the flange.

Growing community of inventors

Eureka, MO, United States of America

Jeffrey H Wood