The Boeing Company

Robert Thomas Johnson

Mark Stephen Shander

Bradley James Mitchell

Kevin Scott Callahan

Trevor Milton Laib

Mark Eugene Liffring

Ty Aaby Larsen

David Mitchell Anderson

Yakentim M Ibrahim

Todd Burton Brouwer

David R Gladish

Mark Gus Mehlhaff

James T Henley

Samuel J Feist

Robert Arthur Nye

Daniel Keith Bittner

Scott Roger Westerfield

Darrel E Santala

Margaret Douglas

Kenneth Harlan Griess

Gerald F Herndon

Marnix Van Der Mee

Timothy Edward Jackson

Thomas R Hasenoehrl

Terrance L Thomas

Matthew C Malkin

Robert Dennis Holley

Christopher Mark Severns

Simon D Senibi

Steven Mark Walstrom

Arnold W Nordsieck

Carolyn Kerr

Matt R Dickerson

Alfredo Zamora Campos

Jin-Seog Seo

John T Peters

James A Williams

Shahzad Aminzadeh

Robert William Kennedy, Jr

Jin Heung Kim

Robert L Springgay

Jesse A Laplante

Jacky-Vy C Chau

Gregory D Gessell

Brian S Oelke

Darrell E Santala

Margaret L Douglas

Carey N Atherton

Mark S Shander

Robert D Holley

Todd B Brouwer

David M Anderson

Gerald F Herndorn

A method of forming a wire bundle, the method includes removably coupling a plurality of wire bundle mounting structures to a wire bundle form board, the plurality of wire bundles mounting structures being coupled to the wire bundle form board in a predetermined pattern corresponding to a configuration of the wire bundle. The method also includes inserting one or more wires, of the wire bundle, into the plurality of wire bundle mounting structures, coupling the one or more wires to the plurality of wire bundle mounting structures with a respective wire bundle retention strap of each of the plurality of wire bundle mounting structures so as to form the wire bundle, and removing the one or more wires and the plurality of wire bundle mounting structures from the wire bundle form board as a singular unit.

Method for forming a wire bundle and coupling the wire bundle to a structure background

A vehicle include an interior cabin including a plurality of structural components, a plurality of electrical devices within the interior cabin, a power supply, and an electrical signal distribution system mounted to at least one of the plurality of structural components and electrically coupled to the power supply and the plurality of electrical devices. The electrical signal distribution system includes a printed circuit board (PCB), and a plurality of outlets coupled to the PCB. The plurality of outlets electrically couple to the plurality of electrical devices. The electrical signal distribution system provides electrical signals to the plurality of electrical devices.

Systems and methods for providing electrical signals to electrical devices within an interior cabin of a vehicle

An electrical multi-connector feedthrough panel comprising a frame configured to couple with a structure and to seal, at least in part, a penetration in the structure across a pressure differential, wherein a first pressurized environment is disposed on one side of the sealed penetration, and wherein a second pressurized environment, different than the first pressurized environment, is disposed on an opposite side of the sealed penetration a plurality of electrical connector insert shells monolithically formed with the frame, each of the plurality of electrical connector insert shells protruding from opposite sides of the frame to form a respective passage through the frame and being configured to sealingly couple with at least one electrical butt connector to thereby seal the respective passage; and an electrically conductive coating disposed on the frame and on each of the plurality of electrical connector insert shells to thereby form an electrical bonding surface.

Electrical multi-connector feedthrough panel and method therefor

An electrical multi-connector feedthrough panel for sealing a penetration in a structure across a pressure differential, the panel including a frame having a first environmental interface surface and a second environmental interface surface configured to couple with the structure so that the first environmental interface surface and the second environmental interface surface span the penetration so as to at least in part seal the penetration, and a plurality of electrical connector insert shells monolithically formed with the frame, each of the plurality of electrical connector insert shells being configured to sealingly couple with at least one electrical connector, where the first environmental interface surface is disposed between the plurality of connector shells so as to be in fluid communication with a first pressurized environment, and the second environmental interface surface is disposed between the plurality of connector shells so as to be in fluid communication with a second pressurized environment.

A system for calculating forces exerted into an aircraft component includes a test hinge assembly and a monitoring system. In at least one embodiment, the test hinge assembly is a triangular shaped assembly, and includes at least one beam, at least one connecting joint having a channel configured to receive and retain a fastening member, and at least one strain gage secured to an outer surface of the beam(s). The strain gage(s) is configured to detect one or more strains exerted into the beam(s). The monitoring system is in communication with the strain gage(s). The monitoring system is configured to calculate forces exerted into the fastening member(s) by analyzing the strain(s) exerted into the beam(s).

Flight test hinge assembly configured for calculating exerted forces through strain analysis

A method and apparatus for establishing a wire network for a platform. The apparatus for establishing a wire network for an aircraft comprises a wire manager and a layout manager. The wire manager sorts a plurality of wires for the aircraft into a plurality of bundles based on a plurality of categories established for the plurality of wires with respect to operation of the aircraft. The plurality of categories includes an essential category and the plurality of bundles includes a primary bundle corresponding to the essential category. The layout manager generates a primary layout output for the primary bundle based on an available space within the aircraft. Forming and installing a primary wire harness corresponding to the primary bundle in the aircraft based on the primary layout output independently of a remaining portion of the plurality of bundles improves a build efficiency of the aircraft.

System and method for wiring an aircraft

A modular truss assembly configured to be placed in small or narrow spaces such as within the floor, sidewall, or crown of a vehicle for mechanically and electrically mounting system components of a modular equipment center (MEC). A plurality of MECs is spatially distributed throughout the vehicle to service equipment loads. The modular truss assembly provides different voltage levels for powering the system components of the MEC and for powering the equipment loads. In one or more configurations, all or part of the modular truss assembly can be removed from the vehicle for repair or replacement.

Modular equipment center distributed equipment packaging truss

A plurality of modular equipment centers (MECs) spatially distributed throughout a vehicle servicing equipment loads. Each MEC independently provides localized power and communication to service the equipment loads and each equipment load is serviced by the nearest MEC. In at least one embodiment, only primary power is distributed across section breaks of the vehicle to minimize the number of connections between section breaks, reduce overall vehicle weight, and to increase vehicle build rate.

Modular equipment center distributed primary power architecture

An interconnect for transferring signals herein includes one or more signal contacts to transfer the power or data to or from an integrated truss system. An interconnect may be configured to transfer power or data between layers of the integrated truss system or within the same layer of the integrated truss system. An interconnect may be configured with one or more compression mechanisms that secure the interconnect in the integrated truss system.

Truss interconnect

A method for interconnecting electronic equipment within an aircraft includes installing a multi-dimensional backplane within the aircraft across a plurality of frame bays associated with the aircraft, the backplane including a plurality of connectors mounted thereon, contacts associated with the connectors interconnected by electrical conductors formed within the backplane, attaching shipside wiring to a first portion of the connectors on the backplane, and attaching electrical connectors of the electronic equipment to corresponding connectors on the backplane.

Methods and systems for incorporating translating backplanes to facilitate wire separation

Electrical connection devices and systems for the electrical interconnection of systems and components within an aerospace vehicle, such as a production airplane, are disclosed. A typical quick lock interconnect comprises a manually installed and coupled modular electrical connector. The connector receptacles may be designed to 'snap' onto a structural support, such as a stamped and formed or extruded rail, providing an inherent electrical ground path. A typical quick lock production interconnect may be fabricated from thermoplastic materials and plated with a metallic finish to provide for electrical bonding and shielding. The connector device may also include a novel slide latch coupling mechanism that provides a positive visual indication of a fully coupled connector eliminating the need for specialized tools. The structural support may be part of an aircraft fuselage section where the plurality of electrical connector shells each support the one or more electrical conductors coupled between separate fuselage sections.

Electrical quick lock interconnect

A method of providing power and/or data to a seat in a seating area. A power distribution system having a continuous power bus is used to supply power and/or data to seats in a mobile platform or fixed structure. The power distribution system generally includes a bus strip that, in a mobile platform, extends along a length of a passenger cabin and a connector operable to provide a connection between the bus strip and the passenger seats. Power and/or data can be transmitted between the bus strip and the passenger seats, via the connector, at any point along the bus strip, thus eliminating the need to run separate connections between the power and/or data source and each seat.

Continuous power bus for seat power

A conductive bus device and method operable to distribute signals throughout a platform. The bus delivers signals to any number of select locations within the platform, such as to seats mounted to a seat track. The bus is mounted beneath a floor of the platform. The signals can be transmitted between the power bus and the passenger seats using a conductor that extends from the passenger seats to the bus through a opening in the seat track. The bus device and method eliminates the need to run separate connections between a signal source and each seat. This device and method significantly reduce the cost, energy, and time necessary to wire each seat individually.

Passenger cabin seat power bus

A power distribution system having a continuous power bus to supply power and/or data to aircraft passenger seats in a mobile platform. The power distribution system generally includes a bus strip that extends along a length of the passenger cabin and a connector operable to provide a connection between the bus strip and the passenger seats. Power and/or data can be transmitted between the bus strip and the passenger seats, via the connector, at any point along the bus strip, thus eliminating the need to run separate connections between the power and/or data source and each passenger seat.

Growing community of inventors

Everett, WA, United States of America

Robert Thomas Johnson