The Boeing Company

Sean Richard Cysewski

Saif Sultan

Michael Steven Lewis

James S Bradley

Brad James Reeves

Christopher Blaine Barney

Nicholas Van Den Handel

Harold G Erickson

Christopher C Veto

Christopher E Plass

Matthew Edmunds

Edward H Chue

Abul K Azad

Bejan B Banihashemi

Alex H Demarne

Joshua R Binder

George B Bojko, Jr

John N Keune

Steven Prudnick

Kevin D Prince

A tie-rod with a swivel tie-rod end includes a tie-rod central rod and a first tie-rod end including a swivel joint. The first tie-rod end is connected to the tie-rod central rod by the swivel joint. The swivel joint is operable to enable rotation of the first tie-rod end with respect to the tie-rod central rod while maintaining a common longitudinal axis between the first tie-rod end and the tie-rod central rod. The tie-rod further includes a second tie-rod end connected to the tie-rod central rod.

Tie-rod with a swivel end

A system and a method for securing a first composite panel to a second composite panel include a latch assembly having one or more latches. The latch assembly is configured to be secured to one of the first composite panel or the second composite panel. One or more strikes are configured to retain at least a portion of the one or more latches. The one or more strikes are configured to be secured to the other of the first composite panel or the second composite panel.

Systems and methods for coupling composite panels

Example implementations relate to decorative display panels for aircraft interiors. An example display panel can include a display shell having one or more openings arranged to form a decorative design and a translucent layer coupled to the display shell. The translucent layer can extend across the openings in the display shell. The display panel can also include a lighting interface coupled to the translucent layer and configured to illuminate one or more portions of the translucent layer positioned relative to the openings in the display shell. The display shell may be coupled to the interior panel such that the translucent layer and the light interface are positioned in between the display shell and the interior panel from an aircraft. In some examples, the lighting interface can illuminate the display panel using different colors and patterns based on desired visual effect and/or operational status of the aircraft.

Decorative display panels for interiors

A tie-rod assembly includes a tube member having a first set of threads at a first end of the tube member and a second set of threads at a second end of the tube member. The tie-rod assembly includes a first clevis coupling assembly having a first width dimension and a third set of threads compatible with first set of threads and first clevis coupling assembly has a second width dimension which includes a portion of the third set of threads with the second width dimension greater than the first width dimension. Further included is second clevis coupling assembly having a third width dimension and a fourth set of threads compatible with second set of threads and the second clevis coupling assembly has a fourth width dimension which includes a portion of the fourth set of threads with the fourth width dimension greater than the third width dimension.

Tie-rod assembly with adjustable length

A method for manufacturing a panel assembly is disclosed. The method includes receiving the panel assembly. The panel assembly includes at least one panel having a finished surface and a covering that is removably adhered to the finished surface of the panel, where the covering includes a plurality of patch sections defined by lines of demarcation. The method also includes removing at least one patch section from the finished surface of the panel to create an opening by tearing the at least one patch section along the lines of demarcation. Each of the plurality of patch sections are frangible with respect to an adjacent patch section at the lines of demarcation.

Reusable covering for protecting a finished surface

Apparatus, systems, and methods that include a variable length linkage for connecting together tie rods. The linkage includes first, second, and third apertures. There is a first distance between the first aperture and the second aperture and a second distance between the first aperture and the third aperture. The apparatus may include a fourth aperture having a third distance between the first aperture and the fourth aperture. The second, third, and fourth apertures may each have a non-circular cross-section. The linkage may include a base, a first finger, a second finger, and a third finger that each extend from the base. The first aperture may be in the base, the second aperture may be in the first finger, the third aperture may be in the second finger, and the fourth aperture may be in the third finger. The first aperture may be oriented vertically with the other apertures oriented horizontally.

Variable linkage for tie-rods

A method of joining panels is disclosed, including adhesively bonding a case in a slot of a first panel, the case having a channel on an inner side, and adhesively bonding a plate to a tab portion of a second panel, the plate having an external pin member. The method further includes inserting the tab portion of the second panel into the case in the slot of the first panel and sliding the external pin member of the plate along the channel on the inner side of the case, to a locking position.

Method and apparatus for joining composite panels

A wall assembly for an interior of an aircraft includes a frame member secured within a cabin of the aircraft having a first side and a second opposing side. The assembly further includes a first decorative panel secured to the frame member on a first side of the frame and a second decorative panel secured to the frame member on a second side of the frame.

Interior aircraft frame assembly for furnishings

Example implementations relate to stowage bin lighting interfaces. An example apparatus includes a panel portion, and a set of fasteners configured to couple the panel portion to a stowage bin such that a curvature of the panel portion aligns with a curvature of the exterior of the stowage bin. Each fastener is configured to extend through the stowage bin into a back portion of the panel portion to couple the panel portion to the stowage bin. Aligning the curvature of the panel portion with the curvature of the exterior of the stowage bin enables the stowage bin to open and close when the panel portion is coupled. The apparatus further includes a lighting interface configured to couple between the panel portion and the exterior of the stowage bin at a position that enables the lighting interface to provide illumination through openings in the panel portion and ambient lighting.

Apparatus, system, and method for a stowage bin lighting interface

Provided are methods of attaching parts using slot cases and assemblies comprising these slot cases. A slot case is inserted into a slot or slid on a tab of a first part prior to attaching it to a second part. The first part may have pores that are partially open at the surface of the slot or tab. These pores may receive adhesive while attaching the two parts. The adhesive volume going into these partially open pores may vary among different first parts. To ensure that enough adhesive is supplied between the slot case and first part, the adhesive is introduced in between these components before attaching the second part and while the slot case and first part are more accessible. The adhesive may be supplied through the bottom of the slot case and continue until the adhesive appears at the top edges of the slot case.

Methods and systems for slot joining using slot cases

In an example, a structural frame is described. The structural frame includes a hub and a plurality of truss members. The hub includes a plurality of hub slots around a perimeter of the hub. The plurality of truss members are configured to couple with the hub and each other. Each truss member is a monolithic structure including: (i) a body extending from a first end of the truss member to a second end of the truss member, (ii) a truss fastener at the first end and configured to couple with a respective one of the plurality of the hub slots of the hub, (iii) a truss slot at the second end and configured to couple to the truss fastener of another one of the plurality of truss members, and (iv) one or more retainers extending along the body between the first end and the second end.

Structural frame

Disclosed embodiments include a structural assembly having a first panel having a first edge and a first aperture adjacent to the first edge, and a clamp having a first piece that passes through the first aperture, a second piece, and a fastening portion that fastens together the first piece and the second piece. The structural assembly may include a second panel having a second edge and a second aperture adjacent to the second edge, and the second piece passes through the second aperture, and the clamp holds the first panel and the second panel together.

Systems and methods for joining composite panels

A panel assembly is disclosed, and includes at least one panel that defines a finished surface and a covering that is removeably adhered to the finished surface of the panel. The covering includes a plurality of patch sections that are defined by lines of demarcation, and each of the plurality of patch sections are frangible with respect to adjacent patch sections at the lines of demarcation.

A panel laminator includes a first frame defining an outer boundary, the first frame operable to support a panel to be laminated and a first flexible diaphragm supported by the first frame to cover the outer boundary. The laminator includes a second frame sized and shaped to conform to the first frame along the outer boundary and a second flexible diaphragm supported by the second frame to match the outer boundary. The laminator includes a passage fluidly connected to the space between the first and second flexible diaphragms, with the passage configured to be coupled to a vacuum system in order to remove air from the space between the first and second flexible diaphragms during a lamination process. The first frame and the second frame are configured to rotate as a unit between a first, generally horizontal, orientation and a second, generally vertical, orientation.

Growing community of inventors

Snohomish, WA, United States of America

Sean Richard Cysewski