The Boeing Company

Jerry Deming Chungbin

John Makoto Shinozaki

Everette Desmond Gray

Mark E Rogalski

Steven Kuan-chi Wu

Narumi Watanabe

Patrick Bickford Stickler

Samuel Francis Pedigo

Joseph L Garbini

Shuonan Dong

Santosh Devasia

Lucky Singh

John W Fuller

Benjamin Yat-Chun Wong

Kyle William Schultz

Wade Marquette

Derek Keith Loy

Everette Gray

Systems and methods are provided for securement of parts. One embodiment is a method for securing a part during fabrication. The method includes forming an interference fit between a pin and a wall defining a hole, supporting a weight of the part with the interference fit, and rotating the part around an axis of the part while the weight of the part is supported.

Method for securing a part during fabrication

There is provided a mechanical avatar assembly for use in a confined space in a structure. The mechanical avatar assembly includes a rail assembly for attachment to an access opening to the confined space. The rail assembly includes two or more rail segments coupled together to form an elongated base having a rail and a gear rack extending along a length of the elongated base. The rail assembly further includes a carriage portion coupled to the rail, and movable relative to the rail, and a drive assembly coupled to the carriage portion and to the gear rack, to move the carriage portion along the rail. The mechanical avatar assembly further includes an articulating avatar arm coupled to, and movable via, the carriage portion. The mechanical avatar assembly further includes an image capturing device.

Mechanical avatar assembly and system for use in a confined space in a structure and method of using the same

Systems and methods for filament fastener that cures with composite part. One embodiment is a method of fabricating a composite part. The method includes placing layers of reinforcement fibers over a tool to form a laminate of composite material to be cured with a first resin, forming a filament fastener comprising bundled fibers with one or more texture elements around the bundled fibers, and coating the filament fastener with a second resin that is chemically compatible with the first resin. The method also includes inserting the filament fastener into the laminate through a plurality of the layers, and curing the filament fastener within the laminate to bind the plurality of the layers of the laminate with the one or more texture elements of the filament fastener via bonding of the first resin and the second resin to form the composite part with delamination resistance.

Filament fastener that cures with composite part

Provided are systems and apparatuses for manufacturing aircraft support structures. An example robotic end effector comprises a rotatable reel with a flat strip of material wound around the reel. The end effector further includes a forming shoe including a forming surface contacting the strip of material. A first end of the forming surface corresponds to a start shape and a second end of the forming surface corresponds to an end shape. As the strip of material passes from the first end of the forming surface to the second end of the forming surface, the strip of material transitions from the first shape to the end shape and is deposited as a formed stringer ply onto an application surface. The forming shoe may further include a vacuum system to suction air through a plurality of ports along the forming surface to urge the strip of material against the forming surface.

Systems and methods for in situ manufacturing of minimally tooled stringers

An apparatus and its method of use provide a preload to the assembly of large structures, for example the assembly of an aircraft wing panel to an aircraft wing frame. The apparatus and its method of use preloads the aircraft wing panel of the aircraft wing structure and presses the aircraft wing panel against the aircraft wing frame of the aircraft wing structure, temporarily securing the aircraft wing panel against the aircraft wing frame and indexing the aircraft wing panel to the aircraft wing frame for the installation of permanent fasteners securing the aircraft wing panel to the aircraft wing frame.

Apparatus and method of providing a preload for the assembly of large structures

A structural assembly including a first structural member defining a first partial bore and including a first protrusion and a second protrusion, a second structural member defining a second partial bore and including a first protrusion and a second protrusion, wherein the second partial bore is aligned with the first partial bore to define a through-bore, a shaft extending through the through-bore, wherein the shaft includes a first end portion and a second end portion, a first engagement member proximate the first end portion, wherein the first engagement member engages both the first protrusion of the first structural member and the first protrusion of the second structural member, and a second engagement member proximate the second end portion, wherein the second engagement member engages both the second protrusion of the first structural member and the second protrusion of the second structural member.

Mechanical fastening system and associated structural assembly and method

Zero mask fixtures for parts

Provided are stiffened stringer panels with integrated indexing stacks. An example composite panel comprises a skin member having an inner surface. An index for positioning a support tool comprises a first set and second set of layered laminate stacks coupled to the inner surface such that a channel is formed between the first and second set of layered laminate stacks. The first and second set of layered laminate stacks is configured to cradle a support tool in the channel to automatically align the support tool relative to the panel. A stringer may include a cap portion that extends from the first set to the second set of layered laminate stacks to form flange portions on the inner surface of the skin member. The index and the skin member may be co-cured or co-bonded.

Stiffened stringer panel with integral indexing laminate stacks

A structural assembly including a first structural member defining a first partial bore and including a first protrusion extending from a periphery of the first partial bore on a first side and a second protrusion extending from the periphery of the first partial bore on a second side, a second structural member defining a second partial bore and including a first protrusion extending from a periphery of the second partial bore on a first side and a second protrusion extending from the periphery of the second partial bore on a second side, wherein the second partial bore is aligned with the first partial bore to define a through-bore, a first engagement member engaged with the first protrusions and a second engagement member engaged with the second protrusions, wherein the first and second structural members are clamped between the first and second engagement members.

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Kenmore, WA, United States of America

Jerry Deming Chungbin