The Boeing Company

Nickolas Scott Ellerbeck

Jeffrey F Stulc

Lyle Ray Deobald

Zeaid F Hasan

Phillip Roger Pratt

James A Backlund, Jr

Patrick B Stone

Paul B Diep

Richard A Skilton

Ronald Leroy McGhee

Robert W Murray

Courtney M Fix

Zachary Nathaniel Stoddard

Robert E Lee

Phillip Andrew Taylor

Robert Wayne Murray

Phillip A Taylor

Ronald Leroy Mcghee

Zeaid Fouad Hasan

Philip Roger Pratt

James A Backlund Jr

Courtney Michele Fix

A system includes a mandrel contoured to define a tapering tubular shape of a workpiece cured on the mandrel and a demolding tool. The demolding tool is configured to remove the workpiece from the mandrel after the workpiece is cured on the mandrel and cut longitudinally. The demolding tool is configured to remove the workpiece from the mandrel by deforming a first end of the workpiece to at least partially disengage the first end of the workpiece from a first end of the mandrel, and subsequently, deforming a second end of the workpiece to at least partially disengage the second end of the workpiece from a second end of the mandrel. The first end of the workpiece may have a first cross-sectional area that is smaller than a second cross-sectional area of the second end of the workpiece.

Demolding

An aircraft includes a wing and a wing box. The wing is joined to the wing box at a side of body joint. The wing and the wing box each includes lower skin and a plurality of stringers on the skin. Ends of at least some of the stringers at the side of body joint have a web cutout and a base that is spanwise tapered to a knife edge at the skin.

Aircraft side of body joint

A stringer beam joint structure of an aircraft formed from fiber-reinforced composites includes a wing and a wing box. The wing is joined to the wing box at a side of a joint structure. The wing and the wing box each includes a lower skin. A plurality of stringers is coupled to the lower skin and all made of fiber-reinforced composites. A first end of at least one of the plurality of stringers at the side of the joint structure features a web cutout with a taper formed in the base flange that spans longitudinal to the respective stringer and the taper located at the end of each respective stringer, where the taper runs from a knife edge of a base flange of the respective stringer to a full height of the base flange. The tapered surface of the base flange is contiguous with an edge of the web cutout.

Composite stringer beam joint structure of an aircraft

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Salt Lake City, UT, United States of America

Nickolas Scott Ellerbeck