The Boeing Company

Richard R Rosman

Bernhard Dopker

Branko Lakic

Kenneth D Cominsky

Steven Edward Pearson

Wallace Chi-Hua Chan

Aaron William Bartel

Randall Dow Wilkerson

Mark Ronald McLaughlin

David Eric Gideon

Paul B Diep

Ian E Schroeder

David H Leibov

Joseph H Campana

Steven D Ingham

Robert Wayne Johnson

Joel Joseph

Greg M Reyneke

Douglas G Marciniak

Rosario Vingiani

Max Tyler Breedlove

Larry Toler

Rajagopalan Margessery

Kristin L Hall

Kin M Ng

Megan C Kinney

Robert W Johnson

Steven E Pearson

David E Gideon

A system and method for forming an aft fuselage section of an aircraft include a forward section having a stabilizer channel. The forward section includes an upper sill beam and a lower sill beam. One or more pivot fittings are securely fastened between the upper sill beam and the lower sill beam. The one or more pivot fittings are configured to pivotally couple to a horizontal stabilizer within the stabilizer channel.

System and method for assembling an aft fuselage section of an aircraft

An auxiliary power unit enclosure of an aircraft includes a space frame configured to carry a load and defining an auxiliary power unit compartment. The space frame includes a plurality of frame elements coupled together at a plurality of nodes. The auxiliary power unit enclosure also includes a fairing coupled to and surrounding the space frame.

Auxiliary power unit enclosure and method of making the same

A pressure deck system for a fuselage of an aircraft. The pressure deck system comprises a first sloping outboard pressure panel, a first longitudinal stiffener connected to the first sloping outboard pressure panel, a second sloping outboard pressure panel opposite the first sloping outboard pressure panel, a second longitudinal stiffener connected to the second sloping outboard pressure panel, pressure panels between the first sloping outboard pressure panel and the second sloping outboard pressure panel and forming the an upper barrier of a wheel well, longitudinal beams connected to the pressure panels and supporting a cabin floor of the fuselage, and a sloping pressure deck connecting a number of these components to the rear spar of the center wing box. A waterline of the pressure deck system is de-coupled from a side-of-body waterline in the fuselage.

Variable waterline for horizontal pressure deck

Disclosed herein is a body of a mobile vehicle. The body includes skin, a stringer, and a frame. The skin comprises a first tab and a second tab, opposite the first tab. The first tab is fixed directly onto the skin and the second tab is fixed directly onto the skin. The frame comprises a cut-out, a first foot, and a second foot. The second foot is spaced apart from the first foot by the cut-out. The first foot is fixed directly onto the first tab of the stringer, such that the first tab of the stringer is immediately interposed between the first foot of the frame and the skin. The second foot is fixed directly onto the skin, such that no portion of the frame is fixed directly onto the second tab of the stringer.

Stringer-frame intersection of aircraft body

Fuselage sections having tapered wing rib interfaces are disclosed. A disclosed example apparatus includes a rib associated with a fuselage section, and a wing interface surface defined by the rib, where the wing interface surface is tapered relative to a longitudinal axis of the fuselage section from an aft end of the fuselage section to a fore end of the fuselage section.

Fuselage sections having tapered wing rib interfaces

A window frame assembly for an aircraft, includes a window frame of composite material, adapted for attachment in a window opening of an aircraft, having an outer flange with an exterior surface and an interior surface, a metal erosion shield attached to the exterior surface of the outer flange, and a polymer adapter ring, attached to the interior surface of the outer flange. The window frame has a substantially constant thickness, and the erosion shield has a substantially constant cross-sectional shape. The adapter ring has a sloped engagement surface configured for supporting a window pane assembly.

Window frame assembly for aircraft

A method of forming a direct bearing joint includes coupling a first load-bearing structure to a second load-bearing structure. The second load-bearing structure includes a first structural feature comprising a first arcuate shape. The method also includes coupling a composite skin including a second structural feature comprising a second arcuate shape to the second load-bearing structure. The composite skin is coupled to the second load-bearing structure such that the first and second structural features are mated against each other to facilitate distributing compressive loads from the second load-bearing structure into the composite skin.

Joints between a composite skin and a load-bearing component and methods of forming same

A method of forming a direct bearing joint includes providing a load bearing structure including a first structural feature having an arcuate shape and providing a composite skin including a second structural feature also having an arcuate shape. The method also includes coupling the first structural feature to the second structural feature such that the first and second structural features are mated against each other to facilitate distributing compressive loads induced into the load bearing structure into the composite skin.

A bulkhead employs a substantially spherical dome having a periphery and an apex with an axis perpendicular to the dome at the apex. A first plurality of straps emanate from a periphery of the dome on geodesics defined by a first pair of virtual poles beyond the periphery of the dome. A second plurality of straps emanate from the periphery of the dome on second geodesics defined by a second pair of virtual poles beyond the periphery of the dome, wherein any overlap on an individual strap in the first plurality of straps is singular to only one individual strap in the second plurality of straps.

Natural-path tearstraps and stiffeners for spherical composite pressure bulkheads

This disclosure is directed to a boron reinforced composite structural member. The concepts and technologies illustrated in this disclosure are taught within the context of a boron reinforced aircraft keel. A boron reinforced composite structural member may be constructed of a structural member core and a surrounding structural member casing. In one embodiment, the structural member core includes alternating layers of boron fiber reinforced plies and layers of interior carbon fiber reinforced plies. The boron fiber reinforced plies are oriented in a longitudinal direction, and the interior carbon fiber reinforced plies are oriented diagonally, perpendicular, and parallel to the boron fiber reinforced plies. The structural member casing includes layers of exterior carbon fiber reinforced plies that substantially surround the structural member core.

Boron fiber reinforced structural components

A fuselage section may include a structural member and a frame member having a stub frame extending over the structural member. The stub frame may have a web. The fuselage section may include an intercostal extending from a terminal end of the stub frame and having an end flange. The fuselage section may additionally include an adjustable splice fitting having a web, a lower flange, and an end flange being mountable in faying contact with respective ones of the stub frame web, the structural member, and the intercostal end flange.

Adjustable splice fitting for shimless connection of structual members

A splice and an associated method are provided in order to efficiently join structures, such as adjacent fuselage sections. A splice for joining fuselage sections may include a strap configured to bridge the fuselage sections, a shear tie overlying the strap and a fitting positioned between the strap and the shear tie such that the strap and the shear tie are spaced apart. At least the strap and the fitting may be formed of a composite material. The fitting may have an H-shape and may have first and second longitudinally extending sections that extend beyond opposite sides of the strap. Each longitudinally extending section is configured to overlie at least two stringers of a respective fuselage section. The fitting may also have a medial portion upon which the shear tie is seated.

Growing community of inventors

Seattle, WA, United States of America

Richard R Rosman