The Boeing Company

Other

Paul B Diep

Bernhard Dopker

Joel Joseph

Max Tyler Breedlove

Robert Wayne Johnson

Aaron William Bartel

Patrick B Stone

Jordan Seth Erickson

David Eric Gideon

Richard R Rosman

Kenneth D Cominsky

Steven Edward Pearson

Wallace C Chan

Richard A Skilton

Peter John Newnham

Ronald Leroy McGhee

Robert W Murray

Rosario Vingiani

Nickolas Scott Ellerbeck

Courtney M Fix

Zachary Nathaniel Stoddard

Julie Frances Murphy

Robert E Lee

Phillip Andrew Taylor

Phiyen T Pham

Mark J Buckley

Trevor S Mccrea

Robert W Johnson

Courtney Michele Fix

Robert Wayne Murray

Phillip A Taylor

Ronald Leroy Mcghee

David E Gideon

A securement assembly for securing a vertical tail fin assembly to an aircraft includes a first lug member secured to the vertical tail fin assembly. The securement assembly further includes a first clevis member. The first clevis member includes a first end portion of the first clevis member is engaged to the first lug member. A second end portion of the first clevis member is secured to a first fuselage frame constructed of a composite material with a first fastener which extends through the second end portion and the first fuselage frame in a first direction transverse to the first fuselage frame.

CFRP fuselage frame with securement to vertical tail fin

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

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 tail assembly includes an aft fuselage section secured to a forward fuselage section, and includes a stiffener-reinforced pivot bulkhead defined by separate parts secured together by a first set of splices. A longeron extends longitudinally along the aft and forward fuselage sections, and includes a discontinuity adjacent a peripheral edge of the pivot bulkhead. The aircraft tail assembly includes a second set of splices that overlie the discontinuity. One of the second set of splices extends laterally over the longeron to bridge the discontinuity adjacent the peripheral edge of the pivot bulkhead, and another of the second set of splices extends longitudinally along the longeron to secure the longeron to the pivot bulkhead adjacent the discontinuity. A chord engages the peripheral edge of the pivot bulkhead to facilitate transfers of force loads from the bulkhead along a load path that includes the longerons and the splices.

Aircraft tail assembly

A vehicle, such as an aircraft, structural architecture for supporting a horizontal stabilizer with a back up beam having an upper longeron fitting connected to the front side and secured with a back up fitting on the back side, a lower longeron fitting connected to the front side and secured with a back up fitting on the back side, and a pivot fitting connected to the front side of the first back up beam in between the upper longeron fitting and the lower longeron fitting and secured with a third back up fitting on the back side of the back up beam.

Pivot fittings back up beam architecture

A twisted strap transfers loads generated by an aircraft passenger floor from the floor to an aircraft fuselage. The twisted strap may be formed of carbon fiber reinforced plastic, fiberglass reinforced plastic, or metal, such as aluminum, stainless steel, or titanium alloy. The twisted strap has first and second ends configured to be twisted between 40 to 120 degrees relative to the other whenever connected to a seat track and a forward-aft extending fuselage stiffener, respectively. In at least one form, the twisted strap has a length ranging from 15 to 30 inches, a width of 1 to 2 inches, and thickness of 0.1 to 0.5 inch. Each end incorporates apertures for accommodating separate connectors spaced at least four-to six diameters apart along the length of the twisted strap, and the twisted strap is configured to accommodate minimums of 9 G's of force in tension and 1.5 G's in compression.

Twisted strap for restraining passenger floor loads

The illustrative embodiments disclose a pressure bulkhead system comprising an aft pressure bulkhead, skin splice angles, and stringer splice angles. The aft pressure bulkhead has an outer compression ring. The skin splice angles are positioned adjacent to one another and joined to the outer compression ring. The skin splice angles form a joint between a first section of a fuselage, a second section of the fuselage, and the aft pressure bulkhead. The stringer splice angles join the skin splice angles to a stringer in the second section of the fuselage.

Pressure bulkhead system

An assembly of thermoplastic parts for forming a final composite part is presented where the assembly includes at least two prefabricated shells fabricated of thermoplastic. Each prefabricated shell has substantially the same shape as the final composite part and where the shapes of the prefabricated shells have dimensions that allow the prefabricated shells to be assembled into a nest for placement into a mold.

Thermoplastic composite part and method of fabrication

A pressure bulkhead for a vehicle disclosed. The pressure bulkhead is configured to separate a pressurized interior from an unpressurized interior of the vehicle. The pressure bulkhead includes a bulkhead wall having a radially inner disk and a radially outer compression ring. The radially inner disk has a surface and a first thickness and the radially outer compression ring having a second thickness that is greater than the first thickness. The radially outer compression ring defines a periphery of the bulkhead wall and the second thickness of the radially outer compression ring is effective to provide a strength to oppose meridional and hoop stresses across the surface of the radially inner disk in response to a pressure differential across the bulkhead wall. The pressure bulkhead also includes an attachment ring that is affixed to the periphery of the bulkhead wall.

Self-balancing pressure bulkhead

A pressure bulkhead may include a bulkhead wall having a radially inner disk and a radially outer compression ring, the outer compression ring being reinforced to balance meridional and hoop stresses sustained by the bulkhead wall in response to a pressure differential across the pressure bulkhead; and the radially inner disk being unitary with the outer compression ring and being made of the same material as the outer compression ring.

The disclosed shell structure splice and method may include a first panel having a first edge, a second panel having a second edge, the second edge being positioned in edgewise alignment with the first edge to form a splice joint, a strap bridging the splice joint and attached to the first panel and the second panel, the strap having a first tapered region and a second tapered region, a first fitting having a tapered section and a flat section, the tapered section being attached to the first tapered region of the strap, and a second fitting having a tapered section and a flat section, the tapered section being attached to the second tapered region of the strap.

Circumference splice for joining shell structures

Growing community of inventors

Bothell, WA, United States of America

Paul B Diep