The Boeing Company

Daniel C Stanley

Mark Stewart Wilenski

Michael Patrick Kozar

Jonathan David Embler

John Hershey Fogarty

John Scott Kruse

Jeremy Nicholas O'Hara

Mark S Wilenski

Jeremy N O'HARA

There is provided a leading edge system for an aerospace vehicle. The leading edge system has at least one structural member. The leading edge system further has a plurality of removable modules removably attached to the at least one structural member. Each removable module has a hollow box substructure and at least one flange portion disposed along a first end of the hollow box substructure. The leading edge system further has a plurality of first attachment elements configured for attaching the at least one flange portion of the removable module to a first end portion of the at least one structural member. The leading edge system further has a plurality of second attachment elements configured for attaching a second end of the hollow box substructure opposite the flange portion, to a second end portion of the at least one structural member opposite the first end portion.

Leading edge systems and methods for aerospace vehicles

A airborne vehicle comprising a fuselage, a folding wing-like structure which is movable from a stowed position to a deployed position, and a hinge mechanism which couples the folding wing-like structure to the fuselage in a manner so that the folding wing-like structure displaces and rotates during movement from the stowed position to the deployed position. The hinge mechanism is housed within an outer mold line of the fuselage and folding wing-like structure to decrease the signature of the airborne vehicle.

Low-profile wing hinge mechanism

A composite structure may include a plurality of fibers at least partially embedded within a matrix. The fibers may be connected to one another at a at least one connection site.

Coupled fibers in composite articles

A structure may include a first layer, a second layer, and an adhesive layer. The first layer may have a faying surface, a side edge, and a first coefficient of thermal expansion. The second layer may also have a faying surface, a side edge, and a second coefficient of thermal expansion that is different than the first coefficient of thermal expansion. The adhesive layer may be interposed between the first and second faying surfaces. The faying surface of at least one of the first and second layers may include an edge treatment extending along at least a portion of a respective one of the side edges. The edge treatment may have an edge treatment length measured along a direction generally parallel to the faying surface and an edge treatment height measured along a direction generally perpendicular to the faying surface.

Panel assembly having thin bondline with reduced edge stress

A composite article may include a plurality of fibers embedded within a matrix. The fibers may include a first fiber and a second fiber which may be oriented in substantially parallel relation to one another. The first and second fibers may be connected to one another at one or more connection sites.

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Renton, WA, United States of America

Daniel C Stanley