The Boeing Company

John V Dovey

Seiya Sakurai

Jan A Kordel

Michael Albert Balzer

Neal Van Huynh

Douglas S Lacy

Gregory M Santini

Chris J Foster

Rolando G Taguinod

Scott P Kube

Ethan L Clemmitt

John A Pechacek

A method of using a seal to seal a space between a first structure and a second structure that is movable relative to the first structure, the method includes engaging both the first structure and the second structure with the seal so as to seal the space with the second structure in a first position relative to the first structure, and disengaging the second structure from at least a portion of the seal with the second structure in a second position relative to the first structure so that at least a portion of the space is unsealed, where the second structure swipes across the seal moving between the first position and the second position.

Method of using a seal to seal a space between structures

A seal is provided. The seal includes a seal panel having lateral sides. The seal also includes a seal locking mechanism coupled to the seal panel. The seal locking mechanism is configured to resiliently move, under impetus of an actuator, between an unbowed position of the seal locking mechanism and a bowed position of the seal locking mechanism.

Aircraft slat aero-restoration seal door and method therefor

A seal for sealing a space between a first structure and second structure. The seal includes a seal base configured to couple with the first structure so as to form a respective seal with the first structure, a resilient lattice body coupled to the seal base, and a cover. The cover includes an inner surface coupled to the resilient lattice body in an opposing relationship relative to the seal base so that the cover moves towards and away from the seal base in a biasing direction of the resilient lattice body, and a bulbous outer surface configured to engage the second structure so as to form a respective seal with the second structure.

Seal, aircraft including the seal, and methods therefor

The present disclosure provides a slat end seal for use with a slat of an aircraft. The slat end seal includes a shell having a first surface, a second surface opposite the first surface, and a sidewall extending from the first surface. The shell includes a plurality of through holes in the first surface of the shell. The slat end seal also includes a lattice structure coupled to the first surface of the shell and configured to compress in response to a force applied to the second surface of the shell. The lattice structure includes a plurality of supports defining a plurality of interstitial voids between the plurality of supports. The lattice structure also includes at least one through hole aligned with at least one through hole of the plurality of through holes in the first surface of the shell.

Slat end seal and method for manufacturing the same

A composite edge of an aircraft wing includes a composite wing box skin panel, attached to an outward wing spar in an attachment region, and a composite ramp, upon an outer surface of, and co-cured with, the composite wing box skin panel. The composite wing box skin panel has a proximal end and a distal end, with an overhanging edge, with substantially constant thickness and ply count in the attachment region. The composite ramp has a maximum ramp thickness at the distal end, the distal end being set back from the overhanging edge, defining a shoulder on the overhanging edge. A composite wing edge skin panel, having a thickness substantially equal to the maximum ramp thickness, is attached to the composite wing box skin panel at the shoulder and adjacent to the distal end of the ramp.

Composite wing edge attachment and method

A composite edge of an aircraft wing includes a composite wing box skin panel, attached to an outward wing spar in an attachment region, and a composite ramp, upon an outer surface of the composite wing box skin panel. The composite wing box skin panel has a proximal end and a distal end, with an overhanging edge, with substantially constant thickness and ply count in the attachment region, the overhanging edge being without any joggle. The composite ramp has a maximum ramp thickness at the distal end, the distal end being set back from the overhanging edge, defining a shoulder, having a relief radius, on the overhanging edge. A composite wing edge skin panel, having a thickness substantially equal to the maximum ramp thickness, is attached to the composite wing box skin panel at the shoulder and adjacent to the distal end of the ramp.

Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods are disclosed. An aircraft system in accordance with one embodiment of the invention includes a wing and a trailing edge device coupled to the wing. The trailing edge device can be movable relative to the wing between a stowed position and a deployed position, with the trailing edge device having a leading edge, a trailing edge, an upper surface, and a lower surface. The upper surface can have an intersection point with the wing when the trailing edge device is in the stowed position. The motion of the trailing edge device relative to the wing can include rotational motion about a hinge line positioned forward of the intersection point, and a gap can be positioned between the trailing edge of the wing and the leading edge of the trailing edge device when the trailing edge device is in the deployed position.

Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods

Trailing edge device catchers and associated systems and methods are disclosed. A system in accordance with one embodiment includes a wing having a wing support, a trailing edge device carried by and movable relative to the wing and having a device support, and a coupling connected between the wing and the trailing edge device. The coupling can include a pivot joint that includes a pivot element aligned along a pivot axis and connected between the wing support and the device support. The coupling can further include an actuator coupled between the wing and the trailing edge device, with the actuator having a first position in which the trailing edge device is stowed, and a second position in which the trailing edge device is deployed, with an air flow gap located between the wing and the trailing edge device when the trailing edge device is in the second position. A cam track is carried by one of the wing and the trailing edge device and has opposing cam track surfaces fixed relative to each other. A cam is carried by the other of the wing and trailing edge device and is positioned within the cam track between the opposing cam track surfaces. The cam is offset from the pivot axis and during normal operation the cam can carry no load or a first load along a load path that includes the cam track, and when a decrease in support provided by at least one of the pivot element, the wing support and the device support occurs, the cam can carry a second non-zero load greater than the first load along the load path.

Trailing edge device catchers and associated systems and methods

A multi-section aircraft door includes a sliding joint permitting a lower door section displacement into the flight deck area. The door includes an upper door section having a lower edge. The lower edge is connectably joined to an upper member of a two-member sliding joint. The upper member slidably joins to a sliding joint lower member. The sliding joint lower member is connectably joined to a lower door section upper edge. The upper member and the lower member of the two-member sliding joint include paired apertured embossments. A frangible pin slidably mates in each apertured embossment pair. A lever and cam form a frangible pin removal assembly. The lever is held in a normally upright position by either a spring device or a clevis and pin assembly. A rotating clasp or a ball d&eacute;tente system can also replace the frangible pin/apertured embossment and cam/lever.

Growing community of inventors

Seattle, WA, United States of America

John V Dovey