The Boeing Company

David Douglas Boes

Warren H Steyaert

Jan A Kordel

Eric Sean Kamila

Eric G Gruner

Eric Dwight Blohm

Matthew Scott Elenbaas

Robert Douglas Maclean

Steven Paul Walker

Paul W Dees

Ian C Burford

Keith Townsend

Rickie Hansken

Renato S Felicio

Charuhas M Soman

Jeffrey Michael Olds

Ryan A Fear

Mark John Herzberg

Daniel E McGinty

Michael Addington

Charuhas Soman

Foldable aircraft wings are disclosed. An example aircraft includes a foldable wing having a fixed wing portion, a foldable wing portion and a hinge to pivotally couple the foldable wing portion relative to the fixed wing portion. The hinge includes a wing transition portion including wing hinge ribs and wing stub ribs, respective ones of the wing hinge ribs coupled to corresponding respective ones of the wing stub ribs. The hinge also includes a tip transition portion including tip hinge ribs, where respective ends of the tip hinge ribs positioned between corresponding respective ones of the wing hinge ribs and the wing stub ribs.

Foldable aircraft wings

Hinge pins for foldable aircraft wings are described. An example apparatus includes a hinge pin to rotatably couple a foldable tip of an aircraft wing to a fixed structure of the aircraft wing. The hinge pin includes a first flange, a second flange spaced apart from the first flange along a central axis of the hinge pin, and a through hole oriented along the central axis.

Hinge pins for foldable aircraft wings

An aircraft comprising: a flight control surface and a rigid hinged panel both pivotably coupled to a wing; a drive linkage which links the flight control surface to the panel so that rotation of the former drives rotation of the latter, the drive linkage comprising first and second links, a first joint which pivotably couples the first and second links to each other, and a second joint which pivotably couples the first link to the flight control surface; and a cam track structure mounted to the wing, the cam track structure comprising first and second cam surfaces having extra run-out space at both ends thereof to prevent jamming. At least one of the links comprises a weakened portion which is designed to fail when a structural overload is produced due to jamming. Additional features can be added to the mechanism to block, shield, and shed other obstruction avenues.

Jam protection and alleviation for control surface linkage mechanisms

A flaperon mechanism that provides jam protection while preventing the component departing from the airplane or causing unacceptable collateral damage. The jam protection feature comprises a controlled failure (fused) mechanism that is associated with the flaperon and flaperon hinge panel and maintains functional movement of the devices. Additional features can be added to the mechanism to block, shield, allow runout and shed other obstruction avenues.

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Bellevue, WA, United States of America

David Douglas Boes