The Boeing Company

Eric Sean Kamila

Eric G Gruner

Renato S Felicio

Matthew Scott Elenbaas

Clifford D Borowicz

Ian E Schroeder

Eric Dwight Blohm

Chilip Chan

David Douglas Boes

Roozbeh Chavoshian

Joseph Lee Sweetin, Iii

Josephine LaCoe

Steven Paul Walker

Paul W Dees

Jerry Deming Chungbin

Troy Winfree

Gary Mark Buckus

Ian C Burford

Farshad Forouhar

Christopher Wayne Fay

Keith Townsend

Charles E Jokisch

Rickie Hansken

Benjamin Joseph Palmer

Kevin M Uhl

Warren H Steyaert

Charuhas M Soman

Daniel E McGinty

William J Moon

Steven Scott Heer

Ryan A Fear

Jeffrey Michael Olds

Mark John Herzberg

Joshua Charles Modrzynski

John B Winn

Matthew S Elenbaas

Michael Addington

Renato Felicio

Charuhas Soman

Daniel E Mcginty

David D Boes

A method performed by a computing system that facilitates formation of an object comprises receiving manufacturing process data associated with an object to be formed via a drape-forming operation. The computing system receives a parametric model of the object. The parametric model facilitates specification of a radius of a fillet within a region associated with the object. The computing system determines, based on the parametric model of the object, a unit vector field associated with a surface of the object and the manufacturing process data. The computing system adjusts the radius of the fillet of the parametric model within the region to reduce an average divergence of the vector field to a minimum amount, and communicates output data associated with an adjusted parametric model to equipment configured to form a mandrel that facilitates formation of the object.

Method and system for optimizing the shape of an object to facilitate wrinkle and stress reduction

Composite assemblies are described that include composite spars that are co-cured with one or more sacrificial members on their flanges, forming an integrated sacrificial surface for the composite spars. In one embodiment, the composite assembly includes a composite spar having a web and flanges that project from sides of the web. The composite assembly further includes a sacrificial member of composite materials co-cured with the composite spar on an outer surface of at least one of the flanges. In addition, the sacrificial member has an outer surface that has been machined into conformance with an inner surface of at least one skin panel for an aircraft structure to form a contact surface with the at least one skin panel.

Composite spars with integrated sacrificial surfaces

A manufacture configured to and process for inhibiting, from wear, a lock in a latching system comprising: a gland surrounding an actuator translating the lock through: a first fixed lock receptor and a moveable lock receptor. The manufacture and process include: inhibiting a skewing, of a lock central axis of the lock with the lock translating through the first opening and the opening in the moveable lock receptor, away from substantially aligning with: a first central axis of a first opening of the first fixed lock receptor, and an actuator central axis of the actuator, via fitting a first translation guide into the first fixed lock receptor. Also included is inhibiting: wear of a gland around an actuator in the lock while translating, and leaking, past the gland, of an actuator fluid within the lock; and skewing of an actuator central axis of the actuator.

Manufacture and process for inhibiting wear in a latch system

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

A breakaway support configured to selectively release an actuator from a fitting and a method of providing the breakaway support. The breakaway support includes a race positioned between the actuator and the fitting. The second end of the actuator is connected to the fitting via a ball joint is positioned within the race. The ball joint permits the actuator to pivot about the ball joint in a vertical plane between a first position and a second position. The breakaway support includes a first knuckle that causes the actuator to release from the fitting when the actuator moves in a first direction beyond the first position. A portion of the fitting or a second knuckle may cause the actuator to release from the fitting when the actuator moves in a second direction beyond the second position. A portion of the actuator may break to release the actuator from the fitting.

Monolithic outboard gear beam support fitting

Stop pads for aircraft folding wing tips are described herein. An example aircraft wing includes a fixed wing portion and a wing tip moveably coupled to the fixed wing portion about a hinge axis. The wing tip is moveable between an extended position and a folded position. The aircraft wing also includes a first stop pad coupled to the fixed wing portion, the first stop pad having a first contact surface, and a second stop pad coupled to the wing tip, the second stop pad having a second contact surface. The first and second contact surfaces are to engage each other when the wing tip is in the extended position. A contact plane between the first and second contact surfaces is coplanar with the hinge axis.

Stop pads for aircraft folding wing tips

A folding wing hinge for a wing having a fixed wing portion and a folding wing portion, the folding wing hinge including a hinge pin including a hinge pin spline and having a first longitudinal axis, an input fitting coupled to one of the fixed wing portion and the folding wing portion, the input fitting including an input fitting spline and a second longitudinal axis, and a spline coupling member having a coupling spline configured to couple with the hinge pin spline and the input fitting spline so that the first longitudinal axis moves relative to the second longitudinal axis by a first predetermined amount of movement.

Folding wing hinge, aircraft and method therefor

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 inspection system is presented. The inspection system comprises a remotely controllable imaging assembly and a scale reticle. The remotely controllable imaging assembly includes a camera and a lens system. The lens system includes a tunable-focus lens and a magnifying lens between the camera and the tunable-focus lens. The scale reticle is positioned within a sight line of the camera of the imaging assembly such that the scale reticle is between the imaging assembly and a target.

Inspection system for alignment in restricted volumes

Growing community of inventors

Edmonds, WA, United States of America

Eric Sean Kamila