The Boeing Company

Gerfried Rudolf Achtner

Young Zeon

Robert Michael Lee

Thomas Dee Hall

Richard L Stark

Ryan M Mahn

Joseph Strachila

Blair Alexandra Lim

Javier Manriquez

Young L Zeon

Thomas D Hall

Systems and methods are provided for consolidating thermoplastic parts. One embodiment is a method of automatically forming a thermoplastic composite structure. The method includes heating a thermoplastic preform to a forming temperature, forming the thermoplastic preform into a thermoplastic part having a desired shape, aligning multiple thermoplastic parts together, and consolidating the multiple thermoplastic parts together while controlling crystallization to form a complex thermoplastic part.

Co-consolidation of thermoplastic parts

A wing includes an upper wing skin, a lower wing skin, and a wing rib positioned between the upper wing skin and the lower wing skin. The wing rib includes: a corrugated composite web comprising a wave pattern and a first fitting coupling said corrugated composite web with one of said upper wing skin and said lower wing skin.

Wing rib, wing having wing rib, and method for manufacturing the same

A wing or stabilizer of an aircraft. The wing or stabilizer comprises a box portion, comprising at least one spar and an outer skin coupled to the at least one spar. The wing or stabilizer also comprises at least one panel, comprising an outer face-sheet and an inner face-sheet. In a fore-aft direction the outer face-sheet terminates at an outer free edge. In the fore-aft direction the inner face-sheet terminates at an inner free edge. The at least one panel also includes a core sandwiched between the outer face-sheet and the inner face-sheet. The inner face-sheet comprises a cantilevered portion. The cantilevered portion defines the inner free edge. The cantilevered portion is fastened to the outer skin of the box portion.

Skin-panel interface of an aircraft

A fastener assembly which includes a sleeve which includes a cylindrical construction having a first and second end portions and an outside diameter. The fastener assembly further includes a washer associated with the sleeve wherein the washer includes a body which defines a first side and an opposing second side and defines an opening which extends from the first side toward the second side. The opening defines a diameter greater than the outside diameter of the sleeve and the body defines a recess which has a diameter greater than the diameter of the opening wherein the recess extends from the second side toward the first side such that the recess and the opening are in communication with one another. A method for using this fastener assembly is also provided.

Hole-filling sleeve and washer design for bolt installation

Apparatus and method for joining composite structures of aircrafts are disclosed. An example apparatus includes an inboard composite wing panel having a first end portion configured to be coupled to upper and lower inboard fittings composed of a metallic material and an outboard composite wing panel having a first end portion configured to be coupled to upper and lower outboard fittings composed of a metallic material. A side of body rib has a plate shaped first end portion composed of a metallic material. A fuselage frame is configured to be joined at one end of the upper inboard fitting, and the upper and lower inboard fittings and the upper and lower outboard fittings are coupled to the side of body rib at the plate shaped first end portion.

Apparatus and methods for joining aircraft composite structures

A system and method for reducing aerodynamic drag is disclosed. A compression seal is attached to the inboard edges of the stabilizer and elevators of an airplane. The seal blocks airflow in a gap located between these inboard edges and a fuselage. The shape of the compression seal changes as the shape of the gap changes due to movement of the stabilizer and elevators during flight to effectively block airflow through the gap during flight. By blocking the airflow, the seal reduces the aerodynamic drag of the airplane.

Flight control surface seal

In one embodiment, a loading fitting includes at least one of an I, a T, and a J shaped cross-section having a flange attached to at least one supporting structure. In another embodiment, a method is disclosed for attaching a loading fitting to at least one supporting structure.

Growing community of inventors

Mukilteo, WA, United States of America

Gerfried Rudolf Achtner