The Boeing Company

Francis E Andrews

Max Urban Kismarton

William John Koch, Iv

Chun-Liang Lin

Grant Brian Thomas

Wendell C K Choy

Devin Knowles

Patrick Woodard

Max U Kismarton

William J Koch

A hybrid carbon/fiberglass structural component or beam for an aircraft is constructed with layers of strips of glass fibers interspersed with layers of strips of unidirectional carbon fibers where the carbon fibers are oriented only in alignment with or along the longitudinal direction of the length of the beam thereby adding strength and stiffness to the beam while reducing weight and manufacturing costs.

Hybrid carbon/fiberglass structural component for an aircraft

A composite laminate, method of forming same, and use for same are disclosed. One example of a composite laminate has multiple layers or plies (A-E) composed of generally parallel reinforcing fibers (A-E) embedded in a matrix (M). The reinforcing fibers have orientations in the ranges of 3 to 8 degrees, &#x2212;3 to &#x2212;8 degrees, 10 to 40 degrees, &#x2212;10 to &#x2212;40 degrees, and approximately 90 degrees, the orientations being with respect to a predetermined axis (), such as an axis of tension (T). A method of manufacturing a composite laminate includes laying a resin and fibers having these orientations and then curing the resulting laminate. One example of a use is for the skin on the fuselage or wing of an aircraft.

Split resistant composite laminate

In accordance with the present invention an aircraft stringerless fuselage structure is provided comprising an impact compliant outer skin having a plurality of resin impregnated skin fibers forming an outer skin surface, an inner stringerless skin surface, and a skin thickness. A plurality of stiffeners is included, each comprising a plurality of resin impregnated stiffener fibers integrated into the inner stringerless skin structure. The plurality of resin impregnated skin fibers are not aligned with the plurality of resin impregnated stiffener fibers.

Single piece fuselage barrel

Compliant stiffener for aircraft fuselage

The present disclosure is generally directed to an aircraft including an aircraft body having a number of body frame members on an outboard portion of the aircraft body, a wing assembly extending through a portion of the aircraft body. At least one pair of an attachment member and an attachment strap member are fixedly attached to an upper surface of the wing assembly proximate the portion of the aircraft body at a location of one of the number of body frame members. A number of fasteners fixedly attach the aircraft body via at least one body frame member to one attachment member and a corresponding attachment strap member, thereby securing the aircraft body to the wing assembly.

Methods and apparatus for attaching an aircraft wing assembly to an aircraft body

The present disclosure is generally directed to an aircraft body including a fuselage skin on an outboard member of the aircraft body and a wing box extending through a member of the aircraft body. The wing box being enclosed and capable of being pressurized is fixedly attached at an outer surface to at least one pair of an attachment member and an attachment link member that is fixedly attached to the aircraft body.

Growing community of inventors

Everett, WA, United States of America

Francis E Andrews