The Boeing Company

Patrick Woodard

Max Urban Kismarton

Jiangtian Cheng

Forouzan Behzadpour

Derek Paul Vetter

Francis E Andrews

Mark M Bleazard

Michael Chih-Huan Wang

Elizabeth Rose Benson

An airfoil coupling system includes plural airfoil coupling structures, each of which includes a body having a horizontal flange with a first coupling interface that is coupled with panels of an airfoil of an aircraft. The first coupling interface extends between first and second ends in a first direction, and between third and fourth ends in a second direction. The body also includes a vertical flange having a mating end that is coupled with the horizontal flange. The vertical flange includes a second coupling interface that is coupled with a rib of the airfoil. The second coupling interface extends between fifth and sixth ends in the second direction, and between mating and free ends in a third direction. Each of the airfoil coupling structures are disposed at different locations along a length of the rib between a leading edge and a trailing edge of the rib.

Airfoil coupling systems and methods

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

A composite structure is provided. The composite structure includes a first stiffener, a second stiffener, and an intermediate structure positioned between the first and second stiffeners such that the first stiffener is coupled to a first side of the intermediate structure, and such that the second stiffener is coupled to a second opposing side of the intermediate structure. A first radius gap is defined at least partially between the first stiffener and the intermediate structure, and a second radius gap is defined at least partially between the second stiffener and the intermediate structure.

Composite structure and methods of forming thereof

Growing community of inventors

Renton, WA, United States of America

Patrick Woodard