The Boeing Company

Thomas Joseph Gonze

James R Kendall

Brett Ian Lyons

Daniel Joseph Braley

Eric Eldon Deck

Andrew Lawrence Bauer

Trevor E Tucker

Nicole Renee Williams

Garrett B Peters

Gina M Miller

David C Jackson

John W Delconte

Janet Mary Wick

Ryan J Hertel

Core structures () for composite panels () of an aircraft (), composite panels () and aircraft () including the core structures (), and methods () of manufacturing the composite panels () are disclosed herein. The core structures () include a first side (), a second side (), and a connecting region () that interconnects an upper portion () of the first side () with an upper portion () of the second side (). The first side (), the second side (), and the connecting region () at least partially define an antenna housing (), which defines a housing volume () configured to contain an aircraft antenna () of the aircraft (), and an electromagnetic wave transmission region () configured to permit electromagnetic waves to pass therethrough. The electromagnetic wave transmission region () defines a plurality of kite-shaped voids () arranged in a repeating pattern and bounded by a corresponding plurality of walls (), at least 10% of which extends at least substantially perpendicular to a surface () that bounds the electromagnetic wave transmission region ().

Core structures for composite panels of an aircraft, composite panels and aircraft including the core structures, and methods of manufacturing the composite panels

Methods of preparing laminate test samples for subsequent testing, including positioning the test sample within a fixture body, securing the test sample within the fixture body, applying a separating force to urge a first layer portion of the test sample away from a second layer portion of the test sample, and separating the first layer portion from the second layer portion to create a predetermined separation length along the test sample, provided that the predetermined separation length is established by an interaction between the fixture body and the test sample as the first layer portion is separating from the second layer portion.

Preparing laminate materials for testing

A method for determining and verifying ply orientation of composite laminates includes performing a first scan of a prepared edge of a composite laminate using an off-axis inclined light source directing light at a first acute angle to a first area on the prepared edge to produce a first scanned image; rotating an orientation of the off-axis inclined light source relative to the prepared edge, such that the off-axis inclined light source directs light at a second acute angle symmetrically opposite the first acute angle; and performing a second scan of the prepared edge using the off-axis inclined light source directing light at the second acute angle to the first area on the prepared edge to produce a second scanned image. The method includes comparing the first and second scanned images to determine a ply orientation of each ply, and verifying the ply orientation against a baseline ply orientation.

Method and system for determining and verifying ply orientation of a composite laminate

Growing community of inventors

North Charleston, SC, United States of America

Thomas Joseph Gonze