The Boeing Company
SYSTEM AND METHOD FOR A COMPOSITE PANEL

Abstract:

A method of manufacturing a composite panel for an air vehicle having a predetermined size and shape. The method includes forming a frame including an outer mold line surface and at least one edge extending from the outer mold line surface. The outer mold line surface includes an OML inner surface. The edge includes an edge inner surface and an edge outer surface opposite the edge inner surface. The OML inner surface and the edge inner surface define a cavity. The method also includes positioning a plurality of uncured plies within the cavity. The OML inner surface and the edge inner surface support the uncured plies during a curing process. The method further includes curing the uncured plies using the curing process. A post-cure size and shape of the cured plies and the frame corresponds to the predetermined size and shape without trimming any of the cured plies.