Patent ID: 8182628
Filing Date: 2012-05-22
Classification: B29C,B29D,B29L,B64C,Y02T,Y10T

Abstract:
1. A method for manufacturing a barrel section of an aircraft fuselage, the method comprising: positioning a plurality of uncured composite stiffeners on a mandrel assembly, the plurality of stiffeners extending substantially parallel to a longitudinal axis of the barrel section; holding the plurality of stiffeners in position on the mandrel assembly by wrapping uncured composite fabric sheets 360 degrees around the mandrel assembly and over the stiffeners; applying a plurality of uncured composite fiber tows over the uncured composite fabric sheets to form a continuous skin extending 360 degrees around the mandrel assembly; and cocuring the stiffeners, the composite fabric sheets, and the plurality of fiber tows on the mandrel assembly to bond the stiffeners to an interior surface of the composite fabric sheets.