COMPOSITE BARREL SECTIONS FOR AIRCRAFT FUSELAGES AND OTHER STRUCTURES, AND METHODS AND SYSTEMS FOR MANUFACTURING SUCH BARREL SECTIONS

摘要

A section of an aircraft fuselage comprises a sheet of composite fabric forming at least a first portion of a skin extending continuously for 360 degrees about a longitudinal axis of the section. Fiber tows are individually applied over the sheet of composite fabric. Each of the individual fiber tows has a width that is narrower than the width of the composite fabric sheet. The fiber tows form at least a second portion of the skin. A first longitudinal stiffener has a first flange portion bonded to an interior surface of the sheet of composite fabric during a cocuring process. At least a second longitudinal stiffener is spaced from the first stiffener. A circumferential frame section extends across the first and second stiffeners, and is mechanically fastened to the skin and the first and second stiffeners after the cocuring process. The section remedies deficiencies of prior art aircraft fuselage sections.