Composite sections for aircraft fuselages and methods and systems for
manufacturing such sections are disclosed herein. A composite section
configured in accordance with one embodiment of the invention includes a
skin and at least first and second stiffeners. The skin can include a
plurality of unidirectional fibers forming a continuous surface extending
360 degrees about an axis. The first stiffener can include a first flange
portion bonded to an interior surface of the skin and a first raised
portion projecting inwardly and away from the interior surface of the
skin. The second stiffener can include a second flange portion bonded to
the interior surface of the skin and a second raised portion projecting
inwardly and away from the interior surface of the skin. A method for
manufacturing a section of a fuselage in accordance with one embodiment
of the invention includes positioning a plurality of uncured stiffeners
on a mandrel assembly. The method can further include applying a
plurality of fiber tows around the plurality of uncured stiffeners on the
mandrel assembly.