Patent ID: 7282107

Claim:
A method for fabricating a section of an aircraft fuselage using a plurality of material delivery heads to apply composite materials on a mandrel surface of a mandrel having an axis, wherein the mandrel is rotatable relative to said plurality of material delivery heads, and wherein the mandrel surface substantially conforms to the section of the aircraft fuselage, the method comprising steps of: applying, via the material delivery heads, composite material along the mandrel surface during fabrication of the section of the aircraft fuselage; moving at least some of said material delivery heads relative to the mandrel surface during application of the composite material by the material delivery heads during fabrication of the section of the aircraft fuselage; and individually adjusting positions of at least some of said material delivery heads relative to the mandrel surface and the other material delivery heads during application of the composite material by the material delivery heads during fabrication of the section of the aircraft fuselage.