INTEGRALLY STIFFENED AXIAL LOAD CARRYING SKIN PANELS FOR PRIMARY AIRCRAFT STRUCTURE AND CLOSED LOOP MANUFACTURING METHODS FOR MAKING THE SAME

摘要

A skin panel is provided that includes an axial load carrying skin and at least one stiffener integrally engaged with the axial load carrying skin. The stiffener includes at least one of a stringer, a frame outer chord, and a flange disposed at about an edge of the skin panel. The skin and the at least one stiffener are integrally formed as a single component structure. Accordingly, the invention provides integrally stiffened axial load carrying skin panels suitable for use in any of a wide range of aircraft structures that employ axial load carrying skins, such as fuselages, wings, empennages, pressure bulkheads, wing carry through sections, escape hatches, passenger doors, cargo doors, and access hatches and panels, among others.