Patent ID: 8220154
Filing Date: 2012-07-17
Classification: B29C,B29L,B64C,B64F,Y02T,Y10T

Abstract:
1. A method of fabricating an aircraft fuselage comprising an internal framework which at least partially comprises a mold for fabricating an outer skin made of composite material, the internal framework being wrapped with an outer skin of composite material, the method comprising the following sequential steps: assembling a plurality of frames and structural parts together, directly around a chuck resting on a frame structure to form the internal framework of the fuselage, installing shell fixtures in a space between at least two frames of the internal framework and fastening each of the shell fixtures onto the two frames by means of detachable fastening, to fill spaces between frames and obtain a solid structure depositing a layer of composite material around the solid structure, firing the solid structure covered with the layer of composite material, and removing the shell fixtures to obtain the internal framework covered with the outer skin .