Method for Frabricating an Aircraft Fuselage in Composite Material

A method of fabricating an aircraft fuselage comprising an internal framework which constitutes at least partially a mold for fabricating an outer skin made of composite material, this internal framework being wrapped with an outer skin of composite material, the method comprising:

• assembling a plurality of frames and structural parts to form the internal framework of the fuselage,
• installing shell fixtures in a space between at least two frames of the framework and fastening each of these fixtures onto the two frames by means of detachable fastening, to 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.