Patent ID: 6105902
Filing Date: 2000-08-22
Classification: B23K,B64C

Abstract:
A method for constructing a fuselage portion of an aircraft, wherein the fuselage includes a portion having a non-constant diameter, said method comprising the steps of:extruding a plurality of panels, each of said panels being formed with at least one integrally formed stiffening portion extending longitudinally therealong generally parallel to a longitudinal edge of said panel;forming each of said panels into a fuselage skin panel having a portion with a non-constant radius of curvature;trimming each of said fuselage skin panels such that when secured together said fuselage skin panels form a section of said aircraft fuselage having a non-constant diameter, and further such that said stiffening portion of each said fuselage skin panel runs out to a longitudinal edge of its associated said fuselage skin panel;securing said longitudinal edges of adjacent pairs of said fuselage skin panels to one another by a plurality of splice longerons; andsecuring each said stiffening portion to a portion of said longeron by a fastening member.