초록 ▼

An apparatus and method for forming an aircraft fuselage having at least one doubly curved portion. A plurality of fuselage panels are extruded with integrally formed stiffening portions extending preferably longitudinally the full length of each fuselage panel. The stiffening portions are further f

An apparatus and method for forming an aircraft fuselage having at least one doubly curved portion. A plurality of fuselage panels are extruded with integrally formed stiffening portions extending preferably longitudinally the full length of each fuselage panel. The stiffening portions are further formed so as to be generally parallel to one another. The fuselage panels are then formed into skin panels having a desired curvature and trimmed into gores, and the stiffening portions trimmed at end portions that run out toward longitudinal edges of the panels. When adjacent panels are affixed together, the stiffening portions run out toward longitudinal edges of adjacent panels. The longitudinal edges are secured by splice longerons which are riveted or welded to the longitudinal edges of the skin panels. Independent fastening members are then secured to the stiffening portions and the splice longerons at the points where the stiffening portions run out to positions closely adjacent the splice longerons. The apparatus and method permits aircraft fuselages having doubly curved portions to be formed from extruded panels which is more cost efficient and makes use of a greater percentage of raw materials than conventional methods of machining such panels out of non-near-net stock such as plate.

대표청구항 ▼

[ What is claimed is:] [1.] 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 s

[ What is claimed is:] [1.] 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.