Patent ID: 6364250
Filing Date: 2002-04-02
Classification: B64C

Abstract:
A shell component for an aircraft fuselage comprising:a fuselage skin panel fabricated of a weldable aluminum alloy; a plurality of stringer webs that are spaced apart from each other, respectively extend in a longitudinal direction along said fuselage skin panel, and are welded respectively by a first continuous weld joint onto said fuselage skin panel; a plurality of frame webs that are spaced apart from each other, respectively extend in a crosswise direction relative to said longitudinal direction, and are welded respectively by a second continuous weld joint onto said fuselage skin panel; a stringer-frame grid comprising stringer flanges extending in said longitudinal direction and frame flanges extending in said crosswise direction, wherein said stringer flanges are respectively welded onto said stringer webs by respective third continuous weld joints and said frame flanges are respectively welded onto said frame webs by respective fourth continuous weld joints; and a plurality of frame heads welded onto said frame flanges opposite said frame webs by respective fifth continuous weld joints.