초록 ▼

A shell component for an aircraft fuselage includes a fuselage skin panel, a plurality of stringers extending in an aircraft lengthwise direction, and a plurality of frames extending crosswise relative to the stringers. The stringers and the frames are respectively welded onto the skin panel with th

A shell component for an aircraft fuselage includes a fuselage skin panel, a plurality of stringers extending in an aircraft lengthwise direction, and a plurality of frames extending crosswise relative to the stringers. The stringers and the frames are respectively welded onto the skin panel with the addition of a weld filler material. Each frame includes a frame root portion and a frame profile portion connected to each other. The frame root portion has cut-out notches receiving the stringers passing therethrough. The frame root portion is welded to the skin panel at the areas between the cut-out notches, and may be welded to the respective stringer in each cut-out notch. The stringers and frames are fabricated from webs and flanges, whereby a premanufactured grid of flanges may be used. The result is a very strong, yet simple shell component structure, that may be manufactured with a simple welding process, at a low cost and with low effort.

대표청구항 ▼

1. 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

1. 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.