Patent ID: 6595467
Filing Date: 2003-07-22
Classification: B23K,B64C

Abstract:
An aircraft fuselage structural shell component comprising:a skin sheet; a plurality of stiffening profile members arranged and joined onto said skin sheet, at least partly by respective weld joints, and wherein said stiffening profile members each extend lengthwise in a lengthwise direction of said stiffening profile members and each respectively comprise at least one profile member web; and a plurality of strengthening elements that respectively extend continuously in said lengthwise direction along respective ones of said profile member webs, and that are respectively non-integrally secured onto said respective profile member webs, and that are respectively discrete non-integral components relative to said profile member webs with respective non-integral boundary interfaces therebetween adapted to hinder any crack formed in said skin sheet or said profile member webs from propagating into said strengthening elements so that said strengthening elements respectively hold together said stiffening profile members even if one or more cracks form in said stiffening profile members.