COMPARATIVE ANALYSIS OF A STRUCTURAL REPAIR IN A LIGHT AIRCRAFT'S FUSELAGE USING FINITE ELEMENT METHOD
André Beires1; Thiago Guimarães1; Giuliano Venson1; Adriano Couto2
1 Federal University of Uberlândia; 2 Algar Aviation
doi:10.20906/CPS/CILAMCE2015-0314
Resumo
The purpose of this paper is to analyze the structural repair that was designed for an aircraft, which accidentally landed without landing gears and damaged the fuselage lower skin near wing junction. As the manufacturer of the aircraft in discussion doesn't provide a structural repair solution to evaluate the repair design, a comparative finite element analysis (FEA) was done in order to check airworthiness conditions, load path and stress distribution between the original structure (without repair) and the modified structure (with repair). The whole analysis process involves: geometry construction of all components in the affected area including the attachment parts, finite element model creation, structural analysis comparison and the compliance demonstration with FAR 23 structural requirements.
Palavras-chave: structural repair; fuselage lower skin; finite element analysis; airworthiness condition; stress distribution; load path; geometry construction