Project Title:Structural Analysis of Fuselage with Lattice Structure USING ANSYS.Prole! State!ent:The design of a fuselage structure for any aircraft is very essential. The fuselage structure for business jet aircraft carries stringers, frames, floor beam and outer skin. The fuselage structure for heavy passenger aircraft carries a wide numerous structural parts such as bulkheads, longerons, frames, stringers, flat plate, outer skin etc. Nowadays, stiffened shell structure was used in fuselage structure. The lattice structure is a complex design which carries an individual structural components of actual fuselage structure seen. In this project, the lattice structure was adapted to the aircraft instead of stiffened shell structure. The design of the lattice structure is carried out and the static structural analysis is carried out in AN! to find the stress and deformation due to the load.Project Intent: ". #nderstand the concept of fuselage $attice structure.%. The fuselage structure consists primarily of frames, stringer and external skin is basically designed to resistthe shears and bending moments resulting from air loads and inertial loads. #pon internal pressuri&ation,however,thistypeofstructurebecomesaninefficient pressurevessel duetoprimarilytostringerandframe bending. The intent is to understand the structural effect of pressuri&ation on fuselage structure.'.(erform finite element analysis to find thea) tress *istribution on tringersb) tress *istribution with kin and tringersc) tress *istribution with tringers and +loorSco"e of "roject:The cope of ,ork is as detailed below,". (roblem study - input data finali&ation%. .oncept study of fuselage $attice structuresubjected to shears and bending moments resulting from airloads and inertial loads. '.'d model generation of the fuselage model /.tructural Analysis using Ansys (latform 0.(roject documentation with plots1sketches - result study observationIn"ut #etails:The Input *etails provides are, 2asic geometry - specifications of sample model Theory reference for fuselage $attice structure 3aterial pecification45..o *ensity45..o Tensile trength4 55o !oung6s 3odulus455o (oisson6s 7atio45.. 8ther loads455 +9A of+uselage with $attice tructuresubjected to shears and bending moments resulting from airloads and inertial loads using AN!.3ethodology 3odelling of +uselage structure. election of suitable material properties. election of suitable elements from AN! element library. 3eshing of the structure using different mesh methods. 8nce meshing is completed, solving the problems using appropriate loads and boundaryconditions.8btaining the result and plotting in AN! post processor.