The fuselage geometry is setup parametrical and modeled as a simplified tube with variable crosssection without cut-outs and wing box, and it is divided in bays and skin panels. The goal of this project is to develop an analytic design, analysis and evaluation tool for both metal and composite fuselage configurations in Visual Basic Application in order to gain insight into the structural performance of these material classes and to estimate the weight and required structural dimensions for both aluminum and composite fuselages. This will give material manufacturers better insight in what properties and performance are specifically needed for materials in aircraft structures. Therefore an evaluation tool is needed for determining the running loads and evaluating the performance of new materials. However material manufacturers, like Tata Steel, are unfamiliar with the determination of running loads and the behavior of materials in fuselage structures. Aircraft manufacturers are responding to this trend and new aerospace materials are introduced to build lighter aircrafts. The strong search for lightweight materials has become a trend in the aerospace industry. Aging aircraft, Multiple site damage, Fuselage fracture and Fatigue. A 3-D FE mesh of a riveted lap joint is also presented. A flat test panel has been designed that demonstrates hoop stress equivalence to the curved fuselage. Analytic techniques have been developed to evaluate stress distributions and to estimate elastic stress intensity factors for flat and curved test panels. Data on basic material properties of interest to the aging aircraft issue have been compiled from existing Literature and from R- curve testing and rivet stiffness testing performed as part of the effort. This report describes the design rationale for the facility, the details of its construction and performance and the design and testing of compatible panels which simulate fuselage structural details. Seven full-sized curved fuselage panels have been built and tested. A dedicated test facility has been designed, built and tested for this purpose.
#Aviation exam crack crack
Understanding predicting, and controlling this crack growth and the ensuing linkup requires analysis and evaluation of the structural parameters in concert with confirmation by testing representative models of the fuselage. Abstract : As the fleet of commercial passenger aircraft is utilized beyond their design Lives, flaws have developed at the rivet holes of fuselage lap joints on some aircraft which can grow and link up into cracks of significant length.
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