Abstract
Topology and Structural Optimization methods have been applied in order to support the development of the A400M rear fuselage. This paper first gives an overview about the optimization assisted design process implemented at EADS Military Aircraft. The optimization models and the topology optimization results for A400M rear fuselage will be described afterwards. The topology optimization has been applied at a system level, in order to determine an optimum concept for the complete A400M rear fuselage. These results have then been refined for the internal support structure and further detailed for a single tail-plane frame. The sizing of a fuselage requires consideration of the post-buckling behavior. The. paper explains the post-buckling analysis capabilities, which have been implemented in the optimization procedure LAGRANGE. The sizing optimization models applied with the ongoing A400M sizing optimization activities are briefly discussed. Topology optimization methods and applications have experienced rapid development within the last few years. Several commercial codes offering topology optimization capabilities have been developed and mainly applied to structures in the mechanical engineering and automotive area. The tools have demo nstrated their power to determine optimum load paths and weight optimum designs for complex comp onents. The huge weight-saving potential and the relatively easy handling of the topology optimization tools have strongly supported their rapid dissemination. The number of applications in aerospace has been fairly l up to now. However, positive experiences have been gained with the application of t opology and structural optimization methods in different aerospace projects at EADS Military Aircraft. The development of the A400M Rear Fuselage has been supported by optimization methods during the concept- and pre-design phase. The paper gives an overview about the optimization process and the results achieved within this project.
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