The design of composite fuselage panels with large cut-outs is a complex task with a huge number of design variables and constraints. Therefore, minimum weight solutions often can be achieved only by the application of numerical optimization methods. In order to handle this kind of problem the optimization code GEOpS has been developed, which is based on evolutionary algorithms. As an example for the applicability of the developed approach optimization results for a test panel are presented, which is made of carbon fibre reinforced plastics (CFRP) and has a cut-out representing a door opening. The obtained results show that the developed code is a useful and reliable tool for designing complex aircraft structures made of composite materials.
Structural optimization of composite aircraft panels with large cut-outs
2008
9 Seiten, 5 Bilder, 2 Tabellen, 6 Quellen
Conference paper
English
Structural Optimization of Composite Aircraft Panels with Large Cut-Outs
British Library Conference Proceedings | 2008
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