Topology/sizing optimization of aicraft structural components

Abstract eng:
The application of energy-based topology optimization methods together with two-level design method for determination of structural sizes is considered. Main stages of such evolutionary approach to synthesis structural layouts of aircraft components are described. The approach is demonstrated on the example of structural optimiza tion of helicopter wing and tail boom. It is shown that sizing optimization with including strength/buckling/aeroelasticity constraints results in to the design with significantly less weight compared with the one obtained by conventional approach.

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