Abstract
Abstract Using of different fidelity computational models and relations between them in the multidisciplinary design system is considered. A structural design procedure and optimization methods for aeroelastic design of aircraft and wind tunnel models are discussed. An application of the topology-based optimization together with the two-level structural sizing method is considered. Main stages of the approach to synthesis of structural layouts of aircraft components are described. Some numerical examples of analysis and aero-structural optimization of aircraft wings are considered to demonstrate the proposed methods and algorithms. The accuracy, reliability and efficiency of using of the considered structural models at design studies are discussed.
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