Detailed design of a lattice composite fuselage structure by a mixed optimization method

Liu, D., Lohse-Buschl, H., Toropov, V., Huhne, C. and Armani, U. (2016) Detailed design of a lattice composite fuselage structure by a mixed optimization method. Engineering Optimization, 48 (10). pp. 1707-1720. ISSN 0305-215X

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Abstract

In this paper, a procedure for designing a lattice fuselage barrel has been developed and it comprises three stages: first, topology optimization of an aircraft fuselage barrel has been performed with respect to weight and structural performance to obtain the conceptual design. The interpretation of the optimal result is given to demonstrate the development of this new lattice airframe concept for the fuselage barrel. Subsequently, parametric optimization of the lattice aircraft fuselage barrel has been carried out using Genetic Algorithms on metamodels generated with Genetic Programming from a 101-point optimal Latin hypercube design of experiments. The optimal design has been achieved in terms of weight savings subject to stability, global stiffness and strain requirements and then was verified by the fine mesh finite element simulation of the lattice fuselage barrel. Finally, a practical design of the composite skin complying with the aircraft industry lay-up rules has been presented. It is concluded that the mixed optimization method, combining topology optimization with the global metamodel-based approach, has allowed to solve the problem with sufficient accuracy as well as provided the designers with a wealth of information on the structural behaviour of the novel anisogrid composite fuselage design.

Item Type: Article
Uncontrolled Keywords: topology optimization,parametric optimization,metamodel,aircraft fuselage design
Faculty \ School: Faculty of Science > School of Mathematics
Depositing User: Pure Connector
Date Deposited: 08 Jan 2016 12:01
Last Modified: 15 Oct 2020 23:47
URI: https://ueaeprints.uea.ac.uk/id/eprint/56158
DOI: 10.1080/0305215X.2015.1125262

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