Exact strip analysis and optimum design of aerospace structures

Kennedy, David ORCID: https://orcid.org/0000-0002-8837-7296 and Featherston, Carol Ann ORCID: https://orcid.org/0000-0001-7548-2882 2008. Exact strip analysis and optimum design of aerospace structures. Presented at: RAeS/CEAS Aircraft Structural Design Conference, Liverpool, UK, 14 - 16 October 2008. Proceedings of RAeS/CEAS Aircraft Structural Design Conference. pp. 1-12.

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Abstract

Minimisation of airframe mass reduces the costs of materials and manufacturing, as well as fuel consumption and atmospheric emissions. Fast, reliable analysis tools are required during preliminary design, when many alternative configurations and load cases are considered. The modelling and computational costs of finite element analysis are avoided by employing exact strip solutions of the governing differential equations, using the Wittrick-Williams algorithm to solve the resulting transcendental eigenproblems of buckling and vibration. This paper reviews recent enhancements to the exact strip method for analysis and optimum design of aerospace structures, using the specialist software VICONOPT. Lighter composite panels can be designed by obtaining reliable estimates of the reduced postbuckling stiffnesses when loaded in compression and shear. Further advances include discrete optimisation of layer thicknesses to allow for practical composite manufacturing constraints, vibration constraints, and a newly extended multi-level interface combining finite element analysis of a whole wing with exact strip postbuckling design of individual panels.

Item Type:	Conference or Workshop Item (Paper)
Date Type:	Publication
Status:	Published
Schools:	Engineering
Subjects:	T Technology > TL Motor vehicles. Aeronautics. Astronautics
Last Modified:	06 Jan 2024 03:52
URI:	https://orca.cardiff.ac.uk/id/eprint/45381

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