Proceedings Vol. 21 (2015)
ENGINEERING MECHANICS 2015
May 11 – 14, 2015, Svratka, Czech Republic
Copyright © 2015 Institute of Theoretical and Applied Mechanics, Academy of Sciences of the Czech Republic, v.v.i., Prague
ISSN 1805-8248 (printed)
ISSN 1805-8256 (electronic)
list of papers scientific commitee
pages 136 - 137, full text
The detail topometrical optimization of the critical wing part of the aircraft is presented in this article. The integral lower wing structural panel of the aircraft in the CS-23 Commuter category is selected for the optimization. The first case demonstrates significant weight savings using the modern FE optimization methods for determined structural constraints. The practical aircraft operation and additional regulation requirements affect optimization constraints in the second case. The detail optimization also consists of the FE model validation, stress analyses and complex load capacity analyses, which are necessary for designed structural modifications with an optimal stress distribution.
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