Proceedings Vol. 17 (2011)
ENGINEERING MECHANICS 2011
May 9 – 12, 2011, Svratka, Czech Republic
Copyright © 2011 Institute of Thermomechanics, 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 99 - 102, full text
The paper deals with the aircraft landing shock aeroelastic response analysis. The analysis was performed as a part of the aircraft certification in order to fulfill the CS / FAR 23 § 23.479(d) regulation requirement. The FE model used for the former flutter analyses was utilized. The excitation force was based on the landing gear drop test results. The airflow parameters were set according the aircraft flight envelope and the regulation statements. The modal transient aeroelastic response solution was employed. The structure response was evaluated at the engine center of gravity and the selected points on the wing.
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