Proceedings Vol. 16 (2010)
ENGINEERING MECHANICS 2010
May 10 – 13, 2010, Svratka, Czech Republic
Copyright © 2010 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 17 - +13p., full text
Submitted paper deals with the aileron flutter of the ultra-light aircraft. It gives an assessment of influence of the additional installation of the tab regarding the aircraft aileron flutter characteristics. The necessary actuation system stiffness and the aileron flapping frequency to ensure the stability at the aircraft maximal speed are evaluated. The work was motivated by the M-7 ultra-light aircraft accident in the western Bohemia in 2006. The FE model was prepared by the optimization approach. The design variables were mass and stiffness characteristics, design responses (constrains and objective functions) were given from the ground vibration tests data.
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