LANDING SHOCK AEROELASTIC RESPONSE ANALYSIS OF UTILITY AIRCRAFT
Abstract eng: 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.
Publisher:
Institute of Thermomechanics AS CR, v.v.i., Brno
Conference Title:
Conference Title:
Engineering Mechanics 2011
Conference Venue:
Svratka (CZ)
Conference Dates:
2011-05-09 / 2011-05-12
Rights:
Text je chráněný podle autorského zákona č. 121/2000 Sb.
Record appears in:
Record created 2014-10-24, last modified 2014-11-18
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