000001853 001__ 1853
000001853 005__ 20141118153452.0
000001853 04107 $$acze
000001853 046__ $$k2011-05-09
000001853 100__ $$aČečrdle, J.
000001853 24500 $$aLANDING SHOCK AEROELASTIC RESPONSE ANALYSIS OF UTILITY AIRCRAFT 

000001853 24630 $$n17.$$pEngineering Mechanics 2011
000001853 260__ $$bInstitute of Thermomechanics AS CR, v.v.i., Brno
000001853 506__ $$arestricted
000001853 520__ $$2eng$$aThe 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.

000001853 540__ $$aText je chráněný podle autorského zákona č. 121/2000 Sb.
000001853 653__ $$aAeroelasticity, aeroelastic response, landing shock response, EV-55 aircraft.

000001853 7112_ $$aEngineering Mechanics 2011$$cSvratka (CZ)$$d2011-05-09 / 2011-05-12$$gEM2011
000001853 720__ $$aČečrdle, J.
000001853 8560_ $$ffischerc@itam.cas.cz
000001853 8564_ $$s1243834$$uhttps://invenio.itam.cas.cz/record/1853/files/p015.pdf$$y
             Original version of the author's contribution as presented on book, page 99.
            
000001853 962__ $$r1835
000001853 980__ $$aPAPER