Abstract This chapter presents modal analysis of isolated blades as well as full four-bladed helicopter main rotor. A finite element model (FEM) of the blade is proposed and verified with results of modal tests as well as with calculations with custom software for modal analysis of composite blades designed by PZL Swidnik. Modal analysis is performed for blades in as-is configuration and with gurney flap actuation mechanism installed. Modal analysis of rotating main rotor for cyclic, collective, and scissors vibration modes is performed for blades with and without active gurney flap system. The effect of blade structural modifications on its natural frequencies is shown.
Modal Analysis of PZL-W-3/W-3A Sokol Main Rotor
2017-01-01
10 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
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