Using simplified model of hub fuselage structure, theoretical analysis is made of response of hub and fuselage of helicopter in flight to harmonic forces transmitted by rotor blades to hub both in, and normal to, plane of rotation; expressions derived for vibration amplitudes of mass points.
Vibrations of helicopter rotor-fuselage system induced by main rotor blades in flight
Am Soc Mech Engrs -- Paper
American Society of Mechanical Engineers -- Meeting S-7 ; 1955 Vibrations
1955
6 pages
Aufsatz (Konferenz)
Englisch
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