The dynamics of helicopters with dissimilar rotor blades is investigated for hingeless rotors in hover. An elastic blade model with finite element formulation is used. Hub motions are included by modeling the fuselage as a rigid body with pitch and roll degrees of freedom. The aeromechanical stability solution is solved in the fixed frame via Floquet theory. A parametric study of the effects of dissimilarity among blades' structural stiffness, mass, and damping on aeromechanical stability is presented. It is found that a slight reduction in the lag stiffness of one blade stabilizes the regressing lag mode instability.
Dynamics of helicopters with dissimilar blades
AHS Annual Forum ; 1991 ; Phoenix, AZ, United States
01.01.1991
Aufsatz (Konferenz)
Keine Angabe
Englisch
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