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The book addresses computational methods for solving the problem of
vibration, response, loads and stability of a helicopter rotor
blade modeled as a rotating beam with flap or out-of-plane bending.
The focus is on explaining the implementation of the finite element
method in the space and time domain for the free vibration,
aeroelastic response and stability problems. The use of Floquet
analysis for the aeroelastic stability analysis of rotor blades is
also shown. The contents of the book will be useful to researchers
in aerodynamics and applied mechanics, and will also serve well
professionals working in the aerospace industry.
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