Abstract
The nonlinear, large amplitude nonrotating free vibration of composite helicopter blades under large static deflection is investigated analytically and experimentally. A new model capable of handling large amplitudes as well as large deflections was developed based on the use of Euler angles and a harmonic balance, finite difference solution of the basic large deflection equations. The behavior of the first and second bending, the first fore-and-aft, and the first torsional modes of [0/90]3s and [45/0]$ graphite/epoxy flat beams were explored analytically as tip static deflection and tip amplitudes vary* Free vibration tests of several different lay-ups of composite blades show good agreement between theory and experiment. It is found that both large static deflection and large amplitudes can affect the fore-and-aft and torsional modes significantly, but bending modes are not influenced much by the geometrical nonlinearities.
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