A STUDY OF THE DYNAMIC MOTIONS OF HINGELESS ROTORED HELICOPTERS.
ARMY ELECTRONICS COMMAND FORT MONMOUTH N J
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The hingeless rotor is modeled as a system of thin cantilevered members, infinitely stiff in torsional and chordwise bending, executing pure elastic flapwise bending. It is shown that to model the rotor from hover thru high speed flight, the motions of a blade must be represented by its first two natural modes of flapwise bending. For this blade model, it is also shown that the hub moment developed is linearly related to the tip path plane tilt in hover but that the relationship becomes markedly nonlinear with increasing forward speed. Consideration is also given to the effects of a non-uniformly distributed induced velocity field. Th characteristics of the Lockheed gyro stabilization system are compared to those of the Bell gyro system and a conventional electronic stabilization system utilizing body mounted sensors. Author