A comparison of theory and experiment for the aeroelastic stability of a bearingless model rotor in hover
A comparison of theory and experiment for the aeroelastic stability of a bearingless model rotor in hover
- New search for: Dawson, Seth
- New search for: Dawson, Seth
Three cases were selected for correlation from an experiment that examined the aeroelastic stability of a small-scale bearingless motor rotor in hover. The 1.8 m diameter model rotor included flap, lead-lag, and torsional degrees of freedom, but no body degrees of freedom. The first case looked at a configuration with a single pitch link on the leading edge, the second case examined a configuration with a single pitch link on the trailing edge, and the third case examined a configuration with pitch links on the leading and trailing edges to simulate a pitch link with shear restraint. Analyses from Bell Helicopter Textron, Boeing Vertol, Hughes Helicopters, Sikorsky Aircraft, and the U.S. Army Aeromechanics Laboratory were compared with the data, and the correlation ranged from poor to fair.
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A comparison of theory and experiment for the aeroelastic stability of a bearingless model rotor in hover
1988-06-01
Conference paper
No indication
English