A program of experimental and analytical research has been performed to demonstrate the effects of rotor and fuselage design parameters on rotor in-plane stability, including aeromechanical stability. The experimental data were obtained from hover and wind-tunnel tests of a scaled advanced bearingless main rotor model. Both isolated-rotor and free-hub conditions were tested. Test parameters included blade built-in cone and sweep angles; rotor inplane structural stiffness and damping; pitch link stiffness and location; and fuselage natural frequency, damping, and inertia. The results show that rotor blade structural damping is one of the most influential design parameters in obtaining acceptable aeromechanical stability margins. Other parameters, such as blade cone angle, pitch link location (rotor delta 3) and anisotropic hub damper configurations, may be used to improve stability margins, but their individual effects are subtle.
Measured and calculated inplane stability characteristics for an advanced bearingless main rotor
1984-01-01
Conference paper
No indication
English
Hover Aeromechanical Stability Trends with Bearingless Main Rotor Design
Online Contents | 1994
|Stability of the Sikorsky S-76 Bearingless Main Rotor
British Library Conference Proceedings | 1993
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