A program of experimental and analytical research has been performed to demonstrate the effects of rotor and fuselage design parameters on rotar inplane 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 angle; rotor inplane structural stiffness and damping; pitch link stiffness and location; and fuselage natural frequency, damping, and
inertia. Analytical results for some of the numerous conditions tested were also obtained. The results from this program show that rotor blade structual damping is one of the most influential design parameters in obtaining acceptable aeromechanical stability margins. Other parameters, such
as blade cone angles, pitch link location (rotor δ3), and anisotropic hub damper configurations, may be used to improve stability margins, but their individual effects are small. The experimental apparatus and procedures, analytical models, and research
findings are discussed in this paper.
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Document Type: Research Article
Bell Helicopter Textron, Inc., Ft. Worth, Texas
Publication date: 1984-07-01
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