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In order to avoid a negative coupling between blade lead-lag movements and blade angle adjustment movements in a helicopter rotor, the angle (b5) for the blade angle adjustment and an effective damping plane (M) of the rotor is increased as compared to the respective angle in conventional rotors. Th

In order to avoid a negative coupling between blade lead-lag movements and blade angle adjustment movements in a helicopter rotor, the angle (b5) for the blade angle adjustment and an effective damping plane (M) of the rotor is increased as compared to the respective angle in conventional rotors. This increase of the angle (b9) having the effective plane (M) for suppressing blade lead-lag movements in such a way on a blade angle control sleeve (4), that the effective plane (M) of the damping device (9) encloses an angle (a

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A rotor structure, especially for rotary wing aircraft, comprising a rotor hub and one or more rotor blades defining a lead-lag plane (B), each blade having a blade root, a blade neck, a blade wing section, and a blade pitch angle control sleeve, said blade neck being torsionally yielding for allowi

A rotor structure, especially for rotary wing aircraft, comprising a rotor hub and one or more rotor blades defining a lead-lag plane (B), each blade having a blade root, a blade neck, a blade wing section, and a blade pitch angle control sleeve, said blade neck being torsionally yielding for allowing a blade pitch angle adjustment movement, said blade neck being arranged between said blade root and said blade wing section, means connecting each rotor blade root to said rotor hub, said control sleeve being torsionally stiff for transmitting blade pitch angle adjustment forces to said wing section, said blade pitch angle control sleeve extending essentially coaxially along but without contacting said blade neck, a radially outer end of said blade pitch angle control sleeve being rigidly connected to said blade wing section, two-armed support strut means for securing a radially inner end of said blade pitch angle control sleeve to said blade root in a movable manner relative to said blade root, a blade pitch angle adjustment rod (5) having a longitudinal axis, means journalling said blade pitch angle adjustment rod to said blade pitch angle control sleeve, damping means arranged between said strut means and said blade pitch angle control sleeve for damping a blade lead-lag movement, said damping means having a single effective plane (M) which is angularly tilted by an angle (aab