Rotor structure, especially for a rotary wing aircraft

Claim 1

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 (α ) relative to said lead-lag plane (B), so that said angle (α) causes an increase in an angle (β) enclosed between said longitudinal axis of said blade pitch angle adjustment rod and said single effective plane (M) of said damping means.