| 摘要 |
In the case of a rotor, especially of a rotary wing aircraft, the individual rotor blade (2) has a blade neck (2.2), which is torsionally soft at least for blade incidence angle movements, between a blade aerofoil (2.3) and a blade root (2.1), and is connected to a rotor hub (1) by means of bolts (3) passing through the latter, a torsionally stiff blade control casing (4), which extends along the blade neck (2.2) without touching it on the one hand being firmly connected to the blade aerofoil (2.3) and on the other hand being supported in a moving manner on the blade root (2.1) via a strut (6) in order to control the blade incidence angle by means of a control rod (5), and at least one damping device (9.1; 9.2), which is limited essentially to an active plane and direction, being arranged between the blade control casing (4) and the strut (6) in order to damp blade pivoting. The articulation of the control rod (5) on a stiff connecting element (10) which is arranged directly between the damping device (9.1; 9.2) and the strut (6) prevents negative coupling, especially of the blade pivoting and blade incidence angle movements, being possible. <IMAGE>
|
