A ROTORCRAFT TAIL ROTOR, A ROTORCRAFT FITTED WITH SUCH A TAIIL ROTOR, AND A METHOD OF STATICALLY AND/OR DYNAMICALLY BALANCING A ROTORCRAFT TAIL ROTOR

摘要

The present invention relates to a rotorcraft tail rotor, a rotorcraft including a tail rotor, and a method for statically and/or dynamically balancing a rotorcraft tail rotor. The purpose of the present invention is to improve safety of the rotorcraft by restricting a cause of control in which a pitch angle of the tail rotor is blocked. The rotorcraft tail rotor includes at least two blade elements (1). Each blade element (1) is suitable to pivot around a corrective pitch change axis (Z) to change a corrective pitch of each blade element of the tail rotor. Each blade element (1) includes at least one compensating weight (2) including a protrusion unit (4) vertically formed on a main inertia axis (5) of the blade element (1). The main inertia axis (5) is parallel with the longitudinal direction of the blade element. According to the present invention, the tail rotor has a compensating weight (2) including a transformable part (6) which can move on the protrusion unit (4) on a plane (P) parallel with the main inertia axis (5) of the blade element (1).