Abstract: An anti-torque rotor is described for a helicopter, comprising: a mast rotatable about a first axis; a plurality of blades hinged on the mast, extending along respective second axes transversal to said first axis and rotatable about respective said second axes to alter the respective angles of attack; a control element sliding and rotating with respect to the mast, and operatively connected to said blades to cause the rotation of said blades about respective second axes following a translation of said element along the first axis; a control rod sliding axially along first axis with respect to the mast and angularly fixed with respect to the first axis; and a bearing interposed between the control rod and the control element, sliding along the first axis with respect to the mast and integrally with the control rod; the anti-torque rotor further comprises an interface made of an antifriction material interposed between said control rod and said bearing.

Abstract: An anti-torque rotor is described that comprises: a mast rotatable about a first axis; a plurality of blades extending along respective second axes; a control element sliding along the first axis with respect to the mast, integrally rotatable with said mast, and connected to said blades; a control rod sliding axially along first axis and angularly fixed with respect to said first axis; a connection element interposed between the control rod and the control element, sliding along the first axis integrally with the control rod, and configured to enable the relative rotation of said control element with respect to the control rod about the first axis; and a transmission unit available in an active configuration or an inactive configuration; the transmission unit, in turn, comprises: an annular ridge axially and angularly integral with the control rod and radially projecting from the control rod; and a seat engaged by the ridge and angularly integral with the control element.

Abstract: An anti-torque rotor is described comprising: a mast rotatable about a first axis; a plurality of blades hinged on the mast and rotatable about respective second axes to vary the respective angles of attack; a control element sliding along the first axis with respect to the mast, rotatable with the mast and connected to the blades to cause the rotation about the second axes; a control mechanism, axially sliding and angularly fixed with respect to the mast; and a connection element interposed between the control mechanism and the control element, sliding integrally with the control mechanism along the mast; the control mechanism comprises a first and a second rod; the rotor comprises a coupling, which is configured to enable/prevent rotation of the second rod with respect to the first rod when the torque exerted by the first connection element on the second rod about the first axis is greater/less than a threshold value in the event of failure of the connection element.

Abstract: An anti-torque rotor is described for a helicopter, comprising: a mast rotatable about a first axis; a plurality of blades hinged on the mast, extending along respective second axes transversal to said first axis and rotatable about respective said second axes to alter the respective angles of attack; a control element sliding and rotating with respect to the mast, and operatively connected to said blades to cause the rotation of said blades about respective second axes following a translation of said element along the first axis; a control rod sliding axially along first axis with respect to the mast and angularly fixed with respect to the first axis; and a connection element interposed between the control rod and the control element, sliding along the first axis with respect to the mast and integrally with the control rod; the anti-torque rotor further comprises an interface made of an antifriction material interposed between said control rod and said connection element.