Abstract: A helicopter is described comprising a motor member comprising an output shaft and a first stator rotatably supporting the output shaft around a first axis; a main rotor adapted to provide the lift necessary for the support and the thrust necessary for the movement of the helicopter; a transmission interposed between the motor member and the main rotor; the transmission comprises, in turn, an input shaft rotatable around a second axis and a second stator rotatably supporting the input shaft around the second axis; the helicopter also comprises a joint interposed between the first and second stator, angularly fixed with respect to the first axis, and configured to allow an inclination between the first and second stator in a plane parallel to said first axis; the joint comprises a first corrugated element made of an elastically deformable material, interposed between said first and second stator, and adapted to allow the inclination through elastic deformation.

Abstract: A rotor for an aircraft is described, comprising an input shaft rotatable around a first axis; an output member rotatable around a second axis; a coupling element functionally interposed between the input shaft and the output member and adapted to transmit the motion from the input shaft to the output member; the coupling element is configured to allow, in use, a fixed or variable inclination between the respective first and second axes; the coupling element comprises at least a first corrugated element made of an elastically deformable material; the first corrugated element allows the inclination through elastic deformation.

Abstract: An anti-torque rotor is described comprising: a mast rotatable about a first axis; a plurality of blades rotatable about respective second axes; an element slidable along the first axis with respect to the mast, rotating integrally with the mast and operatively connected to the blades; a control rod slidable along axis; a first bearing with a first ring rotating integrally with element, a second ring radially internal to the first ring with respect to the first axis and a plurality of first rolling bodies; a third ring sliding integrally with the control rod along the first axis and angularly fixed with respect to the first axis; and a locking element arranged in a standard configuration, in which it prevents the relative rotation of the second and third rings and movable from the standard configuration to at least one emergency configuration, in which it renders the second ring free to rotate with respect to the third ring, when the first bearing is in a failure condition.