Rotor for an aircraft capable of hovering

A convertiplane comprising:

• a fuselage extending along a first axis;
• a pair of half-wings extending from respective side bands opposite one another of said fuselage along respective second axes;
• a pair of rotors associated with said half-wings, rotatable around respective third axes and inclinable around a fourth axis orthogonal to said second and first axis between:
• a first position in which said third axes are parallel to said first axis, which position is reached when said convertiplane is, in use, in an airplane configuration;
• and
• a second position in which said third axes are orthogonal to said first axis, which position is reached when said convertiplane is, in use, in a helicopter configuration;
• each said rotor comprising:
• an input shaft rotatable around a respective fifth axis;
• an output member rotatable around a respective said third axis;
• a coupling element functionally interposed between said input shaft and said output member and adapted to transmit the motion from said input shaft to said output member;
• said coupling element being configured to allow, in use, an inclination by a variable angle between the respective said respective fifth axis and said respective third axis;
• characterized in that said coupling element comprises at least a first corrugated element made of an elastically deformable material;
• said first corrugated element allowing said inclination through elastic deformation;
• said input shaft being a control shaft of the respective said propeller rotatable around the respective said fifth axis;
• said output member being a hub on which a plurality of respective blades are articulated and rotatable around a respective said third axis;
• said coupling element is configured to allow, in use, said variable oscillation angle between respective said fifth and third axes;
• wherein said coupling element comprises a plurality of axially corrugated discs superimposed on one another and connected to one another;
• said discs comprising first radially internal ends and second radially external ends axially offset with respect to said first radially internal ends.

A convertiplane comprising:

• a fuselage extending along a first axis;
• a pair of half-wings extending from respective side bands opposite one another of said fuselage along respective second axes;
• a pair of rotors associated with said half-wings, rotatable around respective third axes and inclinable around a fourth axis orthogonal to said second and first axis between:
• a first position in which said third axes are parallel to said first axis, which position is reached when said convertiplane is, in use, in an airplane configuration;
• and
• a second position in which said third axes are orthogonal to said first axis, which position is reached when said convertiplane is, in use, in a helicopter configuration;
• each said rotor comprising:
• an input shaft rotatable around a respective fifth axis;
• an output member rotatable around a respective said third axis;
• a coupling element functionally interposed between said input shaft and said output member and adapted to transmit the motion from said input shaft to said output member;
• said coupling element being configured to allow, in use, an inclination by a variable angle between the respective said respective fifth axis and said respective third axis;
• characterized in that said coupling element comprises at least a first corrugated element made of an elastically deformable material;
• said first corrugated element allowing said inclination through elastic deformation;
• said input shaft being a control shaft of the respective said propeller rotatable around the respective said fifth axis;
• said output member being a hub on which a plurality of respective blades are articulated and rotatable around a respective said third axis;
• said coupling element is configured to allow, in use, said variable oscillation angle between respective said fifth and third axes;
• wherein said at least one first corrugated element is made of a metallic material coated with a jacket of fibreglass.