Helicopter anti-torque rotor
AssigneeLeonardo S.P.A.
InventorJames Wang
Life of this patent
Estimating the term…
Abstract
An anti-torque rotor of a helicopter, having: a supporting body; a drive shaft which rotates about a first axis with respect to the supporting body; a hub connected operatively to drive shaft and angularly fixed with respect to first axis; at least one blade which is connected operatively to hub, is angularly fixed with respect to first axis, and is angularly movable with respect to a second axis to adjust the pitch angle of blade; and an actuator which can be operated to rotate blade about second axis to adjust the pitch angle of blade; actuator has an electric motor which generates torque along the first axis; and a mechanical stage interposed between the electric motor and blade, and designed to convert the torque into rotation of blade about the respective second axes; electric motor is fixed to supporting body.
Claims6
A helicopter (1) comprising :
- a fuselage (2) with a nose (5);
- a main rotor (3) fitted to the top of said fuselage (2);
- and
- an anti-torque rotor (4) fitted to said fuselage (2) on the opposite side of said nose (5);
- said anti-torque rotor (4) comprising:
- a supporting body (14);
- a drive shaft (10) which rotates about a first axis (B) with respect to said supporting body (14);
- a hub (11) connected operatively to said drive shaft (10) and angularly rotatable together with said drive shaft (10) about said first axis (B);
- at least one pair of blades (12) which are connected operatively to said hub (11), are angularly rotatable together with said hub (11) about said first axis (B), and are angularly rotatable about a second axis (D) and with respect to said hub (11) to adjust the pitch angles of said blades (12);
- and
- an actuator (16) which can be operated to rotate said blades (12) about said second axis (D) to adjust the pitch angle of said blade (12);
- said actuator (16) in turn comprising:
- an electric motor (25) which generates torque along said first axis (B);
- and
- a mechanical stage (30) designed to convert said torque into rotation of said blades (12) about the respective second axes (D);
- a single said mechanical stage being interposed between said electric motor (25) and said at least two blades (12);
- said single mechanical stage (30) comprising:
- a rotary member (31) which rotates about said first axis (B), and is rotated about said first axis (B) by said electric motor (25);
- and
- a sliding member (32) which translates along said first axis (B), is fitted to said rotary member (31), and to which said at least two blades (12) are hinged;
- characterized in that said electric motor (25) is fixed to said supporting body (14);
- said electric motor (25) comprising:
- a stator (26) which is annular with respect to said first axis (B);
- a rotor (27) connected electrically to said stator (26) and rotatable about said first axis (B) by an electric torque generated by stator (26);
- and
- a housing (28) fixed to and projecting from said supporting body (14) and housing said stator (26) and rotor (27);
- said electric motor (25) being arranged outside said fuselage (2) and external with respect to said drive shaft (10), said blades (12) and to said hub (11);
- said rotary member (31) defining a first threaded surface (37), and said sliding member (32) defining a second threaded surface (39) which meshes with said first threaded surface (37).
Dependencies are inferred from the claim text.