Aircraft control device
View Patent ↗The invention relates to a control surface ( 3 ) for an aerodynamic lifting surface ( 2 ) of aircraft comprising a main closing rib ( 9 ) located at one end of the control surface ( 3 ) to which a main torsion bar ( 8 ) is joined, the mentioned torsion bar ( 8 ) being joined at its other end to a lever system ( 14 ) on which at least one actuator ( 15 ) acts, such that it is possible to act on the rotation of the mentioned control surface ( 3 ) during the flight of the aircraft. The invention also relates to an actuation method for actuating such a control surface ( 3 ).
1. A control mechanism for a control surface ( 3 ) for an aerodynamic lifting surface ( 2 ) of aircraft, characterized in that said mechanism comprises a main closing rib ( 9 ) located at one end of the control surface ( 3 ) having joined thereto a main torsion bar ( 8 ) located at the edge of said control surface and defining an axis about which said control surface is configured to rotate such that it may move from an orientation coplanar with said aerodynamic lifting surface to one that is not coplanar with said aerodynamic lifting surface main torsion bar ( 8 ) being joined at its other end to a lever system ( 14 ) on which at least one actuator ( 15 ) acts, whereby rotation of the mentioned control surface ( 3 ) during the flight of the aircraft may be effected, wherein said control mechanism further comprises a secondary torsion bar ( 11 ), which secondary torsion bar is concentric with the main torsion bar ( 8 ), is located inside the main torsion bar ( 8 ) and is connected with the lever system ( 14 ) and with a secondary closing rib ( 28 ) of the control surface ( 3 ).
2. A control mechanism for a control surface ( 3 ) for an aerodynamic lifting surface ( 2 ) of aircraft according to claim 1 , characterized in that the at least one actuator ( 15 ) is a double acting actuator, being able to exert force in both directions of its shaft.
3. A control mechanism for a control surface ( 3 ) for an aerodynamic lifting surface ( 2 ) of aircraft according to claim 1 , characterized in that the actuator ( 15 ) is a servoactuator.
4. A control mechanism for a control surface ( 3 ) for an aerodynamic lifting surface ( 2 ) of aircraft according to claim 1 , characterized in that the at least one actuator is two actuators.
5. A control mechanism for a control surface ( 3 ) for an aerodynamic lifting surface ( 2 ) of aircraft according to claim 4 , characterized in that the actuators ( 15 ) work simultaneously in normal conditions, such that in the event of a failure in one of them, the operating actuator can actuate the control surface on its own.
6. The control mechanism of claim 5 wherein said operating actuator is a sevoactuator.
7. A control mechanism for a control surface ( 3 ) for an aerodynamic lifting surface ( 2 ) of aircraft according to claim 1 , characterized in that the main torsion bar ( 8 ) is manufactured from material made up of highly rigid and strong fibers.
8. A control mechanism for a control surface ( 3 ) for an aerodynamic lifting surface ( 2 ) of aircraft according to claim 7 , characterized in that the main torsion bar ( 8 ) is made of carbon fiber.
9. A control mechanism for a control surface ( 3 ) for an aerodynamic lifting surface ( 2 ) of aircraft according to claim 1 , characterized in that it comprises at least two stringers ( 12 ) which internally stiffen the mentioned control surface ( 3 ).
10. A control mechanism for a control surface ( 3 ) for an aerodynamic lifting surface ( 2 ) of aircraft according to claim 1 , characterized in that the secondary torsion bar ( 11 ) is manufactured from material made up of highly rigid and strong fibers.
11. A control mechanism for a control surface ( 3 ) for an aerodynamic lifting surface ( 2 ) of aircraft according to claim 10 , characterized in that the secondary torsion bar ( 11 ) is made of carbon fiber.
12. A control mechanism for a control surface ( 3 ) for an aerodynamic lifting surface ( 2 ) of aircraft according to claim 1 , characterized in that it further comprises a hinge pin ( 27 ), such that the mentioned control surface ( 3 ) is divided into a primary element ( 24 ) and a secondary element ( 25 ), which may be rotated to different degrees and wherein rotation of the secondary element is restricted by a coupling bar ( 26 ).
13. The control mechanism of claim 1 wherein said control surface is selected from the group consisting of rudders, elevators, ailerons, flaps, or air brakes.
14. A method for actuating a control surface for an aerodynamic lifting surface of an aircraft, the method comprising
providing the control mechanism of claim 1 ; and
applying a torsional moment to at least one of said main torsion bar and said secondary torsion bar.