Control lever assembly for a tilt-rotor aircraft
View Patent ↗A control lever assembly for a tilt-rotor aircraft, comprises at least one control lever which is movable relative to a control lever support. The control lever support has a rotational position that varies in correspondence with the tilt of the rotor of the aircraft. For example, the control lever support is movable by an actuator between a first position, in the airplane mode of the aircraft, in which the control lever moves substantially horizontally and a second position, in the helicopter mode of the aircraft, in which the control lever moves substantially vertically.
1. A control lever assembly for a tilt-rotor air-craft, comprising at least one control lever which is movable relative to a control lever support, wherein the control lever support is configured for rotational movement and wherein its rotational position varies in correspondence with the tilt of the rotor of the aircraft, and an actuator configured to move the control lever support between a first position in which the control lever moves substantially horizontally and a second position in which the control lever moves substantially vertically.
2. The control lever assembly according to claim 1 , wherein the control lever support comprises a housing pivotally connected to another portion of the aircraft through a horizontally and transversally extending pivot axis.
3. The control lever assembly according to claim 2 , wherein actuator comprises a linear actuator connected connected to said another portion of the aircraft and to a part of the housing remote from the pivot axis.
4. The control lever assembly according to claim 2 , wherein actuator comprises a rotary actuator positioned at the pivot axis.
5. The control lever assembly according to claim 1 , and further comprising an element operably coupled to the control lever to selectively increase friction force experienced by the control lever during rotation of the control lever support.
6. The control lever assembly according to claim 5 , wherein the friction force is programmable.
7. The control lever assembly according to claim 1 , wherein the control lever pivots around a rotation axis defined by the control lever support.
8. The control lever assembly according to claim 7 wherein the control lever support comprises a housing pivotally connected to another portion of the aircraft through a horizontally and transversally extending pivot axis, and wherein the rotation axis does not coincide with the pivot axis.
9. The control lever assembly according to claim 1 , wherein the control lever is provided with at least one manually operable control switch.
10. The control lever assembly according to claim 9 , wherein said at least one control switch comprises a switch configured to provide a signal indicative of selecting the tilt of the rotor of the aircraft.
11. The control lever assembly according to claim 1 , and further comprising a control unit configured to provide a control signal for controlling the actuator for rotating the control lever support.
12. An aircraft comprising: a body having a cockpit; an engine tiltable relative to the body; and a control lever assembly disposed in the cockpit for use by a pilot having at least one control lever which is movable relative to a control lever support, wherein the control lever support has a rotational position that varies in correspondence with the tilt of the engine of the aircraft, and an actuator configured to move the control lever support between a first position in which the control lever moves substantially horizontally and a second position in which the control lever moves substantially vertically.
13. The aircraft according to claim 12 , wherein the control lever support comprises a housing pivotally connected to another portion of the aircraft through a horizontally and transversally extending pivot axis.
14. The aircraft according to claim 13 , wherein the actuator comprises a linear actuator connected to said another portion of the aircraft and to a part of the housing remote from the pivot axis.
15. The aircraft according to claim 13 , the actuator comprises a rotary actuator positioned at the pivot axis.
16. The aircraft according to claim 12 , and further comprising an element operably coupled to the control lever to selectively increase friction force experienced by the control lever during rotation of the control lever support.
17. The aircraft according to claim 16 , wherein the friction force is programmable.
18. The aircraft according to claim 12 , wherein the control lever pivots around a rotation axis defined by the control lever support.
19. The aircraft according to claim 18 wherein the control lever support comprises a housing pivotally connected to another portion of the aircraft through a horizontally and transversally extending pivot axis, and wherein the rotation axis does not coincide with the pivot axis.
20. The aircraft according to claim 12 , wherein the control lever is provided with at least one manually operable control switch.
21. The aircraft according to claim 20 , wherein said at least one control switch comprises a switch configured to provide a signal indicative of selecting the tilt of the engine of the aircraft.
22. The aircraft according to claim 12 , and further comprising a control unit configured to provide a control signal for controlling the actuator for rotating the control lever support.