Pylon conversion actuator for tiltrotor aircraft

1. A method of using an instrument system in communication with a pylon conversion actuator for a tiltrotor aircraft comprising a wing extending outboard of a fuselage, a fixed pylon mounted on top of the wing, a rotor system having rotor blades rotatable about a central rotor axis pivotably mounted on the fixed pylon to rotate about a conversion axis, and the pylon conversion actuator directly coupled to the wing by a lower mount and directly coupled to the rotor system by an upper mount, wherein the pylon conversion actuator comprises a platform fixed to an end of an extendable arm that is positioned below and in the same vertical plane as the central rotor axis, the platform located between the upper mount and the lower mount, and a motor mounted on the platform and operable to actuate the extendable arm between an extended position and a retracted position, wherein the extendable arm extends through and below the lower mount in the extended position, the method comprising:

receiving a signal from an instrument system;

determining whether the pylon conversion actuator is in the extended position or the retracted position;

sending a command to the pylon conversion actuator to retract to the retracted position if the pylon conversion actuator is in the extended position; and

sending a command to the pylon conversion actuator to extend to the extended position if the pylon conversion actuator is in the retracted position.

2. The method of claim 1 further comprising:

placing the rotor system into a first rotor position by extending the pylon conversion actuator into the extended position; and

placing the rotor system into a second rotor position by retracting the pylon conversion actuator into the retracted position.

3. The method of claim 2 wherein:

the first rotor position is an upright position; and

the second rotor position is a forward position.

4. The method of claim 1 , wherein the rotor system comprises a proprotor gearbox and the upper mount directly coupled to the proprotor gearbox.

5. The method of claim 1 , wherein at least one of the upper mount or the lower mount is a gimbal.

6. The method of claim 1 , wherein the upper mount is a clevis and the lower mount is a gimbal.

7. The method of claim 6 , wherein the rotor system comprises a proprotor gearbox and the upper mount directly coupled to the proprotor gearbox.

8. The method of claim 6 , wherein the lower mount is located on a leading edge of the wing.

9. The method of claim 8 , wherein the rotor system comprises a proprotor gearbox and the upper mount directly coupled to the proprotor gearbox.

10. A tiltrotor aircraft, the aircraft comprising:

a fuselage body;

a wing;

a first fixed pylon mounted on top of the wing;

a first rotor system having a first proprotor gearbox, first rotor blades rotatable about a first central rotor axis, the first proprotor gearbox pivotally coupled to the first fixed pylon to selectively rotate the first rotor system about a first conversion axis; and

a first pylon conversion actuator comprising:

a first lower mount directly coupled to the wing;

a first upper mount directly coupled to the first proprotor gearbox and located aft of the first lower actuator mount; and

a first extendable arm positioned below and in the same vertical plane as the first central rotor axis;

a first platform fixed to an end of the first extendable arm and located between the first lower mount and the first upper mount and a first motor mounted on the first platform and operable to actuate the first extendable arm between a first retracted position and a first extended position where the first extendable arm extends through and below the first lower mount when in the first extended position;

wherein in the first extended position, the first pylon conversion actuator places the first rotor system in a first upright position; and

wherein in the first retracted position, the first pylon conversion actuator places the first rotor system in a first forward position.

11. The tiltrotor aircraft of claim 10 further comprising:

a second fixed pylon mounted on top of the wing on an opposite side of the fuselage from the first fixed pylon;

a second rotor system having a second proprotor gearbox, second rotor blades rotatable about a second central rotor axis, the second proprotor gearbox pivotally coupled to the second fixed pylon to selectively rotate the second rotor system about a second conversion axis;

a second pylon conversion actuator comprising;

a second lower mount directly coupled the wing;

a second upper mount directly coupled to the second proprotor gearbox and located aft of the second lower actuator mount; and

a second extendable arm positioned below and in the same vertical plane as the second central rotor axis;

a second platform fixed to the second extendable arm and located between the second lower mount and the second upper mount and a second motor mounted on the second platform and operable to actuate the second extendable arm between a second retracted position and a second extended position where the second extendable arm extends through and below the second lower mount when in the second extended position;

wherein in the second extended position, the second pylon conversion actuator places the second rotor system in a second upright position; and

wherein in the second retracted position, the second pylon conversion actuator places the second rotor system in a second forward position.

12. The tiltrotor aircraft of claim 10 , wherein at least one of the first lower mount and the first upper mount is a gimbal.

13. The tiltrotor aircraft of claim 10 , wherein the first lower mount and the first upper mount is a gimbal.

14. The tiltrotor aircraft of claim 10 , wherein the first lower mount is located on a leading edge of the wing.

15. The tiltrotor aircraft of claim 10 , wherein the first lower mount is a gimbal and the first upper mount is a clevis.

16. The tiltrotor aircraft of claim 15 , wherein the first lower mount is located on a leading edge of the wing.