Tiltrotor control system with two rise/fall actuators

Patent metadata

Field	Value
Publication number	US-9567070-B2
Application number	US-201313835705-A
Country	US
Kind code	B2
Filing date	Mar 15, 2013
Priority date	Mar 15, 2013
Publication date	Feb 14, 2017
Grant date	Feb 14, 2017

Abstract

A rotor system for rotor aircraft comprises a rotor hub comprising a plurality of rotor blades, a rotatable rotor mast coupled to the rotor hub, a swashplate assembly comprising a non-rotating ring engaged with a rotatable ring, a plurality of pitch links mechanically coupling the rotatable ring to the plurality of rotor blades, and a swashplate actuator system. The rotatable ring is configured to rotate with the rotor mast, and the non-rotating ring is configured to engage and guide the rotatable ring. The pitch links are configured to control the pitch angle of each rotor blade. The swashplate actuator system consists of: a first actuator and a second actuator, where the first actuator and the second actuator are mechanically coupled to a stationary surface and the non-rotating ring.

First claim

What is claimed:

1. A rotor system for rotor aircraft, the rotor system comprising:
a rotor hub comprising a plurality of rotor blades;
a rotatable rotor mast coupled to the rotor hub;
a swashplate assembly comprising a non-rotating ring engaged with a rotatable ring, wherein the rotatable ring is configured to rotate with the rotor mast, and wherein the non-rotating ring is configured to engage and guide the rotatable ring;
a plurality of pitch links mechanically coupling the rotatable ring to the plurality of rotor blades, wherein the pitch links are configured to control pitch angle of each of the rotor blades; and
a swashplate actuator system comprising a first actuator and a second actuator, wherein the first and the second actuators are positioned about a vertical axis of the rotatable rotor mast, wherein the first actuator and the second actuator are mechanically coupled to a stationary surface and the non-rotating ring, the first actuator and the second actuator are configured to tilt the non-rotating ring about a single axis of rotation; and
a trim actuator mechanically coupled to the non-rotating ring and a translatable sleeve positioned about the rotatable rotor mast, the trim actuator is configured to tilt the non-rotating ring about a second axis of rotation different from the single axis of rotation.

2. The rotor system of claim 1 , wherein the stationary surface is a gear housing within the rotor system.

3. The rotor system of claim 1 , the non-rotating ring is only coupled to the first actuator, the second actuator, and the rotatable ring.

4. The rotor system of claim 1 , further comprising:
a sleeve disposed about the rotatable rotor mast and coupled to the stationary surface; and
a bearing coupled to the sleeve and the non-rotating ring, wherein the bearing is configured to limit the tilt of the non-rotating ring to a single axis.

5. The rotor system of claim 1 , wherein at least one of the first actuator or the second actuator comprises a linear actuator, a rotary actuator, or a hydraulic actuator.

6. The rotor system of claim 1 , wherein the first actuator and the second actuator are triple-redundant actuators.

7. The rotor system of claim 1 , wherein the first actuator and the second actuator are further configured to translate the non-rotating ring along a longitudinal axis of the rotatable rotor mast at a fixed angle.

8. The rotor system of claim 1 , wherein the first actuator is coupled to the non-rotating ring at a first connection point of the non-rotating ring, and the second actuator is coupled to the non-rotating ring at a second connection point of the non-rotating ring opposite the first connection point.

9. The rotor system of claim 8 , wherein the trim actuator is coupled to the non-rotating ring at a point on the non-rotating ring different from the first connection point and the second connection point.

10. The rotor system of claim 9 , wherein the point on the non-rotating ring where the trim actuator is coupled to the non-rotating ring is on a periphery of the non-rotating ring midway between the first connection point and the second connection point.

11. A rotor system for rotor aircraft, the rotor system comprising:
a rotor hub comprising a plurality of rotor blades;
a rotatable rotor mast coupled to the rotor hub;
a swashplate assembly comprising a non-rotating ring engaged with a rotatable ring,
wherein the non-rotating ring is configured to engage and guide the rotatable ring;

a plurality of pitch links mechanically coupling the rotatable ring to the plurality of rotor blades; and
a swashplate actuator system comprising:
a first actuator and a second actuator, wherein the first actuator and the second actuator are mechanically coupled to a housing and the non-rotating ring, wherein the first actuator is coupled to the non-rotating ring at a first connection point of the non-rotating ring, and the second actuator is coupled to the non-rotating ring at a second connection point of the non-rotating ring opposite the first connection point; and
a trim actuator, wherein the trim actuator is mechanically coupled to the non-rotating ring and the housing, wherein the trim actuator is coupled to the non-rotating ring at a point on the non-rotating ring different from the first connection point and the second connection point.

12. The rotor system of claim 11 , wherein the first actuator and the second actuator are configured to tilt the non-rotating ring through a first angle, wherein the trim actuator is configured to tilt the non-rotating ring through a second angle, and wherein the ratio of the first angle to the second angle is in the range of 1000:1 to about 2:1.

13. The rotor system of claim 11 , wherein the trim actuator is mechanically coupled to the housing through a sleeve disposed about vertical axis of the rotatable rotor mast, wherein the sleeve is fixedly coupled to the housing.

14. The rotor system of claim 11 , wherein the first actuator and the second actuator are positioned about the rotatable rotor mast and configured to tilt the non-rotating ring about a first axis of rotation, and wherein the trim actuator is configured to tilt the non-rotating ring about a second axis of rotation, and wherein the first axis of rotation and the second axis of rotation do not align.

15. The rotor system of claim 11 , wherein the rotor system is configured to selectively rotate between a helicopter mode in a vertical position and an airplane mode in a horizontal position, wherein the first actuator and the second actuator are configured to provide a cyclic input to the rotor blades to propel the rotor aircraft fore and aft in the helicopter mode, and wherein the first actuator and the second actuator are configured to provide a collective input to the rotor blades to propel the rotor aircraft in the airplane mode.

16. The rotor system of claim 11 , wherein the first actuator and the second actuator are triple-redundant actuators, and wherein the trim actuator is not a triple-redundant actuator.

17. The rotor system of claim 11 , wherein the rotatable ring is rotationally coupled to the rotatable rotor mast by a rotating link.

18. The rotor system of claim 14 , wherein the second axis of rotation is perpendicular to the first axis of rotation.

19. The rotor system of claim 18 , wherein the trim actuator is not configured to translate the non-rotating ring along a longitudinal axis of the rotatable rotor mast.

20. A swashplate assembly for use with a rotor aircraft, the swashplate assembly comprising:
a non-rotating ring engaged with a rotatable ring, wherein the rotatable ring is configured to rotate with a rotor mast, and wherein the non-rotating ring is configured to engage and guide the rotatable ring; and
a swashplate actuator system comprising:
a first actuator and a second actuator engaged with the non-rotating ring, wherein the first actuator and the second actuator are configured to tilt the non-rotating ring about a single axis of rotation, and
wherein the first actuator and the second actuator are further configured to translate the non-rotating ring along a longitudinal axis of the rotor mast at a fixed angle; and
a trim actuator mechanically coupled to the non-rotating ring and a stationary surface, wherein the trim actuator is configured to tilt the non-rotating ring about a second axis of rotation different from the single axis of rotation.

21. The swashplate assembly of claim 20 , wherein the trim actuator cannot translate

Assignees

• Bell Helicopter Textron Inc

Inventors

• Shundo Ken
• Fenny Carlos A
• Stamps Frank B

Classifications

• B64C27/605

  including swash plate, spider or cam mechanisms · CPC title

• B64C29/0033 Primary

  the propellers being tiltable relative to the fuselage · CPC title

• B64C11/32

  mechanical · CPC title