Adaptable rotor control system for a variable number of blades

Patent metadata

Field	Value
Publication number	US-10358207-B2
Application number	US-201715693397-A
Country	US
Kind code	B2
Filing date	Aug 31, 2017
Priority date	Aug 31, 2017
Publication date	Jul 23, 2019
Grant date	Jul 23, 2019

Abstract

In one embodiment, a rotor hub comprises a yoke for attaching a plurality of rotor blades, a constant velocity joint to drive torque from a mast to the yoke and to enable the yoke to pivot, and a rotor control system configured to adjust an orientation of the plurality of rotor blades. Moreover, the rotor control system comprises: a swashplate, a phase adapter fulcrum, a plurality of actuators controlled based on a flight control input, a plurality of lower pitch links configured to transfer motion between the plurality of actuators and the swashplate, a plurality of phase adjustment levers configured to adjust a control phase associated with motion transferred between the plurality of actuators and the plurality of lower pitch links, and a plurality of upper pitch links configured to adjust a pitch of the plurality of rotor blades, wherein there are more upper pitch links than lower pitch links.

First claim

What is claimed is:

1. A rotor hub, comprising:
a yoke configured to attach a plurality of rotor blades;
a constant velocity joint configured to drive torque from a rotor mast to the yoke and further configured to enable the yoke to pivot relative to the rotor mast; and
a rotor control system configured to adjust an orientation of the plurality of rotor blades, wherein the rotor control system comprises:
a swashplate;
a phase adapter fulcrum;
a plurality of actuators configured to adjust an orientation of the swashplate based on a flight control input;
a plurality of lower pitch links configured to transfer motion between the plurality of actuators and the swashplate;
a plurality of phase adjustment levers configured to adjust a control phase associated with motion transferred between the plurality of actuators and the plurality of lower pitch links; and
a plurality of upper pitch links configured to transfer motion between the swashplate and the plurality of rotor blades to adjust a pitch of the plurality of rotor blades, wherein the plurality of upper pitch links comprises a larger number of pitch links than the plurality of lower pitch links.

2. The rotor hub of claim 1 , wherein the plurality of phase adjustment levers is further configured to transfer motion between the plurality of actuators and the plurality of lower pitch links.

3. The rotor hub of claim 1 , wherein the plurality of phase adjustment levers is coupled to the plurality of actuators, the phase adapter fulcrum, and the plurality of lower pitch links.

4. The rotor hub of claim 3 , wherein the plurality of phase adjustment levers is further configured to pivot relative to the phase adapter fulcrum.

5. The rotor hub of claim 3 , wherein the plurality of phase adjustment levers extends laterally relative to the plurality of actuators.

6. The rotor hub of claim 3 , wherein the plurality of lower pitch links is coupled to the plurality of phase adjustment levers and the swashplate.

7. The rotor hub of claim 1 , wherein the rotor control system further comprises a sleeve configured to slide vertically relative to the rotor mast and further configured to pivot relative to the rotor mast.

8. The rotor hub of claim 7 , wherein the rotor control system further comprises a gimbal configured to slide vertically relative to the sleeve, wherein the swashplate is coupled to the gimbal.

9. The rotor hub of claim 1 , wherein:
the plurality of lower pitch links comprises three lower pitch links; and
the plurality of upper pitch links comprises at least four upper pitch links, wherein each upper pitch link of the plurality of upper pitch links is coupled to a particular rotor blade of the plurality of rotor blades.

10. A rotor, comprising:
a plurality of rotor blades;
a rotor mast configured to rotate around an axis; and
a rotor hub, comprising:
a yoke coupled to the plurality of rotor blades;
a constant velocity joint configured to drive torque from the rotor mast to the yoke and further configured to enable the yoke to pivot relative to the rotor mast; and
a rotor control system configured to adjust an orientation of the plurality of rotor blades, wherein the rotor control system comprises:
a swashplate;
a phase adapter fulcrum;
a plurality of actuators configured to adjust an orientation of the swashplate based on a flight control input;
a plurality of lower pitch links configured to transfer motion between the plurality of actuators and the swashplate;
a plurality of phase adjustment levers configured to adjust a control phase associated with motion transferred between the plurality of actuators and the plurality of lower pitch links; and
a plurality of upper pitch links configured to transfer motion between the swashplate and the plurality of rotor blades to adjust a pitch of the plurality of rotor blades, wherein the plurality of upper pitch links comprises a larger number of pitch links than the plurality of lower pitch links.

11. The rotor of claim 10 , wherein the plurality of phase adjustment levers is further configured to transfer motion between the plurality of actuators and the plurality of lower pitch links.

12. The rotor of claim 10 , wherein the plurality of phase adjustment levers is coupled to the plurality of actuators, the phase adapter fulcrum, and the plurality of lower pitch links.

13. The rotor of claim 12 , wherein the plurality of phase adjustment levers is further configured to pivot relative to the phase adapter fulcrum.

14. The rotor of claim 12 , wherein the plurality of lower pitch links is coupled to the plurality of phase adjustment levers and the swashplate.

15. The rotor of claim 10 , wherein:
the plurality of lower pitch links comprises three lower pitch links; and
the plurality of upper pitch links comprises at least four upper pitch links, wherein each upper pitch link of the plurality of upper pitch links is coupled to a particular rotor blade of the plurality of rotor blades.

16. An aircraft, comprising:
a fuselage; and
one or more rotors, wherein each of the one or more rotors comprises:
a plurality of rotor blades;
a rotor mast configured to rotate around an axis; and
a rotor hub, comprising:
a yoke coupled to the plurality of rotor blades;
a constant velocity joint configured to drive torque from the rotor mast to the yoke and further configured to enable the yoke to pivot relative to the rotor mast; and
a rotor control system configured to adjust an orientation of the plurality of rotor blades, wherein the rotor control system comprises:
a swashplate;
a phase adapter fulcrum;
a plurality of actuators configured to adjust an orientation of the swashplate based on a flight control input;
a plurality of lower pitch links configured to transfer motion between the plurality of actuators and the swashplate;
a plurality of phase adjustment levers configured to adjust a control phase associated with motion transferred between the plurality of actuators and the plurality of lower pitch links; and
a plurality of upper pitch links configured to transfer motion between the swashplate and the plurality of rotor blades to adjust a pitch of the plurality of rotor blades, wherein the plurality of upper pitch links comprises a larger number of pitch links than the plurality of lower pitch links.

17. The aircraft of claim 16 , wherein the plurality of phase adjustment levers is coupled to the plurality of actuators, the phase adapter fulcrum, and the plurality of lower pitch links.

18. The aircraft of claim 17 , wherein the plurality of phase adjustment levers is further configured to pivot relative to the phase adapter fulcrum.

19. The aircraft of claim 16 , wherein:
the plurality of lower pitch links comprises three lower pitch links; and
the plurality of upper pitch links comprises at least four upper pitch links, wherein each upper pitch link of the plurality of upper pitch links is coupled to a particular rotor blade of the plurality of rotor blades.

20. The aircraft of claim 19 , wherein the aircraft comprises a tiltrotor aircraft.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Miller Gary
• Stamps Frank B

Classifications

• B64C2027/7216

  using one actuator per blade · CPC title

• B64C27/605 Primary

  including swash plate, spider or cam mechanisms · CPC title

• B64C11/06

  for variable-pitch blades · CPC title

• B64C11/32 Primary

  mechanical · CPC title

• B64C2027/7255

  using one or more swash plates · CPC title