Electrically driven blade control for rotorcraft

Patent metadata

Field	Value
Publication number	US-10077102-B1
Application number	US-201213536475-A
Country	US
Kind code	B1
Filing date	Jun 28, 2012
Priority date	Mar 3, 2009
Publication date	Sep 18, 2018
Grant date	Sep 18, 2018

Abstract

Multiple redundant harmonic drive motors on a rotor head actuate the angle of attack of rotor blades at the rotor blade roots, providing collective control that, in combination with a system for providing cyclic control on the rotor blades, eliminates the need for a swashplate, thereby advantageously reducing the weight and maintenance cost of a helicopter, increasing its reliability, and reducing its vulnerability to ballistic attack.

First claim

What we claim is:

1. A helicopter or rotorcraft rotor head comprising at least one zero-backlash transmission that communicates torque from an electrically-driven actuator to a rotor blade at the blade root to change the blade's angle of attack with respect to the rotor head.

2. The rotor head of claim 1 , wherein the at least one zero-backlash transmission is a single-stage transmission selected from the group consisting of harmonic drive transmissions, cycloidal drive transmissions, or wobble drive transmissions.

3. The rotor head of claim 1 , wherein the at least one zero-backlash transmission rotates along with the rotor head.

4. The rotor head of claim 1 , wherein the electrically-driven actuator is capable of adjusting the angle of attack of the rotor blade and at least one additional rotor blade.

5. The rotor head of claim 1 , wherein the at least one electrically-driven actuator is capable of adjusting the angle of attack of the rotor blade and at least three additional rotor blades.

6. The rotor head of claim 1 , wherein at least two electrically-driven actuators are adapted to rotate along with the rotor head, and each actuator is individually capable of adjusting the angle of attack of all of the rotor blades on the rotor head.

7. The rotor head of claim 6 , wherein each of the at least two electrically-driven actuators is equipped to be mechanically decoupled from the rotor head in the event that the actuator becomes disabled.

8. The rotor head of claim 6 , wherein fewer than all of the at least two electrically-driven actuators are capable of adjusting the angle of attack of all of the at least two rotor blades.

9. A helicopter or rotorcraft rotor head comprising at least one mechanical transmission that communicates torque from an electrically-driven actuator to a rotor blade at the blade root producing an angular displacement of the rotor blade about the blade's longitudinal axis that is limited to an angular displacement range, wherein the mechanical transmission has an amount of backlash that is less than 0.5% of the angular displacement range of the blade.

10. The rotor head of claim 9 , wherein the at least one mechanical transmission is a hypercycloid transmission.

11. The rotor head of claim 9 , further comprising one or more unifying elements that transmit torque output from the at least one mechanical transmission to the rotor blade and at least one other rotor blade.

12. The rotor head of claim 9 , further comprising unifying elements that transmit torque output from the mechanical transmission to the rotor blade and at least three other rotor blades.

13. The rotor head of claim 9 , further comprising a second electrically-driven actuator, a second mechanical transmission, and at least two decoupling mechanisms, each decoupling mechanism being associated with an electrically-driven actuator and/or mechanical transmission, wherein each of the at least two decoupling mechanisms can disconnect its associated actuator and/or transmission, such that the disconnected actuator and/or transmission is no longer a source of torque or friction to any rotor blade.

14. The rotor head of claim 13 , wherein each of the at least two decoupling mechanisms is capable of disconnecting its associated actuator and/or transmission while the actuator and/or transmission is under mechanical load.

15. The rotor head of claim 9 , wherein the electrically-driven actuator transmits torque to the mechanical transmission through a torque-limiting coupling.

16. A modular line-replaceable unit (LRU) self-containedly comprising:
an electric motor,
a torque-limiting coupling,
a mechanical transmission, and
a mechanical disconnection mechanism capable of disconnecting the motor, coupling, and/or transmission such that they cannot supply torque or friction,
wherein the LRU is adapted to be mounted to and rotate along with a helicopter or rotorcraft rotor head, is adapted to communicate torque to at least one rotor blade on the rotor head so as to adjust the blade's angle of attack with respect to the rotor head, and can be modularly replaced without the disconnection of any rotor blade from the rotor head.

17. The LRU of claim 16 , wherein the mechanical transmission is a zero-backlash transmission.

18. The LRU of claim 17 , wherein the zero-backlash transmission is selected from the group consisting of harmonic drive transmissions, cycloidal drive transmissions, or wobble drive transmissions.

19. The LRU of claim 16 , further comprising an encoder for indicating the position of the motor, coupling, or transmission.

20. The LRU of claim 16 , wherein the motor, torque-limiting coupling, transmission, and disconnection mechanism are arranged serially, in that order.

21. A helicopter or rotorcraft rotor head comprising at least one zero-backlash transmission that communicates torque from an electrically-driven actuator to a rotor blade at the blade root, and having no non-zero-backlash transmission between the electrically-driven actuator and the blade root.

22. The rotor head of claim 21 , wherein the at least one zero-backlash transmission is a single-stage transmission selected from the group consisting of harmonic drive transmissions, cycloidal drive transmissions, or wobble drive transmissions.

23. The rotor head of claim 21 , wherein the at least one zero-backlash transmission rotates along with the rotor head.

24. The rotor head of claim 21 , wherein the electrically-driven actuator is capable of adjusting the angle of attack of the rotor blade and at least one additional rotor blade at the blade root of each blade.

25. The rotor head of claim 21 , comprising at least two electrically-driven actuators adapted to rotate along with the rotor head, wherein each of the at least two electrically-driven actuators is equipped to be mechanically decoupled from the rotor head in the event that the actuator becomes disabled.

26. The rotor head of claim 21 , comprising at least two electrically-driven actuators adapted to rotate along with the rotor head, wherein each actuator is capable of adjusting the angle of attack of all of at least two rotor blades at the blade root of each blade.

27. A helicopter or rotorcraft rotor head comprising at least one zero-backlash transmission that communicates torque from an electrically-driven actuator to a rotor blade at the blade root, and wherein the actuator and transmission can be removed and replaced without removing the blade.

28. The rotor head of claim 27 , wherein the at least one zero-backlash transmission is a single-stage transmission selected from the group consisting of harmonic drive transmissions, cycloidal drive transmissions, or wobble drive transmissions.

29. The rotor head of claim 27 , wherein the at least one zero-backlash transmission rotates along with the rotor head.

30. The rotor head of claim 27 , wherein the electrically-driven actuator is capable of adjusting the angle of attack of the rotor blade and at least one additional rotor blade at the blade root of each blade.

31. The rotor head of claim 27 , comprising at least two electrically-driven actuators adapted to rotate along with the rotor head, wherein each of the at least two electrically-driven actuators is equipped to be mechanically decoupled from the rotor head in the event that the actuator becomes dis

Assignees

• Birch Matthew C
• Sowle Zak
• Orbital Res Inc

Inventors

• Birch Matthew C
• Sowle Zak

Classifications

• B64C11/06

  for variable-pitch blades · CPC title

• B64C11/30 Primary

  Blade pitch-changing mechanisms · CPC title

• B64C27/68 Primary

  using electrical energy, e.g. having electrical power amplification · CPC title