Rotor systems and methods

Patent metadata

Field	Value
Publication number	US-10745124-B2
Application number	US-201916429863-A
Country	US
Kind code	B2
Filing date	Jun 3, 2019
Priority date	Oct 19, 2017
Publication date	Aug 18, 2020
Grant date	Aug 18, 2020

Abstract

A rotor system for an aircraft including a driving member; an externally driven rim configured to be rotated by the driving member; a hub having a hub axis, the hub including a rotatable housing and a non-rotatable housing; a plurality of rotor blade assemblies rotatably coupled to the rotatable housing of the hub and the externally driven rim such that rotation of the externally driven rim rotates the plurality of rotor blade assemblies about the hub axis, each rotor blade assembly having a rotor blade rotatable about a respective pitch change axis; and a pitch control mechanism operably associated with the hub and the plurality of rotor blade assemblies, wherein, actuation of the pitch control mechanism rotates each rotor blade assembly about the respective pitch change axis to collectively control the pitch of the rotor blade, thereby generating a variable thrust output. Also, a method of operating the rotor system.

First claim

The invention claimed is:

1. An aircraft rotor system comprising:
a driving member;
an externally driven rim configured to be rotated by the driving member;
a hub having a hub axis, the hub including a rotatable housing and a non-rotatable housing;
a plurality of rotor blade assemblies rotatably coupled to the rotatable housing of the hub and the externally driven rim such that rotation of the externally driven rim rotates the plurality of rotor blade assemblies and the rotatable housing about the hub axis, each rotor blade assembly having a rotor blade rotatable about a respective pitch change axis by a pitch horn associated therewith; and
a pitch control mechanism operably associated with the hub and the plurality of rotor blade assemblies;
wherein, actuation of the pitch control mechanism rotates each rotor blade assembly about the respective pitch change axis to collectively control the pitch of the rotor blade, thereby generating a variable thrust output.

2. The system of claim 1 , wherein the rotor blade assembly comprises a rod disposed between the rotatable housing and the externally driven rim, the rod being associated with the rotor blade and configured to permit rotation of the rotor blade about the respective pitch change axis.

3. The system of claim 2 , wherein the rod is configured to rotate the rotatable housing of the hub about the hub axis.

4. The system of claim 2 , wherein the rod passes through a channel disposed in the rotor blade.

5. The system of claim 1 , wherein the pitch control mechanism comprises an actuator assembly disposed on the non-rotatable housing of the hub and a spider assembly translatable along at least a portion of the hub axis by the actuator assembly, the spider assembly being rotated about the hub axis by the respective pitch horns in the plurality of rotor blade assemblies.

6. The system of claim 5 , wherein the spider assembly is pivotably coupled to each pitch horn such that translation of the spider assembly along at least a portion of the hub axis rotates the respective rotor blade about the respective pitch change axis.

7. The system of claim 5 , wherein the spider assembly comprising a plurality of arms, each of the arms being pivotably coupled with the respective pitch horn such that translation of the spider assembly rotates each pitch horn about the respective pitch change axis.

8. The system of claim 5 , wherein the actuator assembly comprises an actuator mechanism configured to translate an actuator rod along at least a portion of the hub axis.

9. The system of claim 8 , wherein the actuator assembly further comprises a tube connected to the actuator rod that is capable of translating along at least a portion of the hub axis.

10. The system of claim 9 , wherein the actuator assembly further comprises a sleeve connected to the non-rotatable housing and having an internal spline along at least a portion of the sleeve, the tube being disposed in at least a portion of the sleeve and the tube having an external spline along at least a portion of the tube, wherein relative translation of the external spline on the tube and the internal spline on the sleeve causes the actuator rod to linearly move along the hub axis.

11. The system of claim 1 , wherein the driving member is disposed adjacent to the externally driven rim.

12. The system of claim 11 , wherein the driving member is configured to provide mechanical energy from a power source.

13. The system of claim 12 , wherein the power source is mechanical, hydraulic, and/or electric.

14. An aircraft comprising:
a driving member;
an externally driven rim configured to be rotated by the driving member;
a hub having a hub axis, the hub including a rotatable housing and a non-rotatable housing;
a plurality of rotor blade assemblies, each rotatably coupled to the rotatable housing of the hub and the externally driven rim such that rotation of the externally driven rim rotates the plurality of rotor blade assemblies and the rotatable housing about the hub axis, each rotor blade assembly including a rotor blade and a pitch horn coupled to the rotor blade, each rotor blade assembly being rotatable about a respective pitch change axis by the pitch horn; and
a pitch control mechanism operably associated with the hub and pivotably coupled to the pitch horn of each rotor blade;
wherein, actuation of the pitch control mechanism rotates each rotor blade about the respective pitch change axis to collectively control the pitch of the rotor blades, thereby generating a variable thrust output.

15. The aircraft according to claim 14 , wherein the pitch control mechanism comprises an actuator assembly disposed on the non-rotatable housing of the hub and a spider assembly translatable along at least a portion of the hub axis by the actuator assembly, the spider assembly being rotated about the hub axis by the respective pitch horns in the plurality of rotor blade assemblies.

16. The aircraft of claim 15 , wherein the spider assembly comprising a plurality of arms each of which are pivotably coupled with a respective pitch horn such that translation of the spider assembly rotates each pitch horn about the respective pitch change axis.

17. The aircraft of claim 15 , wherein the actuator assembly comprises an actuator mechanism configured to translate an actuator rod along at least a portion of the hub axis.

18. The aircraft of claim 17 , wherein the actuator assembly further comprises a tube connected to the actuator rod that is capable of translating along at least a portion of the hub axis.

19. The aircraft of claim 18 , wherein the actuator assembly further comprises a sleeve connected to the non-rotatable housing and having an internal spline along at least a portion of the sleeve, the tube being disposed in at least a portion of the sleeve and the tube having an external spline along at least a portion of the tube, wherein relative translation of the external spline on the tube and the internal spline on the sleeve causes the actuator rod to linearly move along the hub axis.

20. A method of operating an aircraft rotor system comprising:
providing a rotor assembly, comprising:
a hub having a hub axis, the hub including a rotatable housing and a non-rotatable housing;
an externally driven rim configured to rotate about the hub axis, the externally driven rim configured to be rotated by a driving member;
a plurality of rotor blade assemblies, each rotatably coupled to the rotatable housing of the hub and the externally driven rim such that rotation of the externally driven rim rotates the plurality of rotor blade assemblies and the rotatable housing about the hub axis, each rotor blade assembly having a rotor blade rotatable about a respective pitch change axis; and
a pitch control mechanism operably associated with the hub and the plurality of rotor blade assemblies, the pitch control mechanism including an actuator assembly disposed on the non-rotatable housing of the hub and a spider assembly translatable along at least a portion of the hub axis by the actuator assembly;

providing a driving member disposed adjacent to the externally driven rim;
rotating the driving member to impart rotation to the externally driven rim, the plurality of rotor blade assemblies, the rotatable housing, and the spider assembly about the hub axis; and
translating the spider assembly along the hub axis to rotate the rotor blades about their respective pitch change axes.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Davis Alison Ann
• Speller Charles

Classifications

• B64C2027/7211

  without flaps · CPC title

• B64C29/0033

  the propellers being tiltable relative to the fuselage · CPC title

• B64C27/72

  Means acting on blades · CPC title

• B64C27/605

  including swash plate, spider or cam mechanisms · CPC title

• B64C27/59

  mechanical · CPC title