Scissoring fold arrangement for dual plane four bladed rotor hubs

Patent metadata

Field	Value
Publication number	US-2016122013-A1
Application number	US-201414533276-A
Country	US
Kind code	A1
Filing date	Nov 5, 2014
Priority date	Nov 5, 2014
Publication date	May 5, 2016
Grant date	—

Abstract

A rotor blade system includes a first hub assembly having a first set of rotor blades and rotatably attached to a rotor mast, a second hub assembly having a second set of rotor blades and rotatably attached to the rotor mast, the second hub assembly being positioned at a space relative to the first hub assembly, a torque splitter device engaged with both the first hub assembly and the second hub assembly, and a locking device operably associated with the torque splitter device. The method includes rotating the first hub relative to the second hub via the torque splitter until the first set of rotor blades align with the second set of rotor blade about a common horizontal axis.

First claim

What is claimed is:

1 . A rotor blade system, comprising:
a first hub assembly having a first set of rotor blades and rotatably attached to a rotor mast; a second hub assembly having a second set of rotor blades and rotatably attached to the rotor mast, the second hub assembly being positioned at a space relative to the first hub assembly; a torque splitter device engaged with both the first hub assembly and the second hub assembly; a locking device operably associated with the torque splitter device; wherein the torque splitter device is configured to allow movement of the of the first hub assembly relative to the second hub assembly; and wherein the locking device is configured to unlock the torque splitter device, which in turn enables the first set of blades to align with the second set of blades relative to a horizontal plane.

2 . The system of claim 1 , wherein the first set of blade comprises a first rotor blade and a second rotor blade.

3 . The system of claim 1 , wherein the first hub assembly is operably associated with a tilt-rotor aircraft.

4 . The system of claim 1 , the torque splitter device comprising:
a base; a first opening extending through the base and configure to receive a first shaft associated with the first hub assembly; and a second opening extending through the base and configure to receive a second shaft associated with the second hub assembly.

5 . The system of claim 4 , further comprising:
an extension member configured to engage with the first opening and the first shaft.

6 . The system of claim 5 , further comprising:
an extension member configured to engage with the first opening and the first shaft.

7 . The system of claim 1 , further comprising:
an actuator operably associated with the torque splitter; wherein the actuator is configured to rotate the torque splitter.

8 . The system of claim 7 , further comprising:
a computer operably associated with the actuator; wherein the computer is configured to control the movement of the torque splitter via the actuator.

9 . A torque splitter system for a dual hub rotor blade system, comprising:
a base; a first opening extending through the base and configured to receive a first shaft associated with a first hub of the dual hub rotor blade system; and a second opening extending through the base and configured to receive a first shaft associated with a first hub of the dual hub rotor blade system.

10 . The system of claim 9 , further comprising:
a third opening extending through the base and configured to receive a third shaft; wherein the torque splitter is configured to rotate about the third shaft.

11 . The system of claim 9 , further comprising:
an extension member configured to engage with the first opening and the first shaft.

12 . The system of claim 9 , further comprising:
an actuator operably associated with the torque splitter; wherein the actuator is configured to rotate the torque splitter.

13 . The system of claim 12 , further comprising:
a computer operably associated with the actuator; wherein the computer is configured to control the movement of the torque splitter via the actuator.

14 . The system of claim 9 , further comprising:
a locking device configured to lock the torque splitter in a fixed position.

15 . A method to scissor a first set of rotor blades relative to a second set of rotor blades, the method comprising:
securing the first set of rotor blades to a first hub; securing the second set of rotor blade to a second hub; securing the first hub and the second hub coaxially along a rotor mast; securing the first hub to the second hub via a torque splitter; and rotating the first hub relative to the second hub via the torque splitter until the first set of rotor blades align with the second set of rotor blade about a common horizontal axis.

16 . The method of claim 15 , further comprising:
locking the torque splitter in position with a locking device.

17 . The method of claim 16 , further comprising:
controlling the locking device with a computer.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Thompson Terry
• Stamps Frank B

Classifications

• B64C27/59 Primary

  mechanical · CPC title

• B64C27/10 Primary

  arranged coaxially · CPC title

• B64C27/50

  Blades foldable to facilitate stowage of aircraft · CPC title