Interconnect drive system

Patent metadata

Field	Value
Publication number	US-10384765-B2
Application number	US-201715495762-A
Country	US
Kind code	B2
Filing date	Apr 24, 2017
Priority date	Feb 6, 2014
Publication date	Aug 20, 2019
Grant date	Aug 20, 2019

Abstract

An interconnect drive system for an aircraft has a driveline and clutch control system. The driveline comprises a shaft for each propulsion assembly, each shaft for transferring torque to and from the associated propulsion assembly, and a clutch operably coupling the shafts and configured for selective engagement. The clutch is capable of transferring a first amount of torque between the shafts while engaged and a second amount of torque between the shafts while disengaged. The system also has a clutch control system, comprising a computer operably connected to the clutch for controlling operation of the clutch and sensors for sensing torque applied to the driveline, output from the sensors being communicated to the computer. The computer commands operation of the clutch in response to the output from the sensors, the clutch being commanded to disengage to relieve a transient torque imbalance in the driveline.

First claim

What is claimed is:

1. An interconnect drive system for an aircraft having at least two propulsion assemblies, the system comprising:
a driveline comprising:
a shaft for each propulsion assembly, each shaft configured for being operably coupled to the associated propulsion assembly for transferring torque to and from the associated propulsion assembly; and
a clutch operably coupling the shafts and configured for selective engagement, the clutch capable of transferring a first amount of torque between the shafts while engaged, the clutch capable of transferring a second amount of torque between the shafts while disengaged; and

a clutch control system, comprising:
a computer operably connected to the clutch for controlling operation of the clutch;

and
sensors for sensing torque applied to the driveline, output from the sensors being communicated to the computer;

wherein the computer commands operation of the clutch in response to the output from the sensors, the computer commanding the clutch to disengage to relieve a transient torque imbalance in the driveline.

2. The system of claim 1 , wherein the computer commands operation of the clutch to allow relative rotation of the shafts, the system being configured to achieve a selected relative phasing of rotors coupled to the propulsion assemblies.

3. The system of claim 1 , wherein the sensors comprise torque sensors.

4. The system of claim 1 , further comprising:
additional sensors configured for sensing attitude and motion of the aircraft, output from the sensors being communicated to the computer;
wherein the computer commands operation of the clutch in response to the output from the additional sensors, the computer commanding the clutch to disengage to relieve an expected transient torque imbalance in the driveline.

5. The system of claim 1 , wherein the clutch is a friction clutch.

6. The system of claim 1 , wherein the clutch is a slipper clutch configured to, while engaged, passively allow relative rotation of the shafts when the torque imbalance exceeds a selected limit.

7. The system of claim 1 , further comprising:
a second clutch within the driveline and operably coupling the shafts, the second clutch being configured for selective engagement, the second clutch capable of transferring a first amount of torque between the shafts while engaged, the second clutch capable of transferring a second amount of torque between the shafts while disengaged.

8. A method of alleviating a least a portion of a torque imbalance within an interconnect drive system of an aircraft, the aircraft comprising at least first and second propulsion assemblies, the method comprising:
a) operably coupling the first propulsion assembly and the second propulsion assembly with a driveshaft system, the driveshaft system having a clutch operably connecting a first output driveshaft operably connected to the first propulsion assembly and a second output driveshaft operably connected to the second propulsion assembly;
b) sensing a transient torque imbalance within the driveshaft system; and
c) selectively disengaging the clutch to allow relative rotation of the first and second driveshafts to reduce the torque imbalance.

9. The method of claim 8 , further comprising:
d) after the torque imbalance subsides, selectively disengaging the clutch to allow relative rotation of the first and second driveshafts to achieve a desired phasing relative to each other.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Elliott David
• Stamps Frank Bradley
• Collins Bobby

Classifications

• B64C29/0033

  the propellers being tiltable relative to the fuselage · CPC title

• F16D2500/1045

  Friction clutch · CPC title

• G10K2210/123

  Synchrophasors or other applications where multiple noise sources are driven with a particular phase relationship · CPC title

• B64D35/04

  characterised by the transmission driving a plurality of propellers or rotors · CPC title

• F16D2500/10412

  Transmission line of a vehicle · CPC title