Tilt-rotor over-torque protection from asymmetric gust

Patent metadata

Field	Value
Publication number	US-10131427-B2
Application number	US-201514932241-A
Country	US
Kind code	B2
Filing date	Nov 4, 2015
Priority date	Nov 4, 2015
Publication date	Nov 20, 2018
Grant date	Nov 20, 2018

Abstract

A system includes a first mast torque transfer system, a second mast torque transfer system coupled to the first mast torque transfer system, and a torque limiting system. The torque limiting system includes a first sensor configured to determine a torque of the first mast torque transfer system, a second sensor configured to determine a torque of the second mast torque transfer system, and a processor configured to determine a differential torque between the torque of the first mast torque transfer system and the torque of the second mast torque transfer system and configured to control at least one of a torque input and a torque output to at least one of the first and second mast torque transfer systems as a function of the determined differential torque.

First claim

What is claimed is:

1. A system, comprising:
a first mast torque transfer system;
a second mast torque transfer system coupled to the first mast torque transfer system; and
a torque limiting system, comprising:
a first sensor configured to determine a torque of the first mast torque transfer system;
a second sensor configured to determine a torque of the second mast torque transfer system; and
a processor configured to determine a differential torque between the torque of the first mast torque transfer system and the torque of the second mast torque transfer system and configured to control at least one of a torque input and a torque output to at least one of the first and second mast torque transfer systems as a function of the determined differential torque.

2. The system of claim 1 , wherein the processor is configured to determine a differential collective pitch command as a function of the determined differential torque.

3. The system of claim 2 , wherein the processor is configured to combine the differential torque with a roll rate value and a lateral stick value.

4. The system of claim 1 , wherein the processor is configured to determine a symmetric collective pitch command as a function of the determined differential torque.

5. The system of claim 4 , wherein the processor is configured to combine the differential torque with a power level value and a rotor governor value.

6. The system of claim 1 , wherein the processor is configured to determine a power demand signal engine command as a function of the determined differential torque.

7. The system of claim 6 , wherein the processor is configured to combine the differential torque with a power demand value.

8. A method, comprising:
sensing a first sensor configured to determine a torque of the first mast torque transfer system;
sensing a second sensor configured to determine a torque of the second mast torque transfer system;
determining a differential torque between the first mast torque transfer system and the second mast torque transfer system coupled to the first mast torque transfer system; and
controlling at least one of a torque input and a torque output to at least one of the first and second mast torque transfer systems as a function of the determined differential torque.

9. The method of claim 8 , further comprising:
determining a differential collective pitch command as a function of the determined differential torque.

10. The method of claim 9 , further comprising:
combining the differential torque with a roll rate value and a lateral stick value.

11. The method of claim 8 , further comprising:
determining a symmetric collective pitch command as a function of the determined differential torque.

12. The method of claim 11 , further comprising:
combining the differential torque with a power level value and a rotor governor value.

13. The method of claim 8 , further comprising:
determining a power demand signal engine command as a function of the determined differential torque.

14. The method of claim 13 , further comprising:
combining the differential torque with a power demand value.

15. A tiltrotor aircraft, comprising:
a first mast torque transfer system;
a second mast torque transfer system coupled to the first mast torque transfer system; and
a torque limiting system, comprising:
first sensor configured to determine a torque of the first mast torque transfer system;
a second sensor configured to determine a torque of the second mast torque transfer system; and
a processor configured to determine a differential torque between the torque of the first mast torque transfer system and the torque of the second mast torque transfer system and configured to control at least one of a torque input and a torque output to at least one of the first and second mast torque transfer systems as a function of the determined differential torque.

16. The tiltrotor aircraft of claim 15 , wherein the differential torque is associated with a reaction to asymmetrical wind conditions acting on a first proprotor associated with the first mast torque transfer system and a second proprotor associated with the second mast torque transfer system.

17. The tiltrotor aircraft of claim 15 , wherein the determined differential torque is associated with operation of the tiltrotor aircraft being operated in an airplane mode of flight.

18. The tiltrotor aircraft of claim 15 , wherein the determined differential torque is associated with operation of the tiltrotor aircraft being operated in a helicopter mode of flight.

19. The tiltrotor aircraft of claim 15 , wherein the processor is configured to determine at least one of a differential collective pitch command, a symmetric collective pitch command, and a power demand signal engine command as a function of the determined differential torque.

20. The tiltrotor aircraft of claim 15 , wherein the processor is configured to combine the determined differential torque with at least one of a roll rate value, a lateral stick value, a power level value, a rotor governor value, and a power demand value.

Assignees

• Blyth Robert Matthew
• Wilkinson Paul Raymond
• Bell Helicopter Textron Inc
• Boeing Co

Inventors

• Blyth Robert Matthew
• Wilkinson Paul Raymond

Classifications

• B64C11/303

  characterised by comprising a governor · CPC title

• B64C29/0033 Primary

  the propellers being tiltable relative to the fuselage · CPC title

• B64C11/308

  automatic · CPC title