System and method for operating a multi-engine aircraft

Patent metadata

Field	Value
Publication number	US-11299286-B2
Application number	US-201916670582-A
Country	US
Kind code	B2
Filing date	Oct 31, 2019
Priority date	May 15, 2019
Publication date	Apr 12, 2022
Grant date	Apr 12, 2022

Abstract

The present disclosure provides methods and systems for operating a rotorcraft comprising a plurality of engines configured to provide motive power to the rotorcraft and at least one rotor coupled to the plurality of engines. Failure of an active engine of the rotorcraft is detected when the rotorcraft is operated in an asymmetric operating regime (AOR), in which at least one first engine of the plurality of engines is the active engine and is operated in an active mode to provide motive power to the rotorcraft and at least one second engine of the plurality of engines is a standby engine and is operated in a standby mode to provide substantially no motive power to the rotorcraft. At least one flight control input is adjusted to compensate for a reduction in rotational speed of the at least one rotor resulting from the failure of the active engine. An increase in a power output of the standby engine of the rotorcraft is commanded.

First claim

The invention claimed is:

1. A method for operating a rotorcraft comprising a plurality of engines configured to provide motive power to the rotorcraft and at least one rotor coupled to the plurality of engines, the method comprising:
detecting failure of an active engine of the rotorcraft when the rotorcraft is operated in an asymmetric operating regime (AOR), in which at least one first engine of the plurality of engines is the active engine and is operated in an active mode to provide motive power to the rotorcraft and at least one second engine of the plurality of engines is a standby engine and is operated in a standby mode to provide substantially no motive power to the rotorcraft;
adjusting at least one flight control input to compensate for a reduction in rotational speed of the at least one rotor resulting from the failure of the active engine; and
commanding an increase in a power output of the standby engine of the rotorcraft.

2. The method of claim 1 , further comprising, responsive to commanding the increase in the power output of the standby engine, further adjusting the at least one flight control input.

3. The method of claim 1 , wherein adjusting at least one flight control input to compensate for the reduction in rotational speed of the at least one rotor comprises adjusting a blade angle of a plurality of blades of the rotor.

4. The method of claim 3 , wherein adjusting the blade angle of the plurality of blades of the rotor comprises adjusting a collective lever input of the rotorcraft.

5. The method of claim 1 , wherein adjusting at least one flight control input to compensate for the reduction in rotational speed of the at least one rotor comprises adjusting a pitch angle of the rotorcraft.

6. The method of claim 5 , wherein adjusting the pitch angle of the rotorcraft comprises adjusting a cyclic input of the rotorcraft.

7. The method of claim 1 , wherein adjusting at least one flight control input comprises adjusting a pedal input of the rotorcraft.

8. The method of claim 1 , wherein adjusting the at least one flight control input comprises commanding an automatic flight control system (AFCS) of the rotorcraft to adjust the at least one flight control input.

9. The method of claim 1 , wherein detecting the failure of the active engine comprises detecting a negative acceleration for the active engine beyond an acceleration threshold.

10. The method of claim 1 , wherein detecting the failure of the active engine comprises detecting a reduction in the speed of the active engine below a speed threshold.

11. A system for mitigating active engine failure in an rotorcraft comprising a plurality of engines configured to provide motive power to the rotorcraft and at least one rotor coupled to the plurality of engines, the system comprising:
a processing unit; and
a non-transitory computer-readable medium having stored thereon program instruction executable by the processing unit for:
detecting failure of an active engine of the rotorcraft when the rotorcraft is operated in an asymmetric operating regime (AOR), in which at least one first engine of the plurality of engines is the active engine and is operated in an active mode to provide motive power to the rotorcraft and at least one second engine of the plurality of engines is a standby engine and is operated in a standby mode to provide substantially no motive power to the rotorcraft;
adjusting at least one flight control input to compensate for a reduction in rotational speed of the at least one rotor resulting from the failure of the active engine; and
commanding an increase in a power output of the standby engine of the rotorcraft.

12. The system of claim 11 , wherein the program instructions are further executable for, responsive to commanding the increase in the power output of the standby engine, further adjusting the at least one flight control input.

13. The system of claim 11 , wherein adjusting at least one flight control input to compensate for the reduction in rotational speed of the at least one rotor comprises adjusting a blade angle of a plurality of blades of the rotor.

14. The system of claim 13 , wherein adjusting the blade angle of the plurality of blades of the rotor comprises adjusting a collective lever input of the rotorcraft.

15. The system of claim 11 , wherein adjusting at least one flight control input to compensate for the reduction in rotational speed of the at least one rotor comprises adjusting a pitch angle of the rotorcraft.

16. The system of claim 15 , wherein adjusting the pitch angle of the rotorcraft comprises adjusting a cyclic input of the rotorcraft.

17. The system of claim 11 , wherein adjusting at least one flight control input comprises adjusting a pedal input of the rotorcraft.

18. The system of claim 11 , wherein adjusting the at least one flight control input comprises commanding an automatic flight control system (AFCS) of the rotorcraft to adjust the at least one flight control input.

19. The system of claim 11 , wherein detecting the failure of the active engine comprises detecting a negative acceleration for the active engine beyond an acceleration threshold.

20. The system of claim 11 , wherein detecting the failure of the active engine comprises detecting a reduction in the speed of the active engine below a speed threshold.

Assignees

• Pratt & Whitney Canada

Inventors

• Beauchesne-Martel Philippe
• Manoukian Patrick

Classifications

• B64D35/08 Primary

  characterised by the transmission being driven by a plurality of power plants (for hybrid-electric power plants B64D35/022) · CPC title

• B64C27/57

  automatic or condition responsive, e.g. responsive to rotor speed, torque or thrust · CPC title

• B64D31/10 Primary

  for preventing asymmetric thrust · CPC title

• B64C27/12

  Rotor drives · CPC title