System and method for controlling rotorcraft

Patent metadata

Field	Value
Publication number	US-11247782-B2
Application number	US-201816138053-A
Country	US
Kind code	B2
Filing date	Sep 21, 2018
Priority date	Sep 21, 2018
Publication date	Feb 15, 2022
Grant date	Feb 15, 2022

Abstract

In an embodiment, a rotorcraft includes: a plurality of engines; a flight control computer connected to the plurality of engines, the flight control computer being configured to: receive an operating parameter of a first engine of the plurality of engines; determine an engine output ramping rate for the first engine according to a difference between the operating parameter of the first engine and a nominal limit of the first engine; and increase the output of the first engine in response to detecting an outage of another engine of the plurality of engines, the output of the first engine being increased according to the engine output ramping rate.

First claim

What is claimed is:

1. A method comprising:
in response to detecting an outage of a first engine of a rotorcraft:
receiving an operating parameter of a second engine of the rotorcraft, the second engine being different from the first engine;
determining an engine output ramping rate for the second engine according to a difference between the operating parameter of the second engine and a nominal limit of the second engine, the engine output ramping rate having a first rate of increase when the difference between the operating parameter of the second engine and the nominal limit of the second engine is less than a predetermined value, the engine output ramping rate having a second rate of increase when the difference between the operating parameter of the second engine and the nominal limit of the second engine is greater than the predetermined value, the second rate of increase being greater than the first rate of increase; and
increasing an output of the second engine according to the engine output ramping rate.

2. The method of claim 1 , wherein increasing the output of the second engine comprises:
temporarily increasing the output of the second engine beyond the nominal limit of the second engine.

3. The method of claim 1 , wherein determining the engine output ramping rate comprises:
calculating the engine output ramping rate at runtime according to the operating parameter of the second engine.

4. The method of claim 1 , wherein determining the engine output ramping rate comprises:
selecting the engine output ramping rate from a lookup table, the lookup table being indexed according to the operating parameter of the second engine.

5. The method of claim 1 , further comprising:
waiting a predetermined amount of time before increasing the output of the second engine.

6. The method of claim 1 , wherein receiving the operating parameter comprises:
selecting the operating parameter from a plurality of operating parameters according to a flight control mode of the rotorcraft; and
requesting the operating parameter from the second engine.

7. The method of claim 1 , wherein the nominal limit of the second engine is a maximum continuous rotation speed of the second engine, and wherein increasing the output of the second engine comprises:
temporarily increasing the output of the second engine such that a rotation speed of the second engine exceeds the maximum continuous rotation speed of the second engine by a first predetermined margin.

8. The method of claim 1 , wherein the nominal limit of the second engine is a maximum continuous torque of the second engine, and wherein increasing the output of the second engine comprises:
temporarily increasing the output of the second engine such that a torque of the second engine exceeds the maximum continuous torque of the second engine by a second predetermined margin.

9. The method of claim 1 , wherein the nominal limit of the second engine is a maximum continuous temperature of the second engine, and wherein increasing the output of the second engine comprises:
temporarily increasing the output of the second engine such that a temperature of the second engine exceeds the maximum continuous temperature of the second engine by a third predetermined margin.

10. The method of claim 1 , wherein the engine output ramping rate is proportional to the difference between the operating parameter of the second engine and the nominal limit of the second engine.

11. A rotorcraft comprising:
a plurality of engines;
a flight control computer connected to the plurality of engines, the flight control computer being configured to, in response to detecting an outage of a first engine of the plurality of engines:
receive an operating parameter of a second engine of the plurality of engines, the second engine being different from the first engine;
determine an engine output ramping rate for the second engine according to a difference between the operating parameter of the second engine and a nominal limit of the second engine, the engine output ramping rate having a first rate of increase when the difference between the operating parameter of the second engine and the nominal limit of the second engine is less than a predetermined value, the engine output ramping rate having a second rate of increase when the difference between the operating parameter of the second engine and the nominal limit of the second engine is greater than the predetermined value, the second rate of increase being greater than the first rate of increase; and
increase an output of the second engine according to the engine output ramping rate.

12. The rotorcraft of claim 11 , wherein the flight control computer increases the output of the second engine by:
temporarily increasing the output of the second engine beyond the nominal limit of the second engine.

13. The rotorcraft of claim 11 , wherein the flight control computer determines the engine output ramping rate by:
calculating the engine output ramping rate at runtime according to the operating parameter of the second engine.

14. The rotorcraft of claim 11 , wherein the flight control computer determines the engine output ramping rate by:
selecting the engine output ramping rate from a lookup table, the lookup table being indexed according to the operating parameter of the second engine.

15. The rotorcraft of claim 11 , wherein the flight control computer is further configured to:
waiting a predetermined amount of time before increasing the output of the second engine.

16. The rotorcraft of claim 11 , wherein the flight control computer receives the operating parameter by:
selecting the operating parameter from a plurality of operating parameters according to a flight control mode of the rotorcraft; and
requesting the operating parameter from the second engine.

17. The rotorcraft of claim 11 , wherein the nominal limit of the second engine is a maximum continuous rotation speed of the second engine, and wherein the flight control computer increases the output of the second engine by:
temporarily increasing the output of the second engine such that a rotation speed of the second engine exceeds the maximum continuous rotation speed of the second engine by a first predetermined margin.

18. The rotorcraft of claim 11 , wherein the nominal limit of the second engine is a maximum continuous torque of the second engine, and wherein the flight control computer increases the output of the second engine by:
temporarily increasing the output of the second engine such that a torque of the second engine exceeds the maximum continuous torque of the second engine by a second predetermined margin.

19. The rotorcraft of claim 11 , wherein the nominal limit of the second engine is a maximum continuous temperature of the second engine, and wherein the flight control computer increases the output of the second engine by:
temporarily increasing the output of the second engine such that a temperature of the second engine exceeds the maximum continuous temperature of the second engine by a third predetermined margin.

20. The rotorcraft of claim 11 , wherein the engine output ramping rate is proportional to the difference between the operating parameter of the second engine and the nominal limit of the second engine.

21. A flight control computer comprising:
a processor; and
a non-transitory computer readable storage medium storing programming for execution by the processor, the programming including instructions for, in response

Assignees

• Textron Innovations Inc

Inventors

• Klein Morganne Cody
• Alfred Jillian Samantha
• Ludtke Christopher James

Classifications

• B64D31/06 Primary

  actuated automatically · CPC title

• B64C27/14

  Direct drive between power plant and rotor hub · CPC title

• F05D2260/84

  Redundancy · CPC title

• F05D2270/091

  in particular sudden load loss · CPC title

• F05D2270/095

  by temporary overriding set control limits · CPC title