Power management systems for multi engine rotorcraft

Patent metadata

Field	Value
Publication number	US-11479348-B2
Application number	US-201916558064-A
Country	US
Kind code	B2
Filing date	Aug 31, 2019
Priority date	Aug 31, 2019
Publication date	Oct 25, 2022
Grant date	Oct 25, 2022

Abstract

A power management system for a multi engine rotorcraft having a main rotor system with a main rotor speed. The power management system includes a first engine that provides a first power input to the main rotor system. A second engine selectively provides a second power input to the main rotor system. The second engine has at least a zero power input state and a positive power input state. A power anticipation system is configured to provide the first engine with a power adjustment signal in anticipation of a power input state change of the second engine during flight. The power adjustment signal causes the first engine to adjust the first power input to maintain the main rotor speed within a predetermined rotor speed threshold range during the power input state change of the second engine.

First claim

What is claimed is:

1. A power management system for a multi engine rotorcraft having a main rotor system with a main rotor speed, the power management system comprising:
a first engine providing a first power input to the main rotor system;
a second engine selectively providing a second power input to the main rotor system, the second engine having at least a zero power input state and a positive power input state;
a combining gearbox coupling the first and second engines to the main rotor system;
a sprag clutch having an input side coupled to the second engine and an output side coupled to the combining gearbox, the sprag clutch configured to generate power input step changes between the zero power input state and the positive power input state when a rotating speed of the input side transitions above or below a rotating speed of the output side; and
a power anticipation system configured to provide the first engine with a power adjustment signal in anticipation of the power input step changes;
wherein, the power adjustment signal causes the first engine to adjust the first power input coincident with the power input step changes to maintain the main rotor speed within a predetermined rotor speed threshold range.

2. The power management system as recited in claim 1 wherein the first engine further comprises a main engine and wherein the second engine further comprises a supplemental power unit.

3. The power management system as recited in claim 1 wherein the first engine further comprises a first main engine and wherein the second engine further comprises a second main engine.

4. The power management system as recited in claim 1 wherein the first engine further comprises a first gas turbine engine and wherein the second engine further comprises a second gas turbine engine.

5. The power management system as recited in claim 1 wherein the first engine further comprises a gas turbine engine and wherein the second engine further comprises an electric motor.

6. The power management system as recited in claim 1 wherein the power anticipation system further comprises a pilot operated input configured to generate the power adjustment signal for the first engine and to provide the second engine with a power input state change signal.

7. The power management system as recited in claim 1 wherein the power anticipation system further comprises one or more sensors configured to detect one or more flight parameters of the rotorcraft to form sensor data and a power anticipation module configured to generate the power adjustment signal for the first engine and to provide the second engine with a power input state change signal responsive to the sensor data.

8. The power management system as recited in claim 7 wherein the sensor data further comprises collective control data.

9. The power management system as recited in claim 7 wherein the sensor data further comprises first engine speed data.

10. The power management system as recited in claim 7 wherein the sensor data further comprises first engine torque output data.

11. The power management system as recited in claim 7 wherein the power anticipation module is implemented on a flight control computer.

12. The power management system as recited in claim 1 wherein the power adjustment signal causes the first engine to reduce the first power input coincident with the power input step changes from the zero power input state to the positive power input state.

13. The power management system as recited in claim 1 wherein the power adjustment signal causes the first engine to increase the first power input coincident with the power input step changes from the positive power input state to the zero power input state.

14. The power management system as recited in claim 1 wherein the power adjustment signal causes an adjustment in the quantity of fuel injected into the first engine.

15. The power management system as recited in claim 1 wherein the positive power input state further comprises a full power input state.

16. The power management system as recited in claim 1 wherein the power adjustment signal is mechanically coupled to the first engine.

17. The power management system as recited in claim 1 wherein the power adjustment signal is electrically coupled to the first engine.

18. The power management system as recited in claim 1 wherein the predetermined rotor speed threshold range is two percent above and two percent below the main rotor speed.

19. The power management system as recited in claim 1 wherein the predetermined rotor speed threshold range is one percent above and one percent below the main rotor speed.

20. A rotorcraft comprising:
a fuselage;
a main rotor system rotatable relative to the fuselage, the main rotor system having a main rotor speed;
a first engine providing a first power input to the main rotor system;
a second engine selectively providing a second power input to the main rotor system, the second engine having at least a zero power input state and a positive power input state;
a combining gearbox coupling the first and second engines to the main rotor system;
a sprag clutch having an input side coupled to the second engine and an output side coupled to the combining gearbox, the sprag clutch configured to generate power input step changes between the zero power input state and the positive power input state when a rotating speed of the input side transitions above or below a rotating speed of the output side; and
a power anticipation system configured to provide the first engine with a power adjustment signal in anticipation of the power input step changes;
wherein, the power adjustment signal causes the first engine to adjust the first power input coincident with the power input step changes to maintain the main rotor speed within a predetermined rotor speed threshold range.

Assignees

• Textron Innovations Inc

Inventors

• Gons William Mathisen

Classifications

• B64C27/06

  with single rotor · CPC title

• F02C9/44

  responsive to the speed of aircraft, e.g. Mach number control, optimisation of fuel consumption · CPC title

• F02C9/56

  with power transmission control · CPC title

• F02C6/206

  the vehicles being airscrew driven · CPC title

• F05D2270/44

  active, predictive, or anticipative · CPC title