Active flow control systems and methods for aircraft

Patent metadata

Field	Value
Publication number	US-12040730-B2
Application number	US-202016880499-A
Country	US
Kind code	B2
Filing date	May 21, 2020
Priority date	May 21, 2020
Publication date	Jul 16, 2024
Grant date	Jul 16, 2024

Abstract

Example active flow control systems and methods for aircraft are described herein. An example an active flow control system includes a plenum, a plurality of nozzles fluidly coupled to the plenum, configured to eject high pressure air across a control surface, a compressor to supply pressurized air to the plenum, an electric motor to drive the compressor, and a control system to determine an amount of power input to the electric motor, determine a current speed of the electric motor, and determine a fault has occurred in the active flow control system based on the current speed of the electric motor.

First claim

What is claimed is:

1. An active flow control system for an aircraft, the active flow control system comprising:
a plenum;
a plurality of nozzles fluidly coupled to the plenum, the plurality of nozzles configured to eject high pressure air across a control surface;
a compressor to supply pressurized air to the plenum;
an electric motor to drive the compressor; and
a control system to:
determine an amount of power input provided to the electric motor;
determine a current speed of the electric motor;
determine a fault has occurred in the active flow control system based on at least one of the current speed of the electric motor or the amount of power input provided to the electric motor, the fault corresponding to at least one clog of the active flow control system;
determine a number of clogs in a corresponding number of nozzles of the active flow control system;
determine an increased amount of power input to the electric motor based on the number of clogs; and
in response to determining the fault has occurred, increase an output of the electric motor by applying the increased amount of power input to the electric motor.

2. The active flow control system of claim 1 , wherein the control system is to determine the current speed of the electric motor based on back-EMF of the electric motor.

3. The active flow control system of claim 1 , the increased amount of power input to the electric motor increases the speed of the electric motor.

4. The active flow control system of claim 1 , wherein the control system is to determine the fault has occurred by determining whether the current speed of the electric motor is within a threshold range of an expected speed of the electric motor associated with the power.

5. The active flow control system of claim 1 , wherein the control system is configured to determine a presence of a clog in a nozzle based on a change in speed of the electric motor that exceeds a predetermined threshold, and the system is configured to responsively determine an increased power level supplied to the electric motor to yield an increased motor speed that increases a current mass flow rate of pressurized air through the plenum and remaining open nozzles to a desired mass flow rate of pressurized air to maintain active flow control system performance.

6. The active flow control system of claim 4 , wherein the expected speed is based on at least one of an aircraft flight condition, a power and speed performance map for the active flow control system, or a power and speed performance map for the compressor, and wherein the control system includes a database to store the power and speed performance map for the active flow control system and the power and speed performance map for the compressor.

7. The active flow control system of claim 1 , wherein the control system is to determine whether the compressor is operating within operational limits of the compressor.

8. The active flow control system of claim 7 , wherein the control system is to, in response to determining the compressor is not operating within the operational limits, to activate a breaker to cease power to the electric motor.

9. The active flow control system of claim 7 , wherein the control system is to, in response to determining the compressor is not operating within the operational limits, open a relief valve coupled to the plenum.

10. A non-transitory computer readable medium comprising instructions that, when executed, cause at least one processor to at least:
determine an amount of power input provided to an electric motor of a compressor of an active flow control system of an aircraft;
determine a current speed of the electric motor while the power input is provided to the electric motor;
determine a fault has occurred in the active flow control system based on at least one of the current speed of the electric motor or the amount of power input provided to the electric motor, the fault corresponding to a clog of the active flow control system;
determine a number of clogs in a corresponding number of nozzles of the active flow control system;
determine an increased amount of power input to the electric motor based on the number of clogs; and
in response to determining the fault has occurred, increase an output of the electric motor by applying the increased amount of power input to the electric motor.

11. The non-transitory computer readable medium of claim 10 , wherein the instructions, when executed, cause the at least one processor to, in response to determining the fault has occurred, generate an alert in a flight deck of the aircraft.

12. The non-transitory computer readable medium of claim 10 , wherein the instructions, when executed, cause the at least one processor to determine the current speed of the electric motor based on back-EMF of the electric motor.

13. The non-transitory computer readable medium of claim 10 , wherein the instructions, when executed, cause the at least one processor to determine the fault has occurred by determining whether the current speed of the electric motor is within a threshold range of an expected speed of the electric motor associated with the power.

14. A method for an active flow control system for an aircraft, the method comprising:
determining, by executing an instruction with at least one processor, a current speed of an electric motor that drives a compressor supplying pressurized air to a plenum coupled to a plurality of nozzles that eject high pressure air across a control surface;
determining, by executing an instruction with the at least one processor, an amount of power input provided to the electric motor;
determining, by executing an instruction with the at least one processor, whether a fault has occurred in the active flow control system based on at least one of the current speed of the electric motor or the amount of power input provided to the electric motor, the fault corresponding to a clog of the active flow control system;
determining, by executing an instruction with the at least one processor, a number of clogs in a corresponding number of nozzles of the active flow control system;
determining, by executing an instruction with the at least one processor, an increased amount of power input to the electric motor based on the number of clogs; and
increasing an output of the motor, by executing an instruction with the at least one processor, in response to the determination that the fault has occurred by applying the increased amount of power input to the electric motor.

15. The method of claim 14 , further including determining that the fault corresponds to the clog in the active flow control system based on a change in speed of the electric motor that exceeds a predetermined threshold, and determining an increased power level supplied to the electric motor to yield an increased motor speed to increase a current mass flow rate of pressurized air through the plenum and remaining open nozzles to a desired mass flow rate of pressurized air for maintaining active flow control.

16. The method of claim 14 , further including:
determining whether the current speed of the electric motor is within an operational limit, and
disabling the active flow control system based on the determination that the current speed of the electric motor is within the operational limit.

17. The active flow control system of claim 1 , wherein the control system is to compare the number of clogs to a threshold to determine that the fault has occurred.

18. The active flow control system of claim 1 , wherein the control syste

Assignees

• Boeing Co

Inventors

• Rafferty Bradley J
• Beckman Mary E
• Leung Andrew
• Cameron Douglas C

Classifications

• B64D2045/0085

  Devices for aircraft health monitoring, e.g. monitoring flutter or vibration · CPC title

• B64C21/08

  adjustable · CPC title

• B64D2221/00

  Electric power distribution systems onboard aircraft · CPC title

• B64C21/04

  for blowing · CPC title

• Y02T50/10

  Drag reduction · CPC title