Active flow control systems and methods for aircraft

Patent metadata

Field	Value
Publication number	US-10526072-B2
Application number	US-201916396177-A
Country	US
Kind code	B2
Filing date	Apr 26, 2019
Priority date	Aug 11, 2016
Publication date	Jan 7, 2020
Grant date	Jan 7, 2020

Abstract

Example active flow control systems and methods for aircraft are described herein. An example active flow control system includes a plurality of nozzles arranged in an array across a surface of an aircraft. The nozzles are oriented to eject air across the surface to reduce airflow separation. The active flow control system also includes an air source coupled to the nozzles and a controller to activate the nozzles to eject air from the air source in sequence from outboard to inboard and then from inboard to outboard to create a wave of air moving from outboard to inboard and then from inboard to outboard across the surface.

First claim

What is claimed is:

1. An active flow control system comprising:
a plurality of nozzles arranged in an array across a surface of an aircraft, the nozzles oriented to eject air across the surface to reduce airflow separation;
an air source coupled to the nozzles, and
a controller to activate the nozzles to eject air from the air source in sequence from outboard to inboard and then from inboard to outboard to create a wave of air moving from outboard to inboard and then from inboard to outboard across the surface.

2. The active flow control system of claim 1 , wherein the plurality of nozzles are a first plurality of nozzles and the wave of air is a first wave of air, further including a second plurality of nozzles arranged in an array across the surface and disposed adjacent the first plurality of nozzles.

3. The active flow control system of claim 2 , wherein the controller is to activate the second plurality of nozzles to eject air from the air source in sequence from outboard to inboard and then from inboard to outboard to create a second wave of air moving from outboard to inboard and then from inboard to outboard across the surface.

4. The active flow control system of claim 3 , wherein the controller activates the first plurality of nozzles and the second plurality of nozzles such that the first and second waves of air move in a same direction inboard and outboard.

5. The active flow control system of claim 3 , wherein the controller activates the first plurality of nozzles and the second plurality of nozzles such that the first and second waves of air move in opposite directions inboard and outboard.

6. The active flow control system of claim 1 , wherein the nozzles are oriented to eject air in a substantially streamwise direction.

7. The active flow control system of claim 1 , wherein at least one of the nozzles is shaped to eject air at an angled direction relative to a streamwise direction.

8. The active flow control system of claim 1 , wherein the air source is from at least one of bleed air from an engine of the aircraft, an auxiliary power unit, a pressure storage vessel, or a compressor.

9. The active flow control system of claim 1 , wherein the surface is a movable flight control surface including at least one of a flap, an aileron, a slat, a rudder, an elevator, or a spoiler.

10. The active flow control system of claim 1 , wherein the aircraft is a fixed wing aircraft.

11. A method comprising:
supplying pressurized air to a plurality of nozzles, the nozzles arranged in an array across a surface of an aircraft, the nozzles oriented to eject air across the surface to reduce airflow separation, and
activating the nozzles to eject the pressurized air in sequence from outboard to inboard and then from inboard to outboard to create a wave of air that moves from outboard to inboard and then from inboard to outboard across the surface.

12. The method of claim 11 , wherein the plurality of nozzles are a first plurality of nozzles and the wave of air is a first wave of air, further including supplying the pressurized air to a second plurality of nozzles arranged an array across the surface and disposed adjacent the first plurality of nozzles.

13. The method of claim 12 , further including activating the second plurality of nozzles to eject air in sequence from outboard to inboard and then from inboard to outboard to create a second wave of air moving from outboard to inboard and then from inboard to outboard across the surface such that the first and second waves of air move in a same direction inboard and outboard.

14. The method of claim 12 , further including activating the second plurality of nozzles to eject air in sequence from outboard to inboard and then from inboard to outboard to create a second wave of air moving from outboard to inboard and then from inboard to outboard across the surface such that the first and second waves of air move in opposite directions inboard and outboard.

15. An active flow control system comprising:
a plurality of nozzles arranged in an array across a surface of an aircraft, the nozzles oriented to eject air in a substantially streamwise direction;
an air source coupled to the nozzles; and
a control system to:
activate the nozzles to eject air from the air source in sequence to create a wave of air moving across the surface; and
control an exit velocity of each of the nozzles such that the exit velocities of the nozzles are different.

16. The active flow control system of claim 15 , wherein a first nozzle of the plurality of nozzles is a converging-diverging nozzle having a throat.

17. The active flow control system of claim 16 , wherein a portion of the first nozzle defining the throat is constructed of a flexible material.

18. The active flow control system of claim 17 , further including an actuator operatively coupled to the portion of the first nozzle defining the throat, wherein the control system is to activate the actuator to apply pressure to or relieve pressure from the portion to change an area of the throat and affect an exit velocity of the first nozzle.

19. The active flow control system of claim 16 , wherein a portion of the first nozzle defining the throat is constructed of a shape memory alloy, wherein the control system is to activate the shape memory alloy to change an area of the throat and affect an exit velocity of the first nozzle.

20. The active flow control system of claim 15 , wherein the control system is to control the exit velocities of the nozzles such that the exit velocities increase from outboard to inboard as the wave of moving air moves from outboard to inboard.

Assignees

• Boeing Co

Inventors

• Shmilovich Arvin
• Yadlin Yoram
• Vijgen Paul

Classifications

• B64C9/38

  Jet flaps · CPC title

• B64C2230/04

  by actively generating fluid flow · CPC title

• G05D7/0664

  the plurality of throttling means being arranged for the control of a plurality of diverging flows from a single flow (G05D7/0652 takes precedence; ratio control G05D11/13) · CPC title

• B64C2230/06

  by explicitly adjusting fluid flow, e.g. by using valves, variable aperture or slot areas, variable pump action or variable fluid pressure · CPC title

• B64C21/04

  for blowing · CPC title