High efficiency low power (HELP) active flow control methodology for simple-hinged flap high-lift systems

Patent metadata

Field	Value
Publication number	US-11884381-B2
Application number	US-202117238443-A
Country	US
Kind code	B2
Filing date	Apr 23, 2021
Priority date	Apr 23, 2020
Publication date	Jan 30, 2024
Grant date	Jan 30, 2024

Abstract

A simple-hinged flap assembly for a winged aircraft includes a simple-hinged flap having a leading airfoil section pivotably connected to a trailing airfoil section via a hinge, and an active flow control (AFC) actuator assembly. The assembly is connected to or integrally formed with the flap and includes upstream and downstream AFC actuators arranged in respective first and second rows, and collectively configured to provide first and second outlet mass flowrates. The downstream AFC actuators emit the second outlet mass flowrate at a rate that substantially exceeds the first outlet mass flowrate, such that the first outlet mass flowrate preconditions a boundary layer around the simple-hinged flap assembly. A winged aircraft includes a pneumatic power supply, fuselage, a wing connected to the fuselage, and the simple-hinged flap assembly.

First claim

What is claimed is:

1. A simple-hinged flap assembly for a winged aircraft, comprising:
a simple-hinged flap having a leading airfoil section that is pivotably connected to a trailing airfoil section via an intervening hinge; and
an active flow control (AFC) actuator assembly connected to or integrally formed with the simple-hinged flap, the AFC actuator assembly including:
a row of preconditioning upstream AFC actuators collectively configured to provide a first outlet mass flowrate, wherein the row of preconditioning upstream AFC actuators is arranged in a spanwise direction of a wing of the winged aircraft, and the first outlet mass flowrate preconditions a boundary layer of a natural flow around the simple-hinged flap assembly before flow separation when the winged aircraft is in flight; and
a row of downstream AFC actuators spaced apart from the row of preconditioning upstream AFC actuators, wherein the row of downstream AFC actuators is arranged in a spanwise direction of the wing of the winged aircraft, and is configured to provide a second outlet mass flowrate that substantially exceeds the first outlet mass flowrate, wherein the second outlet mass flowrate controls separation of the natural flow over the wing of the winged aircraft when the winged aircraft is in flight.

2. The simple-hinged flap assembly of claim 1 , wherein the winged aircraft includes a pneumatic power supply, the AFC actuator assembly is in fluid communication with the pneumatic power supply and is configured to receive an inlet mass flowrate therefrom, and the row of downstream AFC actuators is configured to provide the second outlet mass flowrate in response to the inlet mass flowrate.

3. The simple-hinged flap assembly of claim 2 , wherein the AFC actuator assembly defines therein a pneumatic feed tube connectable to the pneumatic power supply, and a plenum chamber in fluid communication with each of the pneumatic feed tube, the row of preconditioning upstream AFC actuators, and the row of downstream AFC actuators.

4. The simple-hinged flap assembly of claim 3 , wherein the row of preconditioning upstream AFC actuators includes fluidic oscillators.

5. The simple-hinged flap assembly of claim 3 , wherein the row of downstream AFC actuators includes steady-blowing jet nozzles.

6. The simple-hinged flap assembly of claim 1 , wherein the AFC actuator assembly including an actuator housing defining therein the row of preconditioning upstream AFC actuators and the row of downstream AFC actuators.

7. The simple-hinged flap assembly of claim 1 , wherein the AFC actuator assembly includes a floor connectable to the simple-hinged flap, an end wall arranged radially with respect to the floor, spanwise internal supporting walls, and a curved upper wall connected to the end wall and tapering toward a distal end of the floor, wherein the curved upper wall defines the row of preconditioning upstream AFC actuators, and wherein the floor, the spanwise internal supporting walls, and the curved upper wall together define the row of downstream AFC actuators.

8. The simple-hinged flap assembly of claim 7 , wherein the end wall defines a pneumatic feed tube configured to connect to a pneumatic power supply of the winged aircraft.

9. A winged aircraft comprising:
a pneumatic power supply;
a fuselage;
a wing connected to the fuselage;
an engine installed under the wing; and
a simple-hinged flap assembly connected to the wing and having:
a simple-hinged flap having a leading airfoil section that is pivotably connected to a trailing airfoil section via an intervening hinge; and
at least one active flow control (AFC) actuator assembly connected to or integrally formed with the simple-hinged flap, wherein the AFC actuator assembly is in fluid communication with the pneumatic power supply and receives an inlet mass flowrate therefrom, and includes:
a preconditioning upstream array of fluidic oscillators arranged in a first row in a spanwise direction of the wing of the winged aircraft, and collectively configured to emit a first outlet mass flowrate in response to the inlet mass flowrate, wherein the first outlet mass flowrate preconditions a boundary layer of a natural flow around the simple-hinged flap assembly before flow separation when the winged aircraft is in flight;
a downstream array of steady-blowing jet nozzles spaced apart from the preconditioning upstream array of fluidic oscillators and arranged in a second row, wherein the downstream array of steady-blowing jet nozzles is arranged in a spanwise direction of the wing of the winged aircraft, and is collectively configured to emit a second outlet mass flowrate that substantially exceeds the first outlet mass flowrate, the second outlet mass flowrate controls separation of the natural flow over the wing of the winged aircraft when the winged aircraft is in flight.

10. The winged aircraft of claim 9 , wherein the leading airfoil section and the trailing airfoil section are arranged in an upstream tangent plane and a downstream tangent plane of the simple-hinged flap assembly, respectively, the first row is situated in the upstream tangent plane, and the second row is situated in the downstream tangent plane.

11. The winged aircraft of claim 9 , wherein the at least one AFC actuator assembly includes an actuator housing defining therein the preconditioning upstream array of fluidic oscillators and the downstream array of steady-blowing jet nozzles.

12. The winged aircraft of claim 11 , wherein the at least one AFC actuator assembly defines therein a pneumatic feed tube connected to the pneumatic power supply, and a plenum chamber in fluid communication with each of the pneumatic feed tube, the preconditioning upstream array of fluidic oscillators, and the downstream array of steady-blowing jet nozzles.

13. The winged aircraft of claim 12 , wherein the actuator housing includes a floor connectable to the simple-hinged flap, an end wall arranged radially with respect to the floor, spanwise internal supporting walls, and a curved upper wall connected to the end wall and tapering toward a distal end of the floor, wherein the curved upper wall defines the preconditioning upstream array of fluidic oscillators therein, and wherein the floor, the spanwise internal supporting walls, and the curved upper wall together define the downstream array of steady-blowing jet nozzles.

14. The winged aircraft of claim 13 , wherein the end wall defines, as the pneumatic feed tube, a single pneumatic feed tube or multiple pneumatic feed tubes that are connected to the pneumatic power supply.

15. The winged aircraft of claim 9 , wherein the pneumatic power supply includes a compressor, engine bypass air, and/or an auxiliary power unit.

16. The winged aircraft of claim 9 , wherein the simple-hinged flap includes an inboard section and an outboard section, the at least one AFC actuator assembly includes a first plurality of AFC actuator assemblies arranged on or within the inboard section, and a second plurality of AFC actuator assemblies arranged on or within the outboard section.

17. An active flow control (AFC) actuator assembly for a simple-hinged flap aboard an aircraft having a pneumatic power supply, the simple-hinged flap having a leading airfoil section that is pivotably connected to a trailing airfoil section via an intervening hinge, the AFC actuator assembly comprising:
a housing defining a plenum chamber and a pneumatic feed tube configured to connect to the pneumatic power supply, thereby receiving an inlet mass flowrate from the pneumatic power supply, wherein the housing i

Assignees

• Nasa

Inventors

• Lin John C
• Melton Latunia P
• Koklu Mehti
• Andino Marlyn Y

Classifications

• B64C13/40 Primary

  using fluid pressure · CPC title

• B64C9/02

  Mounting or supporting thereof · CPC title

• B64C9/16

  at the rear of the wing · CPC title

• B64C9/18 Primary

  by single flaps · CPC title

• B64C21/04

  for blowing · CPC title