Wing structure for an aircraft including plasma actuators for controlling air flow through a slot, and method of controlling the same

Patent metadata

Field	Value
Publication number	US-11208201-B2
Application number	US-201916373873-A
Country	US
Kind code	B2
Filing date	Apr 3, 2019
Priority date	Apr 23, 2018
Publication date	Dec 28, 2021
Grant date	Dec 28, 2021

Abstract

A wing structure for an aircraft includes a stationary wing, a movable wing and at least one plasma actuator. The movable wing is configured to have a slot between the movable wing and the stationary wing. The at least one plasma actuator is configured to control air flow through the slot.

First claim

The invention claimed is:

1. A wing structure used for an aircraft, comprising:
a stationary wing;
a movable wing disposed so as to form a slot between the movable wing and the stationary wing;
a first plasma actuator disposed on an upper surface of the stationary wing and a second plasma actuator disposed on a lower surface of the stationary wing, the first plasma actuator and the second plasma actuator being configured to control airflow through the slot;
a control device configured to operate the first plasma actuator and the second plasma actuator under a condition corresponding to a steering angle of the movable wing,
wherein the control device is configured to provide air flow for preventing air from flowing through the slot by operating the first plasma actuator and the second plasma actuator when the steering angle of the movable wing is zero.

2. The wing structure according to claim 1 , wherein the controller is configured to form air flow from the upper surface of the stationary wing toward the lower surface of the movable wing through the slot by operating the first plasma actuator disposed on the upper surface of the stationary wing, while not operating the second plasma actuator disposed on the lower surface of the stationary wing when the steering angle of the movable wing is negative.

3. The wing structure according to claim 1 , wherein the control device is configured to form air flow from the lower surface of the stationary wing toward the upper surface of the movable wing through the slot by operating the second plasma actuator disposed on the lower surface of the stationary wing, while not operating the first plasma actuator disposed on the upper surface of the stationary wing when the steering angle of the movable wing is positive.

4. The wing structure according to claim 1 , wherein the movable wing is mechanically controlled by only an actuator configured to control the steering angle of the movable wing.

5. The wing structure according to claim 1 , wherein the wing structure is a main wing structure and the movable wing is a flap.

6. An aircraft comprising the wing structure according to claim 1 .

7. A method of controlling a wing structure of an aircraft, the aircraft comprising a stationary wing, a movable wing disposed so as to form a slot between the movable wing and a stationary wing, and at least one plasma actuator, the at least one plasma actuator comprising a first plasma actuator disposed on an upper surface of the stationary wing and a second plasma actuator disposed on a lower surface of the stationary wing, the first plasma actuator and the second plasma actuator being configured to control airflow through the slot,
wherein the method includes preventing air from flowing through the slot by operating the first plasma actuator and the second plasma actuator when a steering angle of the movable wing is zero.

8. The method of controlling a wing structure according to claim 7 , further comprising determining an alternating current voltage waveform to be applied between electrodes of either the first plasma actuator or the second plasma actuator as a burst waveform having a burst frequency or a burst period.

9. The method of controlling a wing structure according to claim 7 , further comprising forming air flow from the upper surface of the stationary wing toward the lower surface of the movable wing through the slot by operating the first plasma actuator disposed on the upper surface of the stationary wing, while not operating the second plasma actuator disposed on the lower surface of the stationary wing when the steering angle of the movable wing is negative.

10. The method of controlling a wing structure according to claim 7 , further comprising forming air flow from the lower surface of the stationary wing toward the upper surface of the movable wing through the slot by operating the second plasma actuator disposed on the lower surface of the stationary wing, while not operating the first plasma actuator disposed on the upper surface of the stationary wing when the steering angle of the movable wing is positive.

11. The method of controlling a wing structure according to claim 7 , further comprising mechanically controlling an actuator configured to control the steering angle of the movable wing.

12. A wing structure used for an aircraft, comprising:
a stationary wing;
a movable wing disposed so as to form a slot between the movable wing and the stationary wing;
a first plasma actuator disposed on an upper surface of the stationary wing and a second plasma actuator disposed on a lower surface of the stationary wing, the first plasma actuator and the second plasma actuator being configured to control airflow through the slot;
a control device configured to operate the first plasma actuator and the second plasma actuator under a condition corresponding to a steering angle of the movable wing,
wherein the control device is configured to form air flow from the upper surface of the stationary wing toward the lower surface of the movable wing through the slot by operating the first plasma actuator disposed on the upper surface of the stationary wing, while not operating the second plasma actuator disposed on the lower surface of the stationary wing when the steering angle of the movable wing is negative.

Assignees

• Subaru Corp

Inventors

• Kato Hiroki
• Kikuchi Maki
• Yoshida Kentaro
• Nakazato Nobuyuki
• Iwamoto Tomofumi

Classifications

• Y02T50/30

  Wing lift efficiency · CPC title

• B64C13/28

  mechanical · CPC title

• Y02T50/40

  Weight reduction · CPC title

• B64C9/18 Primary

  by single flaps · CPC title

• B64C23/005

  by other means not covered by groups B64C23/02 - B64C23/08, e.g. by electric charges, magnetic panels, piezoelectric elements, static charges or ultrasounds · CPC title