Aircraft steering system, aircraft, and aircraft steering method

Patent metadata

Field	Value
Publication number	US-11459092-B2
Application number	US-201916375141-A
Country	US
Kind code	B2
Filing date	Apr 4, 2019
Priority date	May 8, 2018
Publication date	Oct 4, 2022
Grant date	Oct 4, 2022

Abstract

An aircraft steering system includes an electric actuator, a clutch, at least one plasma actuator, and a controller. The electric actuator is configured to vary an angle of a flight control surface of an aircraft. The clutch is configured to cut off torque by driving of the electric actuator. The torque is to be transmitted to the flight control surface. The at least one plasma actuator is configured to form a flow of air on a surface of the flight control surface when the torque is cut off. The controller is configured to control the electric actuator, the clutch, and the at least one plasma actuator.

First claim

The invention claimed is:

1. An aircraft steering system comprising:
an electric actuator configured to vary an angle of a flight control surface of an aircraft;
a clutch configured to cut off torque driving of the electric actuator, the torque being to be transmitted to the flight control surface;
at least one plasma actuator configured to form a flow of air on a surface of the flight control surface when the torque is cut off; and
a controller configured to control the electric actuator, the clutch, and the at least one plasma actuator, wherein
the controller is further configured to control the plasma actuator on a basis of control information for the flight control surface when the torque is cut off, the control information being inputted from a flight controller of the aircraft.

2. The aircraft steering system according to claim 1 , wherein the electric actuator comprises an electromechanical actuator.

3. The aircraft steering system according to claim 1 , further comprising a sensor configured to detect a malfunction of the electric actuator, wherein the controller is further configured to actuate, when the sensor detects the malfunction of the electric actuator, the clutch to automatically cut off the torque.

4. The aircraft steering system according to claim 3 , wherein the controller is further configured to automatically actuate the plasma actuator when the sensor detects the malfunction of the electric actuator.

5. The aircraft steering system according to claim 1 , wherein the controller is further configured to control, when the torque is cut off, the plasma actuator to perform one or both of suppression and reduction of aerodynamic vibration of the flight control surface.

6. The aircraft steering system according to claim 1 , wherein the controller is further configured to control at least one of amplitude of alternating-current voltage including a continuous wave, burst frequency of alternating-current voltage including a burst wave, and amplitude of the burst wave on the basis of the control information for the flight control surface, the continuous wave being applied between electrodes included in the plasma actuator, the burst wave being applied between the electrodes included in the plasma actuator.

7. The aircraft steering system according to claim 1 , wherein
the at least one plasma actuator comprises at least two plasma actuators,
an upper surface of the flight control surface is provided with at least one of the at least two plasma actuators, and
a lower surface of the flight control surface is provided with at least one of the at least two plasma actuators.

8. The aircraft steering system according to claim 7 , wherein the at least one plasma actuator comprises at least four plasma actuators,
and
at least a leading edge of the upper surface of the flight control surface, a trailing edge of the upper surface of the flight control surface, a leading edge of the lower surface of the flight control surface, and a trailing edge of the lower surface of the flight control surface are each provided with any of the at least four plasma actuators.

9. The aircraft steering system according to claim 1 , wherein the clutch comprises an electric clutch.

10. The aircraft steering system according to claim 1 , wherein the electric actuator includes a power cylinder in which a rod is moved with respect to a cylinder tube, and
a tip of the rod is rotatably coupled, via the clutch, to a first end of an arm, and a second end of the arm is coupled to a rotary shaft configured to vary an angle of attack of the flight control surface via the clutch.

11. The aircraft steering system according to claim 1 , wherein
the electric actuator includes an electric motor that rotates a rotary shaft configured to vary an angle of attack of the flight control surface, and
the clutch is disposed between the electric motor and the rotary shaft.

12. An aircraft comprising the aircraft steering system according to claim 1 .

13. An aircraft steering method comprising steering at least a moveable wing of the aircraft using the aircraft steering system according to claim 1 .

Assignees

• Subaru Corp

Inventors

• Kato Hiroki
• Nakazato Nobuyuki
• Murata Iwao

Classifications

• F16D2500/1023

  Electric motor · CPC title

• Y02T50/10

  Drag reduction · CPC title

• F16D37/008 Primary

  the particles being carried by a fluid, to vary viscosity when subjected to electric change, i.e. electro-rheological or smart fluids (composition of such fluids C10M171/001) · CPC title

• F16D2500/10475

  Magnetic field, e.g. electro-rheological, magnetisable particles · 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