Air vehicle

Patent metadata

Field	Value
Publication number	US-12325519-B2
Application number	US-202318368844-A
Country	US
Kind code	B2
Filing date	Sep 15, 2023
Priority date	Sep 30, 2022
Publication date	Jun 10, 2025
Grant date	Jun 10, 2025

Abstract

An air vehicle has a body, more than one wing located on the body creating a lifting force, at least one control surface located on the wing and movable along the direction in which the wing extends, an open position in which the control surface moves out of the wing in the direction in which the wing extends and increases the lifting force acting on the body, a closed position in which the control surface is moved from the open position and brought to the wing, a main actuator moving the control surface between the open and closed positions, at least one shaft enabling the control surface to be moved with the triggering of the main actuator and having one end connected to the control surface, and at least one additional actuator enabling the attack angle of the wings to be changed by rotating the wings on the body.

First claim

We claim:

1. An air vehicle ( 1 ) comprising:
a body ( 2 ),
a wing ( 3 ) located on the body ( 2 ) and creating a lifting force for flight of the body ( 2 ),
a control surface ( 4 ) located on the wing ( 3 ) and movable along a direction in which the wing ( 3 ) extends, the control surface ( 4 ) having an open position (O) in which the control surface ( 4 ) moves out of the wing ( 3 ) along the direction in which the wing ( 3 ) extends and increases the lifting force acting on the body ( 2 ) and a closed position (C) in which the control surface ( 4 ) is moved from the open position (O) and brought into the wing ( 3 ),
a main actuator ( 5 ) moving the control surface ( 4 ) between the open position (O) and the closed position (C),
at least one shaft ( 6 ) enabling the control surface ( 4 ) to be moved with triggering of the main actuator ( 5 ) and having one end connected to the control surface ( 4 ), and
an additional actuator ( 7 ) enabling an attack angle of the wing ( 3 ) to be changed by rotating the wing ( 3 ) on the body ( 2 ),
a support element ( 8 ) located on the wing ( 3 ) and enabling the wing ( 3 ) to be movably connected onto the body ( 2 ), an opening ( 9 ) extending thoroughly within the support element ( 8 ) and enabling the shaft ( 6 ) to trigger the control surface ( 4 ), and
wherein the additional actuator ( 7 ) is located in connection with the support element ( 8 ) and enables the wing ( 3 ) to be rotated around the shaft ( 6 ) located within the opening ( 9 ) by triggering the support element ( 8 ), the shaft ( 6 ) rotating around an axis thereof along a direction in which the shaft ( 6 ) extends within the support element ( 8 ) and extending from the opening ( 9 ) towards the control surface ( 4 ), enabling the control surface ( 4 ) to be extended telescopically outward from the wing ( 3 ) with the main actuator ( 5 ) triggering the control surface ( 4 ) and thus enabling the control surface ( 4 ) to be moved between the open position (O) and the closed position (C) irrespective of the additional actuator ( 7 ) triggering the wing ( 3 ).

2. The air vehicle ( 1 ) according to claim 1 , comprising a worm gear ( 10 ) located on the shaft ( 6 ), a threaded channel ( 11 ) located in the control surface ( 4 ) in a form fitting manner with the worm gear ( 10 ), and the control surface ( 4 ) coming to the open position (O) or the closed position (C) by moving along the direction in which the control surface ( 4 ) extends on the wing ( 3 ) with the worm gear ( 10 ) moving in the threaded channel ( 11 ) as a result of the shaft ( 6 ) being triggered by the main actuator ( 5 ).

3. The air vehicle ( 1 ) according to claim 1 , comprising at least one intermediate element ( 12 ) extending outwardly from the support element ( 8 ) so as to contact the additional actuator ( 7 ), enabling the support element ( 8 ) to be rotated by being triggered by the additional actuator ( 7 ).

4. The air vehicle ( 1 ) according to claim 3 , comprising at least one extension ( 13 ) located on the support element ( 8 ) and extending outwardly from the support element ( 8 ), at least one recess ( 14 ) located on the intermediate element ( 12 ) in a form fitting manner with the extension ( 13 ) and enabling the movement of the additional actuator ( 7 ) to be transmitted to the wing ( 3 ) by contacting the extension ( 13 ).

5. The air vehicle ( 1 ) according to claim 1 , comprising at least one bracket ( 15 ) located between the wing ( 3 ) and the body ( 2 ), at least one bearing ( 16 ) in the bracket ( 15 ), enabling to position the wing ( 3 ) rotatably relative to the body ( 2 ) around the axis in which the wing is connected to the body ( 2 ) and located on the support element ( 8 ) so as to surround the support element ( 8 ).

6. The air vehicle ( 1 ) according to claim 1 , comprising at least one control unit ( 17 ) that enables the control surface ( 4 ) to move between the open position (O) and the closed position (C) simultaneously by changing the attack angle of the wing ( 3 ) by triggering the main actuator ( 5 ) and the additional actuator ( 7 ).

7. The air vehicle ( 1 ) according to claim 1 , wherein the main actuator ( 5 ) is a step motor.

8. The air vehicle ( 1 ) according to claim 1 , wherein the additional actuator ( 7 ) is a linear actuator.

9. The air vehicle ( 1 ) according to claim 1 , wherein the wing ( 3 ) is located in the nose region of the body ( 2 ) and acts as a canard.

10. An air vehicle ( 1 ) comprising:
a body ( 2 ),
a first wing ( 3 ) and a second wing 3 located on the body ( 2 ), the first wing ( 3 ) and the second wing ( 3 ) each creating a lifting force for flight of the body ( 2 ),
a first control surface ( 4 ) located on the first wing ( 3 ) and a second control surface ( 4 ) located on the second wing ( 3 ), the first control surface ( 4 ) movable along a direction in which the first wing ( 3 ) extends, the first control surface ( 4 ) having a first open position (O) in which the first control surface ( 4 ) moves out of the first wing ( 3 ) along the direction in which the first wing ( 3 ) extends and increases the lifting force acting on the body ( 2 ) and a first closed position (C) in which the first control surface ( 4 ) is moved from the first open position (O) and brought into the first wing ( 3 ), the second control surface ( 4 ) movable along a direction in which the second wing ( 3 ) extends and having a second open position (O) in which the second control surface ( 4 ) moves out of the second wing ( 3 ) along the direction in which the second wing ( 3 ) extends and increases the lifting force acting on the body ( 2 ) and a second closed position (C) in which the second control surface ( 4 ) is moved from the second open position (O) and brought into the second wing ( 3 ),
a main actuator ( 5 ) moving the first and second control surfaces ( 4 ) between the respective first and second open positions (O) and the respective first and second closed positions (C),
a shaft ( 6 ) enabling the first control surface ( 4 ) to be moved with triggering of the main actuator ( 5 ) and having one end connected to the first control surface ( 4 ),
a first additional actuator ( 7 ) enabling an attack angle of the first wing ( 3 ) to be changed by rotating the first wing ( 3 ) on the body ( 2 ),
a second additional actuator ( 7 ) enabling an attack angle of the second wing ( 3 ) to be changed by rotating the second wing ( 3 ) on the body ( 2 ),
a first support element ( 8 ) located on the first wing ( 3 ) and enabling the first wing ( 3 ) to be movably connected onto the body ( 2 ), a first opening ( 9 ) extending thoroughly within the first support element ( 8 ) and enabling the shaft ( 6 ) to trigger the first control surface ( 4 ),
a second support element ( 8 ) located on the second wing ( 3 ) and enabling the second wing ( 3 ) to be movably connected onto the body ( 2 ), a second opening ( 9 ) extending thoroughly within the second support element ( 8 ) and enabling the shaft ( 6 ) to trigger the second control surface ( 4 ),
wherein the first additional actuator ( 7 ) is located in connection with the first support element ( 8 ) and enables the first wing ( 3 ) to be rotated around the shaft ( 6 ) located within the first opening ( 9 ) by triggering the first support element ( 8 ), the shaft ( 6 ) rotating around an axis thereof along a direction in which the shaft ( 6 ) extends within the first support element ( 8 ) and extending from the first opening ( 9 ) towards the first control surface ( 4 ), enabling the first control surface ( 4 ) to be extended telescopically outward from the first wing ( 3 ) with the main actuator ( 5 ) triggering the first control surface ( 4 ) and thus enabling the f

Assignees

• Tusas—Turk Havacilik Ve Uzay Sanayii Anonim Sirketi
• Tusas Turk Havacilik Ve Uzay Sanayii Anonim Sirketi

Inventors

• Ibacoglu Hasan
• Sahin Burhan

Classifications

• B64C5/04

  Noseplanes · CPC title

• B64C5/18

  in area · CPC title

• B64C5/16

  about spanwise axes · CPC title

• B64C39/12 Primary

  Canard-type aircraft · CPC title

• B64C13/38 Primary

  with power amplification · CPC title