WO2024123284A1

WO2024123284A1 - An air vehicle

Info

Publication number: WO2024123284A1
Application number: PCT/TR2023/051260
Authority: WO
Inventors: Hasan Ibacoglu; Burhan SAHIN
Original assignee: Tusas- Turk Havacilik Ve Uzay Sanayii Anonim Sirketi
Priority date: 2022-12-07
Filing date: 2023-11-07
Publication date: 2024-06-13

Abstract

The present invention relates to a body (2); a plurality of propellers (3) on the body (2) that produce the necessary force for the flight of the air vehicle (1); at least one actuator (4) triggering the propellers (3) to change their pitch angles; at least one spindle (5) triggered by the actuator (4) and moving linearly, thus transmitting the movement of the actuator (4) to the propellers (3); at least one bearing element (6) located between the propeller (3) and the body (2) and allowing the propellers (3) to rotate around their own axis on the body (2).

Description

AN AIR VEHICLE

The present invention relates to a propeller control mechanism developed to control the propellers of an air vehicle.

Propellers are used in propulsion, transport and anti-torque systems in air vehicles. These propellers perform tasks such as producing variable forces in their systems, steering the air vehicle or providing flight stabilization by controlling the propeller angles. Various control mechanisms have been developed to provide angle control of the propellers in air vehicles.

The invention discussed in US8444385, which is included in the known-state of the art, discloses a gear mechanism used to change the angle of the propellers, and adjustment of the propeller angles by the rotation of the pinion gear provided on the propellers, on the propeller adjustment gears.

Thanks to an air vehicle according to the present invention, lift force and/or thrust force can be controlled with the propeller control system.

Another object of the invention is to provide a lighter aerodynamic propeller control system thanks to the developed mechanism.

The air vehicle realized to achieve the object of the invention, which is defined in the first claim and other claims dependent thereon, comprises a body; a plurality of propellers on the body that produce the necessary force for the movement of the air vehicle; at least one actuator that triggers the propellers to rotate simultaneously around an axis that they extend; at least one spindle triggered by the actuator and transmitting a linear movement of the actuator in a direction it extends to the propellers; at least one bearing element located between the propeller and the body, and allowing the propellers to rotate around an axis on which they extend on the body.

The air vehicle according to the invention comprises at least one shaft extending from the propeller to the spindle, allowing the propellers to move on the body, rotating in the bearing element by means of the actuator, thus enabling pitch angles of the propellers to change; at least one protrusion extending from the spindle to the shaft to trigger the shaft, placed on the spindle with a distance predetermined by the manufacturer to the axis on which the shaft extends towards the shaft, and/or produced as a single piece with the spindle, thereby triggering the shaft to rotate around the axis it extends upon the linear movement of the spindle.

In an embodiment of the invention, the air vehicle comprises at least one channel extending in a circular form on the body, compatible with the body structure of the air vehicle; a plurality of main shafts extending towards the spindle in the channel and a plurality of main propellers connected to the main shafts and thus moving together with the main shafts; a plurality of auxiliary shafts extending between the auxiliary propellers and the channel; a plurality of pinion gears through which the main shaft and auxiliary shaft pass; at least one rack gear triggered by the pinion gear upon the rotation of the main shaft, and moving on the channel to trigger the pinion gear on the auxiliary shaft, so that the auxiliary propellers rotate around the axis they extend.

In an embodiment of the invention, the air vehicle comprises propellers placed sequentially along the channel, e.g. a main propeller followed by an auxiliary propeller; and rack gears provided on all the main propellers and auxiliary propellers, in contact with the pinion gears.

In an embodiment of the invention, the air vehicle comprises a flow diverter system that provides anti-torque to the air vehicle; an opening through which the flow diverter system conducts air along the tail of the air vehicle; at least one power transmission element that transmits movement of the air vehicle engine to the propellers; the channel located on the tail cone of the air vehicle; a movement transfer element located between the power transmission element and the channel, enabling rotation of the channel by transmitting the movement of the power transmission element to the channel, thus enabling the main propellers and auxiliary propellers to create thrust force on the body.

In an embodiment of the invention, the air vehicle comprises a plurality of rack gears, each capable of moving independently of each other and extending between the main shaft and auxiliary shafts predetermined by the manufacturer; a plurality of actuators which trigger the rack gears for controlling them to move separately relative to each other, and which bring the main shaft and auxiliary shafts to different angle values by allowing them to rotate only in certain positions, thus producing variable lift forces.

In an embodiment of the invention, the air vehicle comprises the main propeller and auxiliary propeller that provide thrust for the air vehicle; the actuator that triggers the spindle to change the pitch angles of the main propeller and auxiliary propellers, thus allowing the thrust force created by the main propellers and auxiliary propellers to be controlled.

In an embodiment of the invention, the air vehicle comprises at least a second protrusion that extends almost perpendicularly and contacts the protrusions on the shaft, thus facilitating the rotation of the main shaft.

In an embodiment of the invention, the air vehicle comprises protrusions located sequentially on the spindle at equal intervals.

In an embodiment of the invention, the air vehicle comprises a helicopter mode (H) in which the body performs tasks such as vertical take-off, autorotation, and hovering; the flow diverter system (N) which creates anti-torque when the body is in helicopter mode (H); an aircraft mode (A) in which the rotor is stopped and the blades are used as fixed wings; the main propeller and auxiliary propeller that form the thrust system (P) providing thrust for the movement of the body in the aircraft mode (A).

In an embodiment of the invention, the air vehicle comprises a control unit that triggers the actuator when the body is in aircraft mode, so that pitch angles of the main propeller and auxiliary propellers are changed, and a thrust force suitable for flight conditions is generated.

In an embodiment of the invention, the air vehicle comprises the main shaft extending between the main propeller and the spindle so as to be in the movement transfer element.

The air vehicle realized to achieve the object of the present invention is illustrated in the attached drawings, in which:

Figure 1 is a perspective view of the propeller, power transmission system and channel. Figure 2 is a perspective view of the actuator, main propeller and auxiliary propeller.

Figure 3 is a schematic view of the main shaft, bearing element and protrusions.

Figure 4 is a perspective view of the opening, thrust system and flow diverter system.

Figure 5 is a schematic view of the engine.

Figure 6 is a schematic view of the pinion gear and rack gear.

Figure 7 is a perspective view of the aircraft mode of the air vehicle.

All the parts illustrated in figures are individually assigned a reference numeral and the corresponding terms of these numbers are listed below:

1. Air vehicle

2. Body

3. Propeller

301. Main propeller

302. Auxiliary propeller

4. Actuator

5. Spindle

6. Bearing element

7. Shaft

701. Main shaft

702. Auxiliary shaft

8. Protrusion

9. Channel

10. Pinion gear

11. Rack gear

12. Opening

13. Power transmission element

14. Movement transfer element

15. Second protrusion

16. Control unit

(N) Flow diverter system

(M) Engine

(P) Thrust system

(A) Aircraft mode The air vehicle (1) comprises a plurality of propellers (3) on the body (2) that produce the necessary force for the flight of the air vehicle (1); at least one actuator (4) triggering the propellers (3) to change their pitch angles; at least one spindle (5) triggered by the actuator (4) and moving linearly, thus transmitting the movement of the actuator (4) to the propellers (3); at least one bearing element (6) located between the propeller (3) and the body (2) and allowing the propellers (3) to rotate around their own axis on the body (2).

The air vehicle (1) according to the invention comprises at least one shaft (7) located between the propeller (3) and the spindle (5) and allowing placement of the propellers (3) on the body (2), wherein the shaft (7) is triggered by the actuator (4) to rotate around its axis on the body (2), thus changing the pitch angles of the propellers (3); at least one protrusion (8) extending from the spindle (5) towards the shaft (7), so as to be in contact with the shaft (7), wherein the protrusion (8) is located on the spindle (5) with a distance to an axis on which the shaft (7) extends, thereby allowing the shaft (7) to be triggered and rotate around its own axis by the linear movement of the spindle (5) on the axis it extends (Figure 1 , Figure 2, Figure 3).

During a flight of an air vehicle, when triggered by the actuator (4) on the body (2), the propellers (3) move rotatably in the bearing elements (6) such that their pitch angles change. In this way, different forces such as thrust or lift can be produced during a flight of the air vehicle.

Upon the linear movement of the actuator (4) on the air vehicle, the protrusion (8) or protrusions (8) on the spindle (5) trigger the shafts (7) simultaneously, allowing the pitch angles of the propellers (3) to be changed simultaneously. The shafts (7) extend on the body (2) with the spindle (5) remaining in the center. By placing the protrusions (8) on the spindle (5) at a distance from the center where the shafts (7) extend, the shafts (7) can rotate around the axis they extend with the force arm created.

In an embodiment of the invention, the air vehicle (1) comprises at least one channel (9), at least a part of which is circular in shape; a plurality of main shafts (701) extending from the channel (9) so as to be in contact with the spindle (5); a plurality of main propellers (301) moving with the main shafts (701); a plurality of auxiliary propellers (302) triggered by the rotation of the main shaft (701); a plurality of auxiliary shafts (702) extending between the auxiliary propellers (302) and the channel (9); a plurality of pinion gears (10) located to surround a wall of the main shaft (701) and auxiliary shaft (702); at least one rack gear (11) located on the body (2) opposite to the pinion gear (10), and triggered by the rotation of the main shaft (701) to move on the channel (9), thereby triggering the pinion gear (10) on the auxiliary shaft (302) for rotating the auxiliary propellers (302). The main shaft (701) and auxiliary shaft (702) passing through the bearing elements (6) on the channel (9) and the main propeller (301) and auxiliary propellers (302) move in a rotatable manner. Thanks to the pinion gear (10) located on the main shafts (701) and auxiliary shafts (702) and the rack gear (11) that provides movement transfer in between, it is possible to change the pitch angles of the auxiliary propellers (302) without the need for a contact between the auxiliary shafts (702) and the spindle (5). Therefore, the weight of the parts used in the system is reduced (Figure 6).

In an embodiment of the invention, the air vehicle (1) comprises the main propellers (301) and auxiliary propellers (302) that are placed sequentially and at equal intervals along the channel (9); the rack gear (11) extending along the channel (9) in contact with the pinion gears (10) which are located on the main shafts (701) and auxiliary shafts (702). The rack gear (11) extends in a circular form along and within the channel (9) and contacts the pinion gears (10) on the main shaft (701) and auxiliary shafts (702). Therefore, all propellers (3) are triggered simultaneously.

In an embodiment of the invention, the air vehicle (1) comprises a flow diverter system (N) located on the air vehicle for providing anti-torque to the air vehicle; an opening (12) through which the flow diverter system (N) transmits air along the tail of the air vehicle; at least one power transmission element (13) that transmits the movement of the air vehicle engine (M) to the propellers (3); the channel (9) located on the tail cone of the air vehicle; a movement transfer element (14) between the power transmission element (13) and the channel (9), which transfers a movement of the power transmission element (13) to the channel (9) to rotate the channel (9), thereby enabling the main propellers (301) and auxiliary propellers (302) to create thrust force on the body (2) (Figure 4).

In an embodiment of the invention, the air vehicle (1) comprises a plurality of rack gears (11), each capable of moving separately and extending between the propellers (3) predetermined by the manufacturer; a plurality of actuators (4) triggering the rack gears (11), so that the propellers (3) which are controlled to move separately relative to each other are provided with different pitch angle values, thereby producing variable lift forces. In an embodiment of the invention, the air vehicle (1) comprises the main propeller (301) and auxiliary propeller (302) that are provided on the air vehicle for providing the thrust for the movement of the air vehicle; the actuator (4) which triggers the spindle (5) to change the pitch angle of the main propeller (301) and auxiliary propellers (302), thus controlling the thrust force produced by the propellers (301 , 302). Therefore, the thrust desired by the user can be produced according to the flight conditions of the air vehicle.

In an embodiment of the invention, the air vehicle (1) comprises at least a second protrusion (15) located on the shaft (7) and contacting the protrusions (8) such that the second protrusion (15) is almost perpendicular to an axis on which the shaft (7) extends towards the spindle (5), thus enabling the main shaft (701) to be rotated. Therefore, due to the lengthening of the force arm, the force required by the protrusions (8) to rotate the shafts (7) decreases.

In an embodiment of the invention, the air vehicle (1) comprises protrusions (8) extending on the spindle (5) at equal radial intervals, with a 90-degree angle between the protrusions (8).

In an embodiment of the invention, the air vehicle (1) comprises a helicopter mode in which the body (2) performs tasks such as vertical landing, take-off, autorotation and hovering; a flow diverter system (N) creating anti-torque when the body (2) is in the helicopter mode; an aircraft mode (A) in which the rotor (4) is stopped and the blades are used as fixed wings; the main propeller (301) and the auxiliary propeller (302) that form the thrust system (P) providing thrust for the movement of the body (2) when the body (2) is in the aircraft mode. In this way, the thrust force produced by the propellers (3) can be controlled according to the mode of a multi-mode air vehicle (Figure 7).

In an embodiment of the invention, the air vehicle (1) comprises at least one control unit (16) which changes a pitch angle of the main propeller (301) and auxiliary propellers (302) by triggering the actuator (4) when the body (2) is in the aircraft mode (A), thereby adjusting the thrust force applied by the thrust system (P) to the air vehicle. Thanks to the control unit (16), control of the main propeller (301) and auxiliary propellers (302) can be achieved automatically (Figure 5). In an embodiment of the invention, the air vehicle (1) comprises the main shaft (701) located in the movement transfer element (14), between the main propeller (301) and the spindle (5). Thus, the shafts (7) are prevented from obstructing the air flow within the opening (12).

Claims

1. An air vehicle (1) comprising a body (2); a plurality of propellers (3) on the body (2) that produce the necessary force for the flight of the air vehicle (1); at least one actuator (4) triggering the propellers (3) to change their pitch angles; at least one spindle (5) triggered by the actuator (4) and moving linearly, thus transmitting the movement of the actuator (4) to the propellers (3); at least one bearing element (6) located between the propeller (3) and the body (2) and allowing the propellers (3) to rotate around their own axis on the body (2), characterized by at least one shaft (7) located between the propeller (3) and the spindle (5) and allowing placement of the propellers (3) on the body (2), wherein the shaft (7) is triggered by the actuator (4) to rotate on the body (2) around an axis it extends, thus changing the pitch angles of the propellers (3); at least one protrusion (8) extending from the spindle (5) towards the shaft (7), so as to be in contact with the shaft (7), wherein the protrusion (8) is located on the spindle (5) with a distance to an axis on which the shaft (7) extends, thereby allowing the shaft (7) to be triggered and rotate around its own axis by the linear movement of the spindle (5) on the axis it extends.

2. An air vehicle (1) characterized by at least one channel (9), at least a part of which is circular in shape; a plurality of main shafts (701) extending from the channel (9) so as to be in contact with the spindle (5); a plurality of main propellers (301) moving with the main shafts (701); a plurality of auxiliary propellers (302) triggered by the rotation of the main shaft (701); a plurality of auxiliary shafts (702) extending between the auxiliary propellers (302) and the channel (9); a plurality of pinion gears (10) located to surround a wall of the main shaft (701) and auxiliary shaft (702); at least one rack gear (11) located on the body (2) opposite to the pinion gear (10), and triggered by the rotation of the main shaft (701) to move on the channel (9), thereby triggering the pinion gear (10) on the auxiliary shaft (302) for rotating the auxiliary propellers (302).

3. An air vehicle (1) according to claim 2, characterized by the main propellers (301) and auxiliary propellers (302) that are placed sequentially and at equal intervals along the channel (9); the rack gear (11) extending along the channel (9) in contact with the pinion gears (10) which are located on the main shafts (701) and auxiliary shafts (702).

4. An air vehicle (1) according to claim 2 or claim 3, characterized by a flow diverter system (N) located on the air vehicle for providing anti-torque to the air vehicle; an opening (12) through which the flow diverter system (N) transmits air along the tail of the air vehicle; at least one power transmission element (13) that transmits the movement of the air vehicle engine (M) to the propellers (3); the channel (9) located on the tail cone of the air vehicle; a movement transfer element (14) between the power transmission element (13) and the channel (9), which transfers a movement of the power transmission element (13) to the channel (9) to rotate the channel (9), thereby enabling the main propellers (301) and auxiliary propellers (302) to create thrust force on the body (2).

5. An air vehicle (1) according to any of the claims 2 to 4, characterized by a plurality of rack gears (11), each capable of moving separately and extending between the propellers (3) predetermined by the manufacturer; a plurality of actuators (4) triggering the rack gears (11), so that the propellers (3) which are controlled to move separately relative to each other are provided with different pitch angle values, thereby producing variable lift forces.

6. An air vehicle (1) according to any of the claims 2 to 4, characterized by the main propeller (301) and auxiliary propeller (302) that are provided on the air vehicle for providing the thrust for the movement of the air vehicle; the actuator (4) which triggers the spindle (5) to change the pitch angle of the main propeller (301) and auxiliary propellers (302), thus controlling the thrust force produced by the propellers (301, 302).

7. An air vehicle (1) according to any of the claims 2 to 6, characterized by at least a second protrusion (15) located on the shaft (7) and contacting the protrusions (8) such that the second protrusion (15) is almost perpendicular to an axis on which the shaft (7) extends towards the spindle (5), thus enabling the main shaft (701) to be rotated.

8. An air vehicle (1) according to any of the above claims, characterized by protrusions (8) extending on the spindle (5) at equal radial intervals, with a 90- degree angle between the protrusions (8).

9. An air vehicle (1) according to any of the claims 2 to 8, characterized by a helicopter mode in which the body (2) performs tasks such as vertical landing, take-off, autorotation and hovering; a flow diverter system (N) creating anti-torque when the body (2) is in the helicopter mode; an aircraft mode in which the rotor (4) is stopped and the blades are used as fixed wings; the main propeller (301) and the auxiliary propeller (302) that form the thrust system (P) providing thrust for the movement of the body (2) when the body (2) is in the aircraft mode.

10. An air vehicle (1) according to any of the claims 2 to 9, characterized by at least one control unit (16) which changes a pitch angle of the main propeller (301) and auxiliary propellers (302) by triggering the actuator (4) when the body (2) is in the aircraft mode (A), thereby adjusting the thrust force applied by the thrust system (P) to the air vehicle.

11. An air vehicle (1) according to any of the claims 4 to 10, characterized by the main shaft (701) located in the movement transfer element (14), between the main propeller (301) and the spindle (5).