WO2024205546A1

WO2024205546A1 - A rotary wing air vehicle

Info

Publication number: WO2024205546A1
Application number: PCT/TR2024/050300
Authority: WO
Inventors: Hasan Ibacoglu
Original assignee: Tusas- Turk Havacilik Ve Uzay Sanayii Anonim Sirketi
Priority date: 2023-03-28
Filing date: 2024-03-26
Publication date: 2024-10-03

Abstract

The present invention relates to a body (2); at least one power system (3) located on the body (2) and providing the necessary power for the movement of the body (2); at least one rotor (4) which is located on the body (2) to make a rotary movement; at least one carrier (5) which extends longitudinally along the body (2) in connection with the rotor (4); a plurality of blades (6) which are located on the rotor (4) and move on the carrier (5) together with the rotor (4).

Description

A ROTARY WING AIR VEHICLE

This invention relates to rotor and power generation systems used in a rotary wing air vehicle.

Conventional designs used for hybrid power systems in helicopters are diverse. Different control mechanisms may be designed for helicopters with co-axial rotors. In hybrid power systems consisting of an internal combustion engine and a generator set, the system can be designed so that it is not directly connected to the rotor system. Therefore, it is possible to create a more efficient power system. Hybrid power systems also provide a significant advantage in fuel consumption.

US9248909, which is included in the known-state of the art, discloses two rotors connected to a transmission, a plurality of blades located on a first rotor, a blade control system configured to allow the pitch of each rotor blade to be adjusted independently of each other. According to this document, the shaft does not carry the rotor loads and remains fixed between lower and upper rotor shafts as an intermediate shaft, enabling the generator rotating with the rotor to produce energy. Rotors, on the other hand, are located connected to rotating shafts, as in conventional systems, in which the rotors are moved inside and outside the fixed shaft and rotated by the transmission system.

CN110816814A, which is included in the known-state of the art, discloses a coaxial helicopter control-transmission system comprising a single gimbal. The coaxial helicopter control-transmission system consists of a transmission system, a cyclic control system and a route control system. The transmission system consists of a gear train, an engine and four concentric shafts. The cyclic control system has a single gimbal with two degrees of freedom, a longitudinal steering motor and a transverse steering motor. Provided that pitch, roll, elevation and descent control are completed in the co-axial helicopter controltransmission system, the single gimbal comprises an operating mode in which the rotor blades and heading control gimbal operate together so that the rotation speed of the rotor blades are controlled. Thus, the number of parts, size, weight and mechanism complexity of the helicopter were reduced, as well as the size of the entire control system. By controlling the rotation speed of the rotor with the rotation speed of the engine, transportation control of the helicopter is achieved, and thus the system can be used instead of conventional collective control.

Thanks to a rotary wing air vehicle according to the present invention, the shaft is located as a carrier in an air vehicle with two coaxial rotors, carries the upper and lower rotors thereon, and is positioned fixedly on the air vehicle, so that a system consisting of fewer parts than other control systems is provided.

Another object of the present invention is to provide a mechanism that controls the lower rotor and upper rotor by a gimbal and provides cyclic control with at least two servo motors connected to the gimbal, one performing rotational movement and the other performing linear movement, so that the mechanism provides collective control by revolution control.

A further object of the present invention is to provide a coaxial rotor structure in which the lower rotor is controlled by the gimbal and the upper rotor is controlled by the revolution control.

Yet another object of the present invention is to provide an air vehicle with a durable and economical carrier system.

The rotary wing air vehicle realized to achieve the object of the invention, which is defined in the first claim and other claims dependent thereon, comprises at least one body required for the flight of the air vehicle; at least one power system which is located on the body and generates the necessary power for the movement of the body; at least one rotor which is located on the body and rotates to allow the air vehicle to take off; at least one carrier on which the rotor is attached, with at least one end thereof connected to the rotor; a plurality of blades as part of the rotor, which are connected with the rotor so as to rotate with the rotor around the axis where it is connected to the carrier, thus enabling the air vehicle to take off.

The rotary wing air vehicle according to the invention comprises the carrier which remains fixed on the body without moving and serves to carry the rotors that are removably attached thereon; at least one actuator located on the rotor and/or carrier, triggered by the energy generated by the power system, and providing the movement of each rotor individually, wherein if the rotor is triggered by the power system, the actuator allows the blades to rotate around the axis on which the carrier lies on the body, depending on the number of revolutions defined by the user; at least one transmission line, i.e. an electrical cable, which is located in the carrier, between the actuator and the power system, and which ensures the transmission of the electrical energy generated by the power system to the actuator. The motor assembly on the carrier determines the positions for the rotor and blades to move. The power system generates the power required for the motor assembly to make linear and rotational movements, and provides the power required for the rotors to rotate at different speeds by providing electrical energy to the actuator. The actuator may be an electric motor.

In an embodiment of the invention, the rotary wing air vehicle comprises a first servo motor located on the motor assembly to move linearly; and a second servo which is capable of moving radially when triggered by the power system. The first servo motor and the second servo motor convert the electrical energy received from the power system into mechanical energy. The first servo motor moves up and down, providing tilt movement to the gimbal. The second servo motor rotates around its own axis and determines the tilt direction of the gimbal.

In an embodiment of the invention, the rotary wing air vehicle comprises at least one gimbal which is connected to each rotor and allows the movement of the rotors thanks to the first servo motor and the second servo motor. The gimbal is located between the motor assembly and the rotor. The first servo motor converts the electrical energy received from the power system into mechanical energy, such that it moves linearly up and down in the direction it extends on the carrier body. The first servo motor enables the gimbal to make the tilt movement. In this way, the blades can move cyclically by means of the rotor. The first servo motor determines the tilt angle of the system. The second servo motor makes a rotational movement when triggered by the power system, such that it adjusts the azimuth position of the blades. The second servo motor determines the direction in which the gimbal will be tilted. In an embodiment of the invention, the rotary wing air vehicle comprises a first rotor and a second rotor that are located coaxially on the carrier, with a distance between them. The first servo motor and the second servo motor are located between the first rotor and the second rotor. The first rotor and the second rotor determine the amount and direction of movement of the gimbals, thanks to the individually provided first gimbal and the second gimbal. Therefore, the cyclic movement of the rotor is enabled. The first servo motor and the second servo motor enable the movement of both the first gimbal and the second gimbal that are located both below and above the servo motors. Thanks to the first servo motor and the second servo motor, cyclic control of the first gimbal and the second gimbal is provided at the desired position and point.

In an embodiment of the invention, the rotary wing air vehicle comprises at least one connection interface which is removably attached to the carrier end and surrounds the carrier end. A gear wheel is connected to the carrier via the connection interface and surrounds the connection interface. An actuator is provided on each blade, which allows each blade to move independently of each other. There is a plurality of pinions extending outward from the center of the actuator and contacting the gear wheel. When the actuator is activated, the pinion rotates so that the gear wheel is rotated. Thanks to the connection interface, the carrier remains fixed. Since the rotor is connected to the gear wheel and actuator at one end, the rotor is activated by the rotation of the gear wheel.

In an embodiment of the invention, the rotary wing air vehicle comprises the actuator which provides the collective control movement of the blades by means of the first gimbal and the second gimbal, when the first rotor and the second rotor are moved at revolutions predetermined by the user with the energy provided by the power system.

In an embodiment of the invention, the rotary wing air vehicle comprises at least one connecting element located between the first rotor and the second rotor, and enabling the first servo motor and the second servo motor to be connected to the first gimbal and the second gimbal. The connecting element provides the mechanical connection between the gimbal and the first servo motor and/or the second servo motor. In an embodiment of the invention, the rotary wing air vehicle comprises the first rotor and the second rotor, which are located one under the other with a distance between them, so that their axes are equal.

In an embodiment of the invention, the rotary wing air vehicle comprises the power system which is run by a diesel engine and obtains power by connecting a generator to the diesel engine.

In an embodiment of the invention, the rotary wing air vehicle comprises the actuator used in manned and/or unmanned air vehicle with a coaxial rotor.

The rotary wing 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 rotary wing air vehicle

Figure 2 is a schematic view of the rotary wing air vehicle.

Figure 3 is a schematic view of gear wheel, pinion, connection interface and actuator.

Figure 4 is a schematic view of the actuator.

Figure 5 is a schematic view of the rotary wing 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. Rotary Wing Air Vehicle

2. Body

3. Power System

4. Rotor

401. First Rotor

402. Second Rotor

5. Carrier

6. Blade

7. Actuator

8. Transmission Line

9. Motor Assembly 10. First Servo Motor

11. Second Servo Motor

12. Gimbal

121. First Gimbal

122. Second Gimbal

13. Connection Interface

14. Gear Wheel

15. Pinion

16. Connecting Element

The rotary wing air vehicle (1) comprises a body (2); at least one power system (3) located on the body (2) and providing the necessary power for the movement of the body (2); at least one rotor (4) which is located on the body (2) to make a rotary movement; at least one carrier (5) which extends longitudinally along the body (2) in connection with the rotor (4); a plurality of blades (6) which are located on the rotor (4) and move on the carrier (5) together with the rotor (4).

The rotary wing air vehicle (1) according to the invention comprises the carrier (5) which is fixed on the body (2); at least one actuator (7) which is located on the rotor (4) and/or carrier (5), wherein the actuator (7) is triggered by the electrical energy provided by the power system (3), thus allowing the blades (6) to rotate by means of the rotor (4) according to the number of revolutions predetermined by the user, around an axis on which the carrier (5) extends on the body (2); at least one transmission line (8) which extends longitudinally between the actuator (7) and the power system (3) and transmits the electrical energy provided by the power system (3) to the actuator (7); a motor assembly (9) located on the carrier (5), consisting of at least one servo motor and allowing the rotor (4) to move in a position predetermined by the user; the power system (3) which triggers both the motor assembly (9) and the actuator (7).

The power system (3) provides the necessary power for the flight of the air vehicle. When triggered by the power system (3), the rotor (4) located on the carrier (5) is activated. The blades (6) provided in connection with the rotor (4) are moved by means of the rotor (4), depending on the number of revolutions predetermined by the user, and around an axis on which the carrier (5) extends. The actuator (7) is triggered by the electrical energy received from the power system (3) by means of the transmission line (8), so that movement control of the blades (6) is provided by the actuator (7) belonging to each blade (6) and the rotors (4) capable of rotating at different revolutions. The motor assembly (9) determines the amount and direction of the movement to be performed by the rotor (4). The power system supplies both the motor assembly (9) and the actuator (7) (Figure - 1, Figure - 2, Figure - 3).

The carrier (5), which is fixed on the body (2) without moving, carries the rotors (4) thereon. The rotor (4) is supported by the carrier (5), such that the rotor (4) is positioned on the carrier (5) in a rotatable manner by means of the gear wheel (14) (Figure - 4, Figure - 5).

In an embodiment of the invention, the rotary wing air vehicle (1) comprises a first servo motor (10) and a second servo motor (11) that are located on the motor assembly (9); the power system (3) which provides electrical energy by means of the transmission line (8), thereby triggering both the actuator (7) and the first servo motor (10) and the second servo motor (11). The power system (3) supplies the first servo motor (10) and the second servo motor (11) mechanically, while supplying the actuator (7) with electricity.

In an embodiment of the invention, the rotary wing air vehicle (1) comprises at least one gimbal (12) (a swah plate) connected to each rotor (4) and enabling the attack angles of the blades (6) to be changed when triggered by the first servo motor (10) and/or the second servo motor (11); a first servo motor (10) which is located on the body (2) in connection with the gimbal (12), wherein the first servo motor (10) moves the gimbal (12) up and down with the energy received from the power system (3), along the direction in which the carrier (5) extends, thus controlling the attack angles of the blades (6) and allowing cyclic movement thereof; a second servo motor (11) which is capable of rotating around its own axis, thus adjusting the azimuth position of the blades (6). The second servo motor (11) can rotate around its own axis by converting electrical energy into mechanical energy with the power provided by the power system (3). The first servo motor (10) moves linearly up and down, thereby moving the gimbal (12). The gimbal (12) enables the blades (6) to move with the tilt angle predetermined by the user. The second servo motor (11) rotates around its own axis and determines the tilt direction of the gimbal (12). In an embodiment of the invention, the rotary wing air vehicle (1) comprises a first rotor (401) and a second rotor (402) that are located on the carrier (5); the first servo motor (10) and the second servo motor (11) that are located between the first rotor (401) and the second rotor (402); a first gimbal (121) and a second gimbal (122) that are located on each of the first rotor (401) and the second rotor (402) and provide movement of the blades (6) via the first servo motor (10) and the second servo motor (11). Movement of the blades (6) can be controlled depending on the amount and direction of tilting of the first gimbal (121) and the second gimbal (122).

In an embodiment of the invention, the rotary wing air vehicle (1) comprises at least one connection interface (13) which is located on the carrier (5) to surround the carrier (5); at least one gear wheel (14) which is located on the connection interface (13) to surround the connection interface (13); a plurality of pinions (15) provided for each blade (6), extending from the actuator (7) to contact the gear wheel (14), and enabling the gear wheel (14) to rotate around the carrier (5). The connection interface (13) is located between the gear wheel (14) and the carrier (5). Therefore, the rotational movement triggered by the actuator (7) is transferred to the blades (6) by means of the pinion (15) and gear wheel (14), without moving the carrier (5).

In an embodiment of the invention, the rotary wing air vehicle (1) comprises the actuator (7) connected to the gear wheel (14) by means of the pinion (15) and enabling the power received from the power system (3) to be transmitted to the blades (6) via the rotor (4), thereby enabling collective control of the blades (6) through the revolution control defined for the first rotor (401) and the second rotor (402) that rotate in opposite directions. When triggered by the actuator (7), first rotor (401) and second rotor (402) are moved depending on the number of revolutions predetermined by the user. The collective movement of the blades (6) is enabled by the rotation of the first rotor (401) and the second rotor (402) at different revolutions and directions.

In an embodiment of the invention, the rotary wing air vehicle (1) comprises at least one connecting element (16) which is located between the first gimbal (121) and the second gimbal (122) and enables the first servo motor (10) and the second servo motor (11) to be connected to the first gimbal (121) and the second gimbal (122). The actuator (7) enables the blades (6) to move when the connecting elements (16) are triggered by the first servo motor (10) and the second servo motor (11) that are supplied by the power system (3).

In an embodiment of the invention, the rotary wing air vehicle (1) comprises the first rotor (401) and the second rotor (402) that are positioned on a co-axial basis on the carrier (5).

In an embodiment of the invention, the rotary wing air vehicle (1) comprises the power system (3), which is a diesel engine with a generator connected thereon. In this way, a hybrid system requiring low fuel costs is achieved.

In an embodiment of the invention, the rotary wing air vehicle (1) comprises the actuator (7) suitable for use in manned and/or unmanned air vehicles.

Claims

1. A rotary wing air vehicle (1) comprising a body (2); at least one power system (3) located on the body (2) and providing the necessary power for the movement of the body (2); at least one rotor (4) which is located on the body (2) to make a rotary movement; at least one carrier (5) which extends longitudinally along the body (2) in connection with the rotor (4); a plurality of blades (6) which are located on the rotor (4) and move on the carrier (5) together with the rotor (4), characterized by the carrier (5) which is fixed on the body (2); at least one actuator (7) which is located on the rotor (4) and/or carrier (5), wherein the actuator (7) is triggered by the electrical energy provided by the power system (3), thus allowing the blades (6) to rotate by means of the rotor (4) according to the number of revolutions predetermined by the user, around an axis on which the carrier (5) extends on the body (2); at least one transmission line (8) which extends longitudinally between the actuator (7) and the power system (3) and transmits the electrical energy provided by the power system (3) to the actuator (7); a motor assembly (9) located on the carrier (5), consisting of at least one servo motor and allowing the rotor (4) to move in a position predetermined by the user; the power system (3) which triggers both the motor assembly (9) and the actuator (7).

2. A rotary wing air vehicle (1) according to claim 1 , characterized by a first servo motor (10) and a second servo motor (11) that are located on the motor assembly (9); the power system (3) which provides electrical energy by means of the transmission line (8), thereby triggering both the actuator (7) and the first servo motor (10) and the second servo motor (11).

3. A rotary wing air vehicle (1) according to claim 2, characterized by at least one gimbal (12) (a swah plate) connected to each rotor (4) and enabling the attack angle of the blades (6) to be changed when triggered by the first servo motor (10) and/or the second servo motor (11); a first servo motor (10) which is located on the body (2) in connection with the gimbal (12), wherein the first servo motor (10) moves the gimbal (12) up and down with the energy received from the power system (3), along the direction in which the carrier (5) extends, thus controlling the attack angles of the blades (6) and allowing cyclic movement thereof; a second servo motor (11) which is capable of rotating around its own axis, thus adjusting the azimuth position of the blades (6).

4. A rotary wing air vehicle (1) according to claim 2 or claim 3, characterized by a first rotor (401) and a second rotor (402) that are located on the carrier (5); the first servo motor (10) and the second servo motor (11) that are located between the first rotor (401) and the second rotor (402); a first gimbal (121) and a second gimbal (122) that are located on each of the first rotor (401) and the second rotor (402) and provide movement of the blades (6) via the first servo motor (10) and the second servo motor (11).

5. A rotary wing air vehicle (1) according to any of the above claims, characterized by at least one connection interface (13) which is located on the carrier (5) to surround the carrier (5); at least one gear wheel (14) which is located on the connection interface (13) to surround the connection interface (13); a plurality of pinions (15) provided for each blade (6), extending from the actuator (7) to contact the gear wheel (14), and enabling the gear wheel (14) to rotate around the carrier (5).

6. A rotary wing air vehicle (1) according to claim 5, characterized by the actuator (7) connected to the gear wheel (14) by means of the pinion (15) and enabling the power received from the power system (3) to be transmitted to the blades (6) via the rotor (4), thereby enabling collective control of the blades (6) through the revolution control defined for the first rotor (401) and the second rotor (402) that rotate in opposite directions.

7. A rotary wing air vehicle (1) according to any of the claims 4 to 6, characterized by at least one connecting element (16) (control link) which is located between the first gimbal (121) and the second gimbal (122) and enables the first servo motor (10) and the second servo motor (11) to be connected to the first gimbal (121) and the second gimbal (122).

8. A rotary wing air vehicle (1) according to any of the claims 4 to 7, characterized by the first rotor (401) and the second rotor (402) that are positioned on a co-axial basis on the carrier (5).

9. A rotary wing air vehicle (1) according to any of the above claims, characterized by the power system (3), which is a diesel engine with a generator connected thereon.

10. A rotary wing air vehicle (1) according to any of the above claims, characterized by the actuator (7) suitable for use in manned and/or unmanned air vehicles.