The present invention relates to an electromechanical actuating system which provides redundancy for drive levers.

Actuators are used to supply mechanical power to parts in air vehicles. A plurality of power supplying units is used to provide redundancy in applications where movement mechanisms are vital. In previous applications, it was intended to provide redundancy only to the levers of the power supply units. However, a large number of equipment is needed in such systems for redundancy and power transfer mechanisms.

The Chinese patent document CN 107425649, which is included in the known state of the art, discloses an actuating system used in air vehicles. The system comprises a first motor supplying power to the actuator, a second motor providing redundancy to the actuator, an electromagnetic brake, a potentiometer, and gear systems used for power transfer. In said system, planet gear systems are used to supply power to the actuator by the auxiliary motor. However, it is not discussed that mechanical redundancy is provided for failures that may occur in the system, other than the first engine.

US patent document US6791245, which is included in the known state of the art, discloses a linear electromechanical actuating system that provides redundancy. Said system includes various alternative designs and comprises a plurality of first motors supplying power to the actuator screw lever, a plurality of second motors providing redundancy to the actuator screw lever, and two distinct gear paths for actuating the screw lever. However, since the system providing redundancy and the primary system are positioned in the same chamber, redundancy cannot be provided efficiently.

Thanks to the actuating system according to the present invention, redundancy can be provided for the entire system against one or more mechanism failures in order to maintain the operation in case of failure of movement mechanisms used for controlling landing gears and/or control surfaces at the air vehicles during operation, and a movement mechanism with less complexity is achieved. Another object of the present invention is to provide a movement mechanism for which structural integrity is provided.

A further object of the present invention is to provide a simplified movement mechanism which is downsized and made lighter volumetrically.

The actuating system realized to achieve the object of the invention and defined in the first claim and the other claims dependent thereon comprises a body which can be used for landing gears and/or control surfaces of air vehicles; a first chamber located in the body and extending in its entire length; a second chamber removably connected to the first chamber; a first motor located in the first chamber; a first gear path which surrounds the first chamber on the outer surface of the first chamber and on which the first chamber is moved as a result of being triggered; at least one shaft located in the second chamber and rotatable clockwise or counter-clockwise around its own axis when actuated by the first motor; and at least a second motor which is operated and provides energy production when the first motor is deactivated by the control unit, and is controlled by the control unit located on the body.

The actuating system according to the present invention comprises at least one power transfer mechanism which is stably positioned on the body, enables the first chamber moving on the first gear path to be triggered by the second motor, and thus, enables the first chamber and the first motor located therein to move out of the body.

In an embodiment of the invention, the actuating system comprises at least one channel which is provided such that it covers a part of the first gear path located on the first chamber; and at least a first wedge which is located in the channel and which, as a result of triggering the power transfer mechanism by the second motor, enables the first motor rotating around its own axis to move forward together with the first motor housed therein and the second chamber to which the first chamber is connected.

In an embodiment of the invention, the actuating system comprises a first power transfer element located on the body and rotatable around its own axis with the power supply by the second motor; and a second power transfer element located between the first chamber and the first power transfer element, triggered by rotation of the first power transfer element around its own axis, and thus, enabling the first chamber to be moved.

In an embodiment of the invention, the actuating system comprises a first power transfer element in the form of a gear wheel and a second power transfer element in the form of a gearwheel.

In an embodiment of the invention, the actuating system comprises at least one coupling which is located in the first chamber and enables the shaft to rotate around its own axis by transferring the power transmitted from the first motor to the shaft.

In an embodiment of the invention, the actuating system comprises a coupling which is partially made of flexible material or partially made of metal material.

In an embodiment of the invention, the actuating system comprises at least a second gear path which is located on the outer surface of the shaft such that it almost completely surrounds the shaft.

In an embodiment of the invention, the actuating system comprises a first gear path and a second gear path, which are in the form of a buttress gear.

In an embodiment of the invention, the actuating system comprises at least one bearing element which is located in the second chamber, positioned such that it almost completely surrounds the shaft, and is movable along the direction in which it extends by the energy transmitted from the shaft.

In an embodiment of the invention, the actuating system comprises a bearing element in the form of a ball bearing or a plain bearing.

In an embodiment of the invention, the actuating system comprises at least one arm located such that it contacts the bearing element, movable along the direction in which it extends by the energy transmitted from the shaft triggered by the first motor, and moves along the direction in which it extends by the energy transmitted from the power transfer mechanism if the second motor is activated.

In an embodiment of the invention, the actuating system comprises at least a second wedge which is located in the second chamber such that it contacts the bearing element and the second chamber, and enables the bearing element to move linearly while enabling the arm connected to the bearing element to move outwards.

Exemplary embodiments of the movement system according to the present invention are illustrated in the attached drawings, in which:

Figure 1 is a perspective view of an actuator mechanism.

Figure 2 is a side sectional view of an actuator mechanism.

Figure 3 is a side sectional view of an actuator mechanism.

Figure 4 is a side sectional view of first chamber, second motor, first transfer element, second transfer element and first gear path.

Figure 5 is a top view of first gear path and channel.

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

1. Actuating system

2. Body

3. First Chamber

4. Second Chamber

5. First Motor

6. First Gear Path

7. Shaft

8. Second Motor

9. Power Transfer Mechanism

901. First Power Transfer Element

902. Second Power Transfer Element

10. Channel

11. First Wedge 12. Coupling

13. Second Gear Path

14. Bearing Element

15. Arm

16. Second Wedge

(K) Control Unit

The actuating system (1) comprises a body (2) suitable for use at landing gears and/or control surfaces of air vehicles; at least a first chamber (3) extending in the body (2) in its entire length; at least a second chamber (4) removably attached to the first chamber (3); at least a first motor (5) located in the first chamber (3) and providing power generation; a first gear path (6) which is located on outer perimeter of the first chamber (3) such that it almost completely surrounds the first chamber (3) that moves when the first gear path (6) is triggered; at least one shaft (7) which is located in the second chamber (4) and is rotatable around its own axis upon being triggered by the first motor (5); and at least a second motor (8) which is located on the body (2), provides energy production when the first motor (5) is deactivated by the control unit (K), and is operated by the control unit (K) (Figure 1 and Figure 2).

An actuating system (1) of the present invention comprises at least one power transfer mechanism (9) which is located on the body (2) such that its position remains unchanged, triggers the first gear path (6) by the energy received from the second motor (8), and thus, provides the first motor (5) to move out of the body (2) together with the first chamber (3) (Figure 2).

Actuation of landing gears and/or control surfaces provided at air vehicles is controlled by the actuating system (1). The shaft (7) provided in the second chamber (4) is triggered by the first motor (5) provided in the first chamber (3) such that the shaft (7) rotates around its own axis, and thus, the actuating system (1) is operated. In case that the first motor (5) fails to supply energy to the shaft (7) or the shaft (7) fails to perform its rotational movement around its own axis, the control unit (K) deactivates the first motor (5) and operates the second motor (8). Therefore, redundancy is provided for the actuating system (1). The power transfer mechanism (9) is triggered by the second motor (8) and the second motor (8) is connected such that it contacts the first chamber (3). The first chamber (3) moves on the first gear path (6) by the energised power transfer mechanism (9). The second chamber (4) which is integrally connected with the first chamber (3) is moved by moving the first chamber (3) on the first gear path (6).

In an embodiment of the invention, the actuating system (1) comprises at least one channel (10) which is located on the first gear path (6) such that it almost partially surrounds the first chamber (3); and at least a first wedge (11) which is located on the channel (10) and allows the first chamber (3) to make a linear movement by rotating around its own axis by means of the power transfer mechanism (9) energised by the second motor (8). The first wedge (11) is positioned in the channel (10) located on the first gear path (6) surrounding the first chamber (3). The first chamber (3), which is triggered by the power transfer mechanism (9) and rotates around its own axis, is moved linearly by means of the first wedge (11) positioned in the channel (10) located on the first gear path (6). Therefore, it is enabled that the first chamber (3) is moved outwards (Figure 3, Figure 4, Figure 5).

In an embodiment of the invention, the actuating system (1) comprises a power transfer mechanism (9) which has a first power transfer element (901) located on the body (2) and rotatable around its own axis by the energy received from the second motor (8), and a second power transfer element (902) which is located on the body (2) such that it is between the first chamber (3) and the first power transfer element (901), wherein the second power transfer element (902) is triggered by rotation of the first power transfer element (901) around its own axis and thus enables the first chamber (3) to move. The second motor (8) operated by the control unit (K) enables the first power transfer element (901), which is connected such that it contacts the second motor (8), to move by rotating around its own axis. The second power transfer element (902), which is connected such that it contacts the first power transfer element (901), is triggered by actuation of the first power transfer element (901) and enables the first chamber (3) to which it is connected in contact to move on the first gear path (6) by rotating (Figure 4).

In an embodiment of the invention, the actuating system (1) comprises a first power transfer element (901) and a second power transfer element (902), which are in the form of a gear. Teeth of the first power transfer element (901) triggered by the second motor (8) trigger the teeth provided on the second power transfer element (902). Teeth on the second power transfer element (902) trigger the first gear path (6) which is located such that it almost completely surrounds the first chamber (3) (Figure 4).

In an embodiment of the invention, the actuating system (1) comprises at least one coupling (12) which is located in the first chamber (3), transmits the power received from the first motor (5) to the shaft (7), and thus, provides the shaft (7) to rotate around its own axis. The coupling (12) is positioned such that it is between the first motor (5) and the shaft (7). It enables that the energy supplied from the first motor (5) is transferred to the shaft (7) and the shaft (7) is triggered such that it rotates around its own axis (Figure 2).

In an embodiment of the invention, the actuating system (1) comprises a coupling (12) which is partially made of flexible material and/or partially made of metal material. The coupling (12) at least partially prevents effect of vibration and pulse that is generated by the energy transferred to the shaft (7) by the first motor (5).

In an embodiment of the invention, the actuating system (1) comprises at least a second gear path (13) which is located on the outer perimeter of the shaft (7) such that it almost completely surrounds the shaft (7). The shaft (7) triggered by the first motor (5) can rotate together with the second gear path (13) around its axis without moving linearly.

In an embodiment of the invention, the actuating system (1) comprises a first gear path (6) and a second gear path (13), which are in the form of a buttress gear.

In an embodiment of the invention, the actuating system (1) comprises at least one bearing element (14) which is located in the second chamber (4), almost completely surrounds the shaft (7), and is movable along the direction in which it extends by the energy transmitted from the shaft (7). The bearing element (14) is triggered such that it rotates on the second gear path (13), which almost completely surrounds the shaft (7), as a result of movement of the shaft (7) around its own axis (Figure 2).

In an embodiment of the invention, the actuating system (1) comprises a bearing element (14) in the form of a ball bearing or a plain bearing. The bearing element (14) in the form of a ball bearing or a plain bearing which almost completely surrounds the shaft (7) easily provides the movement on the shaft (7) out of the second chamber (4).

In an embodiment of the invention, the actuating system (1) comprises at least one arm (15) which is located on the second chamber (4) such that it contacts the bearing element (14), wherein the arm (15) is movable along the direction in which it extends by the energy transmitted from the shaft (7), and can move along the direction in which it extends by the energy transmitted from the power transfer mechanism (9) to the first chamber (3) moving on the first gear path (6), upon activation of the second motor (8). In case power cannot be transmitted by the first motor (5), coupling (12), shaft (7), bearing element (14) or second gear path (13) which are located in the first chamber (3) or the second chamber (4), the arm (15) located such that it contacts the bearing element (14) is actuated as a result of linear movement of the first chamber (3) that is triggered by the second motor (8) on the first gear path (6). Therefore, redundancy is provided for actuation of landing gears and/or control surfaces at air vehicles.

In an embodiment of the invention, the actuating system (1) comprises at least a second wedge (16) which is located in the second chamber (4) such that it contacts the bearing element (14) and the second chamber (4), enables the bearing element (14) to move linearly, and thus, allows the arm (15) to be pushed outwards. The second wedge (16) prevents rotational movement of the bearing element (14), which is located on the shaft (7) such that it surrounds the shaft (7) and moves on the second gear path (13), and enables the bearing element (14) to make linear movement out of the second chamber (4).