Patent ID: 12195165

The parts in the figures are individually designated as following.1. Helicopter tail folding mechanism2. Tail201. Front region202. Rear region3. First shaft4. Second shaft5. First coupling6. Second coupling7. First hub8. Second hub9. Transmission element10. Dampener11. Mouth12. Recess13. Stopper14. Pin15. Nut16. Shoulder17. Gasket18. First suspension bearing19. Second suspension bearing20. Hinge(A) Active mode(P) Passive mode(S) Fastener

DETAILED DESCRIPTION

The helicopter tail folding mechanism (1) comprises a tail (2) located on the helicopter, a front region (201) located on the tail (2), a rear region (202) connected to the front region (201) such as to be able to make a folding movement around the axis on which it is supported, a first shaft (3) located on the front region (201) and a second shaft (4) located on the rear region (202) enabling power to be transmitted to the tail rotor during the flight movement of the helicopter, a first coupling (5) and a second coupling (6) located on the first shaft (3) both with a threaded form, a first hub (7) located on the first shaft (3), surrounding the first coupling (5) all around and is form-fitting to the first coupling (5) so as to enable the first coupling (5) to make at least a partial spherical rotational movement, a second hub (8) located on the second shaft (4) so as to be arranged opposite to the second coupling (6) and being form-fitting to the second coupling (6), an active mode (A) in which power is transmitted from the first shaft (3) to the second shaft (4) by the placement of the second coupling (6) in the second hub (8), a passive mode (P) in which power transmission from the first shaft (3) to the second shaft (4) is prevented when the second coupling (6) is decoupled from the second hub (8) by the folding movement of the rear region (202) around the axis on which it is supported.

The helicopter tail folding mechanism (1) according to the invention comprises at least one helically-shaped transmission element (9) that extends monolithically from the first hub (7) such that the axis in which the first shaft (3) extends is the center and forms the inner wall of the first shaft (3) moves by rotating together with the first hub (7) and supports the engagement of the first coupling (5) and the second coupling (6) for the tail (2) brought from the passive mode (P) to the active mode (A).

There is a front region (201) on the helicopter tails (2) close to the main rotor and a rear region (202) that is able to connect to the front region (201) so as to be rotatable around the axis in which it is connected to the front region. A first shaft (3) transmitting power to the helicopter rotor during its flight is located in the front region (201), a second shaft (4) transmitting motion is located in the rear region (202). A first coupling (5) having a threaded form and a second coupling (6) having a threaded form are located on the first shaft (3). There is a first hub (7) located on the first shaft (3) that surrounds the first coupling (5) so as to be form-fitting to it and enables the first coupling (5) to make a spherical rotational movement around its center, and a second hub (8) located on the second shaft (4) so as to be against and form-fitting to the second coupling (6). As a result of the placement of the second hub (8) in the second coupling (6), there is an active mode (A) in which the first shaft (3) and the second shaft (4) provide power transmission. There is a passive mode (P) to which the rear region (202) is brought by rotating around the axis around which it is supported and removed from the front region (201), and the second coupling (6) and the second hub (8) are decoupled.

For the tail (2) brought to the active mode (A) from the passive mode (P) by the folding movement around the axis on which it is supported, it comprises a transmission element (9) on the axis in which the first shaft (3) extends on the tail (2), extends outward from the first hub (7) and forms the inner wall of the first shaft (3). Thanks to the fact that the transmission element (9) has a helical form, it rotates together with the first hub (7) and enables the first coupling (5) and the second coupling (6) to engage each other. Thanks to the fact that the transmission element (9) has a helical form, it ensures that the first coupling (5) and the second coupling (6) engage each other and do not decouple by applying a linear thrust along the axis where the first shaft (3) extends while the tail (2) is in the active mode (A).

In an embodiment of the invention, the helicopter tail folding mechanism (1) comprises monolithically produced first coupling (5) and second coupling (6). A lighter helicopter tail folding mechanism (1) is provided thanks to the tail (2) whose size is shortened by the monolithic production of the first coupling (5) and the second coupling (6).

In an embodiment of the invention, the helicopter tail folding mechanism (1) comprises at least one dampener (10) that is located in the first shaft (3) so as to be in contact with the first hub (7) and dampens the linear movement of the first coupling (5), dampener (10) that enables to at least partially dampen the movement of the first hub (7) into the first shaft (3), thus damping the linear movement of the first hub (5) while it is switched from the passive mode (P) to the active mode (A), and transmission element (9) that at least partially surrounds the dampener (10) all around. The first coupling (5) and the second coupling (6) move forward towards the rear region (202) in the direction in which they extend from the first shaft (3) towards the first coupling (5) while they are brought from the active mode (A) to the passive mode (P). The first coupling (5) and the second coupling (6) move back towards the front region (201) in the direction in which they extend from the first shaft (3) to the first coupling (5) while they are brought from the passive mode (P) to the active mode (A). In this way, it is enabled to prevent the first coupling (5) and the second coupling (6) from getting stuck to each other.

In an embodiment of the invention, the helicopter tail folding mechanism (1) comprises a mouth (11) on the side of the first shaft (3) where it is connected to the helicopter main rotor, dampener (10) that slows down the movement of the first hub (7) towards the mouth (11) during when the second hub (8) slides from the teeth of the second coupling (6) and gets placed in the first hub (7) while the front region (201) is brought from the passive mode (P) to the active mode (A) by a user. Thanks to the dampener (10) that dampens the linear motion, it is prevented that the first coupling (5) and the second coupling (6) are stuck to each other and while the mechanism is brought from the passive mode (P) to the active mode (A), the movement of the first hub (7) towards the mouth (11) is facilitated during when the second hub (8) slides from the teeth of the second coupling (6) and gets placed in the first hub (7).

In an embodiment of the invention, the helicopter tail folding mechanism (1) comprises a recess (12) located on the first hub (7) so as to extend into the first shaft (3), contacting the inner wall of the first shaft (3), at least partially surrounding the dampener (10) all around, enabling the dampener (10) to be supported, and transmission element (9) having a recessed inner wall compatible with the protrusions on the recess (12) having protrusions thereon. Thanks to the recess (12) having recesses and protrusions form-fitting to the transfer element (9), it is enabled to support the dampener (10) and the transfer element (9).

In an embodiment of the invention, the helicopter tail folding mechanism (1) comprises dampener (10) that moves forward towards the rear region (202) in the direction in which it extends from the first shaft (3) to the first coupling (5) while it is switched from the active mode (A) to the passive mode (P) or moves towards the mouth (11) in the direction in which it extends from the first shaft (3) to the first coupling (5) while it is brought from the passive mode (P) to the active mode (A) to at least partially dampen the load transferred to the front region (201). Thanks to the movement of the dampener (10) towards the mouth (11) in the direction in which it extends from the first shaft (3) towards the first coupling (5), it is enabled to reduce the load transferred to the front region (201).

In an embodiment of the invention, the helicopter tail folding mechanism (1) comprises a stopper (13) that enables the dampener (10) to be mounted so as to limit its movement into the first shaft (3), is form-fitting to the cross-sectional area of the first shaft (3), is located in a region close to the mouth (11) and limits the movement of the recess (12). Thanks to the stopper (13), it is enabled to store energy in the dampener (10).

In an embodiment of the invention, the helicopter tail folding mechanism (1) comprises a pin (14) located on the inner wall of the first shaft (3), extending out of the recess (12), thereby enabling the second coupling (5) to be mounted on the first coupling (4) and centering the first coupling (5) and the second coupling (6), and at least one nut (15) removably mounted to the pin (14) for the assembly/maintenance of the first coupling (5) and being located on the second coupling (6) so that it can be directly accessed by a user in the passive mode (P). Thanks to the pin (14), it is ensured that the first coupling (5) and the second coupling (6) are easily mounted to each other concentrically.

In an embodiment of the invention, the helicopter tail folding mechanism (1) comprises at least one shoulder (16) located on the transmission element (9) and having the form of a protrusion preventing the movement of the recess (12) on the transmission element (12). Thanks to the shoulder (16), it is ensured that the free movement of the transmission element (9) on the recess (12) is prevented.

In an embodiment of the invention, the helicopter tail folding mechanism (1) comprises pin (14) in the recess (12), centering the first coupling (5) and the second coupling (6), a fastener (S) enabling to mount the pin (14) to the recess (12) so that the dampener (10) and the first coupling (4) can be moved together, fastener (S) with protrusions on it, recess (12) having a recessed inner wall compatible with the protrusions on the fastener (S). The fastener (S) enables to mount the pin (14) onto the recess (12) so that the dampener (10) and the first coupling (4) can be moved together. Thanks to this, it is ensured that the first coupling (4) and the second coupling (5) overlap correctly and efficiently during tail folding.

In an embodiment of the invention, the helicopter tail folding mechanism (1) comprises recess (12) having a conical form so that it can be rotatably mounted to the inner wall of the transmission element (9). Thanks to the recess (12) having a conical form, it is enabled to facilitate the mounting of the transmission element (9) in the recess (12).

In an embodiment of the invention, the helicopter tail folding mechanism (1) comprises a gasket (17) located between the first coupling (5) and the second coupling (6), acting as a seal and preventing the entry of foreign substances such as water and dust into the first shaft (3). Thanks to the gasket (17), it is ensured that foreign substances such as water and dust are prevented from entering the first shaft (3).

In an embodiment of the invention, the helicopter tail folding mechanism (1) comprises first shaft (3) surrounding the transmission element (9), a first suspension bearing (18) enabling to mount the first shaft (3) to the front region (201), a second suspension bearing (19) enabling to mount the second hub (8) to the rear region (202), a hinge (20) connecting the first suspension bearing (18) and the second suspension bearing (19) to each other and enabling the second suspension bearing (19) to rotate and move around the axis on which it is connected. The first shaft (3) supports the first suspension bearing (18) and the second hub (8) is supported in the rear region (202) by the second suspension bearing (19).

In an embodiment of the invention, the helicopter tail folding mechanism (1) comprises helically-shaped transmission element (9) connected over the axis where the first suspension bearing (18) is supported and almost completely surrounded by the first suspension bearing (18). Thanks to the transmission element (9) located in the front region (201), it is ensured that the first suspension bearing (18) is supported.

In an embodiment of the invention, the helicopter tail folding mechanism (1) comprises dampener (10) in the form of a wave spring. Thanks to the dampener (10) in the form of a wave spring, more efficient damping is ensured at a shorter distance.