Patent ID: 12195162

All the parts illustrated in figures are individually assigned a reference numeral and the corresponding terms of these numbers are listed below:1. Helicopter Tail Folding System2. Tail201. Front Area202. Rear Area3. First Shaft4. Second Shaft5. First Coupling6. Second Coupling7. First Hub8. Second Hub9. Support Piece10. Pin101. First Pin Region102. Second Pin Region11. Nut12. Stopper13. Transmission Element14. Shoulder15. Stabilizer16. Sealing Element17. Absorber18. First Hanger Bearing19. Second Hanger Bearing20. Hinge(A) Active Mode(B) Passive Mode

DETAILED DESCRIPTION

Helicopter tail folding system (1) comprises a tail (2) located on a helicopter; a front area (201) located on the tail (2); a rear area (202) connected to the front area (201) in a foldable manner around the axis on which it is supported; a first shaft (3) at the front area (201) and a second shaft (4) at the rear area (202) that allow power transfer to the tail (2) rotor throughout the flight movement of the helicopter; a first coupling (5) and a second coupling (6) that are located on the first shaft (3) in a gear form; a first hub (7) on the first shaft (3), which surrounds the first coupling (5) and is form-compatible with the first coupling (5) so as to allow the first coupling (5) to perform at least partially a spherical rotational movement; a second hub (8) form-compatible with the second coupling (6) and located on the second shaft (4) opposite the second coupling (6); an active mode (A) in which power transfer from the first shaft (3) to the second shaft (4) is provided when the second coupling (6) is placed into the second hub (8); a passive mode (P) in which power transfer from the first shaft (3) to the second shaft (4) is prevented when the rear area (202) is folded to disconnect the second coupling (6) from the second hub (8).

Helicopter tail folding system (1) according to the invention comprises a support piece (9) located on an inner wall of the first shaft (3); a pin (10) that extends from the support piece (9) for mounting the second coupling (6) to the first coupling (5), and centers the first coupling (5) and the second coupling (6); at least one nut (11) which is attached removably to the pin (10) for the assembly/maintenance of the first coupling (5), and located on the second coupling (6) so as to be directly accessible by the user in passive mode (P) (FIG.1,FIG.2).

On the helicopter tails (2), there is a front area (201) close to the main rotor and a rear area (202) that can be folded by rotating around an axis where it is connected to the front area (201). A first shaft (3) that transfers power to the helicopter rotor during a flight is located in the front area (201), and a second shaft (4) that provides movement transfer is located in the rear area (202). A first coupling (5) having a gear form and a second coupling (6) having a gear form are located on the first shaft (3). There is a first hub (7) on the first shaft (3) that surrounds the first coupling (5) in a form-compatible manner with the first coupling (5) and allows the first coupling (5) to make a spherical rotational movement around its own center; a second hub (8) located on the second shaft (4) in a form-compatible manner with the second coupling (6), wherein the first coupling (5) and second coupling (6) are located opposite each other. There is an active mode (A) in which the first shaft (3) and the second shaft (4) provide power transfer when the second coupling (6) is placed in the second hub (8). There is a passive mode (P) in which the rear area (202) is rotated around the axis on which it is supported, so as to be moved to the front area (201) and away from the front area (201), and in which the second coupling (6) is disconnected from the second hub (8), thereby preventing power transfer from the first shaft (3) to the second shaft (4).

It comprises a support piece (9) mounted on the inner wall of the first shaft (3); and a pin (10) extending from the support piece (9) to hold the second coupling (6) on the first coupling (5). The pin (10) holds the first coupling (5) and the second coupling (6) from their centers to keep them in the first hub (7) adjacent to each other. Further, the nut (11) is attached to the pin (10) to prevent the first coupling (5) and the second coupling (6) from moving out of the pin (10). The nut (11) on the pin (10) is directly accessible to the operator when the tail (2) is folded, that is, in passive mode (P). In this way, the first coupling (5) in need of frequent maintenance can be easily accessed or visually inspected by the operator for assembly/disassembly (FIG.3,FIG.4).

In an embodiment of the invention, the helicopter tail folding system (1) comprises a first pin region (101) on the pin (10), in which the first coupling (5) and the second coupling (6) are centered; a second pin region (102) on the pin (10), which at least partially restricts spherical movement of the first coupling (5) on the first pin region (101), thereby enabling the first coupling (5) and the first hub (7) to overlap. Thanks to the partially flexible spherical movement of the first coupling (5) within the first hub (7), couplings and hub are prevented from damage during the transitions between passive mode (P) and active mode (A). Moreover, thanks to the second pin region (102) blocking the first coupling (5), linear movement is restricted during the transition from passive mode (P) to active mode (A) and the second coupling (6) is enabled to fit tightly into the second hub (8) (FIG.3,FIG.4).

In an embodiment of the invention, the helicopter tail folding system (1) comprises at least one stopper (12) which is a protrusion between the first pin region (101) and the second pin region (102), in order to at least partially restrict the spherical movement of the first coupling (5) and the second coupling (6) on the first pin region (101). Thus, distance of the first pin region (101) between the stopper (12) and the nut (11) can be determined by the user and movement of the first coupling (5) and the second coupling (6) moving together with the first coupling (5) can be restricted (FIG.7).

In an embodiment of the invention, the helicopter tail folding system (1) comprises a transmission element (13) extending from the first hub (7) integrally, with the axis on which the first shaft (3) extends being the center, wherein the transmission element (13) forms inner wall of the first shaft (3). Thanks to the integral production of the first coupling (5) and the second coupling (6), a shorter folding tail (2) is produced, thereby providing a lighter tail (2). Producing the transmission element (13) and the first hub (7) integrally enables a more compact structure because, when the helicopter is in passive mode (P), the nut (11), therefore the first coupling (5), the second coupling (6), the pin (10) and the support piece (9) that are located in the first hub (7) and the transmission element (13) are easily accessible by the operator (FIG.5).

In an embodiment of the invention, the helicopter tail folding system (1) comprises the support piece (9) extending from the second pin region (102) to the transmission element (13) and enabling the pin (10) to be mounted on the transmission element (13). Thanks to the removable attachment of the support piece (9) to the transmission element (13), the pin (10) can be replaced easily by the operator (FIG.3,FIG.4,FIG.5).

In an embodiment of the invention, the helicopter tail folding system (1) comprises at least one shoulder (14), which is a protrusion on the transmission element (13) and prevents linear movement of the support piece (9) in the transmission element (13) in the direction of the first shaft (3); at least one stabilizer (15) extending from the support piece (9) and preventing rotational movement of the support piece (9) within the transmission element (13) due to its contact with the protrusion on the shoulder (14). Thanks to the shoulder (14), the support piece (9) is prevented from moving freely on the transmission element (13), and thanks to the stabilizer (15), the pin (10) is prevented from rotating freely while the nut is torqued (FIG.3,FIG.4).

In an embodiment of the invention, the helicopter tail folding system (1) comprises the support piece (9) with protrusions thereon; the transmission element (13) with a recessed inner wall compatible with the protrusions on the support piece (9). Since the protrusions and recesses are form-compatible with each other, the support piece (9) is prevented from moving freely on the transmission element (13) (FIG.3,FIG.4).

In an embodiment of the invention, the helicopter tail folding system (1) comprises the support piece (9) which has a conical form, thus attached to the inner wall of the transmission element (13) by rotating. The support element (9), which can be rotated in a practical manner so as to be removed and attached to the transmission element (13), may preferably have a conical form. Thanks to the conical shaped support element (9), the second pin region (102) can be produced short in length. As the support element (9) is removable and attachable, when the pin (10) is required to be changed or damaged, it can be easily replaced with a new one. Thanks to the conical shaped support piece (9), the support element (9) is easily attached in the transfer element (13).

In an embodiment of the invention, the helicopter tail folding system (1) comprises the first coupling (5) and the second coupling (6), which are integral. Therefore, extra elements and connectors are not required to hold the first coupling (5) and the second coupling (6) together, which move together in active mode (A), passive mode (P) and during mode transitions. Therefore, a more compact and lightweight structure is achieved. Due to the force applied to the first coupling (5) or the second coupling (6), the connection therebetween is not damaged and maintenance period is decreased.

In an embodiment of the invention, the helicopter tail folding system (1) comprises a sealing element (16) located between the first coupling (5) and the second coupling (6). The sealing element (16) prevents foreign substances, such as water and dust, from entering into the first shaft (3) located between the first coupling (5) and the second coupling (6) (FIG.5).

In an embodiment of the invention, the helicopter tail folding system (1) comprises the transmission element (13) in helical form, which forms the inner wall of the first shaft (3), moves by rotating with the first hub (7) and supports the first coupling (5) and the second coupling (6) to be held together, wherein for the tail (2) switched from passive mode (P) to active mode (A), the transmission element (13) extends integrally from the first hub (7) with the axis where the first shaft (3) extends being the center. Thanks to its helical form, the transmission element (13) moves with the first hub (7) by rotating, and allows the first coupling (5) and the second coupling (6) to be held together by means of the support element (9). Since the helically modified transmission element (3) moves forward towards the rear area (202) in the direction it extends from the first shaft (3) to the first coupling (5) while the first coupling (5) and the second coupling (6) are switched from active mode (A) to passive mode (P), or moves back towards the front area (201) in the direction it extends from the first shaft (3) to the first coupling (5) while switching from passive mode (P) to active mode (A), the first coupling (5) and second coupling (6) can be prevented from getting stuck (FIG.3,FIG.4).

In an embodiment of the invention, the helicopter tail folding system (1) comprises an absorber (17) located in the first shaft (3) so as to be in contact with the transmission element (13); the absorber (17) at least partially absorbing the movement of the first hub (7) into the first shaft (3), thus absorbing linear movement of the first hub (7) together with the transmission element (13) during the transition from passive mode (P) to active mode (A). Thanks to the absorber (17) in the form of a wave spring, more effective absorbing is provided in a shorter distance. Thanks to the absorber (17), first coupling (5) and second coupling (6) are prevented from getting stuck, and while switching from passive mode (P) to active mode (A), the second hub (8) slides from the teeth of the second coupling (6) to be inserted into the first hub (7), facilitating the linear movement of the first hub (7) on the axis on which the first shaft (3) extends. A small volume helicopter tail folding system (1) has been provided since a part of the absorber (17) is inside the first shaft (3), and another part thereof is inside the transmission element (13) (FIG.1,FIG.2,FIG.3,FIG.4).

In an embodiment of the invention, the helicopter tail folding system (1) comprises the absorber (17) which is stretched towards the rear area (202) in the direction it extends from the first shaft (3) to the first coupling (5), while the helicopter is switched from active mode (A) to passive mode (P), or which is compressed in the direction it extends from the first shaft (3) to the first coupling (5), while the helicopter is switched from passive mode (P) to active mode (A), so that the load transferred to the front area (201) is at least partially absorbed. By moving the absorber (17) from the first shaft (3) towards the first coupling (5), in the direction where the first shaft (3) extends, the load transferred to the front area (201) is reduced. Thanks to the helical modification of the transmission element (13) and to the damper (17), load distributions on the rear area (202) and the front area (201) can be homogeneous during transitions of the helicopter between active mode (A) and passive mode (P) (FIG.5).

In an embodiment of the invention, the helicopter tail folding system (1) comprises a first shaft (3) surrounding the transmission element (13); a first hanger bearing (18) that enables the first shaft (3) to be mounted the front area (201); a second hanger bearing (19) that enables the second hub (8) and the second shaft (4) to be mounted to the rear area (202). The first hanger bearing (18) bears the first shaft (3) and the second hanger bearing (19) bears the second hub (8) in the rear area (202). Thanks to the first hanger bearing (18), the first shaft (3) can be mounted to the front area (201) so as to rotate independently of the front area (201). Likewise, thanks to the second hanger bearing (19), the second shaft (4) can be mounted to the rear area (202) so as to rotate independently of the rear area (202) (FIG.5,FIG.6).

In an embodiment of the invention, the helicopter tail folding system (1) comprises a hinge (20) that connects the front area (201) and the rear area (202) and allows the rear area (202) to rotate around the axis to which it is connected. While the helicopter tail (2) is folded, that is, during the transition from active mode (A) to passive mode (P), first shaft (3) and second shaft (4) are disconnected. The hinge (20), which connects the rear area (201) holding the second shaft (4) and the front area (201) holding the first shaft (3) to each other, is separated by rotating around its axis, so that the connection is interrupted. In this way, rear area (202) of the tail (2) can be folded and separated from the front area (201) of the tail (2) except for the hinge (20).