Folding caudal vertebra structure for ship-borne unmanned aerial vehicle and ship-borne unmanned aerial vehicle

Abstract

The invention provides a folding caudal vertebra structure for a ship-borne unmanned aerial vehicle and the ship-borne unmanned aerial vehicle, and relates to the technical field of folding caudal vertebras of unmanned aerial vehicles, the folding caudal vertebra structure is connected with a tail body of the ship-borne unmanned aerial vehicle and comprises an upper caudal vertebra and a lower caudal vertebra, and the upper caudal vertebra and the lower caudal vertebra are connected with a steering engine arranged in the tail body through a connecting rod mechanism; the connecting rod mechanism comprises two first rods, two second rods and two third rods, one ends of the two first rods are rotationally connected with the steering engine, one ends of the two second rods are rotationally connected with the tail body, the other ends of the two second rods are rotationally connected with the upper caudal vertebra and the lower caudal vertebra respectively, and the other ends of the two first rods are rotationally connected with the two second rods respectively; one ends of the two third rods are rotationally connected with the machine tail body, the other ends of the two third rods are rotationally connected with the upper caudal vertebra and the lower caudal vertebra respectively, a through groove is formed in the machine tail body, and the second rod and the third rods penetrate through the through groove; the problems that in the prior art, a fixed caudal vertebra of an unmanned aerial vehicle cannot contract, the occupied space is large, and the deformation risk is high are solved.

Description

Technical Field

[0001] The present invention belongs to the technical field of foldable tail vertebrae of unmanned aerial vehicles (UAVs), and more specifically, relates to a foldable tail vertebrae structure for a shipborne UAV and the shipborne UAV. Background Art

[0002] The tail cone of a ship-borne drone must simultaneously meet the requirements for an efficient aerodynamic shape for aerial flight and the structural strength and stability required for ground operation on a ship. Traditional aircraft tail cones often use a streamlined design to optimize aerodynamic performance. However, when not in flight, the tail cone cannot retract, resulting in an excessive amount of space occupied when on board the ship. Furthermore, the tail cone must withstand the vibration and impact of shipboard operation, which can easily cause structural fatigue and, in turn, alter the streamlined structure of the tail cone during flight. The tail cone of ship-borne drones uses a fixed structure, which increases aerodynamic drag when operating on the ground and occupies a larger area on the ground. Summary of the Invention

[0003] The purpose of the present invention is to address the deficiencies in the prior art and provide a folding tail vertebra structure for a shipborne UAV and a shipborne UAV, so as to solve the problem that the fixed tail vertebra of the UAV in the prior art cannot be retracted, occupies a large space and has a high risk of deformation.

[0004] In order to achieve the above-mentioned object, the present invention provides a foldable tail cone structure for a shipborne UAV, which is connected to the tail body of the shipborne UAV, comprising:

[0005] An upper tail vertebra and a lower tail vertebra, the upper tail vertebra and the lower tail vertebra are connected to a steering gear arranged in the tail body through a connecting rod mechanism, the connecting rod mechanism includes two first rods, two second rods and two third rods, one end of the two first rods is rotatably connected to the steering gear, one end of the two second rods is rotatably connected to the tail body, the other end of the two second rods is rotatably connected to the upper tail vertebra and the lower tail vertebra respectively, the other end of the two first rods is rotatably connected to the two second rods respectively, one end of the two third rods is rotatably connected to the tail body, the other end of the two third rods is rotatably connected to the upper tail vertebra and the lower tail vertebra respectively, the tail body is provided with a through slot, the second rod and the third rod pass through the through slot.

[0006] Optionally, at least one of the upper and lower coccyx vertebrae is provided with end plates at both ends, and the through groove can accommodate the end plates to pass through. When the upper and lower coccyx vertebrae are in the expanded state, the upper and lower coccyx vertebrae and the end plates form a box shape.

[0007] Optionally, when the upper tail vertebrae and the lower tail vertebrae are in a folded state, the upper tail vertebrae and the lower tail vertebrae are respectively located on the outer side of the upper surface and the outer side of the lower surface of the tail body.

[0008] Optionally, when the upper coccyx and the lower coccyx are in an unfolded state, the two first rods are collinear with the two second rods respectively.

[0009] Optionally, at least two connecting rod mechanisms are provided, wherein the two connecting rod mechanisms are respectively provided on both sides of the tail body.

[0010] Optionally, it further includes a first synchronization rod, a second synchronization rod and a third synchronization rod, wherein the first synchronization rod, the second synchronization rod and the third synchronization rod are rotatably arranged inside the tail body, and one end of the two second synchronization rods are respectively connected to the first synchronization rod and the second synchronization rod to achieve rotational connection with the tail body, and one end of the two third rods are connected to the third synchronization rod to achieve rotational connection with the tail body.

[0011] Optionally, when the upper tail vertebrae and the lower tail vertebrae are in a folded state, the upper tail vertebrae and the lower tail vertebrae are respectively in contact with the upper surface and the lower surface of the tail body.

[0012] Optionally, when the upper tail vertebrae and the lower tail vertebrae are in the unfolded state, the upper tail vertebrae smoothly transitions to the upper surface of the tail body, and the lower tail vertebrae smoothly transitions to the lower surface of the tail body.

[0013] The present invention also provides a shipborne UAV, comprising:

[0014] a fuselage, wherein the rear portion of the fuselage is the tail body;

[0015] The above-mentioned folding tail vertebra structure for ship-borne UAV.

[0016] Optionally, the tail body is a trapezoidal box, the upper tail vertebra and the lower tail vertebra are both flat-plate-shaped, the second rod and the third rod are the same length, the second rod and the third rod connecting the upper tail vertebra form a parallelogram, and the second rod and the third rod connecting the lower tail vertebra form a parallelogram.

[0017] The present invention provides a foldable tail vertebra structure for a shipborne UAV and a shipborne UAV, the beneficial effects of which are as follows: the foldable tail vertebra structure for the shipborne UAV sets the tail vertebra in a form including an upper tail vertebra and a lower tail vertebra, the upper tail vertebra and the lower tail vertebra are connected to a steering gear arranged in the tail body of the aircraft through a connecting rod mechanism, the extension and contraction of the steering gear drives the upper tail vertebra and the lower tail vertebra to move synchronously through the transmission of the connecting rod mechanism, thereby realizing the folding and unfolding of the upper tail vertebra and the lower tail vertebra, and the operation is performed by extending the steering gear to push the first rod to move and rotate, and the first rod drives the second rod to rotate, while the third rod rotates, and the second rod and the third rod connected to the upper tail vertebra drive the upper tail vertebra to move, and the second rod and the third rod connected to the lower tail vertebra drive the lower tail vertebra to move, until the upper tail vertebra is connected to the lower tail vertebra to reach the unfolded state, and similarly, the contraction of the steering gear can pull the first rod to move and rotate. The rod moves and rotates, and the first rod drives the second rod to rotate. At the same time, the third rod rotates, and the second rod and the third rod connected to the upper tail vertebra drive the upper tail vertebra to move, and the second rod and the third rod connected to the lower tail vertebra drive the lower tail vertebra to move, until the upper tail vertebra and the lower tail vertebra respectively reach the upper and lower sides of the tail body to reach a folded state; the folding tail vertebra structure for the ship-borne UAV enables the ship-borne UAV to fold the tail vertebra to fit with the tail body when in the ship-borne state, reducing the space occupied, reducing the aerodynamic resistance, and avoiding deformation of the tail vertebra due to vibration or swinging. In the flight state, the tail vertebra is fully unfolded, and the streamlined design of the ship-borne UAV is ensured by the smooth transition between the tail cone and the rear part of the fuselage. This design is conducive to the modification of the ship-borne UAV and has a positive promoting effect on the development and configuration of UAVs in the ship-borne direction.

[0018] Other features and advantages of the present invention will be described in detail in the following detailed description. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The above and other objects, features and advantages of the present invention will become more apparent through a more detailed description of exemplary embodiments of the present invention with reference to the accompanying drawings, wherein like reference numerals generally represent like components throughout the exemplary embodiments of the present invention.

[0020] Figure 1 A schematic diagram of a folding tail cone structure for a shipborne UAV according to an embodiment of the present invention is shown.

[0021] Figure 2 A schematic diagram showing the unfolded state of a foldable tail cone structure for a shipborne UAV according to an embodiment of the present invention is shown.

[0022] Description of reference numerals:

[0023] 1. Tail body; 2. Servo; 3. Upper first rod; 4. Lower first rod; 5. Upper second rod; 6. Upper tail vertebrae; 7. Lower second rod; 8. First synchronization rod; 9. Second synchronization rod; 10. Third synchronization rod; 11. Upper third rod; 12. Lower third rod; 13. Lower tail vertebrae. DETAILED DESCRIPTION

[0024] The preferred embodiments of the present invention will be described in more detail below. Although the preferred embodiments of the present invention are described below, it should be understood that the present invention can be implemented in various forms and should not be limited by the embodiments set forth herein. Instead, these embodiments are provided to make the present invention more thorough and complete and to fully convey the scope of the present invention to those skilled in the art.

[0025] like Figure 1 As shown, the present invention provides a folding tail cone structure for a shipborne UAV, which is connected to the tail body 1 of the shipborne UAV, including:

[0026] The upper tail vertebrae 6 and the lower tail vertebrae 13 are connected to the steering gear 2 arranged in the tail body 1 through a connecting rod mechanism. The connecting rod mechanism includes two first rods, two second rods and two third rods. One end of the two first rods is rotatably connected to the steering gear 2, one end of the two second rods is rotatably connected to the tail body 1, the other end of the two second rods is respectively rotatably connected to the upper tail vertebrae 6 and the lower tail vertebrae 13, the other end of the two first rods is respectively rotatably connected to the two second rods, one end of the two third rods is rotatably connected to the tail body 1, and the other end of the two third rods is respectively rotatably connected to the upper tail vertebrae 6 and the lower tail vertebrae 13. The tail body 1 is provided with a through slot, and the second rod and the third rod pass through the through slot.

[0027] Specifically, in order to solve the problem that the fixed tail vertebra of the UAV in the prior art cannot be retracted, occupies a large space and has a high risk of deformation, the folding tail vertebra structure for the ship-borne UAV provided by the present invention sets the tail vertebra to include an upper tail vertebra 6 and a lower tail vertebra 13. The upper tail vertebra 6 and the lower tail vertebra 13 are connected to the servo 2 arranged in the tail body 1 through a connecting rod mechanism. The extension and retraction of the servo 2 drives the upper tail vertebra 6 and the lower tail vertebra 13 to move synchronously through the transmission of the connecting rod mechanism, thereby realizing the folding and unfolding of the upper tail vertebra 6 and the lower tail vertebra 13. During operation, the extension of the servo 2 can push the first rod to move and rotate, and the first rod drives the second rod to rotate. At the same time, the third rod rotates, and the second rod and the third rod connected to the upper tail vertebra 6 drive the upper tail vertebra 6 to move, and the second rod and the third rod connected to the lower tail vertebra 13 drive the lower tail vertebra 13 to move, until the upper tail vertebra 6 is connected to the lower tail vertebra 13 and reaches the unfolded state. Similarly, The contraction of the servo 2 can pull the first rod to move and rotate, and the first rod drives the second rod to rotate. At the same time, the third rod rotates, and the second rod and the third rod connected to the upper tail vertebra 6 drive the upper tail vertebra 6 to move, and the second rod and the third rod connected to the lower tail vertebra 13 drive the lower tail vertebra 13 to move, until the upper tail vertebra 6 and the lower tail vertebra 13 respectively reach the upper and lower sides of the tail body 1 to reach a folded state; the folding tail vertebra structure for the ship-borne UAV enables the ship-borne UAV to fold the tail vertebra to fit with the tail body 1 when in the ship-borne state, reducing the space occupied, reducing aerodynamic resistance, and avoiding deformation of the tail vertebra due to vibration or swinging. In the flight state, the tail vertebra is fully unfolded, and the streamlined design of the ship-borne UAV is ensured by the smooth transition between the tail cone and the rear part of the fuselage. This design is conducive to the modification of the ship-borne UAV and has a positive promoting effect on the development and configuration of UAVs in the ship-borne direction.

[0028] In this embodiment, the two first links, the two second links and the two third links in the connecting rod mechanism are all symmetrically arranged, distributing the push-pull power output by the servo 2 to the upper tail vertebra 6 and the lower tail vertebra 13 in a straight line.

[0029] In this embodiment, the two first rods are an upper first rod 3 and a lower first rod 4 , the two second rods are an upper second rod 5 and a lower second rod 7 , and the two third rods are an upper third rod 11 and a lower third rod 12 .

[0030] Optionally, at least one of the upper caudal vertebra 6 and the lower caudal vertebra 13 is provided with end plates at both ends, and the through groove can accommodate the end plates to pass through. When the upper caudal vertebra 6 and the lower caudal vertebra 13 are in the unfolded state, the upper caudal vertebra 6, the lower caudal vertebra 13 and the end plates form a box shape.

[0031] Specifically, the end plates are arranged at both ends of the upper coccyx 6 or at both ends of the lower coccyx 13 or at both ends of the upper coccyx 6 and the lower coccyx 13. The arrangement of the end plates enables the upper coccyx 6 and the lower coccyx 13 to form a complete box shape with the end plates when they are in the expanded state, thereby forming a complete coccyx shape.

[0032] In this embodiment, if Figure 1 As shown, the two end plates are respectively arranged at both ends of the upper coccyx 6, as shown in FIG. Figure 2 As shown, the upper caudal vertebra 6, the lower caudal vertebra 13 and the end plate form a triangular box structure.

[0033] Optionally, when the upper tail vertebra 6 and the lower tail vertebra 13 are in the folded state, the upper tail vertebra 6 and the lower tail vertebra 13 are respectively located on the outer side of the upper surface and the outer side of the lower surface of the tail body 1 .

[0034] Specifically, the folding tail vertebra structure for the ship-borne UAV allows the upper tail vertebra 6 and the lower tail vertebra 13 to be moved to the outside of the upper surface of the tail body 1 and the lower tail vertebra 13 to be moved to the outside of the lower surface of the tail body 1 when the upper tail vertebra 6 and the lower tail vertebra 13 are in the folded state, through the drive of the second rod and the third rod, thereby shortening the tail length of the ship-borne UAV and reducing its wind resistance and occupied space during driving.

[0035] Optionally, when the upper coccyx 6 and the lower coccyx 13 are in the unfolded state, the two first rods are collinear with the two second rods respectively.

[0036] Specifically, after the upper tail cone and the lower tail vertebra 13 enter the deployed state, the second rod connected to the upper tail vertebra 6 and the first rod connected thereto are collinear, forming a dead point of the connecting rod mechanism, thereby ensuring the stability of the deployed state of the tail cone. Similarly, the second rod connected to the lower tail vertebra 13 and the first rod connected thereto are also collinear, forming a dead point of the connecting rod mechanism, thereby ensuring the stability of the deployed state of the tail cone.

[0037] Optionally, at least two connecting rod mechanisms are provided, wherein the two connecting rod mechanisms are respectively provided on both sides of the tail body 1 .

[0038] Specifically, the number of connecting rod mechanisms can be set according to the size and load distribution requirements of the ship-borne UAV and the folding tail vertebra structure used for the ship-borne UAV. A connecting rod mechanism is set at the position of the two side walls of the tail body 1 respectively, which can optimize the driving force transmission of the folding tail vertebra structure used for the ship-borne UAV and ensure that the forces at both ends are balanced when the upper tail vertebra 6 and the lower tail vertebra 13 move.

[0039] In this embodiment, two connecting rod mechanisms are provided, which are located on the left and right sides of the tail body 1 respectively, so that isoplanarity of force can be achieved during the folding process.

[0040] Optionally, it further includes a first synchronization rod 8, a second synchronization rod 9 and a third synchronization rod 10, which are rotatably arranged inside the tail body 1, and one end of the two second rods are respectively connected to the first synchronization rod 8 and the second synchronization rod 9 to achieve rotational connection with the tail body 1, and one end of the two third rods are respectively connected to the third synchronization rod 10 to achieve rotational connection with the tail body 1.

[0041] Specifically, the first synchronization rod 8, the second synchronization rod 9 and the third synchronization rod 10 can be rotatably connected to the internal structure of the tail body 1. Among the two second rods, one is connected to the first synchronization rod 8, and the other is connected to the second synchronization rod 9. The two third rods are connected to the same third synchronization rod 10. The connecting rod mechanism at both ends of the first synchronization rod 8, the second synchronization rod 9 and the third synchronization rod 10 ensures synchronization during operation and the solid connection of the movement on both sides due to the existence of the first synchronization rod 8, the second synchronization rod 9 and the third synchronization rod 10.

[0042] Optionally, when the upper tail vertebra 6 and the lower tail vertebra 13 are in the folded state, the upper tail vertebra 6 and the lower tail vertebra 13 are respectively in contact with the upper surface and the lower surface of the tail body 1 .

[0043] Specifically, the shape of the upper tail vertebra 6 is the same as the shape of part of the upper surface of the tail body 1, and the shape of the lower tail vertebra 13 is the same as the shape of part of the lower surface of the tail body 1. When the upper tail vertebra 6 and the lower tail vertebra 13 are in a folded state, the upper tail vertebra 6 and the lower tail vertebra 13 are tightly fitted on the upper surface and the lower surface of the tail body 1, respectively, which can stabilize and strengthen the strength of the tail vertebra structure, and have better stability and deformation resistance when facing vibration and swaying on board.

[0044] Optionally, when the upper tail vertebra 6 and the lower tail vertebra 13 are in the unfolded state, the upper tail vertebra 6 smoothly transitions to the upper surface of the tail body 1 , and the lower tail vertebra 13 smoothly transitions to the lower surface of the tail body 1 .

[0045] Specifically, when the upper tail cone 6 and the lower tail cone 13 are in the unfolded state, the upper tail cone 6 and the lower tail cone 13 are tightly connected to the rear ends of the upper and lower surfaces of the tail body 1, respectively. The streamlined design of the tail of the carrier-based aircraft is ensured by the smooth transition of the upper tail cone 6 and the lower tail cone 13 with the rear curved streamline of the tail body 1. This requires that the surface curvature of the upper tail cone 6 and the lower tail cone 13 is consistent with the surface curvature of the rear end of the tail body 1 at the connection point, or that the curvature of the upper tail cone 6 and the lower tail cone 13 is as close as possible to the curvature of the rear end of the tail body 1.

[0046] The present invention also provides a shipborne UAV, comprising:

[0047] The fuselage, the rear part of the fuselage is the tail body 1;

[0048] The above-mentioned folding tail vertebra structure for ship-borne UAV.

[0049] Specifically, the ship-borne UAV is equipped with the above-mentioned folding tail cone structure for ship-borne UAVs. When traveling on a ship, the tail cone can be retracted to fit closely with the tail body 1 of the ship-borne UAV, reducing the space occupied and reducing aerodynamic resistance. In the flight state after leaving the ship, the tail cone can be fully unfolded, and the streamlined design of the UAV tail is ensured through the smooth transition of the tail cone and the rear curved streamline of the tail body 1.

[0050] In this embodiment, the tail body 1 is a trapezoidal box, the upper tail vertebra 6 and the lower tail vertebra 13 are both flat-plate-shaped, the second rod and the third rod are the same length, the second rod and the third rod connecting the upper tail vertebra 6 form a parallelogram, and the second rod and the third rod connecting the lower tail vertebra 13 form a parallelogram.

[0051] Specifically, in this embodiment, Figure 1 As shown, the tail body 1 is a trapezoidal box structure with an isosceles trapezoidal cross-section. The upper tail vertebra 6 and the lower tail vertebra 13 are two symmetrically arranged flat plates, and the two ends of the upper tail vertebra 6 are connected with triangular end plates. The second rod and the third rod connecting the upper tail vertebra 6, and the second rod and the third rod connecting the lower tail vertebra 13 are symmetrically arranged up and down, and all form a parallelogram connecting rod mode, driving the expansion and folding movement of the upper tail vertebra 6 and the lower tail vertebra 13; when the upper tail vertebra 6 and the lower tail vertebra 13 are in the expanded state, the front ends of the upper tail vertebra 6 and the lower tail vertebra 13 are respectively connected to the upper surface and the lower surface of the tail body 1, and the rear ends of the upper tail vertebra 6 and the lower tail vertebra 13 are connected to form an isosceles triangle structure, and the slopes of the upper tail vertebra 6 and the lower tail vertebra 13 are respectively consistent with the slopes of the upper surface and the lower surface of the tail body 1, achieving a smooth transition. In this embodiment, when the servo 2 is pushed horizontally backward, the connecting rod mechanism can realize rotation and translation of the upper tail vertebra 6 and the lower tail cone; the upper and lower parts of the connecting rod mechanism are completely symmetrical, which can ensure that the tail cone is completely in contact with the surface of the tail body 1 after being folded into place.

[0052] In another example, the shapes of the upper and lower surfaces of the tail body 1 and the upper tail vertebra 6 and the lower tail vertebra 13 may also be curved plates. In this case, the folding and unfolding requirements of the folding tail vertebra structure for ship-borne UAVs can be met by designing the lengths of the first link, the second link and the third link and the connection position of the first link and the second link.

[0053] Furthermore, to ensure a smooth transition between the upper and lower surfaces of the tail cone 1 and the upper and lower surfaces of the fuselage 1, respectively, the upper and lower surfaces of the fuselage 1 can be directly intercepted to form the curved surfaces of the upper and lower tail cones 6 and 13. Two groups of connecting rods can be arranged between the upper and lower tail cones 13: the second and third rods connecting the upper and lower tail cones 6, and the second and third rods connecting the lower tail cone 13, to ensure that they do not interfere with each other. Furthermore, dotted lines can be used to represent the extended curves of the upper and lower surfaces of the fuselage 1, i.e., the rear end extreme position of the tail cone when deployed. By drawing a perpendicular midline between these two positions, the relative rotation point of the connecting rod mechanism can be inferred, and the length of each rod in the connecting rod mechanism can be further determined using this rotation point as a reference. Regarding the length design of the two first rods connecting the servo 2, the connecting rod mechanism is rotated to the fully deployed position, and the first rod is set parallel to the second rod. This allows the length ratio of the first and second rods to be determined, and the detailed dimensions of the third rod can then be determined based on spatial constraints.

[0054] In summary, the present invention maximizes the use of space in a group of shipborne UAVs through the above-mentioned folding tail vertebrae structure for shipborne UAVs, adapts to different application scenarios of UAVs by folding and unfolding the tail vertebrae, improves the compactness of the group of shipborne UAVs, and improves the problem of rigidity and inflexibility of existing shipborne UAVs; at the same time, when the shipborne UAV is carrying out a flight mission, the unfolding of the tail vertebrae can improve its aerodynamic performance, reduce the flying windward area of ​​the fuselage, and improve the mission load capacity and flight control performance of the entire aircraft.

[0055] While various embodiments of the present invention have been described above, the above description is intended to be illustrative, not exhaustive, and not limited to the disclosed embodiments. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments.

Claims

1. A folding tail cone structure for a shipborne UAV, connected to the tail body of the shipborne UAV, characterized in that: include: An upper tail vertebra and a lower tail vertebra, the upper tail vertebra and the lower tail vertebra are connected to a steering gear arranged in the tail body through a connecting rod mechanism, the connecting rod mechanism includes two first rods, two second rods and two third rods, one end of the two first rods is rotatably connected to the steering gear, one end of the two second rods is rotatably connected to the tail body, the other end of the two second rods is rotatably connected to the upper tail vertebra and the lower tail vertebra respectively, the other end of the two first rods is rotatably connected to the two second rods respectively, one end of the two third rods is rotatably connected to the tail body, the other end of the two third rods is rotatably connected to the upper tail vertebra and the lower tail vertebra respectively, the tail body is provided with a through slot, the second rod and the third rod pass through the through slot.

2. The foldable tail cone structure for a shipborne UAV according to claim 1, characterized in that: End plates are provided at both ends of at least one of the upper and lower coccyx vertebrae, and the through groove can accommodate the end plates to pass through. When the upper and lower coccyx vertebrae are in an unfolded state, the upper and lower coccyx vertebrae and the end plates form a box shape.

3. The foldable tail cone structure for a shipborne UAV according to claim 1, characterized in that: When the upper tail vertebrae and the lower tail vertebrae are in a folded state, the upper tail vertebrae and the lower tail vertebrae are respectively located on the outer side of the upper surface and the outer side of the lower surface of the tail body.

4. The foldable tail cone structure for a shipborne UAV according to claim 1, characterized in that: When the upper coccyx and the lower coccyx are in an unfolded state, the two first rods are collinear with the two second rods respectively.

5. The foldable tail cone structure for a shipborne UAV according to claim 1, characterized in that: At least two connecting rod mechanisms are provided, wherein the two connecting rod mechanisms are respectively provided on both sides of the tail body.

6. The foldable tail cone structure for a shipborne UAV according to claim 5, characterized in that: It also includes a first synchronization rod, a second synchronization rod and a third synchronization rod. The first synchronization rod, the second synchronization rod and the third synchronization rod are rotatably arranged inside the tail body. One end of the two second synchronization rods are respectively connected to the first synchronization rod and the second synchronization rod to achieve rotational connection with the tail body, and one end of the two third rods are connected to the third synchronization rod to achieve rotational connection with the tail body.

7. The foldable tail cone structure for a shipborne UAV according to claim 1, characterized in that: When the upper tail vertebrae and the lower tail vertebrae are in a folded state, the upper tail vertebrae and the lower tail vertebrae are respectively fitted with the upper surface and the lower surface of the tail body.

8. The foldable tail cone structure for a shipborne UAV according to claim 1, characterized in that: When the upper tail vertebrae and the lower tail vertebrae are in an unfolded state, the upper tail vertebrae transitions smoothly to the upper surface of the tail body, and the lower tail vertebrae transitions smoothly to the lower surface of the tail body.

9. A shipborne UAV, characterized in that: include: The fuselage, the rear part of the fuselage is the tail body ； The foldable tail vertebra structure for a shipborne UAV according to any one of claims 1 to 8.

10. The shipborne UAV according to claim 9, characterized in that: The tail body is in the shape of a trapezoidal box, the upper tail vertebrae and the lower tail vertebrae are both flat-plate-shaped, the second rod and the third rod are the same length, the second rod and the third rod connecting the upper tail vertebrae form a parallelogram, and the second rod and the third rod connecting the lower tail vertebrae form a parallelogram.

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