Unmanned aerial vehicle tail cone structure

Abstract

The utility model discloses an unmanned plane tail cone structure, including the framework, sets up the tail of the organism, is used for supporting the skin to fixedly to the electric governing, the skin sets up outside the framework, is used for maintaining the aerodynamic shape of unmanned plane tail cone, the electric governing heat dissipation hole is set up on the skin, is used for the heat dissipation of electric governing radiating fin. The utility model has improved the space utilization, reduced the weight, promoted the motor response speed and control stability, shortened the overhauling time and reduced the labor intensity of operating personnel and so on beneficial effect.

Description

Technical Field

[0001] This utility model relates to a tail cone structure, and more specifically, to a tail cone structure for a drone. Background Technology

[0002] With its advantages of flexibility, cost control, and adaptability, unmanned aerial vehicles (UAVs) have been widely used in various fields such as aerial surveying and mapping, agricultural plant protection, emergency rescue, logistics and distribution, power line inspection, and film and television shooting, becoming an important piece of equipment for promoting the intelligent development of various industries. As a core component of the UAV's tail section, the tail cone's structural design needs to be adapted and adjusted to meet the functional requirements of the UAV. Existing technologies regarding tail cone structures mainly suffer from the following problems:

[0003] 1. The tail cone section is not used properly. Equipment such as ESCs that are matched with the tail pusher motor are not integrated and arranged in the tail cone area, resulting in the equipment being installed in a scattered manner, occupying other valuable space in the machine body. In addition, the ESCs are far away from the tail pusher motor, which affects the stability of control signal transmission and response speed.

[0004] 2. The ESC generates a lot of heat when it is working. In the existing tail cone design, the ESC is mostly enclosed inside, lacking a heat dissipation path that directly contacts the external airflow. It relies only on the limited internal air circulation for heat dissipation, which can easily lead to the ESC temperature being too high, affecting its working performance or even causing failure, and failing to meet the requirements for long-term stable operation.

[0005] 3. Some tail cones have holes or protruding structures in aerodynamically sensitive areas of the fuselage to accommodate equipment installation or heat dissipation requirements, which disrupts the overall aerodynamic shape of the fuselage. At the same time, the airflow design at the tail and inside of the tail cone is unreasonable, which can easily generate airflow turbulence, increase flight drag, and affect the flight efficiency and stability of the UAV.

[0006] 4. The tail cone frame adopts a traditional solid or complex frame structure without lightweight optimization. If the electronic speed controller and other equipment need heat dissipation, they often rely on an additional cooling system, which further increases the weight of the whole machine and is not conducive to improving the drone's endurance. At the same time, the design of the skin and frame components is redundant and does not make full use of the characteristics of lightweight and high-strength materials, making it difficult to reduce the structural weight.

[0007] 5. The installation location of critical equipment such as the ESC is concealed, and the surrounding structure lacks dedicated maintenance channels or convenient operation ports. During maintenance, multiple components of the tail cone need to be disassembled, which is time-consuming and labor-intensive, greatly reducing maintenance efficiency and increasing the cost of use in the later stage.

[0008] Therefore, those skilled in the art are dedicated to providing a UAV tail cone structure that can effectively solve the above-mentioned technical problems. Utility Model Content

[0009] To achieve the above objectives, this utility model provides a tail cone structure for a drone, including a frame disposed at the tail of the fuselage for supporting the skin and fixing the electronic speed controller;

[0010] The skin, located outside the frame, is used to maintain the aerodynamic shape of the UAV's tail cone;

[0011] The power switch heat dissipation holes are formed on the skin to dissipate heat from the power switch heat dissipation fins.

[0012] Furthermore, the frame includes an ESC bracket connected to the tail frame for mounting two ESCs corresponding to the left and right tail push motors respectively.

[0013] The tail frame is made according to the shape of the fuselage and vertical tail, and is connected to the skin;

[0014] The sealing rib, connected to the tail frame, is used to prevent airflow from mixing inside and outside the tail cone, while also supporting the skin.

[0015] Furthermore, the skin comprises two interconnected skin bodies; the interior of each skin body is connected to the tail frame;

[0016] The plug is connected to the tail of each of the skin bodies and is used to cooperate with the sealing rib to form a tail cone closed space.

[0017] Furthermore, the plug is provided with a plurality of adhesive edges, and the plug is bonded to the skin body through each of the adhesive edges.

[0018] Furthermore, there is a step between the plug and the adhesive edge, the height of which is the thickness of the skin body plus the thickness of the structural adhesive, and the adhesive edge adopts a segmented structure.

[0019] Furthermore, it also includes a cover hole, which, along with the electrically adjustable heat dissipation hole, is located at the lower part of the skin body and is formed by the fastening of two skin bodies.

[0020] Furthermore, the lower half of the tail frame is provided with a wire harness through hole for the power supply wire harness to pass through;

[0021] The tail frame has a flange on its edge, and the flange is bonded to the skin body with structural adhesive to support the skin body.

[0022] The upper end of the tail frame is provided with a tail beam, which is connected to the rear beam of the vertical tail.

[0023] Furthermore, the ESC bracket includes a main frame, and auxiliary frames are provided on both the left and right sides of the main frame;

[0024] Both the main frame and the sub-frame are provided with light-reducing holes. The main frame is provided with two reinforcing ribs, and the two ends of each reinforcing rib are respectively connected to the sub-frame.

[0025] Each of the reinforcing ribs has several electrical adjustment mounting holes on the outer side of the main frame;

[0026] Each of the sub-frames is provided with a connecting edge for connecting to the tail frame.

[0027] Furthermore, the ESC bracket has a hollow structure.

[0028] Furthermore, the skin is a carbon fiber composite foam sandwich structure, wherein the foam core is PMI foam with a density of 50 kg / m³. 3 The thickness is 3mm; the carbon fiber composite material is a 200gsm twill fabric.

[0029] This utility model has the following beneficial effects:

[0030] 1. Fully utilize the unused space inside the drone's tail cone to integrate and install the ESCs for the left and right tail thrust motors, avoiding the ESCs from being scattered and occupying other areas such as the fuselage center or wing compartments, reserving more installation space for core equipment such as batteries and sensors, and effectively improving space utilization.

[0031] 2. In this utility model, the skin adopts a carbon fiber composite foam sandwich structure, and the foam core has a density of 50 kg / m³. 3 The material is made of 3mm thick PMI material, with an outer layer of 200gsm twill carbon fiber fabric, which balances high out-of-plane stiffness and low weight. It can maintain shape stability when subjected to flight aerodynamic forces. The end cap is made of 1.5mm thick PA12 3D printed plastic parts, which avoids the problem of molding carbon fiber with large curvature surfaces while reducing the weight of the tail. The ESC bracket is a 7075 aluminum alloy hollow structure. Both the main frame and the sub-frame have light-reducing holes, which, together with two reinforcing ribs, form a three-dimensional frame, further reducing weight while ensuring support stiffness.

[0032] 3. The lower part of the skin body has an ESC heat dissipation hole. The ESC heat dissipation fins are directly exposed to the air through the hole. When the UAV is flying, the forward airflow can directly pass through the heat dissipation hole to carry away the heat. This eliminates the need to install cooling devices such as fans and water cooling pipes, and avoids the ESC from performance degradation or failure due to high temperature. In addition, the heat dissipation hole is located in the tail cone area at the rear of the fuselage. This area is aerodynamically insensitive. After the hole is opened, it has minimal interference with the airflow field of the whole aircraft and will not significantly increase aerodynamic drag.

[0033] 4. The ESC is arranged close to the tail push motor. The wiring harness is neatly connected through the wiring harness through hole in the lower half of the tail frame, which shortens the control signal transmission distance between the ESC and the motor, reduces signal delay and interference, and improves the motor response speed and control stability.

[0034] 5. The skin is designed in accordance with the shape of the body and tail. The edge of the tail frame is tightly bonded to the skin. The sealing ribs block the opening area of ​​the skin. After the plug is bonded to the skin, it forms a closed space, which effectively prevents the airflow inside and outside the tail cone from crossing and avoids the additional resistance caused by airflow turbulence.

[0035] 6. A cover hole is opened at the lower part of the skin body in front of the ESC heat dissipation hole. The cover covers the outside and is close to the ESC installation position. During maintenance, there is no need to disassemble the entire tail cone structure. Only the cover needs to be opened to directly contact the ESC. This has the beneficial effects of shortening maintenance time and reducing the labor intensity of operators. Attached Figure Description

[0036] Figure 1 This is a schematic diagram of the structure of this practical tail cone structure used on a drone.

[0037] Figure 2 yes Figure 1 A magnified schematic diagram of the structure at point A in the middle.

[0038] Figure 3 yes Figure 1 The diagram shows a structure without components such as horizontal and vertical tail.

[0039] Figure 4 yes Figure 3 A magnified schematic diagram of the structure at point B in the middle.

[0040] Figure 5 This is an exploded structural diagram of the tail cone structure in this utility model.

[0041] Figure 6 yes Figure 5 A magnified schematic diagram of the structure at point C.

[0042] Figure 7 yes Figure 3 A schematic diagram of the three-dimensional structure viewed from below.

[0043] Figure 8 yes Figure 7 A magnified schematic diagram of the structure at point D.

[0044] Figure 9 This is a schematic diagram of the skeleton structure in this utility model.

[0045] Figure 10 This is a schematic diagram of the structure of the ESC bracket in this utility model.

[0046] Figure 11 This is a three-dimensional structural diagram of the tail frame in this utility model.

[0047] Figure 12 This is a three-dimensional structural diagram of the plug in this utility model.

[0048] The attached diagram lists the components represented by each number as follows:

[0049] 1. Tail cone structure; 2. Body; 100. Horizontal tail; 101. Vertical tail; 11. Skin; 111. End cap; 1111. Adhesive edge; 112. Skin body; 1121. ESC heat dissipation hole; 1122. Hose hole; 12. Frame; 121. Tail frame; 1211. Tail beam; 1212. Wiring harness through hole; 1213. Flanged edge; 122. ESC bracket; 122a. Main frame; 122b. Sub-frame; 1221. ESC mounting hole; 1222. Connecting edge; 1223. Lightening hole; 1224. Reinforcing rib; 123. Sealing rib. Detailed Implementation

[0050] The present invention will be further described below with reference to the accompanying drawings and embodiments:

[0051] In the description of this utility model, it should be noted that the terms "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0052] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "setting," and "connection" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0053] like Figures 1 to 12 As shown, this utility model relates to a tail cone structure for a drone. The tail cone structure 1 is located at the tail of the body 2 (drone), with horizontal tails 100 on both the left and right sides and a vertical tail 101 on the top. The electronic speed controller (ESC) is arranged inside the tail cone structure 1 and is connected to the tail thrust motors on the horizontal tails 100 on both sides through wiring harnesses to control the motors and realize their operation, meeting the requirements for level flight of the drone. The tail cone structure 1 consists of a skin 11 and a frame 12. Specifically, the frame 12 is located at the tail of the body 2 and is used to support the skin 11 and fix the ESC to ensure the reliability of the ESC installation.

[0054] Skin 11, disposed outside the frame 12, is used to maintain the aerodynamic shape of the UAV tail cone. Preferably, in this invention, the skin body 112 is a carbon fiber composite foam sandwich structure, possessing high out-of-plane stiffness to maintain the aerodynamic shape and prevent deformation of the skin body 112 under aerodynamic forces. The foam core is preferably made of PMI material with a preferred density of 50 kg / m³. 3 The preferred thickness is 3mm; the preferred carbon fiber composite material is a 200gsm twill fabric.

[0055] The power switch heat dissipation hole 1121 is formed on the skin 11 and is used to dissipate heat from the power switch heat dissipation fins;

[0056] The frame 12 includes an ESC bracket 122, which is connected to the tail frame 121 and is used to install two ESCs corresponding to the left and right tail push motors respectively.

[0057] The tail frame 121 is made according to the shape of the fuselage and vertical tail, and is connected to the skin 11;

[0058] The sealing rib 123 is connected to the tail frame 121 to prevent airflow from mixing inside and outside the tail cone, and to support the skin 11.

[0059] Specifically, the tail frame 121 supports the skin body 112 and the ESC bracket 122, and also bears the main load of the tail cone. The tail frame 121 is bonded to the skin body 112 with structural adhesive, and connected to the ESC using fasteners, preferably blind rivets. The sealing rib 123 seals the opening area formed by the two skin bodies 112, preventing airflow between the inside and outside of the tail cone, reducing drag, and supporting the skin body 112. In addition, the sealing rib 123 is cut from a foam-core carbon fiber composite material plate. This processing method does not require special molds, so the cost is low.

[0060] The skin 11 includes two interconnected skin bodies 112; the interior of the skin body 112 is connected to the tail frame 121; the tail frame 121 supports the skin body 112, and a portion of it serves as the rear beam of the tail, bearing the load of the tail and supporting the ESC bracket 122.

[0061] The plug 111 is connected to the tail of each of the skin bodies 112 and is used to cooperate with the sealing rib 123 to form a tail cone closed space. The plug 111 is provided with a plurality of adhesive edges 1111, and the plug 111 is glued to the skin body 112 through each of the adhesive edges 1111.

[0062] A step is provided between the plug 111 and the adhesive edge 1111. The height of the step is the sum of the thickness of the skin body 112 and the thickness of the structural adhesive. The adhesive edge 1111 adopts a segmented structure. Considering the deformation characteristics of 3D printed plastic parts, the adhesive edge 1111 adopts a segmented design rather than a whole ring structure. If the adhesive edge 111 is a whole ring, it will be difficult to deform due to excessive stiffness, making it impossible to smoothly insert into the cavity formed by the skin body 112 during use. The segmented structure can significantly reduce the overall stiffness. During assembly, only a small external force is needed to make the adhesive edge 1111 adapt to the deformation, thus smoothly inserting into the cavity. After insertion, structural adhesive is applied, and the adhesive edge 1111 will naturally spring back, forming stable pressure on the structural adhesive, effectively improving the tightness and connection strength of the adhesive, and ensuring the reliability of the overall structure.

[0063] In this invention, the plug 111 is located at the very end of the tail cone structure, and the curvature of the surface is relatively large. If carbon fiber composite material is used, the molding difficulty is high. Therefore, a 3D printed plastic part is used, preferably PA12, with a preferred thickness of 1.5mm. 1.5mm is the minimum thickness for molding PA12 material, which effectively reduces the weight of the plug 111. In addition, the two skin bodies 112 are bonded to the structural adhesive in the middle position by a strip plate, together forming the overall shell of the tail cone.

[0064] In this invention, the heat dissipation fins are exposed to the air through the electrically adjustable heat dissipation holes 1121 formed by the skin body 112, and heat dissipation is achieved by utilizing the airflow of the UAV flying forward. The cover 111 is connected to the tail of each skin body 112 and cooperates with the sealing rib 123 to form a relatively closed space of the tail cone, which can effectively prevent the disorderly airflow from entering the interior of the tail cone and avoid the additional resistance caused by the turbulent airflow. At the same time, through the electrically adjustable heat dissipation holes 1121 at the bottom of the skin body 112, the hot airflow generated by the electrical control inside the tail cone and the cold air outside can be directionally exchanged, ensuring heat dissipation efficiency while maintaining aerodynamic stability.

[0065] This utility model also includes a cover hole 1122, which and the electric cooling hole 1121 are both located at the lower part of the skin body 112 and are formed by the two skin bodies 112 fastening together.

[0066] In this invention, the heat dissipation fins are directly exposed to the air through the electrically adjustable heat dissipation holes 1121 formed by the skin body 112. With this design, efficient heat dissipation can be achieved by utilizing the airflow generated when the drone flies forward. The rearmost part of the fuselage adopts a large curvature surface design, which is bonded to the skin body 112 by 3D printed plastic parts and together with the sealing ribs 123 to form a closed space. This space can realize the flow of internal and external airflow, effectively reducing the overall flight drag.

[0067] In this invention, the lower region enclosed by the skin body 112 is selected as the location for the opening of the electronic control heat dissipation hole 1121. Since the airflow in the rear tail cone region has little impact on the overall airflow field, the increase in aerodynamic drag of the whole machine is extremely limited when designing openings or protruding structures in this region. Based on this characteristic, this invention exposes the electronic control heat dissipation fins to the air through the electronic control heat dissipation hole 1121, using natural airflow to dissipate heat from the electronic control, which can not only meet the heat dissipation requirements of the electronic control and eliminate the need for a cooling system, but also minimize the impact on the aerodynamic performance of the whole machine, thus achieving a balance between function and performance.

[0068] In addition, to improve maintenance convenience, this utility model has specially designed a cover hole 1122 in front of the heat dissipation hole 1121 of the ESC. The cover covers the outside of the cover hole 1122. The cover is close to the ESC, which allows the operator to easily open the cover to inspect and maintain the ESC, further optimizing the user experience of the equipment.

[0069] The tail frame 121 follows the shape of the fuselage inside the fuselage and the shape of the tail at the tail position. It adopts a carbon fiber composite laminate structure. The lower half of the tail frame 121 has a wire harness through hole 1212 for the power supply wire harness to pass through, avoiding the wire harness from being messy and tangled. During maintenance, the wire harness fault point can be quickly located, reducing troubleshooting time.

[0070] The edge of the tail frame 121 is provided with a flange 1213, which is bonded to the skin body 112 with structural adhesive to support the skin body 112.

[0071] The upper end of the tail frame 121 is provided with a tail beam 1211, which is connected to the rear beam of the vertical tail and serves as part of the rear beam of the vertical tail to bear the load of the vertical tail. The wiring harness through hole 1212 is located at the lower part corresponding to the ESC, providing a passage for the ESC wiring harness. The flange 1213 is bonded to the skin body 112 with structural adhesive, providing support for the skin body 112 and bearing the aerodynamic force of the skin body 112.

[0072] The power adjustment bracket 122 includes a main frame 122a, and auxiliary frames 122b are provided on both the left and right sides of the main frame 122a.

[0073] Both the main frame 122a and the sub-frame 122b are provided with light-reducing holes 1223. The main frame 122a is provided with two reinforcing ribs 1224, and the two ends of each reinforcing rib 1224 are respectively connected to each sub-frame 122b. Each reinforcing rib 1224 has a plurality of electrical adjustment mounting holes 1221 on the outer side of the main frame 122a.

[0074] Fasteners secure the ESC to the ESC bracket 122 via ESC mounting holes 1221. Each ESC is mounted using four ESC mounting holes 1221, and two ESCs are mounted on the ESC bracket 122 to control the tail thrust motors on both sides. The connecting edge 1222 connects to the tail frame 121 directly to the web of the tail frame 121 and is installed using fasteners. The preferred fasteners are blind rivets made of stainless steel. The weight-reducing holes 1223 effectively reduce the weight of the ESC bracket 122, and the reinforcing ribs 1224 increase the rigidity of the ESC bracket 122, minimizing deformation during flight and ensuring the gap between the ESC and the skin body 112 does not interfere due to deformation. The reinforcing ribs 1224 and the weight-reducing holes 1223 give the ESC bracket 122 a three-dimensional frame structure, improving material utilization efficiency.

[0075] Each of the sub-frames 122b is provided with a connecting edge 1222 for connecting to the tail frame 121. Preferably, the electrically adjustable bracket 122 in this utility model has a hollow structure, which is lightweight. It is made of machined aluminum alloy material. In this embodiment, the material used is 7075, and the preferred heat treatment state is T7351.

[0076] The optimal structural principle of this utility model is as follows:

[0077] The skin 11 consists of two skin bodies 112 and a plug 111. The skin body 112 adopts a carbon fiber composite foam sandwich structure, which has high out-of-plane stiffness and can maintain shape stability under the action of flight aerodynamics, thus maintaining the aerodynamic shape of the tail cone. The two skin bodies 112 are bonded together with a strip and structural adhesive to form the main shell of the tail cone. The tail is closed by the adhesive edge 1111 of the plug 111, and the step between the plug 111 and the adhesive edge 1111 ensures tight bonding and avoids airflow leakage. The frame 12 includes a tail frame 121, an electronic control bracket 122, and a sealing rib 123. The tail frame 121 is made in accordance with the shape of the fuselage and the vertical tail 101. The upper tail beam 1211 is connected to the rear beam of the vertical tail 101, which not only bears the load of the vertical tail, but also is glued to the skin body 112 through the edge flange 1213 to provide support for the skin 11. The sealing rib 123 is connected to the tail frame 121 to block the opening formed by the skin body 112, prevent the airflow inside and outside the tail cone from passing through to reduce drag, and at the same time assist in supporting the skin 11 to prevent it from deforming under aerodynamic force.

[0078] The ESC bracket 122 is connected to the tail frame 121 via the connecting edge 1222 of the sub-frame 122b using blind rivets. The sub-frames 122b on the left and right sides of the main frame 122a form a symmetrical structure for mounting two ESCs corresponding to the left and right tail thrust motors, respectively. The ESCs are fixed by fasteners passing through the ESC mounting holes 1221 of the main frame 122a. Each ESC has four mounting holes to ensure stable ESC position. The two reinforcing ribs 1224 on the main frame 122a increase the overall rigidity of the bracket and prevent the bracket from deforming during flight, which could cause interference between the ESC and the skin 11. The weight-reducing holes 1223 and the overall hollow structure on the main frame 122a and sub-frame 122b reduce the weight of the bracket without affecting the load-bearing capacity, meeting the lightweight requirements of UAVs.

[0079] The lower part of the skin body 112 has an ESC heat dissipation hole 1121, through which the heat dissipation fins of the ESC are exposed to the air; when the UAV is flying, the forward airflow passes through the ESC heat dissipation hole 1121 and directly carries away the heat of the heat dissipation fins, thereby cooling the ESC and preventing the ESC from failing due to high temperature; and the ESC heat dissipation hole 1121 is located in the tail cone area, so the opening will not significantly increase aerodynamic drag.

[0080] The wiring harness through-hole 1212 in the lower half of the tail frame 121 provides a passage for the ESC wiring harness. The connection harnesses of the ESC and the left and right tail thrust motors pass through this hole, avoiding the wiring harness from interfering with other components and preventing the wiring harness from wearing during flight. This ensures stable transmission of control signals from the ESC to the tail thrust motors, enabling the UAV to fly horizontally. The plug 111 is glued to the skin body 112 through a segmented adhesive edge 1111, and cooperates with the sealing rib 123 to form a closed space for the tail cone, further reducing airflow interference and drag. The lower part of the skin body 112 also has a cover hole 1122, which is adjacent to the ESC heat dissipation hole 1121 and is formed by two skin bodies 112 snapping together. The cover covers the outside of the cover hole 1122. When the ESC needs to be inspected, the cover can be opened to access the ESC through the cover hole 1122 without disassembling the entire tail cone, improving maintenance efficiency.

[0081] The preferred embodiments of this utility model have been described in detail above. It should be understood that those skilled in the art can make numerous modifications and variations based on the concept of this utility model without creative effort. Therefore, all technical solutions that can be obtained by those skilled in the art based on the concept of this utility model through logical analysis, reasoning, or limited experimentation on the basis of existing technology should be within the scope of protection defined by the claims.

Claims

1. A tail cone structure for an unmanned aerial vehicle (UAV), characterized in that, Includes a frame (12), which is set at the tail of the body (2) to support the skin (11) and fix the ESC; Skin (11), disposed outside the frame (12), is used to maintain the aerodynamic shape of the UAV tail cone; Electrically adjustable heat dissipation holes (1121) are provided on the skin (11) for dissipating heat from the electrically adjustable heat dissipation fins.

2. The UAV tail cone structure as described in claim 1, characterized in that, The frame (12) includes an ESC bracket (122) connected to the tail frame (121) for mounting two ESCs corresponding to the left and right tail push motors respectively; The tail frame (121) is made according to the shape of the fuselage and vertical tail and is connected to the skin (11); The sealing rib (123) is connected to the tail frame (121) to prevent airflow from crossing between the inside and outside of the tail cone, and to support the skin (11).

3. The UAV tail cone structure as described in claim 2, characterized in that, The skin (11) includes two interconnected skin bodies (112); the interior of the skin body (112) is connected to the tail frame (121); The plug (111) is connected to the tail of each of the skin bodies (112) and is used to cooperate with the sealing rib (123) to form a tail cone closed space.

4. The UAV tail cone structure as described in claim 3, characterized in that, The plug (111) is provided with a plurality of adhesive edges (1111), and the plug (111) is bonded to the skin body (112) through each of the adhesive edges (1111).

5. The UAV tail cone structure as described in claim 4, characterized in that, There is a step between the plug (111) and the adhesive edge (1111), the height of which is the thickness of the skin body (112) plus the thickness of the structural adhesive, and the adhesive edge (1111) adopts a segmented structure.

6. The UAV tail cone structure as described in claim 5, characterized in that, It also includes a cover hole (1122), which, along with the electrically adjustable heat dissipation hole (1121), is located at the lower part of the skin body (112) and is formed by the two skin bodies (112) fastening together.

7. The UAV tail cone structure as described in claim 6, characterized in that, The lower half of the tail frame (121) is provided with a wire harness through hole (1212) for the power supply wire harness to pass through; The tail frame (121) has a flange (1213) on its edge, and the flange (1213) is bonded to the skin body (112) with structural adhesive to support the skin body (112); the upper end of the tail frame (121) is provided with a tail beam (1211), and the tail beam (1211) is connected to the rear beam of the vertical tail.

8. The UAV tail cone structure as described in claim 7, characterized in that, The electrical control bracket (122) includes a main frame (122a), and auxiliary frames (122b) are provided on both the left and right sides of the main frame (122a). Both the main frame (122a) and the sub-frame (122b) are provided with light-reducing holes (1223). The main frame (122a) is provided with two reinforcing ribs (1224), and the two ends of each reinforcing rib (1224) are respectively connected to each sub-frame (122b). Each of the reinforcing ribs (1224) has a plurality of electrically adjustable mounting holes (1221) on the outer side of the main frame (122a); Each of the sub-frames (122b) is provided with a connecting edge (1222) for connecting with the tail frame (121).

9. The UAV tail cone structure as described in claim 8, characterized in that, The power switch bracket (122) has a hollow structure.

10. The UAV tail cone structure as described in any one of claims 1 to 9, characterized in that, The skin (11) is a carbon fiber composite foam sandwich structure, wherein the foam core is PMI foam with a density of 50 kg / m³. 3 The thickness is 3mm; the carbon fiber composite material is a 200gsm twill fabric.

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