Combined wing unmanned aerial vehicle structure and method switchable between single wing and tandem double wings

Abstract

The application discloses a combined wing unmanned aerial vehicle structure capable of switching between a single wing and tandem double wings and a method thereof, relates to the technical field of unmanned aerial vehicles, and comprises an unmanned aerial vehicle body, front wings and rear wings. Two rear wings are respectively arranged above one end of two front wings. A combination mechanism for combining the front wings and the rear wings is arranged on the unmanned aerial vehicle body. A stabilizing mechanism for improving the combination stability of the front wings and the rear wings is arranged on the unmanned aerial vehicle body. In actual use, the positions of the front wings and the rear wings can be adjusted according to the use requirements and the characteristics of the single-wing unmanned aerial vehicle and the tandem double-wing unmanned aerial vehicle. When the front wings and the rear wings are combined into combined wings, the positions of the combined wings can be adjusted according to actual requirements, so that the unmanned aerial vehicle can be conveniently switched between the single wing and the tandem double wings.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a combined-wing UAV structure and method that can switch between a single wing and a tandem biwing. Background Technology

[0002] A drone is an unmanned aerial vehicle that is controlled by radio remote control equipment and its own program control device. It can operate without a pilot and can be operated by radio remote control or preset program control device. Its application fields are extremely wide, covering both military and civilian categories.

[0003] In use, drones are classified into different categories according to different actual needs. These include monoplane drones and tandem biplane drones. A monoplane drone is a drone that uses a single rotor or wing to fly and is usually called a single-rotor drone. A tandem biplane drone is a drone with a special layout, the core feature of which is that two sets of wings are arranged along the fuselage axis.

[0004] Monoplane UAVs are characterized by high speed and strong maneuverability, while tandem biplane UAVs are characterized by high flight altitude, long loiter time and short takeoff runway. In terms of application, monoplane UAVs can be used as attack UAVs, while tandem biplane UAVs can be used for reconnaissance, surveillance and relay communication.

[0005] Currently, both monoplane and tandem biplane drones adopt an integrated structural design. This makes it impossible for drones to flexibly switch between monoplane and tandem biplane modes according to actual needs during use. In order to achieve the goal of drones being able to switch conveniently between monoplane and tandem biplane modes, a combined-wing drone structure and method that can switch between monoplane and tandem biplane modes is now provided, which can eliminate the drawbacks of existing devices. Summary of the Invention

[0006] The purpose of this invention is to provide a combined-wing unmanned aerial vehicle (UAV) structure and method that can switch between a single wing and a tandem biwing, in order to solve the problems in the prior art.

[0007] To achieve the above objectives, the present invention provides the following technical solution:

[0008] A combined-wing UAV structure that can switch between single-wing and tandem dual-wing configuration includes a UAV body, two front wings symmetrically arranged on the outer side of the UAV body, two rear wings symmetrically arranged on the outer side of the UAV body, the two rear wings being located above one end of each of the two front wings, and a coupling mechanism for coupling the front wings and rear wings being provided on the UAV body.

[0009] The connecting mechanism includes: two first guide plates symmetrically fixedly connected to the outer wall of the drone body; two front wings slidably sleeved on the outer walls of the two first guide plates; two second guide plates symmetrically fixedly connected to the outer wall of the drone body; the two second guide plates are respectively located above the two first guide plates; and two rear wings slidably sleeved on the outer walls of the two first guide plates and the two second guide plates.

[0010] The main body of the drone is equipped with a stabilizing mechanism to improve the stability of the connection between the forewing and the rearwing.

[0011] Based on the above technical solutions, the present invention also provides the following optional technical solutions:

[0012] In one alternative embodiment, the coupling mechanism further includes:

[0013] A guide component mounted on the main body of the drone;

[0014] The guiding component includes: a guide rod disposed inside the drone body, and two fixing plates symmetrically fixed to the outer wall of the guide rod, the two fixing plates being located at the two ends of the guide rod, and both fixing plates being fixedly connected to the drone body;

[0015] The guide rod is equipped with a first drive assembly.

[0016] In one alternative: the first drive assembly includes: two first lead screws symmetrically arranged on the outside of the guide rod, the two first lead screws being located between two fixed plates, the two first lead screws being rotatably connected to the two fixed plates via a rotating shaft, and two servo motors symmetrically mounted on one of the fixed plates away from the guide rod, the output ends of the two servo motors being fixedly connected to the two first lead screws respectively.

[0017] A first displacement component is provided on the first lead screw, which is used to drive the two front wings to move synchronously.

[0018] In one alternative: the first displacement component includes: a second movable sleeve plate sleeved on the outer wall of a first lead screw, the second movable sleeve plate being threadedly connected to a first lead screw, the second movable sleeve plate being slidably sleeved on the outer wall of a guide rod, and two second connecting rods being symmetrically and fixedly connected to the outer wall of the second movable sleeve plate, the two second connecting rods passing through the main body of the UAV and being fixedly connected to two forewings respectively, and both second connecting rods being slidably connected to the main body of the UAV.

[0019] Another first lead screw is equipped with a second displacement component, which is used to drive the two rear wings to move synchronously.

[0020] In one alternative: the second displacement component includes: a first movable sleeve plate sleeved on the outer wall of another first lead screw, the first movable sleeve plate being threadedly connected to the other first lead screw, the first movable sleeve plate being slidably sleeved on the outer wall of a guide rod, and two first connecting rods being symmetrically and fixedly connected to the outer wall of the first movable sleeve plate, the two first connecting rods penetrating the main body of the UAV and being fixedly connected to the two rear wings respectively, and both first connecting rods being slidably connected to the main body of the UAV.

[0021] In one alternative embodiment, the stabilizing mechanism includes a second drive component disposed on the main body of the drone.

[0022] The second drive component includes: a dual-head motor disposed inside the main body of the drone, the dual-head motor being located below the first movable sleeve plate, the outer wall of the dual-head motor being symmetrically fixedly connected to two support plates by bolts, both of the support plates being fixedly connected to the first movable sleeve plate, and two second lead screws being symmetrically disposed on the outer side of the dual-head motor, the two second lead screws being fixedly connected to two output ends on the dual-head motor respectively;

[0023] The second lead screw is equipped with a moving component.

[0024] In one alternative: the moving component includes: a sliding sleeve plate sleeved on the outer wall of the second lead screw, the sliding sleeve plate being threadedly connected to the second lead screw, the sliding sleeve plate being slidably sleeved on the outer wall of the first connecting rod, and two limiting sliders being symmetrically fixedly connected to the inner wall of the sliding sleeve plate, both of the limiting sliders penetrating into the interior of the first connecting rod;

[0025] The sliding sleeve is equipped with a locking component.

[0026] In one alternative embodiment: the engaging assembly includes: a movable insert rod fixedly connected to one end of the sliding sleeve plate, the movable insert rod being located at the end of the sliding sleeve plate near the front wing, and a limit baffle integrally formed on the outer wall of the end of the movable insert rod away from the sliding sleeve plate.

[0027] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0028] 1. The present invention, through a combination mechanism, allows for the adjustment of the positions of the front and rear wings during actual use, based on usage requirements and the characteristics of monoplane and tandem biplane drones. After the front and rear wings are combined to form a combined wing, the position of the combined wing can be adjusted according to actual needs, thereby enabling the drone to conveniently switch between monoplane and tandem biplane modes.

[0029] 2. The present invention, through a stabilizing mechanism, can further improve the stability of the front and rear wings during movement after they are joined together, by cooperating with the joining mechanism. Attached Figure Description

[0030] Figure 1 This is a schematic diagram of the structure of the present invention.

[0031] Figure 2 This is a schematic diagram of the internal structure of the drone body of the present invention.

[0032] Figure 3 This is a schematic diagram of the connecting mechanism structure of the present invention.

[0033] Figure 4 This is a schematic diagram of the connection structure between the second displacement component and the rear wing of the present invention.

[0034] Figure 5 This is a schematic diagram of the connection structure between the first displacement component and the front wing of the present invention.

[0035] Figure 6 This is a schematic diagram of the connection structure between the guide component and the first drive component of the present invention.

[0036] Figure 7 This is a schematic diagram of the stabilizing mechanism of the present invention. Figure 8 This is a schematic diagram of the connection structure between the front wing and the rear wing of the present invention.

[0037] Figure reference numerals: 1. UAV body; 201. First connecting rod; 202. First movable sleeve; 203. Second connecting rod; 204. Second movable sleeve; 205. Servo motor; 206. First lead screw; 207. Guide rod; 208. Fixing plate; 209. First guide plate; 2010. Second guide plate; 301. Limiting baffle; 302. Movable insert rod; 303. Dual-head motor; 304. Support plate; 305. Sliding sleeve; 306. Second lead screw; 307. Limiting slider; 4. Front wing; 5. Rear wing. Detailed Implementation

[0038] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments.

[0039] In one embodiment, such as Figures 1-8As shown, the combined-wing UAV structure that can switch between single-wing and tandem dual-wing configuration includes a UAV body 1. Two front wings 4 are symmetrically arranged on the outer side of the UAV body 1, and two rear wings 5 ​​are symmetrically arranged on the outer side of the UAV body 1. The two rear wings 5 ​​are located above one end of the two front wings 4 respectively. The bottom end of each of the two rear wings 5 ​​is provided with a mating surface that matches the outer wall of the front wings 4. The UAV body 1 is provided with a joining mechanism for joining the front wings 4 and the rear wings 5.

[0040] The connecting mechanism includes: two first guide plates 209 symmetrically fixedly connected to the outer wall of the UAV body 1; two front wings 4 slidably sleeved on the outer walls of the two first guide plates 209; two second guide plates 2010 symmetrically fixedly connected to the outer wall of the UAV body 1; the two second guide plates 2010 are respectively located above the two first guide plates 209; and two rear wings 5 ​​slidably sleeved on the outer walls of the two first guide plates 209 and the two second guide plates 2010.

[0041] The main body 1 of the drone is equipped with a stabilizing mechanism to improve the stability of the connection between the forewing 4 and the rear wing 5;

[0042] In this embodiment, during use, the front wing 4 and the rear wing 5 can be driven to slide along the outer walls of the first guide plate 209 and the two second guide plates 2010 respectively through the connecting mechanism. At the same time, the stabilizing mechanism moves synchronously with the movement of the rear wing 5, so that the positions of the front wing 4 and the rear wing 5 can be conveniently adjusted according to actual needs.

[0043] When it is necessary to combine the front wing 4 and the rear wing 5 into one piece, the two front wings 4 and the two rear wings 5 ​​can be brought close to each other through the combination mechanism until the two front wings 4 and the outer walls of the two rear wings 5 ​​are respectively attached to each other, so as to achieve the purpose of convenient combination of the front wing 4 and the rear wing 5.

[0044] During this process, the stability of the front wing 4 and the rear wing 5 after they are joined can be further improved by the stabilizing mechanism. Afterwards, the positions of the front wing 4 and the rear wing 5 after they are joined can be easily adjusted according to actual needs.

[0045] When it is necessary to separate the combined forewing 4 and rearwing 5, the above operation is reversed, thereby enabling the UAV to conveniently switch between monoplane and tandem biplane modes.

[0046] In one embodiment, such as Figures 2-8 As shown, the connecting mechanism also includes: a guide component disposed on the main body 1 of the UAV;

[0047] The guiding assembly includes: a guide rod 207 disposed inside the drone body 1, and two fixing plates 208 symmetrically fixed to the outer wall of the guide rod 207. The two fixing plates 208 are located at the two ends of the guide rod 207, and both fixing plates 208 are fixedly connected to the drone body 1.

[0048] The guide rod 207 is equipped with a first drive assembly;

[0049] The first drive assembly includes two first lead screws 206 symmetrically arranged on the outside of the guide rod 207. The two first lead screws 206 are located between two fixed plates 208. The two first lead screws 206 are rotatably connected to the two fixed plates 208 through a rotating shaft. Two servo motors 205 are symmetrically installed on one end of a fixed plate 208 away from the guide rod 207. The output ends of the two servo motors 205 are respectively fixedly connected to the two first lead screws 206. Through the cooperation between the guide assembly and the first drive assembly, the front wing 4 and the rear wing 5 can be driven to move, and the front wing 4 and the rear wing 5 can be guided to move.

[0050] A first displacement component is provided on a first lead screw 206, which is used to drive the two front wings 4 to move synchronously.

[0051] In one embodiment, such as Figures 2-8 As shown, the first displacement component includes: a second movable sleeve plate 204 sleeved on the outer wall of a first lead screw 206, the second movable sleeve plate 204 being threadedly connected to a first lead screw 206, the second movable sleeve plate 204 being slidably sleeved on the outer wall of a guide rod 207, and two second connecting rods 203 being symmetrically fixedly connected to the outer wall of the second movable sleeve plate 204, the two second connecting rods 203 penetrating the UAV body 1 and being fixedly connected to two forewings 4 respectively, and both second connecting rods 203 being slidably connected to the UAV body 1;

[0052] Another first lead screw 206 is equipped with a second displacement component, which is used to drive the two rear wings 5 ​​to move synchronously.

[0053] The second displacement component includes: a first movable sleeve plate 202 sleeved on the outer wall of another first lead screw 206, the first movable sleeve plate 202 being threadedly connected to the other first lead screw 206, the first movable sleeve plate 202 being slidably sleeved on the outer wall of the guide rod 207, and two first connecting rods 201 being symmetrically fixedly connected to the outer wall of the first movable sleeve plate 202, the two first connecting rods 201 penetrating the UAV body 1 and being fixedly connected to the two rear wings 5 ​​respectively, and both first connecting rods 201 being slidably connected to the UAV body 1. Through the cooperation of the first displacement component and the second displacement component, the positions of the front wing 4 and the rear wing 5 can be conveniently adjusted.

[0054] In one embodiment, such as Figures 2-8 As shown, the stabilizing mechanism includes: a second drive component disposed on the main body 1 of the drone;

[0055] The second drive assembly includes: a dual-head motor 303 disposed inside the main body 1 of the UAV, the dual-head motor 303 being located below the first movable sleeve 202, the outer wall of the dual-head motor 303 being symmetrically fixedly connected to two support plates 304 by bolts, both support plates 304 being fixedly connected to the first movable sleeve 202, and two second lead screws 306 being symmetrically disposed on the outer side of the dual-head motor 303, the two second lead screws 306 being fixedly connected to two output ends on the dual-head motor 303 respectively;

[0056] A moving component is provided on the second lead screw 306;

[0057] The moving component includes: a sliding sleeve 305 sleeved on the outer wall of the second lead screw 306, the sliding sleeve 305 being threadedly connected to the second lead screw 306, the sliding sleeve 305 being slidably sleeved on the outer wall of the first connecting rod 201, and two limiting sliders 307 being symmetrically fixedly connected to the inner wall of the sliding sleeve 305, both limiting sliders 307 penetrating into the interior of the first connecting rod 201, and a guide groove for the limiting sliders 307 to slide at the contact position between the first connecting rod 201 and the limiting sliders 307, the sliding sleeve 305 can be slidably limited by the cooperation between the guide groove and the limiting sliders 307;

[0058] A locking assembly is provided on the sliding sleeve 305;

[0059] The engaging assembly includes: a movable insert rod 302 fixedly connected to one end of the sliding sleeve plate 305. The movable insert rod 302 is located at the end of the sliding sleeve plate 305 near the front wing 4. A limit baffle 301 is integrally formed on the outer wall of the end of the movable insert rod 302 away from the sliding sleeve plate 305. The outer wall of the end of the movable insert rod 302 away from the sliding sleeve plate 305 is frustum-shaped. A straight groove is provided on the second connecting rod 203 for the movable insert rod 302 to slide. Through the mutual cooperation between the frustum-shaped outer wall and the straight groove, the movable insert rod 302 can be accurately inserted into the interior of the second connecting rod 203 until the movable insert rod 302 penetrates the second connecting rod 203.

[0060] The above embodiments disclose a combined-wing UAV structure that can switch between single-wing and tandem dual-wing configurations. In use, two servo motors 205 drive two first lead screws 206 to rotate. During this process, a second movable sleeve 204 slides along the outer wall of a guide rod 207 under the threaded drive of a first lead screw 206. Simultaneously, two front wings 4 slide along the outer walls of two first guide plates 209 under the drive of the second movable sleeve 204 via a second connecting rod 203. At the same time, two rear wings 5 ​​slide along the outer walls of two first guide plates 209 and two second guide plates 2010 under the drive of the first movable sleeve 202 via a first connecting rod 201. Simultaneously, a dual-head motor 303 moves synchronously under the drive of the support plate 304 via the first movable sleeve 202. This allows for convenient adjustment of the positions of the front wings 4 and rear wings 5 ​​according to actual needs.

[0061] When it is necessary to combine the front wing 4 and the rear wing 5 into one piece, the two servo motors 205 drive the two first lead screws 206 respectively, so that the two front wings 4 and the two rear wings 5 ​​can approach each other until the two front wings 4 and the outer walls of the two rear wings 5 ​​are in contact with each other, thereby achieving the purpose of conveniently combining the front wings 4 and the rear wings 5.

[0062] During this process, the movable insert rod 302, pushed by the sliding sleeve 305 under the first connecting rod 201, passes through the straight groove to penetrate the second connecting rod 203 until the outer wall of the front wing 4 contacts the outer wall of the rear wing 5. At this time, the limiting baffle 301, pushed by the movable insert rod 302, moves to the outside of the second connecting rod 203. Then, the dual-head motor 303 is started to drive the two second lead screws 306 to rotate. At the same time, the two sliding sleeves 305, driven by the threads of the two second lead screws 306, slide along the outer walls of the two first connecting rods 201 respectively. When the time limit slider 307 is driven by the sliding sleeve 305, it slides along the inner wall of the guide groove. At the same time, the limit baffle 301 moves synchronously under the drive of the sliding sleeve 305 via the moving rod 302 until the limit slider 307 contacts one side of the inner wall of the guide groove. At this time, the moving rod 302 can block the outer wall of the second connecting rod 203 through the limit baffle 301, thereby further improving the stability of the front wing 4 and the rear wing 5 during the movement after they are combined. Then, the position of the front wing 4 and the rear wing 5 after they are combined can be conveniently adjusted according to actual needs.

[0063] When it is necessary to separate the combined forewing 4 and rearwing 5, the above operation is reversed, thereby enabling the UAV to conveniently switch between monoplane and tandem biplane modes.

[0064] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A combined-wing UAV structure capable of switching between a single wing and a tandem wing configuration, comprising a UAV body (1), wherein two forewings (4) are symmetrically arranged on the outer side of the UAV body (1), and two rear wings (5) are symmetrically arranged on the outer side of the UAV body (1), wherein the two rear wings (5) are respectively located above one end of the two forewings (4), characterized in that, The main body (1) of the UAV is provided with a joining mechanism for joining the forewing (4) and the rearwing (5); The connecting mechanism includes: two first guide plates (209) symmetrically fixedly connected to the outer wall of the UAV body (1); two front wings (4) slidably sleeved on the outer walls of the two first guide plates (209); two second guide plates (2010) symmetrically fixedly connected to the outer wall of the UAV body (1); the two second guide plates (2010) are respectively located above the two first guide plates (209); and two rear wings (5) slidably sleeved on the outer walls of the two first guide plates (209) and the two second guide plates (2010). The main body (1) of the UAV is equipped with a stabilizing mechanism to improve the stability of the connection between the forewing (4) and the rear wing (5).

2. The combined-wing UAV structure capable of switching between a single wing and a tandem biwing as described in claim 1, characterized in that, The connecting mechanism also includes: a guide component disposed on the main body (1) of the UAV; The guiding component includes: a guide rod (207) disposed inside the drone body (1), and two fixing plates (208) are symmetrically fixedly connected to the outer wall of the guide rod (207). The two fixing plates (208) are respectively located at the two ends of the guide rod (207), and both fixing plates (208) are fixedly connected to the drone body (1). The guide rod (207) is provided with a first drive assembly.

3. The combined-wing UAV structure capable of switching between a single wing and a tandem biwing according to claim 2, characterized in that, The first drive assembly includes: two first lead screws (206) symmetrically arranged outside the guide rod (207), both first lead screws (206) being located between two fixed plates (208), both first lead screws (206) being rotatably connected to the two fixed plates (208) via rotating shafts, and two servo motors (205) symmetrically mounted on one end of one fixed plate (208) away from the guide rod (207), the output ends of the two servo motors (205) being fixedly connected to the two first lead screws (206) respectively; A first displacement component is provided on one of the first lead screws (206), which is used to drive the two front wings (4) to move synchronously.

4. The combined-wing UAV structure capable of switching between a single wing and a tandem biplane as described in claim 3, characterized in that, The first displacement component includes: a second movable sleeve plate (204) sleeved on the outer wall of a first lead screw (206), the second movable sleeve plate (204) being threadedly connected to a first lead screw (206), the second movable sleeve plate (204) being slidably sleeved on the outer wall of a guide rod (207), and two second connecting rods (203) being symmetrically fixedly connected to the outer wall of the second movable sleeve plate (204), the two second connecting rods (203) penetrating the main body of the UAV (1) and being fixedly connected to the two forewings (4) respectively, and both second connecting rods (203) being slidably connected to the main body of the UAV (1); Another first lead screw (206) is provided with a second displacement component, which is used to drive the two rear wings (5) to move synchronously.

5. The combined-wing UAV structure capable of switching between a single wing and a tandem biplane as described in claim 4, characterized in that, The second displacement component includes: a first movable sleeve plate (202) sleeved on the outer wall of another first lead screw (206), the first movable sleeve plate (202) being threadedly connected to the other first lead screw (206), the first movable sleeve plate (202) being slidably sleeved on the outer wall of the guide rod (207), and two first connecting rods (201) being symmetrically fixedly connected to the outer wall of the first movable sleeve plate (202), the two first connecting rods (201) penetrating the main body of the UAV (1) and being fixedly connected to the two rear wings (5) respectively, and both first connecting rods (201) being slidably connected to the main body of the UAV (1).

6. The combined-wing UAV structure capable of switching between a single wing and a tandem biwing as described in claim 1, characterized in that, The stabilizing mechanism includes a second drive component disposed on the main body (1) of the drone; The second drive component includes: a dual-head motor (303) disposed inside the main body (1) of the UAV, the dual-head motor (303) being located below the first movable sleeve (202), the outer wall of the dual-head motor (303) being symmetrically fixedly connected to two support plates (304) by bolts, both of the support plates (304) being fixedly connected to the first movable sleeve (202), and two second lead screws (306) symmetrically disposed on the outer side of the dual-head motor (303), the two second lead screws (306) being fixedly connected to two output ends on the dual-head motor (303) respectively; The second lead screw (306) is provided with a moving component.

7. The combined-wing UAV structure capable of switching between a single wing and a tandem biplane as described in claim 6, characterized in that, The moving component includes: a sliding sleeve (305) sleeved on the outer wall of the second lead screw (306), the sliding sleeve (305) being threadedly connected to the second lead screw (306), the sliding sleeve (305) being slidably sleeved on the outer wall of the first connecting rod (201), and two limiting sliders (307) being symmetrically fixedly connected to the inner wall of the sliding sleeve (305), both of the limiting sliders (307) penetrating into the interior of the first connecting rod (201); The sliding sleeve (305) is provided with a locking component.

8. The combined-wing UAV structure capable of switching between a single wing and a tandem biplane as described in claim 7, characterized in that, The engaging assembly includes a movable insert rod (302) fixedly connected to one end of the sliding sleeve plate (305), the movable insert rod (302) being located at the end of the sliding sleeve plate (305) near the front wing (4), and a limit baffle (301) integrally formed on the outer wall of the end of the movable insert rod (302) away from the sliding sleeve plate (305).

9. A method of using a combined-wing unmanned aerial vehicle structure capable of switching between a single wing and a tandem biwing as described in any one of claims 1-8, characterized in that, Includes the following steps: Step 1: The front wing (4) and rear wing (5) can be moved by the connecting mechanism. At this time, the two front wings (4) slide along the outer walls of the two first guide plates (209) respectively, and the two rear wings (5) slide along the outer walls of the two first guide plates (209) and the two second guide plates (2010) respectively, until the two front wings (4) contact the outer walls of the two rear wings (5) respectively, so that the front wings (4) and rear wings (5) can be connected. Step 2: The first connecting rod (201) and the second connecting rod (203) can be fixedly connected by the stabilizing mechanism, thereby further improving the stability of the front wing (4) and the rear wing (5) during the assembly process; Step 3: The front wing (4) and rear wing (5) after being combined can be driven to move synchronously through the combination mechanism, so that the position of the front wing (4) and rear wing (5) after being combined can be conveniently adjusted according to actual needs.

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