A large unmanned aerial vehicle wing flip docking device and use method

Abstract

The invention discloses a large-scale unmanned aerial vehicle wing flip docking device and a use method thereof, and relates to the technical field of unmanned aerial vehicle transportation, and specifically comprises: a chassis assembly, comprising a chassis frame and omnidirectional wheels, wherein the omnidirectional wheels are fixedly mounted on the chassis frame; a flip assembly, comprising a support table, a linear guide rail and a connecting rod, wherein the linear guide rail is fixedly arranged coplanarly with the support table surface, a slider and a driving mechanism for driving the slider to move are arranged in the linear guide rail, a connecting rod is hinged in the slider, and a first hinge support is fixedly arranged on the extension line of the linear guide rail; the large-scale unmanned aerial vehicle wing flip docking device and the use method thereof adopt the method of adding a lifting assembly and a flip assembly to a movable chassis assembly, so that the wing can obtain the ability of flipping and height adjustment, thereby facilitating the docking of the fuselage and the wing.

Description

Technical Field

[0001] The present invention relates to the field of unmanned aerial vehicle transportation technology, and more specifically, to a large unmanned aerial vehicle wing flip docking device. In addition, the present invention also relates to a method for using the large unmanned aerial vehicle wing flip docking device. Background Art

[0002] Large UAV wings are usually transported with the leading edge facing down (vertical state). To dock the wing with the fuselage, the wing needs to be removed from the transport device and then flipped 90° to a horizontal state. The following methods are usually used to complete the flipping process:

[0003] 1. Use a crane to lift the root of the wing, and use manpower to support the other end. Then, through the cooperation of manpower and the crane, the wing is flipped to a horizontal state;

[0004] 2. Use a crane to lift the wing vertically from two locations on the wing, and also use manpower to flip it;

[0005] 3. Use a special hoist. This type of hoist can use a hand winch or motor to adjust the length of the hoist rope to gradually adjust the wing from a vertical state to a horizontal state.

[0006] The above flipping method mainly has the following inconveniences:

[0007] 1. Rely on more operators;

[0008] 2. The center of gravity is difficult to control during lifting;

[0009] 3. Flipping in the air is difficult to operate and time-consuming;

[0010] 4. After the flip is completed, the wing needs to be placed on the bracket for wing-body docking.

[0011] In summary, how to avoid the need for large lifting equipment and numerous operators during the docking process between the wing and the fuselage of the existing drone after transportation, and how to avoid the entire docking process being time-consuming and labor-intensive, is an urgent problem to be solved by technical personnel in this field. Summary of the invention

[0012] In view of this, the purpose of the present invention is to provide a large UAV wing flip docking device, which adopts the method of adding a lifting assembly and a flip assembly to a movable chassis assembly so that the wing can obtain the ability of flipping and height adjustment, thereby facilitating the docking of the fuselage and the wing.

[0013] Another object of the present invention is to provide a method for using the above-mentioned large UAV wing flip docking device, which reduces the dependence on lifting equipment and the number of operators during the docking and assembly process of the wings, making the docking process quick and simple.

[0014] In order to achieve the above object, the present invention provides the following technical solutions:

[0015] A large unmanned aerial vehicle wing flip docking device, comprising:

[0016] A chassis assembly, comprising a chassis frame and an omnidirectional wheel, wherein the omnidirectional wheel is fixedly mounted on the chassis frame;

[0017] A flip assembly, comprising a support table, a linear guide rail and a connecting rod, wherein the linear guide rail is fixedly arranged coplanarly with the support table surface, a slider and a driving mechanism for driving the slider to move are arranged in the linear guide rail, a connecting rod is hinged in the slider, a first hinge support is fixedly arranged on the extension line of the linear guide rail, and the connecting rod, the extension line of the linear guide rail and the connecting line of the free end of the connecting rod and the first hinge support form a triangle;

[0018] The lifting assembly has upper and lower ends fixedly connected to the chassis frame and the supporting table surface respectively.

[0019] Preferably, a parking mechanism is provided in the chassis assembly for stopping the movement of the chassis assembly.

[0020] Preferably, the parking mechanism comprises a vertically arranged parking foot, and the parking foot is connected to the chassis frame by threads.

[0021] Preferably, an adjusting hand wheel is fixedly provided at the upper end of the parking foot, and a supporting block is rotatably provided at the lower end.

[0022] Preferably, a sub-chassis frame is provided at one end of the chassis assembly close to the first hinge support, and the omnidirectional wheel is provided below the sub-chassis frame.

[0023] Preferably, a traction rod is provided at one end of the chassis assembly away from the first hinge support, and the traction rod is hinged to the chassis frame.

[0024] Preferably, the driving mechanism comprises a screw and a sleeve support;

[0025] The screw rod is arranged in parallel with the linear guide rail, and one end of the screw rod is coaxially slidably mounted with the sleeve support, and the other end is hinged with the connecting rod and the slider;

[0026] The sleeve support is fixedly connected to the support table, and a hand wheel is rotatably arranged in the sleeve support, and the hand wheel is connected to the screw rod through a threaded connection.

[0027] Preferably, the lifting assembly is a scissor-fork type lifting mechanism, and the telescopic rod in the lifting assembly is connected to a manual pump via an oil circuit, and the manual pump is fixedly mounted to the chassis assembly.

[0028] A method of use, applied to any one of the large UAV wing flip docking devices described above, the method of use comprising the following steps:

[0029] Dragging the chassis assembly to bring the large UAV wing flip docking device close to the transport bracket;

[0030] Adjust the lifting assembly so that the first hinge support is at the same height as the third hinge support on the lower side of the clamping frame in the transport bracket;

[0031] Adjust the driving mechanism and the connecting rod so that the height of the free end of the connecting rod is equal to the height of the second hinge support on the upper side of the clamping frame, and the vertical projection of the free end of the connecting rod overlaps with the first hinge support;

[0032] Using a pin shaft to hinge the first hinge support with the third hinge support, and hinge the free end of the connecting rod with the second hinge support;

[0033] Adjust the lifting assembly so that the flip assembly drives the wing to rise to a set height;

[0034] Adjusting the driving mechanism to move the slider toward a side away from the first hinge support until the wing flips to a set angle and stops;

[0035] Dragging the chassis assembly to bring the large UAV wing flip docking device close to the fuselage to be assembled;

[0036] The lifting assembly and the driving mechanism are adjusted to complete the position docking and assembly of the wing and the fuselage, and the clamping frame outside the wing is removed.

[0037] Compared with the prior art, the large-scale UAV wing flip docking device provided by the present invention has at least the following beneficial effects:

[0038] 1. By adding a lifting assembly to the chassis assembly, the height of the flip assembly in contact with the wing can be adjusted, so that it can be suitable for different wings or different transport brackets. When the wing is separated from the transport bracket, the wing can be separated from the top of the transport bracket with the help of the lifting assembly. When the wing is docked with the fuselage, the height of the wing can be adjusted conveniently, thereby solving the dependence on lifting equipment in the traditional wing docking process;

[0039] 2. By setting a flip assembly on the lifting assembly, the wing can be flipped after leaving the transport bracket, which is convenient for adjusting the angle of the wing. The adjustment process only requires the operation of the driving mechanism, and does not require the assistance of many operators, thereby reducing the number of operators and facilitating the improvement of the efficiency of docking and assembly between the wing and the fuselage.

[0040] The use method provided by the present invention is applied to the above-mentioned large-scale unmanned aerial vehicle wing flip docking device and has the same technical effect. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without paying creative work.

[0042] Figure 1 This is a schematic diagram of the structure of a specific large-scale UAV wing flip docking device provided by the present invention;

[0043] Figure 2 It is a structural schematic diagram of a specific chassis assembly provided by the present invention;

[0044] Figure 3 This is a schematic diagram of the structure of a specific lifting assembly provided by the present invention;

[0045] Figure 4 A schematic diagram of the structure of a specific flip assembly provided by the present invention;

[0046] Figure 5 A schematic diagram of the structure of a specific clamping frame provided by the present invention;

[0047] Figure 6 This is a schematic diagram of the combination of a specific large-scale UAV wing flip docking device and a clamping frame provided by the present invention;

[0048] Figure 7 A schematic diagram of the structure of a specific transport bracket provided by the present invention;

[0049] Figure 8 This is a schematic diagram of the combination of a specific large-scale UAV wing flip docking device and a transport bracket provided by the present invention;

[0050] Fig. 9 This is a schematic diagram of the working state of the specific large-scale UAV wing flip docking device provided by the present invention;

[0051] Fig.10 This is a schematic diagram of the state of the specific wing and fuselage provided by the present invention when docking;

[0052] Fig.11 This is a schematic diagram of the combination of the specific large-scale UAV wing flip docking device provided by the present invention and the wing in a vertical state;

[0053] Fig.12This is a schematic diagram of the wing angle adjustment process in the wing flip docking device of a specific large-scale unmanned aerial vehicle provided by the present invention.

[0054] Figure 1-Figure 12 middle:

[0055] 1. Chassis assembly; 101. Chassis frame; 102. Sub-chassis frame; 103. Parking feet; 104. Omnidirectional wheels; 105. Drawbar;

[0056] 2. Lifting assembly; 201. Telescopic rod; 202. Manual pump;

[0057] 3. Flip assembly; 301. Support table; 302. Screw; 303. Linear guide; 304. Slider; 305. Connecting rod; 306. First hinge support; 307. Hand wheel; 308. Sleeve support;

[0058] 4. Clamping frame; 401. Second hinge support; 402. Third hinge support; 5. Transport bracket; 6. Wing. DETAILED DESCRIPTION

[0059] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0060] The core of the present invention is to provide a large UAV wing flip docking device, which adopts the method of adding a lifting component and a flip component to a movable chassis component so that the wing can obtain the ability of flipping and height adjustment, thereby facilitating the docking of the fuselage and the wing.

[0061] Another core of the present invention is to provide a method for using the above-mentioned large UAV wing flip docking device, which reduces the dependence on lifting equipment and the number of operators during the docking and assembly process of the wings, making the docking process quick and simple.

[0062] Please refer to Figure 1-Figure 4 , a large unmanned aerial vehicle wing flip docking device, comprising:

[0063] The chassis assembly 1 includes a chassis frame 101 and an omnidirectional wheel 104, wherein the omnidirectional wheel 104 is fixedly mounted on the chassis frame 101;

[0064] The flip assembly 3 includes a support table 301, a linear guide 303 and a connecting rod 305. The linear guide 303 and the support table 301 are fixedly arranged in the same plane. A slider 304 and a driving mechanism for driving the slider 304 to move are arranged in the linear guide 303. The slider 304 is hinged with a connecting rod 305. A first hinge support 306 is fixedly arranged on the extension line of the linear guide 303. The connecting rod 305, the extension line of the linear guide 303 and the line connecting the free end of the connecting rod 305 and the first hinge support 306 form a triangle.

[0065] The lifting assembly 2 has upper and lower ends fixedly connected to the chassis frame 101 and the support table 301 respectively;

[0066] like Figure 1 and Figure 6 As shown, by setting the flip assembly 3, the first hinge support 306 in the flip assembly 3 and the free end of the connecting rod 305 are combined with the third hinge support 402 and the second hinge support 401 of the clamping frame 4, so that the wing 6 in the vertical state, the inclined state and the horizontal state can be supported by the flip docking device under the action of the clamping frame 4, and the angle of the wing 6 can be adjusted synchronously by changing the position of the lower end of the connecting rod 305 and adjusting the angle of the connecting rod 305, so as to facilitate the docking of the wing 6 and the fuselage, and in the whole process, the frame of the clamping frame 4, the supporting table 301 and the connecting rod 305 form a triangle with a stable supporting structure, which can ensure the stability of the wing 6 during the docking process and avoid the damage of the wing 6;

[0067] Moreover, when adjusting the angle of the wing 6, it is only necessary to adjust the driving mechanism, that is, the driving mechanism drives the slider 304 to move, that is, to change the length of one side of the triangle, and then change the angle of the inner angle of the triangle, so as to achieve the purpose of adjusting the angle of the wing 6. During the process, the operation is relatively simple, fewer operators are required, and no additional lifting tools are required, which is convenient for improving the convenience of operation.

[0068] At the same time, the lifting assembly 2 is integrated to adjust the height of the flip assembly 3, so that the flip assembly 3 can be suitable for wings 6 of different sizes and transport brackets 5 of different sizes, thereby improving the versatility of the equipment. When separating the wing 6 from the transport bracket 5, only the height of the lifting assembly 2 needs to be adjusted to separate the two, without the need for additional lifting tools, which helps to simplify the operation process.

[0069] Furthermore, an omnidirectional wheel 104 is integrated in the chassis assembly 1, so that the chassis assembly 1 has the ability to move, which is convenient for the close-range transfer of the wing 6 and for the position adjustment of the wing 6 and the fuselage during the assembly process;

[0070] like Figure 8 and Fig. 9As shown, when the wing 6 is separated from the transport bracket 5, two sets of flip docking devices are used to combine with the clamping frames 4 at different positions of the wing 6, so as to support the wing 6 in the form of a simply supported beam, thereby ensuring the support stability of the wing 6 during the transfer process, and when adjusting the height and angle of the wing 6, the two sets of flip docking devices need to be operated simultaneously to avoid bending or twisting of the wing 6.

[0071] In some embodiments, a parking mechanism is provided in the chassis assembly 1 to stop the chassis assembly 1 from moving;

[0072] like Figure 1 and Figure 2 As shown, a parking mechanism is integrated in the chassis assembly 1, so that the flip docking device has good stability in a stationary state. For example, when the wing 6 is separated from the transport bracket 5, the chassis assembly 1 is ensured to be always in a stationary state to avoid bending or twisting of the wing 6 caused by asynchronous movement of the two sets of flip docking devices during the process.

[0073] In some embodiments, the parking mechanism includes a vertically arranged parking foot 103, and the parking foot 103 is connected to the chassis frame 101 by threads;

[0074] like Figure 2 As shown, the parking foot 103 adopts a stud structure and is connected to the chassis frame 101 through a threaded connection. The parking foot 103 is rotated to change the relative position of the parking foot 103 and the chassis frame 101 in the vertical direction, thereby reducing the positive pressure between the omnidirectional wheel 104 and the ground and improving the stability of the chassis frame 101;

[0075] The parking foot 103 is connected to the chassis frame 101 by threaded connection, and the adjustment method thereof is simple and convenient, and is suitable for quick operation.

[0076] In some embodiments, the upper end of the parking foot 103 is fixedly provided with an adjustment hand wheel, and the lower end is rotatably provided with a support block;

[0077] like Figure 2 As shown, an adjusting hand wheel is provided above the parking foot 103 to facilitate manual rotation of the parking foot 103, and a support block is rotatably provided below the parking foot 103 to increase the contact area between the parking foot 103 and the ground, thereby preventing the parking foot 103 from sinking into the ground and improving the applicability of different venues.

[0078] In some embodiments, a sub-chassis frame 102 is disposed at one end of the chassis assembly 1 close to the first hinge support 306, and an omnidirectional wheel 104 is disposed below the sub-chassis frame 102;

[0079] like Figure 2As shown, a sub-chassis frame 102 is provided at one end of the chassis assembly 1, and an omnidirectional wheel 104 is provided for support, thereby expanding the area of ​​the chassis assembly 1, so that after the flip docking device receives the wing 6, the center of gravity is within the vertical projection area of ​​the chassis assembly 1, and during the entire process of flipping and adjusting the wing 6, the overall center of gravity of the device is always within the vertical projection area of ​​the chassis assembly 1, thereby avoiding the overturning problem of the flip docking device caused by the change of the center of gravity position during the flipping of the wing 6.

[0080] In some embodiments, a traction rod 105 is disposed at one end of the chassis assembly 1 away from the first hinge support 306 , and the traction rod 105 is hinged to the chassis frame 101 .

[0081] like Figure 2 As shown, a traction rod 105 is provided in the chassis assembly 1, and the traction rod 105 is preferably hinged to the chassis frame 101 by a spherical hinge, so that the traction rod 105 can obtain a variety of rotation angles, which is convenient for the operator to tow the flip docking mechanism from a variety of angles.

[0082] In some embodiments, the drive mechanism includes a screw 302 and a sleeve support 308;

[0083] The screw rod 302 is arranged in parallel with the linear guide rail 303, and one end of the screw rod 302 is coaxially slidably mounted with the sleeve support 308, and the other end is hinged with the connecting rod 305 and the slider 304;

[0084] The sleeve support 308 is fixedly connected to the support table 301, and a hand wheel 307 is rotatably arranged in the sleeve support 308, and the hand wheel 307 is connected to the screw rod 302 through a threaded connection;

[0085] like Figure 4 As shown, by setting a linear guide rail 303 and a slider 304, the linearity of the movement of the fixed end of the connecting rod 305 is ensured, and the connecting rod 305 is first hinged with the screw rod 302, and then the screw rod 302 and the slider 304 are connected, which can effectively avoid the bending of the screw rod 302 caused by the force;

[0086] Moreover, by adding a sleeve support 308, the jumping degree of the screw 302 is guaranteed, and a hand wheel 307 is added and connected to the screw 302 through a thread. By rotating the hand wheel 307, the screw 302 can be axially displaced, thereby driving the slider 304 to move, that is, driving the connecting rod 305 to adjust the angle, and then driving the wing 6 to adjust the angle.

[0087] In some embodiments, the lifting assembly 2 uses a hydraulic lifting platform or a screw lifting platform, both of which can adjust the height of the flip assembly 3;

[0088] In some embodiments, the lifting assembly 2 is a scissor-fork type lifting mechanism, and the telescopic rod 201 in the lifting assembly 2 is connected to a manual pump 202 through an oil circuit, and the manual pump 202 is fixedly installed with the chassis assembly 1;

[0089] like Figure 3 As shown, the scissor-fork lifting mechanism is used to help improve the stability of the lifting assembly 2, and the pressure and length of the telescopic rod 201 are adjusted by a manual pump 202, thereby achieving height adjustment of the lifting assembly 2 without the need for external equipment, thereby improving the applicability of different scenarios;

[0090] In some embodiments, the telescopic rod 201 uses an oil cylinder connected to an external high-pressure hydraulic oil supply device, or uses an air cylinder connected to an external high-pressure air source, which also falls within the protection scope of the present application.

[0091] In addition to the large unmanned aerial vehicle wing flip docking device disclosed in the above embodiments, the present invention also provides a method for using the large unmanned aerial vehicle wing flip docking device, such as Figure 5-Figure 12 As shown, the method of use includes the following steps:

[0092] Drag the chassis assembly 1 to make the large UAV wing flip docking device close to the transport bracket 5;

[0093] Adjust the lifting assembly 2 so that the first hinge support 306 and the third hinge support 402 on the lower side of the clamping frame 4 in the transport bracket 5 are at the same height;

[0094] Adjust the driving mechanism and the connecting rod 305 so that the height of the free end of the connecting rod 305 is equal to the height of the second hinge support 401 on the upper side of the clamping frame 4, and the vertical projection of the free end of the connecting rod 305 overlaps with the first hinge support 306;

[0095] The first hinge support 306 is hinged to the third hinge support 402 by using a pin, and the free end of the connecting rod 305 is hinged to the second hinge support 401;

[0096] Adjust the lifting assembly 2 so that the flip assembly 3 drives the wing 6 to rise to a set height;

[0097] Adjust the driving mechanism to make the slider 304 move to the side away from the first hinge support 306 until the wing 6 flips to a set angle and stops;

[0098] Drag the chassis assembly 1 to make the large UAV wing flip docking device close to the fuselage to be assembled;

[0099] The lifting assembly 2 and the driving mechanism are adjusted to complete the docking and assembly of the wing 6 and the fuselage, and the clamping frame 4 outside the wing 6 is removed.

[0100] like Figure 7, two groups of movable clamping frames 4 are arranged in the transport bracket 5, and a group of fixed clamping frames 4 is arranged between the two groups of movable clamping frames 4;

[0101] When transferring, if Figure 8 As shown, two sets of flip docking devices are used to respectively combine with two sets of movable clamping frames 4, and the combination method is as follows Figure 6 As shown, the first hinge support 306 is combined with the third hinge support 402, and the free end of the connecting rod 305 is combined with the second hinge support 401;

[0102] Then adjust the lifting assembly 2 to separate the wing 6 from the transport bracket 5, and then drag the chassis assembly 1 to keep the wing 6 away from the transport bracket 5. Fig. 9 As shown;

[0103] Then, the wing 6 is moved to the vicinity of the fuselage, and the angle of the wing 6 is adjusted. The process is as follows. Fig.11 and Fig.12 As shown, after the wing 6 is adjusted to the specified angle, it docks with the fuselage. Fig.10 shown.

[0104] The various embodiments in this specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referenced to each other.

[0105] The above is a detailed introduction to the large UAV wing flip docking device and the method of use provided by the present invention. This article uses specific examples to illustrate the principles and implementation methods of the present invention. The description of the above embodiments is only used to help understand the method of the present invention and its core idea. It should be pointed out that for ordinary technicians in this technical field, without departing from the principles of the present invention, the present invention can also be improved and modified, and these improvements and modifications also fall within the scope of protection of the claims of the present invention.

Claims

1. A method for using a large-scale UAV wing flip docking device, characterized in that: Applicable to a large unmanned aerial vehicle wing flip docking device, the large unmanned aerial vehicle wing flip docking device comprises: A chassis assembly (1) comprises a chassis frame (101) and an omnidirectional wheel (104), wherein the omnidirectional wheel (104) is fixedly mounted on the chassis frame (101); A flip assembly (3), comprising a support table (301), a linear guide rail (303) and a connecting rod (305), wherein the linear guide rail (303) and the support table (301) are coplanarly arranged and fixed, a slider (304) and a driving mechanism for driving the slider (304) to move are arranged in the linear guide rail (303), a connecting rod (305) is hinged in the slider (304), a first hinge support (306) is fixedly arranged on the extension line of the linear guide rail (303), and a line connecting the connecting rod (305), the extension line of the linear guide rail (303), and the free end of the connecting rod (305) and the first hinge support (306) form a triangle; A lifting assembly (2), the upper and lower ends of which are respectively fixedly connected to the chassis frame (101) and the supporting table (301); The method of use comprises the following steps: Dragging the chassis assembly (1) so that the large UAV wing flip docking device is close to the transport bracket (5); Adjusting the lifting assembly (2) so that the first hinge support (306) and the third hinge support (402) on the lower side of the clamping frame (4) in the transport bracket (5) are at the same height; Adjusting the driving mechanism and the connecting rod (305) so that the height of the free end of the connecting rod (305) is equal to the height of the second hinge support (401) on the upper side of the clamping frame (4), and the vertical projection of the free end of the connecting rod (305) overlaps with the first hinge support (306); Using a pin shaft to hinge the first hinge support (306) with the third hinge support (402), and hinge the free end of the connecting rod (305) with the second hinge support (401); Adjusting the lifting assembly (2) so that the flip assembly (3) drives the wing (6) to rise to a set height; Adjusting the driving mechanism so that the sliding block (304) moves toward a side away from the first hinge support (306) until the wing (6) flips over to a set angle and stops; Dragging the chassis assembly (1) to bring the large UAV wing flip docking device closer to the fuselage to be assembled; The lifting assembly (2) and the driving mechanism are adjusted to complete the docking and assembly of the wing (6) and the fuselage, and the clamping frame (4) outside the wing (6) is removed.

2. The method for using the large-scale UAV wing flip docking device according to claim 1 is characterized in that: A parking mechanism is provided in the chassis assembly (1) for stopping the movement of the chassis assembly (1).

3. The method for using the large-scale UAV wing flip docking device according to claim 2 is characterized in that: The parking mechanism comprises a vertically arranged parking foot (103), and the parking foot (103) is connected to the chassis frame (101) via threads.

4. The method for using the large-scale UAV wing flip docking device according to claim 3 is characterized in that: An adjusting hand wheel is fixedly arranged at the upper end of the parking foot (103), and a supporting block is rotatably arranged at the lower end.

5. The method for using the large-scale UAV wing flip docking device according to claim 1 is characterized in that: A sub-chassis frame (102) is provided at one end of the chassis assembly (1) close to the first hinge support (306), and the omnidirectional wheel (104) is provided below the sub-chassis frame (102).

6. The method for using the large-scale UAV wing flip docking device according to claim 1, characterized in that: A traction rod (105) is provided at one end of the chassis assembly (1) away from the first hinge support (306), and the traction rod (105) is hinged to the chassis frame (101).

7. The method for using the large-scale UAV wing flip docking device according to claim 1 is characterized in that: The driving mechanism comprises a screw rod (302) and a sleeve support (308); The screw rod (302) is arranged in parallel with the linear guide rail (303), and one end of the screw rod (302) is coaxially slidably mounted with the sleeve support (308), and the other end is hinged with the connecting rod (305) and the slider (304); The sleeve support (308) is fixedly connected to the support table (301), and a hand wheel (307) is rotatably arranged in the sleeve support (308), and the hand wheel (307) is connected to the screw rod (302) via a threaded connection.

8. The method for using the large-scale UAV wing flip docking device according to claim 1, characterized in that: The lifting assembly (2) is a scissor-fork type lifting mechanism, and the telescopic rod (201) in the lifting assembly (2) is connected to a manual pump (202) via an oil circuit, and the manual pump (202) is fixedly mounted on the chassis assembly (1).

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