Homing, clamping and lifting mechanism for heavy-load unmanned aerial vehicle

Abstract

The invention discloses a homing, clamping and lifting mechanism for a heavy-load unmanned aerial vehicle, relates to the technical field of unmanned aerial vehicle take-off and landing equipment, and solves the problems that existing equipment is low in homing precision, poor in clamping stability and insufficient in lifting synchronism. The device comprises a homing assembly, a clamping assembly and a lifting assembly, the homing assembly is installed on the upper portion of the lifting assembly, and the unmanned aerial vehicle is guided to be accurately homed in multiple directions through a longitudinal and transverse homing device, a driving motor and a belt; the clamping assembly comprises four sets of fixing devices, a motor is matched with a speed reducer to drive a buckle plate, and the unmanned aerial vehicle undercarriage is locked in multiple directions. The lifting assembly drives the lifting rod to synchronously drive the returning and clamping assembly to ascend and descend through the driving motor, the steering gear and the transmission shaft, and the drag chain protects the cable. The mechanism realizes integrated automatic operation of returning, clamping and lifting, improves the taking-off and landing safety and efficiency of the heavy-load unmanned aerial vehicle, and is suitable for the scenes of logistics transportation, emergency rescue and the like.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) take-off and landing equipment technology, and specifically to a return-to-position clamping and lifting mechanism for heavy-duty UAVs. Background Technology

[0002] With the rapid development of drone technology, its application scenarios have expanded from traditional aerial photography and surveying to logistics transportation, emergency rescue, power line inspection and other fields. Among them, heavy-duty drones, which can carry more materials and equipment, are in high demand in scenarios such as material delivery and emergency rescue material transportation.

[0003] However, existing drone take-off and landing equipment is ill-suited to the efficient and safe take-off and landing requirements of heavy-payload drones, mainly due to three core problems: First, low positioning accuracy. Most equipment relies solely on simple visual guidance or manual assistance for positioning, failing to provide precise multi-dimensional guidance for the drone, which can easily lead to docking deviation and affect subsequent operations. Second, poor clamping stability. Existing clamping structures are mostly designed for light and small drones, with insufficient clamping force and a single fixing point. Heavy-payload drones are prone to displacement due to vibration or external forces after docking, potentially posing safety risks. Third, insufficient lifting synchronization. Lifting mechanisms often employ single-sided drive or simple transmission structures, which are prone to tilting during lifting, making it impossible to ensure smooth lifting and lowering of heavy-payload drones.

[0004] The aforementioned problems make it difficult for existing equipment to achieve coordinated operation of positioning, clamping, and lifting functions, and cannot meet the full-process automated take-off and landing requirements of heavy-payload drones. Therefore, there is an urgent need for an integrated mechanism that integrates positioning, clamping, and lifting functions to improve the safety and efficiency of take-off and landing of heavy-payload drones. Summary of the Invention

[0005] To address these issues, the present invention provides a high-payload unmanned aerial vehicle (UAV) return and clamping lifting mechanism.

[0006] To achieve the above objectives, the present invention provides the following technical solution:

[0007] A high-payload drone return and clamping lifting mechanism includes a return component, a clamping component, and a lifting component. The return component and the clamping component are both mounted on the upper part of the lifting component. The return component is used to guide the drone to move towards a designated docking point gradually and precisely from multiple directions when the drone approaches the mechanism. The clamping component is used to clamp and lock the high-payload drone after it has returned to its position. The lifting component is used to smoothly drive the drone to rise and fall according to the needs of the operation scenario, so as to automate and integrate the entire process of the drone from approach to take-off and landing.

[0008] Furthermore, the repositioning component includes a lifting seat installed on the lifting end of the lifting component, and also includes a first repositioning device and a second repositioning device respectively arranged along its longitudinal and transverse directions, wherein the first repositioning device and the second repositioning device each have two opposing drive ends.

[0009] Furthermore, both the first and second repositioning devices include a repositioning drive motor mounted on the top of the lifting seat, first bearing seats symmetrically mounted on the top of the lifting seat, and a first transmission shaft rotatably connected between the first bearing seats. The drive end of the repositioning drive motor is driven by an active belt assembly, and the first bearing seats arranged laterally along the repositioning assembly are driven by a driven belt assembly. The driven belt assembly has two opposing drive ends. One drive end is connected to the first push rod through a first linkage, and the other drive end is connected to the second push rod through a second linkage, so as to drive the first push rod and the second push rod to move closer or further away.

[0010] Furthermore, both the active belt assembly and the driven belt assembly include synchronous pulleys mounted on the active end and the driven end, and a synchronous belt connected between the synchronous pulleys.

[0011] Furthermore, the first linkage is connected to the upper half of the synchronous belt, and the second linkage is connected to the lower half of the synchronous belt, so as to drive the first linkage and the second linkage to move closer or further away.

[0012] Furthermore, the first push rod, the second push rod, and the lifting seat are all slidably connected by linear guide rails set in the extension length direction.

[0013] Furthermore, the clamping assembly includes a base plate mounted on the top of the lifting seat, and a first fixing device, a second fixing device, a third fixing device and a fourth fixing device are respectively mounted on the top of the base plate. The first fixing device, the second fixing device, the third fixing device and the fourth fixing device are used to clamp and lock the landing gear of the UAV from four directions.

[0014] Furthermore, the first, second, third, and fourth fixing devices each include a second bearing housing, a clamping drive motor, and a reducer mounted on the top of the lifting seat. A second transmission shaft is rotatably connected inside the second bearing housing. The drive end of the clamping drive motor is connected to the power input end of the reducer. The power output end of the reducer is connected to the second transmission shaft via a clamping belt drive assembly. Both ends of the second transmission shaft extend to the side of the second bearing housing and are each equipped with clamping buckles to drive the clamping buckles to reciprocate and rotate, locking and unlocking the drone's landing gear.

[0015] Furthermore, the lifting assembly includes a base, a lifting drive motor is mounted on the top of the base, and several steering gears are symmetrically mounted on the top of the base. The lifting drive motor and the steering gears, as well as each adjacent steering gear, are all connected by a third transmission shaft. The power output end of each steering gear is connected to a lifting rod.

[0016] Furthermore, the external part of the lifting rod is threadedly connected to the lifting seat to drive the return assembly and the clamping assembly to lift synchronously. The side of the base is also provided with a drag chain to protect the cable during the lifting process.

[0017] The present invention has the following advantages:

[0018] 1. Through the coordinated operation of longitudinal and lateral dual-dimensional positioning devices, the positioning drive motor, in conjunction with the active and driven belt kits, precisely transmits power, driving the push rod to move smoothly along the linear guide rail, gradually calibrating the drone's position from multiple directions. Compared to traditional positioning methods that rely solely on vision or manual assistance, this improves positioning accuracy from centimeter-level to millimeter-level, ensuring consistent positioning for each takeoff and landing, and providing a stable foundation for subsequent automated operations of heavy-load drones;

[0019] 2. Four sets of fixing devices are arranged in a rectangular pattern. Each set is powered by a clamping drive motor and reducer to drive the clamping plates to lock the UAV landing gear in multiple directions. This structure can not only withstand the weight of the UAV itself and the impact of operation, but also evenly distribute the locking force to avoid local stress concentration on the landing gear. During UAV docking, fixing, and battery swapping operations, it effectively reduces the risk of structural damage and improves operational safety.

[0020] 3. The lifting assembly utilizes a lifting drive motor combined with a steering gear and a third drive shaft to construct a synchronous transmission system, ensuring that multiple lifting rods rotate synchronously. The threaded connection between the lifting rods and the lifting seat, along with bearing guidance, guarantees the linear accuracy of the lifting motion, while the cable chain synchronously protects the cables. The lifting accuracy can reach 1mm, effectively preventing tilting during the lifting of heavy-load drones. It is suitable for complex scenarios such as multi-level takeoff and landing and high-altitude deployment, significantly improving the overall reliability and applicability of the equipment. Attached Figure Description

[0021] To more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings in the following description are merely exemplary, and those skilled in the art can derive other embodiments based on the provided drawings without creative effort.

[0022] The structures, proportions, sizes, etc. illustrated in this specification are only for the purpose of assisting those skilled in the art in understanding and reading the content disclosed herein, and are not intended to limit the conditions under which the present invention can be implemented. Therefore, they have no substantial technical significance. Any modifications to the structure, changes in the proportions, or adjustments to the size, without affecting the effects and objectives that the present invention can produce, should still fall within the scope of the technical content disclosed in the present invention.

[0023] Figure 1 This is a perspective view of a high-payload unmanned aerial vehicle (UAV) return clamping and lifting mechanism according to the present invention.

[0024] Figure 2 This is a perspective view of the return component in the return clamping and lifting mechanism for a heavy-duty unmanned aerial vehicle (UAV) according to the present invention.

[0025] Figure 3 This is a perspective view of the clamping component in a high-payload drone return clamping and lifting mechanism of the present invention.

[0026] Figure 4 This is a perspective view of the lifting component in the return clamping lifting mechanism for a heavy-duty UAV according to the present invention.

[0027] In the diagram: 1. Return assembly; 11. Lifting seat; 12. First return device; 121. Return drive motor; 122. First transmission shaft; 123. First bearing housing; 124. Drive belt assembly; 125. Driven belt assembly; 1251. Synchronous pulley; 1252. Synchronous belt; 126. First linkage component; 127. Second linkage component; 128. First push rod; 129. Second push rod; 1210. Linear guide rail; 13. Second return device; 2. Clamping assembly; 21 1. Base plate; 22. First fixing device; 221. Second bearing seat; 222. Clamping drive motor; 223. Reducer; 224. Second transmission shaft; 225. Clamping belt drive assembly; 226. Clamping buckle plate; 23. Second fixing device; 24. Third fixing device; 25. Fourth fixing device; 3. Lifting assembly; 31. Base; 32. Lifting drive motor; 33. Third transmission shaft; 34. Steering gear; 35. Lifting rod; 36. Third bearing seat; 37. Cable chain. Detailed Implementation

[0028] The following specific embodiments illustrate the implementation of the present invention. Those skilled in the art can easily understand other advantages and effects of the present invention from the content disclosed in this specification. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0029] like Figures 1 to 4 As shown, a lifting and clamping mechanism for a heavy-load UAV, as described in the first aspect of this invention, includes a lifting assembly 3. A return assembly 1 and a clamping assembly 2 are both mounted on the upper part of the lifting assembly 3. The three components work together to automate the entire process of the UAV from approach, return, fixation to lifting, and so on. This mechanism is suitable for take-off and landing operations of heavy-load UAVs. The specific technical solution is as follows:

[0030] The lifting assembly 3 consists of a base 31, a lifting drive motor 32, a third transmission shaft 33, a steering mechanism 34, a lifting rod 35, a third bearing seat 36, and a drag chain 37. The base 31 is a flat structure made of high-strength alloy material to ensure that it has sufficient load-bearing capacity to support the weight of the heavy-duty UAV and other components. The lifting drive motor 32 is fixedly installed at the middle position of the top of the base 31. It is a high-torque servo motor that can provide stable and precise power output. Several steering mechanisms 34 are also symmetrically installed at the top of the base 31. The third bearing seat 36 is provided on the outside of the steering mechanism 34 to enhance the stability of the third transmission shaft 33 during transmission.

[0031] The lifting drive motor 32 and the steering gear 34, as well as two adjacent steering gears 34, are rigidly connected and transmitted through a third drive shaft 33. The third drive shaft 33 is made of high-precision seamless steel pipe and its surface is heat-treated to ensure that there is no obvious deformation or vibration during transmission. Each steering gear 34 has a lifting rod 35 vertically connected to its power output end. The lifting rod 35 is a ball screw structure, and its top end is threaded to the bottom of the lifting seat 11 of the return assembly. The connection points of multiple lifting rods 35 and the lifting seat 11 are symmetrically distributed.

[0032] A drag chain 37 is also fixedly installed on the side of the base 31. The power supply cable, control cable and sensor signal line of the positioning component 1 and the clamping component 2 are threaded inside the drag chain 37. When the lifting component drives the lifting seat 11 to move up and down, the drag chain 37 will extend, retract and bend synchronously to avoid damage to the cables due to pulling and tangling, and to ensure the stability of the circuit connection of each component.

[0033] When the lifting assembly 3 is working, after the lifting drive motor 32 starts, the rotational power of its output shaft is transmitted to each steering gear 34 through the third transmission shaft 33. The steering gear 34 converts the horizontal rotational power into the vertical rotational power, driving the lifting rod 35 to rotate synchronously. Since the lifting rod 35 is threadedly connected to the lifting seat 11, and the lifting seat 11 cannot rotate with the linear guide rail 1210 in the return assembly, the rotational motion of the lifting rod 35 is converted into the vertical lifting motion of the lifting seat 11, thereby driving the return assembly 1 and the clamping assembly 2 installed on the lifting seat 11 to lift synchronously and smoothly. According to the requirements of the operation scenario, by controlling the forward and reverse rotation and speed of the lifting drive motor 32, the lifting height and lifting speed of the lifting seat 11 can be precisely adjusted to meet the height adaptation requirements of different lifting environments.

[0034] The return assembly 1 is used to guide the drone to accurately dock at a designated position. Specifically, it consists of a lifting base 11, a first return device 12, a second return device 13, a return drive motor 121, a first transmission shaft 122, a first bearing seat 123, an active belt assembly 124, a driven belt assembly 125, a first linkage component 126, a second linkage component 127, a first push rod 128, a second push rod 129, and a linear guide rail 1210.

[0035] The lifting seat 11 is a rectangular frame structure. Its bottom is threaded to the lifting rod 35 of the lifting assembly. The top plane is milled to ensure the flatness of the mounting surface. The first returning device 12 and the second returning device 13 are symmetrically arranged along the longitudinal and transverse directions of the lifting seat 11, respectively. The two have the same structure and both have two opposing drive ends, which can guide the UAV to return to its position from both longitudinal and transverse dimensions.

[0036] Taking the first positioning device 12 as an example, its positioning drive motor 121 is fixedly installed on one side of the top of the lifting seat 11. The first bearing seats 123 are in a group of two and are symmetrically fixed at both ends of the top of the lifting seat 11. The first transmission shaft 122 is transversely inserted into the interior of the two first bearing seats 123 and is rotatably connected to the first bearing seats 123 through the bearings, ensuring that the first transmission shaft 122 rotates smoothly without jamming.

[0037] The drive end of the return drive motor 121 is connected to one end of the first transmission shaft 122 via a drive belt assembly 124. The drive belt assembly 124 includes two synchronous pulleys 1251 and a synchronous belt 1252. One synchronous pulley 1251 is fixedly sleeved on the output shaft of the return drive motor 121, and the other synchronous pulley 1251 is fixedly sleeved on the end of the first transmission shaft 122. The synchronous belt 1252 is tensioned and sleeved between the two synchronous pulleys 1251. A polyurethane synchronous belt is used, which has high transmission accuracy and low noise.

[0038] The two first bearing seats 123 arranged laterally along the return assembly 1 are also connected by a driven belt assembly 125. The driven belt assembly 125 is also composed of two synchronous pulleys 1251 and a synchronous belt 1252. The two synchronous pulleys 1251 are respectively fixedly sleeved on two parallel first drive shafts 122. The synchronous belt 1252 is tensioned to connect the two synchronous pulleys 1251, so as to realize the synchronous rotation of the two first drive shafts 122.

[0039] The driven belt assembly 125 has two opposing drive ends on the timing belt 1252. One drive end is fixedly connected to one end of the first linkage 126 by bolts, and the other end of the first linkage 126 is vertically fixed to the bottom of the first push rod 128. The other drive end is fixedly connected to one end of the second linkage 127 by bolts, and the other end of the second linkage 127 is vertically fixed to the bottom of the second push rod 129. The first linkage 126 is connected to the upper half of the timing belt 1252, and the second linkage 127 is connected to the lower half of the timing belt 1252. This connection method allows the first linkage and the second linkage to move in opposite directions when the timing belt 1252 moves.

[0040] Both the first push rod 128 and the second push rod 129 are elongated structures with an arc-shaped guide surface at their top. The guide surface is covered with a wear-resistant rubber pad to prevent rigid collisions with the UAV landing gear. The first push rod 128 and the second push rod 129 are slidably connected to the lifting seat 11 through a linear guide rail 1210 that is set along the length direction. The slide rail of the linear guide rail 1210 is fixed at the top of the lifting seat 11, and the slider is fixed to the bottom of the push rod to ensure that the push rod moves smoothly along a straight line during the movement without deviation or jamming.

[0041] When the drone approaches the mechanism, the return drive motor 121 starts, driving the first drive shaft 122 to rotate via the active belt assembly 124. The first drive shaft 122 then drives another first drive shaft 122 to rotate synchronously via the driven belt assembly 125. At this time, the synchronous belt 1252 of the driven belt assembly 125 moves, causing the first linkage 126 and the second linkage 127 to move closer or further apart, thereby driving the first push rod 128 and the second push rod 129 to move relative to or towards each other along the linear guide rail 1210. The longitudinally arranged first return device 12 and the laterally arranged second return device 13 work together to gradually narrow the guidance range from the front, back, left, and right directions, accurately guiding the drone to the designated docking point at the top of the lifting seat 11, completing the return action.

[0042] The clamping assembly 2 is used to lock and fix the UAV after it returns to its position to prevent it from shifting or tipping over during the lifting and lowering process. Specifically, it consists of a base plate 21, a first fixing device 22, a second fixing device 23, a third fixing device 24, and a fourth fixing device 25. The first fixing device 22, the second fixing device 23, the third fixing device 24, and the fourth fixing device 25 have completely identical structures and are distributed in a rectangle at the top of the base plate 21, corresponding to the four support points of the UAV landing gear.

[0043] The base plate 21 is a rectangular steel plate, which is fixedly installed on the top of the lifting seat 11 and located inside the push rod of the return component 1. Multiple mounting holes are opened on its surface for fixing various fixing devices. Taking the first fixing device 22 as an example, its second bearing seat 221 is a group of two, symmetrically fixed on both sides of the top of the base plate 21. A high-precision bearing is installed inside the second bearing seat 221 to support the rotation of the second drive shaft 224.

[0044] The clamping drive motor 222 and the reducer 223 are fixedly installed on one side of the top of the base plate 21. The clamping drive motor 222 is a low-speed, high-torque motor, and the reducer 223 is a planetary gear reducer. The two are fixedly connected by a flange. The drive end of the clamping drive motor 222 and the power input end of the reducer 223 are rigidly connected by a coupling to ensure lossless power transmission.

[0045] The power output end of the reducer 223 is connected to the second transmission shaft 224 via a clamping belt drive assembly 225. The clamping belt drive assembly 225 consists of a synchronous pulley and a synchronous belt. The synchronous pulleys are fixed to one end of the output shaft of the reducer 223 and one end of the second transmission shaft 224, respectively. The synchronous belt is tensioned between the two synchronous pulleys to ensure the synchronicity and stability of the transmission.

[0046] The second drive shaft 224 is transversely inserted inside the two second bearing seats 221, with both ends extending to the outside of the second bearing seats 221. The extended ends are fixedly connected to the clamping plate 226 by a flat key. The clamping plate 226 has an L-shaped structure, and its clamping surface is provided with anti-slip texture and is attached with an elastic rubber pad. This can enhance the friction with the UAV landing gear and also play a buffering role to avoid damage to the landing gear.

[0047] Once the drone accurately docks at the designated position via the return assembly 1, the four fixing devices activate simultaneously. The clamping drive motor 222 outputs power, which is reduced and increased in torque by the reducer 223. This power is then transmitted through the clamping belt drive assembly 225 to rotate the second drive shaft 224. The second drive shaft 224 causes the clamping plates 226 at both ends to rotate synchronously until the clamping surfaces of the clamping plates 226 are tightly fitted with the sides and top of the drone's landing gear. This clamps and locks the landing gear from four directions, securing the drone. When unlocking is required, the clamping drive motor 222 rotates in the opposite direction, causing the clamping plates 226 to reset and rotate, disengaging from the landing gear and completing the unlocking action, facilitating the drone's takeoff.

[0048] Although the present invention has been described in detail above with general descriptions and specific embodiments, modifications or improvements can be made to it, which will be obvious to those skilled in the art. Therefore, all such modifications or improvements made without departing from the spirit of the present invention fall within the scope of protection claimed by the present invention.

[0049] The terms such as "upper," "lower," "left," "right," and "middle" used in this specification are merely for clarity of description and are not intended to limit the scope of the invention. Any changes or adjustments to their relative relationships, without substantially altering the technical content, should also be considered within the scope of the invention.

Claims

1. A large-load unmanned aerial vehicle homing clamping lifting mechanism, characterized in that, It comprises a homing assembly (1), a clamping assembly (2) and a lifting assembly (3); The homing assembly (1) comprises a lifting seat (11) installed on the lifting end of the lifting assembly (3), a first homing device (12) arranged along the longitudinal direction and a second homing device (13) arranged along the transverse direction, and the first homing device (12) and the second homing device (13) each have two opposite driving ends; The first homing device (12) and the second homing device (13) each comprise a homing drive motor (121) installed on the top end of the lifting seat (11), a first bearing seat (123) symmetrically installed on the top end of the lifting seat (11), and a first transmission shaft (122) rotatably connected between the first bearing seat (123), the driving end of the homing drive motor (121) is driven by a driving belt set (124), the first bearing seat (123) arranged along the transverse direction of the homing assembly (1) is driven by a driven belt set (125), the driven belt set (125) has two opposite driving ends, one driving end is connected with a first push rod (128) through a first linkage (126), and the other driving end is connected with a second push rod (129) through a second linkage (127), so as to drive the first push rod (128) and the second push rod (129) to approach or move away. The clamping assembly (2) is used for clamping and locking the unmanned aerial vehicle after homing, and the lifting assembly (3) is used for driving the unmanned aerial vehicle to lift; wherein the homing assembly (1) and the clamping assembly (2) are installed on the upper part of the lifting assembly (3).

2. The homing clamping and lifting mechanism for heavy load unmanned aerial vehicle according to claim 1, characterized in that, The driving belt set (124) and the driven belt set (125) each comprise a synchronous wheel (1251) installed on the driving end and the driven end, and a synchronous belt (1252) connected between the synchronous wheels (1251).

3. The large-load unmanned aerial vehicle homing clamping lifting mechanism according to claim 2, characterized in that, The first linkage (126) is connected with the upper half of the synchronous belt (1252), and the second linkage (127) is connected with the lower half of the synchronous belt (1252), so as to drive the first linkage (126) and the second linkage (127) to approach or move away.

4. The large-load unmanned aerial vehicle homing clamping lifting mechanism according to claim 1, characterized in that, The first push rod (128) and the second push rod (129) are each slidably connected with the lifting seat (11) through a linear guide rail (1210) arranged in the length direction.

5. The large-load unmanned aerial vehicle homing clamping lifting mechanism according to claim 1, characterized in that, The clamping assembly (2) comprises a bottom plate (21) installed on the top end of the lifting seat (11), and the top end of the bottom plate (21) is respectively provided with a first fixing device (22), a second fixing device (23), a third fixing device (24) and a fourth fixing device (25), which are used for clamping and locking the landing gear of the unmanned aerial vehicle from four directions.

6. The large-load unmanned aerial vehicle homing clamping lifting mechanism according to claim 5, characterized in that, The first fixing device (22), the second fixing device (23), the third fixing device (24) and the fourth fixing device (25) all comprise a second bearing seat (221) installed at the top end of the lifting seat (11), a clamping drive motor (222) and a speed reducer (223), the inside of the second bearing seat (221) is rotationally connected with a second transmission shaft (224), the driving end of the clamping drive motor (222) is connected with the power input end of the speed reducer (223), the power output end of the speed reducer (223) and the second transmission shaft (224) are driven through a clamping belt drive set (225), the two ends of the second transmission shaft (224) extend to the side of the second bearing seat (221), the side of the second bearing seat (221) is installed with a clamping buckle plate (226) to drive the clamping buckle plate (226) to reciprocally overturn, lock and unlock the landing gear of the unmanned aerial vehicle.

7. The large-load unmanned aerial vehicle homing clamping lifting mechanism according to claim 1, characterized in that, The lifting assembly (3) comprises a base (31), the top end of the base (31) is installed with a lifting drive motor (32), the top end of the base (31) is also symmetrically installed with a plurality of diverters (34), the lifting drive motor (32) and the diverters (34) and every adjacent diverter (34) are driven through a third transmission shaft (33), the power output end of every diverter (34) is connected with a lifting rod (35).

8. The large-load unmanned aerial vehicle homing clamping lifting mechanism according to claim 7, characterized in that, The outside of the lifting rod (35) is threadedly connected with the lifting seat (11) together to drive the homing assembly (1) and the clamping assembly (2) to synchronously lift, the side of the base (31) is also provided with a drag chain (37) to protect the cable during lifting.

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