Foldable unmanned aerial vehicle wing for petroleum pipeline

Abstract

The foldable unmanned aerial vehicle wing for the petroleum pipeline comprises a fuselage, first containing cavities and a second containing cavity are formed in the bottom end of the fuselage, the first containing cavities are located at the two ends of the second containing cavity, supporting bases are arranged at the four corners of the two first containing cavities, a supporting assembly is arranged at one end of each supporting base, and the other end of each supporting assembly is provided with a supporting rod. Round blocks are rotationally connected to the four corners of the second storage cavity correspondingly, wings are fixedly connected to the outer walls of the opposite sides of every two round blocks, and fixing bases are fixedly connected to the positions, close to the opposite sides of every two round blocks, in the second storage cavity correspondingly. The wings and the supporting assemblies can be stored through the unique fuselage storage cavity design, maneuverability and flexibility are improved, cost and difficulty are reduced, the positioning assemblies accurately achieve wing locking and unlocking and multi-directional limiting to guarantee structural stability, and the unmanned aerial vehicle keeps horizontal stability on different grounds through damping rotation of the supporting bases and the connecting blocks and related design of the supporting legs; the unstable risk of the machine body is reduced, and powerful support is provided for petroleum pipeline inspection.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles (UAVs), in particular to a foldable UAV wing for oil pipelines. Background Art

[0002] Drones are playing an increasingly important role in the monitoring and maintenance of oil pipelines. They can inspect oil pipelines and promptly detect pipeline leaks, damage, and abnormal surrounding environments, greatly improving the safety and reliability of oil pipeline operations. However, traditional drones face some challenges when used in oil pipeline-related operations.

[0003] Oil pipelines are often laid in complex geographical environments, and drones need to be deployed and operated in different locations, which places high demands on the portability of drones. The wings of ordinary drones are usually fixed and cannot be folded, which takes up a large space during transportation and storage, making it inconvenient to carry to remote or space-constrained oil pipeline operation areas; moreover, at the oil pipeline operation site, drones may need to be placed and take off under different terrain conditions, such as rugged ground or areas with a certain slope. This requires the drone to have good ground stability and adaptability to prevent the fuselage from tipping over and causing equipment damage or affecting the normal progress of the operation mission.

[0004] To this end, we propose a foldable drone wing for oil pipelines. Utility Model Content

[0005] The main purpose of the present utility model is to provide a foldable drone wing for oil pipelines, in order to prevent the problems of inconvenience in transportation and storage caused by the non-foldable wings of the drone, as well as the problems of fuselage tipping, equipment damage or obstruction of work tasks due to insufficient ground stability, thereby improving the maneuverability, flexibility, safety and reliability of the drone in oil pipeline monitoring and maintenance work, and can effectively solve the problems in the background technology.

[0006] In order to achieve the above purpose, the technical solution adopted by the utility model is:

[0007] A foldable drone wing for oil pipelines comprises a fuselage, wherein a first receiving cavity and a second receiving cavity are respectively defined in the interior of the bottom end of the fuselage, wherein the first receiving cavity is located at both ends of the second receiving cavity, support bases are provided at the four corners of the two first receiving cavities, and support assemblies are provided at one end of the four support bases;

[0008] Round blocks are rotatably connected to the four corners of the second storage cavity, and outer walls of opposite sides of the two round blocks are fixedly connected to the wings. A fixing seat is fixedly connected to the inside of the second storage cavity and close to the opposite side of the two round blocks, and a positioning assembly is provided between the fixing seat and the round blocks;

[0009] The positioning assembly includes a second limiting groove provided inside the fixing seat, a first limiting block is slidably provided in the second limiting groove, an outer wall of one end of the first limiting block is fixedly connected to a limiting rod, a plurality of first limiting grooves corresponding to the limiting rods are evenly provided on the outer wall of the round block, and one end of the limiting rod passes through one of the first limiting grooves, an outer wall of the other end of the first limiting block is fixedly connected to a connecting rod, and the other end of the connecting rod extends to the outside of the fixing seat and is fixed with a movable plate;

[0010] The movable plate is close to the outer wall of one side of the round block and is fixedly connected to a sliding rod on both sides of the fixed seat. The other end of the sliding rod is fixedly connected to a slider. A groove is provided inside the slider, and a limiting ball and a spring are arranged in the groove. Two third limiting grooves corresponding to the limiting balls are provided on both side surfaces of the fixed seat. The limiting ball is movably installed in the groove by the spring, and the limiting ball pops out into one of the third limiting grooves at one end away from the spring.

[0011] By adopting the above technical solution, when it is necessary to unfold the wing, the locking of the positioning assembly on the wing must first be released. The operator pulls the movable plate by external force, and the movable plate drives the connecting rod to move. The connecting rod in turn pulls the first limiting block to slide in the second limiting groove. The movement of the first limiting block causes the limiting rod to withdraw from the first limiting groove of the round block, thereby releasing the restriction on the rotation direction of the round block and the wing. At the same time, the movement of the movable plate drives the sliding rod and the slider to move together. The limiting ball in the inner groove of the slider is squeezed by the side of the fixed seat during the movement of the slider, and the spring is compressed, causing the limiting ball to withdraw from the third limiting groove where it was originally located. In this way, the locking of the wing by the entire positioning assembly is completely released. Then, the wing is manually unfolded by the operator and rotates and unfolds around the rotation connection point with the second storage cavity. When the wing is unfolded to the appropriate position, the movable plate is released. Under the action of the spring, the limiting ball pops out again into another third limiting groove. At the same time, the limiting rod is also inserted into the corresponding first limiting groove on the round block, re-positioning and locking the wing, so that the wing remains unfolded.

[0012] When the wing is to be stored, the movable plate is pulled first. The movement method of the movable plate and the principle of unlocking are the same as when the wing is unfolded, so that the limit rod is withdrawn from the first limit groove of the round block, and the limit ball is withdrawn from the third limit groove. Then the wing is rotated around the rotating connection point and stored in the second storage cavity. After the storage is completed, the movable plate is released, and the spring causes the limit ball to enter the corresponding third limit groove again. The limit rod also returns to the initial position, completing the storage and locking of the wing.

[0013] Furthermore, the support assembly includes a connecting block connected to the inner side of the support seat in a damping rotation manner, and one end of the connecting block is fixedly connected to the support sleeve.

[0014] By adopting the above technical solution, the connecting block and the support seat adopt an inner damping rotation connection method. When the UAV is in different working states, the support sleeve will change position due to the damping rotation relationship between the connecting block and the support seat. When the UAV is placed on a plane, the support sleeve will rotate to a suitable angle relative to the support seat through the connecting block under the action of factors such as gravity, so that the support sleeve provides stable support force for the fuselage, preventing the fuselage from tipping over due to shaking or imbalance, and due to the existence of damping, the support sleeve will not rotate at will and can remain in a stable supporting position. When the UAV needs to be moved or stored, a certain external force is applied to overcome the damping, so that the connecting block can drive the support sleeve to rotate to a position that does not affect the operation, and it can be stored in the first storage cavity or adjusted to an angle that does not hinder the movement of other components, so as to facilitate the transportation, storage or other actions of the UAV.

[0015] Furthermore, an inner hole is provided inside the support sleeve, and a support leg is fitted in the inner hole.

[0016] By adopting the above technical solution, when the drone needs to be placed on the ground and obtain more stable support, the support legs can be extended from the inner hole of the support sleeve. The operator moves the support legs outward along the inner hole by rotating, stretching, etc., and adjusts the length of the extended support legs until they touch the ground and reach the appropriate support height. This adjustable support leg can adapt to different ground flatness. If the ground has a certain slope or is uneven, by adjusting the length of the extended support legs, the fuselage can still be kept level, ensuring the stability of the drone during the placement process. Moreover, the coordinated installation of the support legs and the inner hole ensures that the support legs are sufficiently stable during the support process and will not easily shake or shift, thereby better sharing the weight of the fuselage and preventing the drone from tipping over.

[0017] When the drone needs to be stored or transported, the support legs can be retracted into the inner hole of the support sleeve. By reverse operation, the support legs are moved inward along the inner hole so that they are completely stored in the inner hole. This can reduce the overall space occupied by the support assembly, making it easier to place the drone in the first storage cavity or other transport containers, thereby improving the portability and storage convenience of the drone.

[0018] Furthermore, a protruding second limiting block is provided on the outer side of the supporting leg, and a linear limiting groove, a first locking limiting groove and a second locking limiting groove that cooperate with the second limiting block are respectively opened on the outer side of the inner hole.

[0019] By adopting the above technical solution, when the height of the support leg needs to be adjusted, the second limit block on the outer side of the support leg moves in the linear limit groove. The linear limit groove provides a linear movement path for the second limit block, ensuring that the support leg can smoothly extend or retract into the inner hole of the support sleeve along the vertical direction;

[0020] When the support leg needs to be extended out of the inner hole, the operator applies external force to move the support leg up or down, and the second limit block slides in the linear limit groove accordingly. When it needs to be locked, the second limit block can be snapped into the second locking limit groove. After being snapped in, it can limit the left and right movement of the support leg, thereby firmly fixing the support leg at the required height position, providing stable support for the drone;

[0021] When the support leg needs to be stored in the inner hole, the second limit block can be snapped into the first locking limit groove. This design provides additional locking position options to meet the needs of different usage scenarios, such as ensuring that the support leg is fully stored and will not extend accidentally during transportation.

[0022] Furthermore, the linear limit groove, the first locking limit groove and the second locking limit groove are connected, and the bottom inner wall of the first locking limit groove and the top inner wall of the second locking limit groove are respectively provided with a first magnet and a second magnet.

[0023] By adopting the above technical solution, when the second limit block on the outside of the support leg is adjusting its position, since the linear limit groove, the first locking limit groove and the second locking limit groove are connected, this provides a continuous and clear movement path for the second limit block. During the process of adjusting the height of the support leg, the second limit block moves smoothly along the linear limit groove, thereby realizing the up and down extension and retraction movement of the support leg in the inner hole of the support sleeve, ensuring that the support leg can be accurately adjusted to the required height to adapt to different ground conditions and drone placement requirements.

[0024] Furthermore, the first magnet and the second magnet are both magnetically connected to the second limiting block.

[0025] By adopting the above technical solution, when the support leg is adjusted to a suitable position and the second limit block moves to the first locking limit groove or the second locking limit groove, the first magnet or the second magnet is magnetically connected to the second limit block, which generates an adsorption force. This adsorption force can enhance the stability of the second limit block in the locking limit groove; when the second limit block enters the first locking limit groove, the first magnet generates a downward adsorption force on it, so that the second limit block fits tightly with the bottom of the first locking limit groove, thereby firmly locking the support leg in the retracted state, providing stable support for the drone. Similarly, when the second limit block enters the second locking limit groove, the second magnet generates an upward adsorption force on it, ensuring that the support leg is reliably locked in the fully extended state;

[0026] To unlock the support leg, it is necessary to overcome the magnetic attraction force between the first magnet or the second magnet and the second limit block. The operator applies external force to make the second limit block disengage from the first locking limit groove or the second locking limit groove under the action of a sufficiently large external force and return to the linear limit groove. The magnitude of this external force depends on factors such as the magnetic strength of the magnet and the friction between the second limit block and the locking limit groove. Once the second limit block returns to the linear limit groove, the height of the support leg can be freely adjusted or operations such as storage and extension can be performed.

[0027] Compared with the prior art, the present invention has the following beneficial effects:

[0028] (1) The utility model provides a foldable UAV wing for oil pipelines. By arranging a first storage cavity and a second storage cavity at the bottom of the fuselage, the wing can be folded and stored in the second storage cavity when not in use, and the support assembly can be stored in the first storage cavity. This greatly reduces the overall size of the UAV, making it easier to carry to the oil pipeline operation site. Whether it is transported by vehicle or carried by personnel, it is more convenient and quick, thereby improving the maneuverability and flexibility of the UAV in oil pipeline monitoring and maintenance work, and reducing transportation costs and operating difficulties.

[0029] (2) The utility model provides a foldable UAV wing for oil pipelines. By means of a first limit block, a limit rod and a first limit groove on a round block, and a movable plate and a connecting rod driving the first limit block to slide in a second limit groove of a fixed seat, the wing rotation direction can be accurately locked and unlocked, ensuring that the wing is in a stable position and reliable in operation during the unfolding and storage process. With the help of a slide rod, a slider, a limit ball and a spring in the groove and a third limit groove on the fixed seat, when the movable plate moves, the limit ball can cooperate with the third limit groove in different states, further enhancing the locking effect of the overall position of the wing, preventing the wing from being displaced or shaken under unexpected circumstances, and effectively protecting the integrity and stability of the wing structure and the overall UAV during flight, storage or transportation.

[0030] (3) The utility model provides a foldable UAV wing for oil pipelines. The damping rotation connection between the support base and the connecting block enables the support sleeve to automatically adjust the angle according to the placement state of the UAV and stably support the fuselage to prevent the fuselage from shaking or tipping over. In addition, the cooperation between the support legs and the support sleeve and the setting of the linear limit groove, the first locking limit groove and the second locking limit groove enable the support legs to be adjusted in height according to different ground flatness and to be reliably locked. Whether on flat ground or in a sloping area, the UAV can maintain a horizontal and stable state, ensuring the safety of the UAV during takeoff, landing and ground stationary, providing a solid foundation for the smooth progress of oil pipeline inspection tasks, and reducing the risk of operational errors or equipment failures caused by unstable fuselage. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 This is a structural schematic diagram of a foldable UAV wing for oil pipelines in the utility model.

[0032] Figure 2 The utility model is a structural schematic diagram of a positioning component for a foldable UAV wing for an oil pipeline.

[0033] Figure 3 The utility model is a structural schematic diagram of a support component for a foldable UAV wing for an oil pipeline.

[0034] In the figure: 1. fuselage; 2. wing; 3. round block; 4. fixing seat; 5. positioning assembly; 6. first storage cavity; 7. second storage cavity; 8. first limiting groove; 9. movable plate; 10. limiting rod; 11. slider; 12. slide rod; 13. support assembly; 14. second limiting groove; 15. first limiting block; 16. connecting rod; 17. groove; 18. limiting ball; 19. third limiting groove; 20. spring; 21. support seat; 22. connecting block; 23. support sleeve; 24. support leg; 25. second limiting block; 26. linear limiting groove; 27. first locking limiting groove; 28. first magnet; 29. ​​second locking limiting groove; 30. second magnet. DETAILED DESCRIPTION

[0035] In order to make the technical means, creative features, objectives and effects achieved by the present invention easier to understand, the present invention is further described below in conjunction with specific implementation methods.

[0036] In order to prevent the inconvenience of transportation and storage caused by the non-foldable wings of the drone, as well as the problems of the fuselage tipping over, equipment damage or obstruction of the operation task due to insufficient ground stability, the maneuverability, flexibility, safety and reliability of the drone in oil pipeline monitoring and maintenance work can be improved. Figure 1 、 Figure 2 、 Figure 3 As shown, a foldable UAV wing for oil pipelines includes a fuselage 1, wherein a first receiving cavity 6 and a second receiving cavity 7 are respectively formed inside the bottom end of the fuselage 1, and the first receiving cavity 6 is located at both ends of the second receiving cavity 7. Support bases 21 are provided at the four corners of the two first receiving cavities 6, and support assemblies 13 are provided at one end of the four support bases 21;

[0037] The four corners of the second storage cavity 7 are rotatably connected to round blocks 3, and the outer walls of the opposite sides of the two round blocks 3 are fixedly connected to the wings 2. The inside of the second storage cavity 7 and the side close to the opposite sides of the two round blocks 3 are fixedly connected to fixing seats 4, and a positioning assembly 5 is provided between the fixing seats 4 and the round blocks 3;

[0038] The positioning assembly 5 includes a second limiting groove 14 provided inside the fixing seat 4, a first limiting block 15 is slidably provided in the second limiting groove 14, an outer wall of one end of the first limiting block 15 is fixedly connected to the limiting rod 10, a plurality of first limiting grooves 8 corresponding to the limiting rod 10 are evenly provided on the outer wall of the round block 3, and one end of the limiting rod 10 passes through one of the first limiting grooves 8, a connecting rod 16 is fixedly connected to the outer wall of the other end of the first limiting block 15, and the other end of the connecting rod 16 extends to the outside of the fixing seat 4 and is fixed with a movable plate 9;

[0039] The movable plate 9 is close to the outer wall of one side of the round block 3 and is fixedly connected to a sliding rod 12 on both sides of the fixed seat 4. The other end of the sliding rod 12 is fixedly connected to a slider 11. A groove 17 is provided inside the slider 11. A limiting ball 18 and a spring 20 are provided in the groove 17. Two third limiting grooves 19 corresponding to the limiting ball 18 are provided on both side surfaces of the fixed seat 4. The limiting ball 18 is movably installed in the groove 17 by the spring 20, and the limiting ball 18 pops out into one of the third limiting grooves 19 at the end away from the spring 20.

[0040] During use, when the wings need to be unfolded, the lock of the wing by the positioning assembly must first be released. The operator pulls the movable plate 9 through external force, and the movable plate 9 drives the connecting rod 16 to move. The connecting rod 16 pulls the first limit block 15 to slide in the second limit groove 14. The movement of the first limit block 15 causes the limit rod 10 to withdraw from the first limit groove 8 of the round block 3, thereby releasing the restriction on the rotation direction of the round block 3 and the wing 2; at the same time, the movement of the movable plate 9 drives the sliding rod 12 and the slider 11 to move together. The limiting ball 18 in the internal groove 17 of the slider 11 will be affected by the fixed seat 4 during the movement of the slider 11. The side squeeze compresses the spring 20, and the limiting ball 18 withdraws from the third limiting groove 19 where it was originally located. In this way, the lock of the entire positioning assembly 5 on the wing 2 is completely released. Then, under the action of manual unfolding by the operator, the wing 2 rotates and unfolds around the rotation connection point with the second storage cavity 7. When the wing 2 is unfolded to the appropriate position, the movable plate 9 is released. Under the action of the spring 20, the limiting ball 18 pops out again and enters another third limiting groove 19. At the same time, the limiting rod 10 is also inserted into the corresponding first limiting groove 8 on the round block 3, re-positioning and locking the wing 2, so that the wing 2 remains in the unfolded state.

[0041] When the wing 2 is to be stored, the movable plate 9 is pulled first. The movement method and unlocking principle of the movable plate 9 are the same as when the wing 2 is unfolded, so that the limiting rod 10 withdraws from the first limiting groove 8 of the round block 3, and the limiting ball 18 withdraws from the third limiting groove 19. Then the wing 2 is rotated around the rotating connection point and stored in the second storage cavity 7. After the storage is completed, the movable plate 9 is released, and the spring 20 makes the limiting ball 18 enter the corresponding third limiting groove 19 again. The limiting rod 10 also returns to the initial position, completing the storage and locking of the wing 2.

[0042] For example, Figure 1 、 Figure 2 、 Figure 3 As shown, the present invention further includes that the support assembly 13 includes a connecting block 22 connected to the inner side of the support seat 21 for damping rotation, and one end of the connecting block 22 is fixedly connected to a support sleeve 23.

[0043] When in use, the connecting block 22 and the support seat 21 adopt an inner damping rotation connection method. When the drone is in different working states, the support sleeve 23 will change its position due to the damping rotation relationship between the connecting block 22 and the support seat 21. When the drone is placed on a plane, the support sleeve 23 will rotate to a suitable angle relative to the support seat 21 through the connecting block 22 under the action of factors such as gravity, so that the support sleeve 23 provides stable support force for the fuselage 1, preventing the fuselage 1 from tipping over due to shaking or imbalance, and due to the existence of damping, the support sleeve 23 will not rotate at will and can remain in a stable supporting position. When the drone needs to be moved or stored, a certain external force is applied to overcome the damping, so that the connecting block 22 can drive the support sleeve 23 to rotate to a position that does not affect the operation, and it can be stored in the first storage cavity 6 or adjusted to an angle that does not hinder the movement of other components, so as to facilitate the transportation, storage or other actions of the drone.

[0044] For example, Figure 1 、 Figure 2 、 Figure 3 As shown, the present invention further includes that an inner hole is provided inside the support sleeve 23, and a support leg 24 is fitted in the inner hole.

[0045] During use, when the drone needs to be placed on the ground and obtain a more stable support, the support legs 24 can be extended from the inner hole of the support sleeve 23. The operator moves the support legs 24 outward along the inner hole by rotating, stretching, etc., and adjusts the extended length of the support legs 24 until they touch the ground and reach a suitable support height. This adjustable support leg 24 can adapt to different ground flatness. If the ground has a certain slope or is uneven, by adjusting the extended length of the support legs 24, the fuselage 1 can still be kept horizontal, ensuring the stability of the drone during the placement process. Moreover, the support legs 24 are installed in conjunction with the inner hole, so that the support legs 24 have sufficient stability during the support process and will not easily shake or shift, thereby better sharing the weight of the fuselage 1 and preventing the drone from tipping over.

[0046] When the drone needs to be stored or transported, the support legs 24 can be retracted into the inner hole of the support sleeve 23. By reversing the operation, the support legs 24 are moved inward along the inner hole so that they are completely stored in the inner hole. This can reduce the overall space occupied by the support assembly 13, making it easier to place the drone in the first storage cavity 6 or other transport containers, thereby improving the portability and storage convenience of the drone.

[0047] For example, Figure 1 、 Figure 2 、 Figure 3 As shown, the present invention also includes that a raised second limit block 25 is provided on the outer side of the support leg 24, and a linear limit groove 26, a first locking limit groove 27 and a second locking limit groove 29 are respectively opened on the outer side of the inner hole to cooperate with the second limit block 25.

[0048] During use, when the height of the support leg 24 needs to be adjusted, the second limit block 25 on the outer side of the support leg 24 moves in the linear limit groove 26. The linear limit groove 26 provides a linear movement path for the second limit block 25, ensuring that the support leg 24 can smoothly extend or retract into the inner hole of the support sleeve 23 along the vertical direction;

[0049] When the support leg 24 needs to be extended out of the inner hole, the operator applies external force to move the support leg 24 upward or downward, and the second limit block 25 slides in the linear limit groove 26. When it needs to be locked, the second limit block 25 can be snapped into the second locking limit groove 29. After being snapped in, it can limit the left and right movement of the support leg 24, thereby firmly fixing the support leg 24 at the required height position, providing stable support for the drone;

[0050] When the support leg 24 needs to be stored in the inner hole, the second limit block 25 can be snapped into the first locking limit groove 27. This design provides additional locking position options to meet the needs of different usage scenarios, such as ensuring that the support leg 24 is fully stored and will not extend accidentally during transportation.

[0051] For example, Figure 1 、 Figure 2 、 Figure 3 As shown, the utility model also includes that the linear limit groove 26, the first locking limit groove 27 and the second locking limit groove 29 are connected, and the bottom inner wall of the first locking limit groove 27 and the top inner wall of the second locking limit groove 29 are respectively provided with a first magnet 28 and a second magnet 30.

[0052] During use, when the second limit block 25 on the outside of the support leg 24 is adjusting its position, since the linear limit groove 26, the first locking limit groove 27 and the second locking limit groove 29 are connected, this provides a continuous and clear movement path for the second limit block 25. During the process of adjusting the height of the support leg 24, the second limit block 25 moves smoothly along the linear limit groove 26, thereby realizing the up and down extension and contraction movement of the support leg 24 in the inner hole of the support sleeve 23, ensuring that the support leg 24 can be accurately adjusted to the required height to adapt to different ground conditions and drone placement requirements.

[0053] For example, Figure 1 、 Figure 2 、 Figure 3 As shown, the present invention further includes that the first magnet 28 and the second magnet 30 are both magnetically connected to the second limiting block 25 .

[0054] When in use, when the support leg 24 is adjusted to a suitable position and the second limit block 25 moves to the first locking limit groove 27 or the second locking limit groove 29, the first magnet 28 or the second magnet 30 is magnetically connected to the second limit block 25, which generates an adsorption force. This adsorption force can enhance the stability of the second limit block 25 in the locking limit groove; after the second limit block 25 enters the first locking limit groove 27, the first magnet 28 generates a downward adsorption force on it, so that the second limit block 25 is tightly fitted with the bottom of the first locking limit groove 27, thereby firmly locking the support leg 24 in the storage state, providing stable support for the drone. Similarly, when the second limit block 25 enters the second locking limit groove 29, the second magnet 30 generates an upward adsorption force on it, ensuring that the support leg 24 is reliably locked in the fully extended state;

[0055] To unlock the support leg 24, it is necessary to overcome the magnetic attraction force between the first magnet 28 or the second magnet 30 and the second limit block 25. The operator applies external force so that the second limit block 25 is separated from the first locking limit groove 27 or the second locking limit groove 29 under the action of a sufficiently large external force and returns to the linear limit groove 26. The magnitude of this external force depends on factors such as the magnetic strength of the magnet and the friction between the second limit block 25 and the locking limit groove. Once the second limit block 25 returns to the linear limit groove 26, the height of the support leg 24 can be freely adjusted or operations such as storage and extension can be performed.

[0056] It should be noted that the utility model is a foldable drone wing for oil pipelines. The operator pulls the movable plate 9 through external force, and the movable plate 9 drives the connecting rod 16 to move. The connecting rod 16 then pulls the first limit block 15 to slide in the second limit groove 14. The movement of the first limit block 15 causes the limit rod 10 to withdraw from the first limit groove 8 of the round block 3, thereby releasing the restriction on the round block 3 and the wing 2 in the rotation direction. At the same time, the movement of the movable plate 9 drives the slide rod 12 and the slider 11 to move together. The limit ball 18 in the internal groove 17 of the slider 11 is squeezed by the side of the fixed seat 4 during the movement of the slider 11. , the spring 20 is compressed, and the limiting ball 18 withdraws from the third limiting groove 19 where it was originally located. At this point, the entire positioning assembly 5 is completely released from the lock of the wing 2. After the positioning assembly is released, the wing 2 is manually unfolded by the operator and rotates and unfolds around the rotation connection point with the second storage cavity 7. When the wing 2 is unfolded to the appropriate position, the movable plate 9 is released. Under the action of the spring 20, the limiting ball 18 pops out again and enters another third limiting groove 19. At the same time, the limiting rod 10 is also inserted into the corresponding first limiting groove 8 on the round block 3, re-positioning and locking the wing 2, so that the wing 2 remains in the unfolded state;

[0057] When unlocking the positioning assembly, the movable plate 9 is also pulled first. The movement method and unlocking principle of the movable plate 9 are the same as when the wing 2 is deployed, so that the limiting rod 10 is withdrawn from the first limiting groove 8 of the round block 3, and the limiting ball 18 is withdrawn from the third limiting groove 19, and the wing 2 is rotated around the rotation connection point and stored in the second storage cavity 7. After the storage is completed, the movable plate 9 is released, and the spring 20 causes the limiting ball 18 to re-enter the corresponding third limiting groove 19, and the limiting rod 10 also returns to the initial position, completing the storage and locking of the wing 2;

[0058] The connecting block 22 and the support seat 21 adopt an inner damping rotation connection method. When the drone is placed on a plane, the support sleeve 23 will rotate to a suitable angle relative to the support seat 21 through the connecting block 22 under the action of factors such as gravity. The support sleeve 23 provides a stable supporting force for the fuselage 1 to prevent the fuselage 1 from tipping over due to shaking or imbalance. In addition, due to the presence of damping, the support sleeve 23 will not rotate at will and can remain in a stable supporting position. When the drone needs to be moved or stored, a certain external force is applied to overcome the damping, so that the connecting block 22 drives the support sleeve 23 to rotate to a position that does not affect the operation, and is stored in the first storage cavity 6 or adjusted to an angle that does not hinder the movement of other components, so as to facilitate the transportation, storage or other actions of the drone.

[0059] When the UAV needs to be placed on the ground and obtain a more stable support, the operator moves the support leg 24 outward along the inner hole by rotating, stretching, etc., and adjusts the extended length of the support leg 24 until it touches the ground and reaches a suitable support height. During this process, the second limit block 25 on the outer side of the support leg 24 moves in the linear limit groove 26. The linear limit groove 26 provides a linear movement path for the second limit block 25, ensuring that the support leg 24 can be smoothly extended or retracted into the inner hole of the support sleeve 23 in the vertical direction. When the support leg 24 needs to be locked at a desired height position, the second limit block 25 can be snapped into the second locking limit groove 29. After being snapped in, it can limit the left and right movement of the support leg 24, thereby firmly fixing the support leg 24 at the desired height position, providing stable support for the UAV;

[0060] When the drone needs to be stored or transported, the support leg 24 can be retracted into the inner hole of the support sleeve 23. By reverse operation, the support leg 24 is moved inward along the inner hole so that it is completely stored in the inner hole. When the support leg 24 needs to be locked in the stored state, the second limit block 25 can be snapped into the first locking limit groove 27. This design provides additional locking position options to meet the needs of different usage scenarios, such as ensuring that the support leg 24 is completely stored and does not extend accidentally during transportation;

[0061] To unlock the support leg 24, it is necessary to overcome the magnetic attraction force between the first magnet 28 or the second magnet 30 and the second limit block 25. The operator applies external force so that the second limit block 25 is disengaged from the first locking limit groove 27 or the second locking limit groove 29 under the action of a sufficiently large external force and returns to the linear limit groove 26. Once the second limit block 25 returns to the linear limit groove 26, the height of the support leg 24 can be freely adjusted or operations such as storage and extension can be performed.

[0062] The above shows and describes the basic principles, main features and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The above embodiments and descriptions are merely illustrative of the principles of the present invention. Various changes and improvements may be made to the present invention without departing from the spirit and scope of the present invention. Such changes and improvements are intended to fall within the scope of the present invention. The scope of protection claimed in this invention is defined by the appended claims and their equivalents.

Claims

1. A foldable drone wing for oil pipelines, comprising a fuselage (1), characterized in that: A first receiving cavity (6) and a second receiving cavity (7) are respectively provided inside the bottom end of the body (1), and the first receiving cavity (6) is located at both ends of the second receiving cavity (7), and support seats (21) are provided at the four corners of the two first receiving cavities (6), and support components (13) are provided at one end of the four support seats (21); The four corners of the second receiving cavity (7) are all rotatably connected to round blocks (3), and the outer walls of the opposite sides of the two round blocks (3) are fixedly connected to the wings (2). The interior of the second receiving cavity (7) and the side close to the opposite sides of the two round blocks (3) are all fixedly connected to fixed seats (4), and a positioning assembly (5) is provided between the fixed seat (4) and the round blocks (3); The positioning assembly (5) includes a second limiting groove (14) provided inside the fixing seat (4), a first limiting block (15) is slidably provided in the second limiting groove (14), an outer wall of one end of the first limiting block (15) is fixedly connected to the limiting rod (10), a plurality of first limiting grooves (8) corresponding to the limiting rod (10) are evenly provided on the outer wall of the round block (3), and one end of the limiting rod (10) passes through one of the first limiting grooves (8), an outer wall of the other end of the first limiting block (15) is fixedly connected to a connecting rod (16), and the other end of the connecting rod (16) extends to the outside of the fixing seat (4) and is fixed with a movable plate (9); The movable plate (9) is fixedly connected to a sliding rod (12) on one side outer wall of the round block (3) and on both sides of the fixed seat (4); the other end of the sliding rod (12) is fixedly connected to a slider (11); a groove (17) is provided inside the slider (11); a limiting ball (18) and a spring (20) are provided in the groove (17); two third limiting grooves (19) corresponding to the limiting ball (18) are provided on both side surfaces of the fixed seat (4); the limiting ball (18) is movably installed in the groove (17) by the spring (20), and the limiting ball (18) pops out into one of the third limiting grooves (19) at one end away from the spring (20).

2. The foldable UAV wing for oil pipeline according to claim 1, characterized in that: The support assembly (13) comprises a connecting block (22) connected to the inner side of the support seat (21) in a damping rotation manner, and one end of the connecting block (22) is fixedly connected to a support sleeve (23).

3. The foldable UAV wing for oil pipeline according to claim 2, characterized in that: An inner hole is provided inside the support sleeve (23), and a support leg (24) is fitted in the inner hole.

4. The foldable UAV wing for oil pipeline according to claim 3 is characterized by: A protruding second limiting block (25) is provided on the outside of the support leg (24), and a linear limiting groove (26), a first locking limiting groove (27) and a second locking limiting groove (29) are respectively provided on the outside of the inner hole to match the second limiting block (25).

5. The foldable UAV wing for oil pipeline according to claim 4 is characterized in that: The linear limit groove (26), the first locking limit groove (27) and the second locking limit groove (29) are connected, and the bottom inner wall of the first locking limit groove (27) and the top inner wall of the second locking limit groove (29) are respectively provided with a first magnet (28) and a second magnet (30).

6. The foldable UAV wing for oil pipeline according to claim 5, characterized in that: The first magnet (28) and the second magnet (30) are both magnetically connected to the second limiting block (25).

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