Cargo hold folding structure of low-altitude economic freight unmanned aerial vehicle

Abstract

The utility model relates to freight unmanned plane technical field, and disclose low altitude economic freight unmanned plane cargo hold pick -and -place structure, including fuselage, the lower extreme of fuselage is provided with buffer structure, and one side of buffer structure is provided with carrying structure, and the bottom of fuselage is pasted with storage box, the utility model discloses through starting micro motor, makes the output of micro motor drive screw to rotate, to the inside of moving groove of the outer surface of screw surface push -out board upward or down moves, and then can make the one end of push -out board and the outer surface of hinged plate one side side, thereby can drive hinged plate to downward hinged rotation, and make the positioning rod insert in the inside of the positioning hole at corresponding position location, the position of storage box is positioned, thereby can avoid the condition that storage box separates from the lower extreme of fuselage, and then through the inside of the positioning hole of positioning rod insertion can make storage box clamping in the lower extreme of fuselage can be more stable.

Description

Technical Field

[0001] This utility model relates to the field of cargo drone technology; more specifically, it relates to the cargo hold deployment and retraction structure of a low-altitude economic cargo drone. Background Technology

[0002] Low-altitude economic cargo drones are becoming a new force in logistics transportation. They come in various sizes, designed according to load requirements; small, agile drones can navigate complex terrain, while larger ones offer considerable cargo capacity. Relying on advanced flight control systems and navigation technology, they can accurately plan routes for efficient cargo delivery. They offer significant advantages in remote areas and emergency relief supplies transportation, overcoming ground transportation limitations and delivering goods quickly.

[0003] The cargo hold deployment and recovery structure of low-altitude economical cargo drones is a core component for achieving efficient cargo transfer. It utilizes a lightweight aluminum alloy frame and carbon fiber skin, balancing strength and weight reduction requirements. The cargo hold is stably fixed during flight and precisely deployed during ground operations. Suitable for low-altitude flight scenarios up to 150 meters, its compact structure and wind resistance ensure the safety and efficiency of cargo handling in short-distance transportation, helping to reduce costs and accelerate last-mile logistics.

[0004] Currently, existing cargo drones, when in use, typically fly to a suitable location to drop off their cargo. During flight, the vibration of the blades causes the cargo to vibrate synchronously, potentially damaging it and reducing its practicality. Furthermore, most existing drones rely on storage boxes for cargo placement, and current methods use clamps for positioning these boxes. These clamping devices are prone to falling and are not very stable, further reducing usability. Therefore, a new cargo hold deployment structure for low-altitude economical cargo drones is urgently needed to address these issues. Utility Model Content

[0005] In order to overcome the above-mentioned defects of the prior art, this utility model provides a cargo compartment retraction and deployment structure for low-altitude economic cargo drones, so as to solve the problems existing in the background art.

[0006] This utility model provides the following technical solution: a cargo hold retraction structure for a low-altitude economic cargo drone, comprising: a fuselage, a buffer structure at the lower end of the fuselage, a transport structure on one side of the buffer structure, and a storage box attached to the bottom of the fuselage; the buffer structure includes a movable groove, a fixed rod, a first spring, a connecting plate, a clamping block, and a second spring; the transport structure includes a support plate, a hinge plate, a positioning rod, a positioning hole, a moving groove, a micro motor, a lead screw, and a push plate.

[0007] Preferably, the movable slots are provided in two sets, and the two sets of movable slots are respectively opened inside the outer surface of the lower end of the machine body. The inner wall surfaces of the upper and lower ends of the two sets of movable slots are fixedly connected with fixing rods, and there are multiple sets of fixing rods. The outer surfaces of the upper and lower ends of the multiple sets of fixing rods are respectively fitted with first springs, and there are multiple sets of first springs. The outer surfaces of the multiple sets of fixing rods are fitted with connecting plates. The connecting plates are respectively inserted into the interior of the two sets of movable slots, and the inner surfaces of the outer surfaces at both ends of the connecting plates are fitted with abutting blocks. The inner surfaces of the outer surfaces at both ends of the two sets of connecting plates are provided with second springs. The outer surfaces of the two sets of connecting plates on the opposite side are respectively fixedly connected with support plates. This design allows the connecting plates to move up or down inside the movable slots.

[0008] Preferably, the two ends of the first spring abut against the inner wall surface of the movable groove and the outer surface of the connecting plate, respectively. This design allows the movable groove to automatically reset after moving to the outer surface of the connecting plate.

[0009] Preferably, the outer surfaces of the two sets of abutting blocks that are close to each other are fixedly connected with limit rings, and the outer surfaces of the two sets of abutting blocks that are far from each other are fixedly connected with wear-resistant blocks, and the wear-resistant blocks are made of rubber. The two ends of the second spring abut against the surface of one side of the limit ring and the inner wall surface of the connecting plate, respectively. This design allows the abutting blocks to move inside the connecting plate, and prevents the abutting blocks from detaching from the inside of the connecting plate when they move inside the connecting plate.

[0010] Preferably, the support plate is provided in two sets, and the outer surface of the lower end of the support plate of both sets is hinged to a hinge plate. The outer surfaces of the two sets of hinge plates on the side closer to each other are fixedly connected to a positioning rod. The inner surfaces of the outer surfaces of both sides of the storage box are provided with positioning holes. The inner surfaces of the outer surfaces of the two sets of support plates on the side farther from each other are provided with a moving groove. The inner surface of the upper end of the moving groove is equipped with a micro motor. The output end of the micro motor is fixedly connected to a lead screw. The outer surface of the lead screw is fitted with a push plate. This design allows the micro motor to be started, so that the output end of the micro motor drives the lead screw to rotate, and the push plate on the outer surface of the lead screw moves up or down inside the moving groove.

[0011] Preferably, torsion springs are provided inside the connection between the two sets of support plates and hinge plates, and the internal dimensions of the positioning holes are adapted to the external dimensions of the positioning rods. This design allows the hinge plates to self-reset after hinged rotation.

[0012] The technical effects and advantages of this utility model are as follows: This utility model can buffer the vibration generated by the fuselage through the cooperation of multiple sets of fixing rods and multiple sets of positioning rods, thereby avoiding the vibration generated by the fuselage during flight from affecting the objects inside the storage box, thus avoiding damage to the objects inside the storage box. At the same time, it can buffer the vibration generated by the fuselage during descent when the fuselage lands on the ground, thereby improving the practicality of the equipment to a certain extent. By activating the micro motor, the output end of the micro motor drives the lead screw to rotate, causing the push plate on the outer surface of the lead screw to move up or down inside the moving slot. This allows one end of the push plate to abut against the outer surface of one side of the hinge plate, thereby causing the hinge plate to rotate downwards and hinge. This allows the positioning rod to be inserted into the positioning hole at the corresponding position, positioning the storage box and preventing it from detaching from the lower end of the machine body. Furthermore, the positioning rod inserted into the positioning hole makes the storage box more stable when clamped at the lower end of the machine body, improving the practicality of the equipment to a certain extent. Moreover, its overall structure is simple and reasonable in design, highly practical, and easy to promote and apply. Attached Figure Description

[0013] Figure 1 This is a three-dimensional structural diagram of the present invention.

[0014] Figure 2 This is a three-dimensional exploded view of the buffer structure of this utility model.

[0015] Figure 3 This utility model Figure 2 Enlarged diagram of point A in the middle.

[0016] Figure 4 This is a three-dimensional exploded view of the carrier structure of this utility model.

[0017] The attached diagram is labeled as follows: 1. Body; 2. Buffer structure; 21. Movable groove; 22. Fixed rod; 23. First spring; 24. Connecting plate; 25. Clamping block; 26. Second spring; 3. Carrier structure; 31. Support plate; 32. Hinge plate; 33. Positioning rod; 34. Positioning hole; 35. Moving groove; 36. Micro motor; 37. Lead screw; 38. Push plate; 4. Storage box. Detailed Implementation

[0018] The technical solution of this utility model will be clearly and completely described below with reference to the accompanying drawings. In addition, the forms of the various structures described in the following embodiments are merely illustrative. The cargo drone involved in this utility model is not limited to the structures described in the following embodiments. All other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.

[0019] Example 1, as Figures 1-4 As shown, this embodiment proposes a cargo hold deployment and retraction structure for a low-altitude economic cargo UAV, including: a fuselage 1, a buffer structure 2 at the lower end of the fuselage 1, a transport structure 3 on one side of the buffer structure 2, and a storage box 4 attached to the bottom of the fuselage 1; the buffer structure 2 includes a movable groove 21, a fixed rod 22, a first spring 23, a connecting plate 24, a clamping block 25, and a second spring 26. Two sets of movable grooves 21 are provided, and the two sets of movable grooves 21 are respectively opened inside the outer surface of both sides of the lower end of the fuselage 1. Fixed rods 22 are fixedly connected to the inner wall surfaces of the upper and lower ends of the two sets of movable grooves 21, and multiple sets of fixed rods 22 are provided. First springs 23 are respectively sleeved on the outer surfaces of the upper and lower ends of the multiple sets of fixed rods 22, and multiple sets of first springs 23 are provided. A connecting plate 24 is fitted on the outer surface of the fixed rod 22. The connecting plates 24 are inserted into the interior of the two sets of movable slots 21 respectively. The abutment blocks 25 are inserted into the interior of the outer surfaces at both ends of the connecting plates 24. The second spring 26 is provided inside the interior of the outer surfaces at both ends of the two sets of connecting plates 24. The support plate 31 is fixedly connected to the outer surfaces of the two sets of connecting plates 24 on the side away from each other. The two ends of the first spring 23 abut against the inner wall surface of the movable slot 21 and the outer surface of the connecting plate 24 respectively. This design allows the movable slot 21 to move up or down on the outer surface of the connecting plate 24 and then reset itself under the elasticity of the first spring 23. Thus, the vibration generated by the body 1 can be converted into the dynamic potential energy of the movable slot 21 moving up or down on the outer surface of the connecting plate 24. Limiting rings are fixedly connected to the outer surfaces of the two sets of clamping blocks 25 at their close ends, and wear-resistant blocks are fixedly connected to the outer surfaces of the two sets of clamping blocks 25 at their far ends. The wear-resistant blocks are made of rubber. The two ends of the second spring 26 abut against the surface of one side of the limiting ring and the inner wall surface of the connecting plate 24, respectively. This design prevents the clamping blocks 25 from detaching from the interior of the connecting plate 24 when they move inside the connecting plate 24. This design also allows the clamping blocks 25 to abut against the inner wall surfaces of both sides of the movable groove 21 under the elasticity of the second spring 26. The good elasticity and wear resistance of the wear-resistant blocks can buffer and offset the movement of the movable groove 21 when it moves on the outer surface of the connecting plate 24.

[0020] Example 2, as Figure 4As shown, based on the same concept as the above embodiments, this embodiment also proposes: the transport structure 3 includes a support plate 31, a hinge plate 32, a positioning rod 33, a positioning hole 34, a moving groove 35, a micro motor 36, a lead screw 37, and a push plate 38. Two sets of support plates 31 are provided, and the outer surfaces of the lower ends of both sets of support plates 31 are hingedly connected to the hinge plates 32. The outer surfaces of the two sets of hinge plates 32, which are close to each other, are fixedly connected to the positioning rods 33. Positioning holes 34 are opened inside the outer surfaces of both ends of the storage box 4, and moving grooves are opened inside the outer surfaces of the two sets of support plates 31, which are far apart from each other. 35, and micro motors 36 are installed inside the inner wall surface of the upper end of the moving groove 35, and the output end of the micro motor 36 is fixedly connected to a lead screw 37. A push plate 38 is sleeved on the outer surface of the lead screw 37. Torsion springs are installed inside the connection between the two sets of support plates 31 and the hinge plate 32. The internal size of the positioning hole 34 is adapted to the external size of the positioning rod 33. This design allows the hinge plate 32 to reset itself under the elasticity of the torsion spring after hinge rotation. This design also makes the positioning rod 33 more stable when inserted into the positioning hole 34, so as to position the storage box 4 at the lower end of the body 1. The micro motor 36 is a product that can be purchased directly on the market. Its principle, connection method and control method are existing technologies that are well known to those skilled in the art, so they will not be described in detail here. The lead screw 37 in this application, as well as all movable parts, require regular cleaning and maintenance, including but not limited to dust removal and lubrication.

[0021] Working principle: When the equipment is in use, the micro motor 36 is started, causing the output end of the micro motor 36 to drive the lead screw 37 to rotate. This causes the push plate 38 on the outer surface of the lead screw 37 to move up or down, allowing the push plate 38 to abut against or disengage from the outer surface of the hinge plate 32. When the push plate 38 abuts against the outer surface of the hinge plate 32, it causes the hinge plate 32 to rotate, causing the positioning rod 33 on the other side of the hinge plate 32 to be inserted into the positioning hole 34 at the corresponding position, thus positioning the storage box 4 at the lower end of the machine body 1, thereby completing the installation of the storage box 4. When the push plate 38 disengages from the outer surface of the hinge plate 32... This allows the hinge plate 32 to self-reset under the elasticity of the torsion spring, thereby disengaging the positioning rod 33 on the other side of the hinge plate 32 from the interior of the positioning hole 34, thus enabling the storage box 4 to be disassembled. Furthermore, the combination of multiple sets of fixing rods 22 and multiple sets of positioning rods 33 can buffer the vibrations generated by the fuselage 1 during flight and the vibrations generated when the fuselage 1 lands on the ground. The wear-resistant blocks at the opposite ends of the two sets of abutting blocks 25 abut against the inner wall surface of the movable groove 21, converting the movement of the movable groove 21 on the outer surface of the connecting plate 24 into heat energy for dissipation. This can prevent the vibrations generated by the fuselage 1 during flight from damaging the objects inside the storage box 4. The above is the complete working principle of this utility model.

[0022] Finally, the following points should be noted: First, in the description of this application, it should be noted that, unless otherwise specified and limited, the terms "installation", "connection", and "linkage" should be interpreted broadly, and can be mechanical or electrical connections, or internal connections between two components, or direct connections. "Up", "down", "left", "right", etc. are only used to indicate relative positional relationships. When the absolute position of the described object changes, the relative positional relationship may change. Secondly: The accompanying drawings of the embodiments disclosed in this utility model only involve the structures involved in the embodiments disclosed in this utility model. Other structures can refer to the general design. In the absence of conflict, the same embodiment and different embodiments of this utility model can be combined with each other. In conclusion, the above are merely preferred embodiments of this utility model and are not intended to limit this utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this utility model should be included within the protection scope of this utility model.

Claims

1. A cargo hold retraction structure for low-altitude economic cargo drones, characterized in that: include: The fuselage (1) has a buffer structure (2) at its lower end, and a transport structure (3) is provided on one side of the buffer structure (2), and a storage box (4) is attached to the bottom of the fuselage (1). The buffer structure (2) includes a movable groove (21), a fixed rod (22), a first spring (23), a connecting plate (24), a pressing block (25), and a second spring (26); The carrier structure (3) includes a support plate (31), a hinge plate (32), a positioning rod (33), a positioning hole (34), a moving groove (35), a micro motor (36), a lead screw (37), and a push plate (38).

2. The cargo hold retraction structure for low-altitude economic cargo UAVs according to claim 1, characterized in that: The movable groove (21) is provided in two sets, and the two sets of movable grooves (21) are respectively opened inside the outer surface of the lower end of the machine body (1). The inner wall surfaces of the upper and lower ends of the two sets of movable grooves (21) are fixedly connected with fixed rods (22), and there are multiple sets of fixed rods (22). The outer surfaces of the upper and lower ends of the multiple sets of fixed rods (22) are respectively fitted with first springs (23), and there are multiple sets of first springs (23). The outer surfaces of the multiple sets of fixed rods (22) are fitted with connecting plates (24). The interior of the two sets of movable grooves (21) is respectively fitted with connecting plates (24), and the interior of the outer surfaces at both ends of the connecting plates (24) is fitted with abutting blocks (25). The interior of the outer surfaces at both ends of the two sets of connecting plates (24) is provided with second springs (26). The outer surfaces of the two sets of connecting plates (24) on the side away from each other are respectively fixedly connected with support plates (31).

3. The cargo hold retraction structure for low-altitude economic cargo UAVs according to claim 1, characterized in that: The two ends of the first spring (23) abut against the inner wall surface of the movable groove (21) and the outer surface of the connecting plate (24), respectively.

4. The cargo hold retraction structure for low-altitude economic cargo UAVs according to claim 1, characterized in that: The outer surfaces of the two sets of abutting blocks (25) that are close to each other are fixedly connected with limit rings, and the outer surfaces of the two sets of abutting blocks (25) that are far apart from each other are fixedly connected with wear-resistant blocks, and the wear-resistant blocks are made of rubber. The two ends of the second spring (26) abut against the surface of the limit ring and the inner wall surface of the connecting plate (24) respectively.

5. The cargo hold retraction structure for low-altitude economic cargo UAVs according to claim 1, characterized in that: The support plate (31) is provided in two sets, and the outer surface of the lower end of the two sets of support plates (31) is hinged to a hinge plate (32). The outer surfaces of the two sets of hinge plates (32) on the side closer to each other are fixedly connected to a positioning rod (33). The inner surface of the outer surface of both sides of the storage box (4) is provided with a positioning hole (34). The inner surface of the outer surface of the two sets of support plates (31) on the side farther from each other is provided with a moving groove (35). The inner surface of the upper end of the moving groove (35) is provided with a micro motor (36). The output end of the micro motor (36) is fixedly connected to a lead screw (37). The outer surface of the lead screw (37) is fitted with a push plate (38).

6. The cargo hold retraction structure for low-altitude economic cargo UAVs according to claim 5, characterized in that: Both sets of support plates (31) and hinge plates (32) are provided with torsion springs inside the connection, and the internal dimensions of the positioning hole (34) are adapted to the external dimensions of the positioning rod (33).

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