Low-altitude flying delivery device for logistics

Abstract

The utility model belongs to logistics low altitude transportation equipment technical field especially for a logistics low altitude flight transmission equipment, including unmanned aerial vehicle goods warehouse outer shell, unmanned aerial vehicle goods warehouse inner shell, center tube, a plurality of take -off and -on roll, a plurality of hollow shaft, take -off and -on self -resetting assembly, two -way air pump and two warehouse doors that are set to opposite -open, unmanned aerial vehicle goods warehouse inner shell can be dismantled and installed in unmanned aerial vehicle goods warehouse outer shell, the center tube fixed mounting is in the bottom inner wall of unmanned aerial vehicle goods warehouse outer shell central position. The utility model design is reasonable, can carry out efficient and stable limit to the goods needed to transport, effectively avoids the situation that the goods affect unmanned aerial vehicle flight stability because of excessive displacement in the transportation process, simultaneously, it is convenient to carry out the quick replacement of unmanned aerial vehicle goods warehouse inner shell according to the shape of different goods, simple and convenient operation has better use flexibility, effectively improves the security and practicality of logistics transportation.

Description

Technical Field

[0001] This utility model relates to the technical field of low-altitude transportation equipment for logistics, and in particular to a low-altitude flight delivery device for logistics. Background Technology

[0002] In the current logistics industry, low-altitude flight delivery equipment (such as logistics drones) is widely used in short-distance cargo transportation scenarios due to its flexibility and efficiency. However, the cargo compartments of existing logistics drones are mostly fixed structures, mainly using partitions, straps, or integral airbags to secure the cargo. This results in significant defects in adaptability and stability: First, fixed partitions and straps can only accommodate regular cargo of specific sizes. When dealing with irregular or multi-sized cargo, gaps are likely to appear, causing the cargo to shift or collide due to vibration during transportation, and even causing the center of gravity to shift, affecting flight safety. Second, although traditional integral airbags can fill some gaps, they cannot adapt to the contours of the cargo, and local gaps are still difficult to eliminate. Moreover, the airbags lack convenient storage structures after inflation, resulting in low loading and unloading efficiency. Third, some cargo compartments do not have a removable inner shell design, requiring the replacement of the entire cargo compartment component for different cargo volumes, which is cumbersome and has poor equipment versatility.

[0003] Therefore, this utility model proposes a low-altitude flight delivery device for logistics to solve the above problems.

[0004] The information disclosed in this background section is intended only to enhance the understanding of the overall background of this utility model and should not be construed as an admission or in any way implying that the information constitutes prior art known to those skilled in the art. Utility Model Content

[0005] The purpose of this utility model is to address the shortcomings mentioned in the background art and to propose a low-altitude flight delivery device for logistics.

[0006] The above-mentioned technical objective of this utility model is achieved through the following technical solution: a low-altitude flight delivery device for logistics, comprising a drone cargo hold outer shell, a drone cargo hold inner shell, a central cylinder, multiple take-up and release rollers, multiple hollow shafts, a take-up and release self-resetting assembly, a bidirectional air pump, and two cargo doors arranged in a bi-directional manner.

[0007] The inner shell of the drone cargo compartment is detachably installed inside the outer shell of the drone cargo compartment. The central cylinder is fixedly installed at the center of the bottom inner wall of the drone cargo compartment outer shell. Multiple hollow shafts are rotatably installed on the bottom inner wall of the drone cargo compartment outer shell and are arranged in a circular array around the axis of the central cylinder. All hollow shafts are located inside the central cylinder. Multiple take-up and untake-up rollers are respectively fixedly installed on the corresponding hollow shafts. Each take-up and untake-up roller is fixed and wound with an inflatable hollow partition membrane. The ends of the hollow partition membranes away from the take-up and untake-up rollers extend outside the central cylinder and are respectively fixedly installed with retaining strips. The inner wall of the drone cargo compartment has multiple slots for locking and fixing with clips. The retraction and retraction self-resetting assembly is located on the bottom inner wall of the drone cargo compartment and connected to multiple hollow shafts. The bidirectional air pump is fixedly installed on the bottom inner wall of the drone cargo compartment and located inside the central cylinder. Multiple conveying pipes are connected to the bidirectional air pump and are rotatably sealed to the corresponding hollow shafts. An air pipe that passes through the retraction and retraction roller and is connected to the hollow shaft is fixedly pasted inside the hollow partition membrane. Two compartment doors that are arranged in a split configuration are hinged to the top opening of the drone cargo compartment.

[0008] Preferably, the retraction and unfolding self-resetting assembly includes multiple circular baffles and multiple torsion springs. Circular baffles are fixedly installed on multiple hollow shafts. The top side of the circular baffle abuts against the bottom end of the corresponding retraction and unfolding roller. A torsion spring is fixedly installed on the bottom side of the circular baffle and movably sleeved on the outside of the hollow shaft. The bottom end of the torsion spring is fixedly connected to the bottom inner wall of the UAV cargo compartment shell.

[0009] Preferably, the inner wall of the central cylinder is provided with multiple guide openings, and multiple hollow partition membranes pass through the corresponding guide openings, and the sidewalls of the multiple guide openings are all rounded.

[0010] Preferably, the hollow partition membrane is a thermoplastic polyurethane film, and a layer of ultra-high strength polyethylene fiber woven fabric is laminated in the thermoplastic polyurethane film.

[0011] Preferably, the outer surface of the thermoplastic polyurethane film is treated with a micro-bump texture, with bumps having a diameter of 0.5 mm and a spacing of 2 mm.

[0012] Preferably, a one-way valve is fixedly installed on the delivery pipe, and the one-way valve is a miniature spring-loaded one-way valve.

[0013] Preferably, the bidirectional air pump is an electric bidirectional diaphragm pump.

[0014] Preferably, the outer side of the drone cargo compartment shell is fixedly equipped with multiple connecting buckles that are compatible with and connected to the drone's attachment points.

[0015] Preferably, a plurality of limiting strips are fixedly installed on the inner side wall of the drone cargo compartment shell, which are arranged parallel to each other with the central cylinder. A plurality of limiting grooves adapted to and engaging with the limiting strips are opened on the outer periphery of the drone cargo compartment inner shell. The drone cargo compartment inner shell is engaged and installed in the drone cargo compartment shell through the plurality of limiting grooves and the plurality of limiting strips.

[0016] Preferably, the trachea is flat and made of the same material as the hollow partition membrane. Multiple air holes are provided on the side of the trachea away from the hollow partition membrane, and the trachea is connected to the inner wall of the hollow partition membrane by a discontinuous bonding method.

[0017] The beneficial effects of this utility model are:

[0018] This invention achieves adaptive wrapping and securing of goods by setting up an outer shell and a detachable inner shell for the drone cargo compartment, along with a central cylinder, take-up and release rollers, a hollow partition membrane, and a two-way air pump. After the goods are placed in the cargo compartment, the hollow partition membrane is inflated by the two-way air pump. The thermoplastic polyurethane film composite ultra-high-strength polyethylene fiber woven fabric deforms with the contours of the goods, and the micro-protrusion texture enhances friction to prevent slippage. When air is pumped out, a torsion spring drives the take-up and release rollers to automatically collect the hollow partition membrane. A guide port and a circular baffle ensure smooth take-up and release. The design of a self-resetting take-up and release component, a one-way valve, and a flat air pipe further enhances the practicality, stability, and safety of the equipment. It is suitable for low-altitude transportation of goods of different specifications and effectively solves the problems of poor cargo securing effect and insufficient adaptability of traditional logistics delivery equipment. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of this utility model, the drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 This is a three-dimensional structural diagram of a low-altitude flight delivery device for logistics proposed in this utility model.

[0021] Figure 2 for Figure 1 A three-dimensional structural diagram with the cargo door open;

[0022] Figure 3 This is a structural diagram of the drone cargo compartment shell, connecting buckle, and limiting strip proposed in this utility model;

[0023] Figure 4 This is a partial three-dimensional structural schematic diagram of the present invention;

[0024] Figure 5 for Figure 4 Enlarged view of section A;

[0025] Figure 6 for Figure 4 A schematic diagram of a partial three-dimensional structure;

[0026] Figure 7 This is a cross-sectional structural diagram of the central cylinder portion proposed in this utility model;

[0027] Figure 8 This is a three-dimensional structural diagram of the inner shell of the drone cargo compartment proposed in this utility model;

[0028] Figure 9 for Figure 8 A top-view structural diagram;

[0029] Figure 10 This is a partial cross-sectional view of the hollow partition membrane and trachea portion proposed in this utility model.

[0030] Figure 11 This is a schematic diagram of the bidirectional air pump, delivery pipe, and one-way valve components proposed in this utility model.

[0031] In the diagram: 1. Outer shell of the drone cargo hold; 11. Cargo door; 12. Connecting buckle; 2. Inner shell of the drone cargo hold; 21. Limiting groove; 22. Limiting strip; 3. Center cylinder; 31. Guide port; 4. Take-up and untake-off rollers; 41. Hollow shaft; 42. Hollow partition membrane; 421. Air pipe; 43. Locking strip; 431. Locking groove; 44. Circular baffle; 45. Torsion spring; 5. Two-way air pump; 51. Delivery pipe; 52. One-way valve. Detailed Implementation

[0032] The technical solution of this utility model will now be clearly and completely described with reference to specific embodiments. Obviously, the described embodiments are only a part of the embodiments of this utility model, and not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of this utility model without creative effort are within the scope of protection of this utility model.

[0033] Reference Figure 1-11 A low-altitude flight delivery device for logistics includes a drone cargo hold outer shell 1, a drone cargo hold inner shell 2, a central cylinder 3, multiple take-up and release rollers 4, multiple hollow shafts 41, a bidirectional air pump 5, and two cargo doors 11 arranged in a split configuration.

[0034] The inner shell 2 of the drone cargo compartment is detachably installed inside the outer shell 1 of the drone cargo compartment. The central cylinder 3 is fixedly installed at the center of the bottom inner wall of the drone cargo compartment 1. Multiple hollow shafts 41 are rotatably installed on the bottom inner wall of the drone cargo compartment 1 and are arranged in a circular array with the axis of the central cylinder 3 as the center. The multiple hollow shafts 41 are all located inside the central cylinder 3. Multiple take-up and untake-up rollers 4 are fixedly installed on the corresponding hollow shafts 41. Each of the multiple take-up and untake-up rollers 4 is fixed and wound with an inflatable hollow partition membrane 42. The ends of the multiple hollow partition membranes 42 away from the take-up and untake-up rollers 4 extend to the outside of the central cylinder 3 and are respectively fixedly installed with a locking strip 43. Multiple slots 431 for locking and fixing the locking strip 43 are opened on the inner side wall of the drone cargo compartment inner shell 2.

[0035] Among them, the hollow partition film 42 is a thermoplastic polyurethane film, and a layer of ultra-high strength polyethylene fiber woven fabric is composited in the thermoplastic polyurethane film, which has both rubber elasticity and plastic strength. It can be freely deformed to fit the contour of the goods after inflation, and has good tensile strength and wear and puncture resistance. In order to increase the friction with the goods and prevent the goods from sliding after inflation, and to disperse the pressure through the convex points to reduce local wear, the outer surface of the thermoplastic polyurethane film is treated with micro-convex texture, with a convex point diameter of 0.5mm and a spacing of 2mm.

[0036] A circular baffle 44 is fixedly installed on each of the multiple hollow shafts 41. The top side of the circular baffle 44 abuts against the bottom end of the corresponding take-up and undo roller 4. A torsion spring 45 is fixedly installed on the bottom side of the circular baffle 44 and is movably sleeved on the outside of the hollow shaft 41. The bottom end of the torsion spring 45 is fixedly connected to the bottom inner wall of the drone cargo compartment shell 1. When the locking strip 43 is released, the take-up and undo roller 4 can automatically take in the hollow partition film 42. At the same time, the circular baffle 44 can limit the hollow partition film 42 during the take-up and undo process to avoid entanglement and deviation.

[0037] The bidirectional air pump 5 is fixedly installed on the bottom inner wall of the drone cargo shell 1 and located inside the central cylinder 3. The bidirectional air pump 5 is connected to multiple conveying pipes 51 that are sealed and rotatably connected to the corresponding hollow shafts 41. In order to achieve the conversion between air extraction and inflation by controlling the forward and reverse rotation, and at the same time provide a stable airflow output, the hollow diaphragm 42 can quickly reach the required pressure when inflating to achieve tight wrapping of the goods. When extracting air, it can quickly release air, which is convenient for the roll-up roller 4 to store it. The bidirectional air pump 5 is an electric bidirectional diaphragm pump. The electric bidirectional diaphragm pump is small in size and light in weight, which is suitable for installation inside the drone cargo shell 1 without increasing the overall load of the equipment too much, ensuring the stability and endurance of the drone's low-altitude flight.

[0038] An air pipe 421 is fixedly attached inside the hollow partition film 42, passing through the take-up and untake-down roller 4 and connected to the hollow shaft 41. The air pipe 421 is flat and made of the same material as the hollow partition film 42. Multiple air holes are opened on the side of the air pipe 421 away from the hollow partition film 42. The air pipe 421 is connected to the inner wall of the hollow partition film 42 by a discontinuous adhesive method. When inflated, gas can be evenly introduced into the hollow partition film 42 through the air holes to ensure its overall expansion effect. The discontinuous adhesive design can reduce the pulling on the air pipe 421 during the inflation and deformation of the hollow partition film 42, and avoid damage to the air pipe 421 due to excessive stretching. At the same time, the flat design of the air pipe 421 can reduce the volume occupied when the take-up and untake-down roller 4 is stored. In addition, it will not affect the winding and storage effect of the hollow partition film 42 when stored.

[0039] Two hinged doors 11, arranged in a split configuration, are mounted at the top opening of the drone cargo compartment shell 1, facilitating opening and closing during loading and unloading.

[0040] In this embodiment, in order to provide guidance for the hollow partition film entering and exiting the central cylinder 3 and avoid scratching, multiple guide holes 31 are provided on the inner side wall of the central cylinder 3, and multiple hollow partition films 42 pass through the corresponding guide holes 31 respectively, and the side walls of the multiple guide holes 31 are all rounded.

[0041] In this embodiment, in order to effectively prevent gas leakage due to insufficient negative pressure, which would affect the cargo limit, a one-way valve 52 is fixedly installed on the conveying pipe 51. The one-way valve 52 is a miniature spring-type one-way valve. Since the opening pressure of the miniature spring-type one-way valve is low, it can be directly reversed without setting up an additional airflow pipeline when switching between inflation and deflation.

[0042] In this embodiment, in order to facilitate the connection of the device with the drone and also to facilitate disassembly, a plurality of connecting buckles 12 adapted to the drone's attachment points are fixedly installed on the outside of the drone's cargo compartment shell 1.

[0043] In this embodiment, in order to facilitate the disassembly and replacement of the drone cargo compartment inner shell 2 according to the actual loading needs, and at the same time to ensure the stability of the drone cargo compartment inner shell 2 during use, a plurality of limiting strips 22 are fixedly installed on the inner side wall of the drone cargo compartment outer shell 1, which are parallel to each other with the central cylinder 3. A plurality of limiting grooves 21 adapted to and engaging with the limiting strips 22 are opened on the outer periphery of the drone cargo compartment inner shell 2. The drone cargo compartment inner shell 2 is engaged and installed inside the drone cargo compartment outer shell 1 through the plurality of limiting grooves 21 and the plurality of limiting strips 22.

[0044] Specifically, the motor control line (or electromagnetic coil control line) of the bidirectional air pump 5 is connected to the UAV's flight control system, and the function is automatically switched through the following logic:

[0045] After the cargo is stacked (inflation stage): The flight control system sends a "positive current signal", the bidirectional air pump 5 rotates forward (inflation mode), and inflates the hollow partition membrane 42 to the preset pressure (a pressure sensor for pressure monitoring can be installed in the air circuit for pressure monitoring).

[0046] After the goods are delivered (air extraction stage): The flight control system sends a "reverse current signal", and the bidirectional air pump 5 reverses (air extraction mode) to extract the gas in the hollow partition membrane 42 until the hollow partition membrane 42 is completely contracted (this can be detected by an additional flow sensor or by the operator visually).

[0047] Since the content protected by this application does not involve improvements to software, circuits, and methods, the circuits, electronic components, and module mechanisms involved all adopt existing technologies, which can be fully implemented by those skilled in the art, and need not be elaborated upon.

[0048] Working principle: In use, first, precisely align the limiting groove 21 on the outer periphery of the drone cargo inner shell 2 with the limiting strip 22 on the inner wall of the outer shell, and then push it in axially to complete the installation of the drone cargo inner shell 2. The cooperation between the limiting groove 21 and the limiting strip 22 can effectively limit the lateral displacement of the inner shell during transportation. Hold the clamping strip 43 and pull the hollow partition film 42 to unwind it from the take-up and unwinding roller 4. Then, according to the shape of the actual loaded goods, clamp the clamping strip 43 onto the corresponding groove on the drone cargo inner shell 2. Once the cargo is loaded into slot 431, start the bidirectional air pump 5. The bidirectional air pump 5 blows air into the hollow shaft 41 through the delivery pipe 51, so that the air enters the hollow partition membrane 42 through the air pipe 421 and blows it up to fit tightly against the outside of the cargo, thereby limiting the cargo and preventing displacement during flight. The one-way valve 52 prevents the air pressure in the hollow partition membrane 42 from dropping too quickly. Then close the hatch 11 and connect the hanger on the drone attachment point to the connecting buckle 12.

[0049] When it is necessary to replace the inner shell with a different specification to fit different sized goods, simply take out the drone cargo inner shell 2 before loading, replace it, and snap the new drone cargo inner shell 2 into the required position.

[0050] When unloading is required, release the locking state of the drone mount and connecting buckle 12, and then control the bidirectional air pump 5 to extract the air from the hollow partition membrane 42 to facilitate the unloading operation.

[0051] The present invention provides a detailed description of a low-altitude flight transfer device for logistics. Specific embodiments have been used to illustrate the principles and implementation methods of the present invention. These embodiments are merely illustrative and are intended to aid in understanding the method and core concepts of the present invention. It should be noted that those skilled in the art can make various improvements and modifications to the present invention without departing from its principles, and these improvements and modifications also fall within the scope of protection of the claims of the present invention.

Claims

1. A low-altitude flight delivery device for logistics, characterized in that, It includes the outer shell of the drone cargo compartment (1), the inner shell of the drone cargo compartment (2), the central cylinder (3), multiple take-up and take-down rollers (4), multiple hollow shafts (41), a take-up and take-down self-resetting assembly, a bidirectional air pump (5), and two compartment doors (11) arranged in a bi-directional manner; The inner shell (2) of the drone cargo compartment is detachably installed inside the outer shell (1) of the drone cargo compartment. The central cylinder (3) is fixedly installed at the center of the bottom inner wall of the drone cargo compartment (1). Multiple hollow shafts (41) are rotatably installed on the bottom inner wall of the drone cargo compartment (1) and are arranged in a circular array with the axis of the central cylinder (3) as the center. The multiple hollow shafts (41) are all located inside the central cylinder (3). Multiple take-up and untake-up rollers (4) are respectively fixedly installed on the corresponding hollow shafts (41). Each of the multiple take-up and untake-up rollers (4) is fixed and wound with an inflatable hollow partition film (42). The ends of the multiple hollow partition films (42) away from the take-up and untake-up rollers (4) extend to the outside of the central cylinder (3) and are respectively fixedly installed with clips (43). The inner wall of the drone cargo compartment shell (2) is provided with multiple slots (431) for locking and fixing the clips (43). The retraction and retraction self-resetting assembly is set on the bottom inner wall of the drone cargo compartment shell (1) and connected to multiple hollow shafts (41). The bidirectional air pump (5) is fixedly installed on the bottom inner wall of the drone cargo compartment shell (1) and located inside the central cylinder (3). Multiple delivery pipes (51) are connected to the bidirectional air pump (5) and are sealed and rotatably connected to the corresponding hollow shafts (41). An air pipe (421) that passes through the retraction and retraction roller (4) and is connected to the hollow shaft (41) is fixedly pasted inside the hollow partition membrane (42). Two compartment doors (11) that are arranged in a split shape are hinged to the top opening of the drone cargo compartment shell (1).

2. The low-altitude flight transfer device for logistics according to claim 1, characterized in that: The self-resetting take-up and take-up assembly includes multiple circular baffles (44) and multiple torsion springs (45). Circular baffles (44) are fixedly installed on multiple hollow shafts (41). The top side of the circular baffle (44) abuts against the bottom end of the corresponding take-up and take-up roller (4). A torsion spring (45) is fixedly installed on the bottom side of the circular baffle (44) and is movably sleeved on the outside of the hollow shaft (41). The bottom end of the torsion spring (45) is fixedly connected to the bottom inner wall of the UAV cargo compartment shell (1).

3. The low-altitude flight transfer device for logistics according to claim 1, characterized in that: The inner wall of the central cylinder (3) is provided with multiple guide openings (31), and multiple hollow partition membranes (42) pass through the corresponding guide openings (31) respectively, and the side walls of the multiple guide openings (31) are all rounded.

4. The low-altitude flight transfer device for logistics according to claim 1, characterized in that: The hollow partition membrane (42) is a thermoplastic polyurethane film, and a layer of ultra-high strength polyethylene fiber woven fabric is composited in the thermoplastic polyurethane film.

5. A low-altitude flight transfer device for logistics according to claim 4, characterized in that: The outer surface of the thermoplastic polyurethane film is treated with a micro-bump texture, with bumps having a diameter of 0.5 mm and a spacing of 2 mm.

6. A low-altitude flight transfer device for logistics according to claim 1, characterized in that: A one-way valve (52) is fixedly installed on the delivery pipe (51), and the one-way valve (52) is a miniature spring-loaded one-way valve.

7. A low-altitude flight transfer device for logistics according to claim 1, characterized in that: The bidirectional air pump (5) is an electric bidirectional diaphragm pump.

8. A low-altitude flight transfer device for logistics according to claim 1, characterized in that: The outer side of the drone cargo compartment shell (1) is fixedly equipped with multiple connecting buckles (12) that are adapted to and connected to the drone's attachment points.

9. A low-altitude flight transfer device for logistics according to claim 1, characterized in that: Multiple limiting strips (22) are fixedly installed on the inner wall of the drone cargo container shell (1) and are arranged parallel to each other with the central cylinder (3). Multiple limiting grooves (21) that are adapted to and engage with the limiting strips (22) are opened on the outer periphery of the drone cargo container inner shell (2). The drone cargo container inner shell (2) is engaged and installed inside the drone cargo container shell (1) through multiple limiting grooves (21) and multiple limiting strips (22).

10. A low-altitude flight transfer device for logistics according to claim 1, characterized in that: The air tube (421) is flat and made of the same material as the hollow partition membrane (42). Multiple air holes are provided on the side of the air tube (421) away from the hollow partition membrane (42), and the air tube (421) is connected to the inner wall of the hollow partition membrane (42) by a discontinuous bonding method.

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