Unmanned aerial vehicle landing protection device

Abstract

The utility model discloses an unmanned aerial vehicle landing protection device which comprises a supporting frame, a pressure relief mechanism is arranged on the supporting frame, the pressure relief mechanism comprises a transverse rod, an air bag, a bottom sleeve, a pressure relief pipe, a one-way mechanism, a threaded ring, a threaded section, a sealing sleeve and a pressure adjusting mechanism, the transverse rod is installed on the supporting frame, the air bag is connected to the transverse rod in a sleeved mode, and the bottom sleeve is arranged on the bottom sleeve. The one-way mechanism can be opened to allow gas to be discharged through the gas outlet pipe, so that impact force is relieved, the unmanned aerial vehicle is protected against damage, the pressure adjusting mechanism allows an operator to adjust pressure relief pressure according to needs, the compression degree of a spring is changed by rotating a threaded section, and then sealing pressure is adjusted. The design not only improves the safety of the unmanned aerial vehicle during landing, but also enhances the adaptability and flexibility of the equipment.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicle landing protection, and more specifically, to a unmanned aerial vehicle landing protection device. Background Art

[0002] In the current field of drone technology, drone landing protection devices usually use softer materials to absorb the impact force generated during landing to protect the drone from damage. The design concept of these protection devices is based on the fact that soft materials can alleviate the impact to a certain extent and reduce potential damage to the drone. However, this protection method is not perfect. During the landing process of the drone, once the impact force exceeds the tolerance range of the soft material, these protection devices will not be able to effectively play their due role. In this case, the drone may suffer serious damage or even be completely scrapped.

[0003] Although soft materials provide necessary protection to a certain extent, their limitations become particularly evident when faced with high-intensity impacts. This is because when the impact force exceeds the structural strength of the soft materials, these materials lose their energy absorption properties and can no longer provide effective cushioning for the drone. This limitation means that existing drone landing protection devices may not be able to ensure the safety of drones when facing extreme landing conditions or unexpected situations, thus posing a potential risk to the drone's service life and operational safety. Utility Model Content

[0004] 1. Technical issues to be solved

[0005] In view of the problems existing in the prior art, the utility model provides a drone landing protection device to solve the technical problems mentioned in the background technology.

[0006] (II) Technical solution

[0007] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: a UAV landing protection device, comprising a support frame, a pressure relief mechanism is arranged on the support frame, the pressure relief mechanism comprises a transverse rod, an airbag, a bottom sleeve, a pressure relief pipe, a one-way mechanism, a threaded ring, a threaded segment, a sealing sleeve and a pressure regulating mechanism, the transverse rod is installed on the support frame, the airbag is sleeved on the transverse rod, the bottom sleeve is installed on the airbag, the pressure relief pipe is connected to the bottom sleeve, the one-way mechanism is installed on the pressure relief pipe, the threaded ring is installed in the pressure relief pipe, the threaded segment is threadedly connected to the threaded ring, the sealing sleeve is installed on the threaded segment, and the pressure regulating mechanism is installed on the threaded segment.

[0008] The utility model is further configured that an air outlet pipe is connected to the side wall of the pressure relief pipe, and the sealing sleeve is attached to the inner wall of the pressure relief pipe. The design of the air outlet pipe ensures the continuity of pressure relief.

[0009] The utility model is further configured that the one-way mechanism includes a fitting disk and a one-way disk, the fitting disk is installed in the pressure relief pipe, and the one-way disk is pressed on the fitting disk. The design of the one-way mechanism ensures the continuity of pressure relief.

[0010] The utility model is further configured that a spring is arranged on the threaded section, the spring is pressed on the one-way disk, a rotating sleeve is coaxially arranged on the threaded section, and the design of the spring ensures the generation of pressure.

[0011] The utility model is further configured that a receiving sleeve is arranged in the pressure relief pipe, a sealing groove is opened on the sealing sleeve, and the sealing groove is threadedly connected to the receiving sleeve. The design of the sealing groove ensures the sealing effect.

[0012] The utility model is further configured as follows: the pressure regulating mechanism includes an intermediate tube, a limiting sleeve and a stopper; the intermediate tube is slidably connected in the threaded section; a bottom groove is provided on the intermediate tube; the stopper is slidably connected in the bottom groove; a limiting sleeve is installed in the pressure relief tube; the intermediate tube is slidably connected in the limiting sleeve; and the design of the pressure regulating mechanism ensures the continuity of pressure regulation.

[0013] The utility model is further configured that a plurality of guide plates are arranged in the middle tube, a pressure rod is arranged on the stopper, and the pressure rod is slidably connected between the plurality of guide plates. The design of the guide plates ensures convenient discharge of airflow.

[0014] The utility model is further configured that the pressure rod is provided with a pressure head, the pressure head is provided with a return spring, the intermediate tube is provided with a pull plate, and the return spring abuts against the pull plate.

[0015] (III) Beneficial effects

[0016] Compared with the prior art, the utility model provides a UAV landing protection device, which has the following beneficial effects:

[0017] 1. The pressure relief mechanism achieves effective buffering and pressure regulation when the drone lands through the combination of the airbag and the pressure relief pipe, as well as the cooperation of the one-way mechanism and the pressure regulating mechanism. When the drone lands, the airbag first contacts the ground to absorb the impact force. When the pressure in the airbag exceeds the set value, the one-way mechanism will open, allowing the gas to be discharged through the outlet pipe, thereby reducing the impact force and protecting the drone from damage. The pressure regulating mechanism allows the operator to adjust the pressure of the pressure relief as needed, and change the compression degree of the spring by turning the threaded section, thereby adjusting the sealing pressure. This design not only improves the safety of the drone during landing, but also enhances the adaptability and flexibility of the equipment.

[0018] 2. The design of the one-way mechanism ensures that the gas can only be discharged from the airbag in one direction, preventing gas backflow. When the pressure in the airbag exceeds the elastic force of the spring, the one-way disc will separate from the fitting disc, allowing the gas to be discharged through the outlet pipe. This one-way flow characteristic ensures the stability and safety of the drone during landing and avoids accidents caused by gas backflow. At the same time, the design of the one-way mechanism simplifies the operation process and improves the reliability and durability of the equipment.

[0019] 3. The pressure regulating mechanism allows the operator to flexibly adjust the pressure in the airbag according to the landing situation and environmental conditions of the drone. By pressing the pressure head, the operator can control the position of the block, thereby adjusting the leakage rate of the gas in the airbag. The setting of the return spring ensures the return of the block, making the pressure regulation process smoother and more precise. This design not only improves the safety and stability of the drone during landing, but also enhances the adaptability and operability of the equipment. The flexibility and precision of the pressure regulating mechanism are crucial to ensure that the drone can land safely under various conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 This is a schematic diagram of the overall structure of a UAV landing protection device in the utility model;

[0021] Figure 2 It is a schematic cross-sectional view of the airbag in the utility model;

[0022] Figure 3 It is a structural schematic diagram of the pressure relief mechanism in the utility model;

[0023] Figure 4 It is a schematic cross-sectional structure diagram of the pressure relief pipe in the utility model;

[0024] Figure 5 It is a schematic cross-sectional structure diagram of the intermediate tube in the utility model.

[0025] In the figure: 1. support frame; 2. transverse rod; 3. airbag; 4. bottom sleeve; 5. pressure relief pipe; 6. threaded ring; 7. threaded section; 8. sealing sleeve; 9. outlet pipe; 10. fitting disk; 11. one-way disk; 12. spring; 13. rotating sleeve; 14. receiving sleeve; 15. sealing groove; 16. intermediate tube; 17. limiting sleeve; 18. block; 19. bottom groove; 20. guide sheet; 21. pressure rod; 22. pressure head; 23. return spring; 24. pull plate. DETAILED DESCRIPTION

[0026] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application can be combined with each other. The present utility model will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0027] It should be noted that, unless otherwise specified, all technical and scientific terms used in this application have the same meanings as commonly understood by ordinary technicians in the technical field to which this application belongs.

[0028] In the present invention, unless otherwise specified, directions such as "up" and "down" are usually used in reference to the directions shown in the drawings, or in reference to the vertical, perpendicular or gravity direction; similarly, for ease of understanding and description, "left" and "right" are usually used in reference to the left and right shown in the drawings; "inside" and "outside" refer to the inside and outside relative to the outline of each component itself, but the above-mentioned directions are not used to limit the present invention.

[0029] See also Figure 1-5 A landing protection device for an unmanned aerial vehicle comprises a support frame 1, a pressure relief mechanism is arranged on the support frame 1, the pressure relief mechanism comprises a transverse rod 2, an airbag 3, a bottom sleeve 4, a pressure relief pipe 5, a one-way mechanism, a threaded ring 6, a threaded section 7, a sealing sleeve 8 and a pressure regulating mechanism, the transverse rod 2 is mounted on the support frame 1, the airbag 3 is sleeved on the transverse rod 2, the bottom sleeve 4 is mounted on the airbag 3, the pressure relief pipe 5 is connected to the bottom sleeve 4, the one-way mechanism is mounted on the pressure relief pipe 5, the threaded ring 6 is mounted in the pressure relief pipe 5, the threaded section 7 is threadedly connected to the threaded ring 6, and the sealing sleeve 8 is mounted on the threaded ring 6. On the groove section 7, the pressure regulating mechanism is installed on the threaded section 7, the side wall of the pressure relief pipe 5 is connected with an air outlet pipe 9, the sealing sleeve 8 is fitted on the inner wall of the pressure relief pipe 5, the one-way mechanism includes a fitting disk 10 and a one-way disk 11, the fitting disk 10 is installed in the pressure relief pipe 5, the one-way disk 11 is pressed on the fitting disk 10, a spring 12 is provided on the threaded section 7, the spring 12 is pressed on the one-way disk 11, a rotating sleeve 13 is coaxially provided on the threaded section 7, a receiving sleeve 14 is provided in the pressure relief pipe 5, a sealing groove 15 is opened on the sealing sleeve 8, and the sealing groove 15 is threadedly connected to the receiving sleeve 14.

[0030] In this embodiment, when the drone lands, the airbag 3 will first hit the ground, and then when the pressure exceeds the elastic force of the spring 12, the seals of the one-way disk 11 and the fitting disk 10 will be released, and then the gas in the airbag 3 will be discharged through the outlet pipe 9, thereby playing a corresponding buffering role. When the pressure of the pressure relief needs to be adjusted, first rotate the threaded section 7. Since the threaded section 7 is threadedly connected to the threaded ring 6, it can drive the sealing ring to move up and down, and the spring 12 is compressed synchronously, and then the elastic force of the spring 12 will be changed, thereby changing the sealing pressure. Since the sealing sleeve 8 can move synchronously, when the pressure relief pressure needs to increase, the follow-up sealing sleeve 8 blocks the outlet pipe 9, which can reduce the opening degree of the outlet pipe 9, thereby completing the adjustment process. When the outlet pipe 9 needs to be completely sealed, the sealing groove 15 is threadedly connected to the receiving sleeve 14, thereby completing the sealing process.

[0031] See also Figure 4 and Figure 5As an implementation method of the pressure regulating mechanism: the pressure regulating mechanism includes an intermediate tube 16, a limiting sleeve 17 and a stopper 18, the intermediate tube 16 is slidably connected in the threaded section 7, a bottom groove 19 is opened on the intermediate tube 16, the stopper 18 is slidably connected in the bottom groove 19, the limiting sleeve 17 is installed in the pressure relief pipe 5, the intermediate tube 16 is slidably connected in the limiting sleeve 17, a plurality of guide plates 20 are arranged in the intermediate tube 16, a pressure rod 21 is arranged on the stopper 18, the pressure rod 21 is slidably connected between the plurality of guide plates 20, a pressure head 22 is arranged on the pressure head 22, a return spring 23 is arranged on the intermediate tube 16, a pull plate 24 is arranged on the intermediate tube 16, and the return spring 23 abuts against the pull plate 24.

[0032] More specifically, when the pressure in the airbag 3 needs to be adjusted, first press on the pressure head 22. Since the pressure rod 21 is connected to the pressure head 22 and the block 18, then release the block 18 and the bottom groove 19, and then the internal gas leaks out through the airbag 3. The return of the block 18 is guaranteed by the return spring 23, and then the pressure adjustment process can be completed.

[0033] In summary, when the overall equipment is in use or running: when the drone lands, the airbag 3 will first hit the ground, and then when the pressure exceeds the elastic force of the spring 12, the seal of the one-way disk 11 and the fitting disk 10 will be released, and then the gas in the airbag 3 will be discharged through the outlet pipe 9, thereby playing a corresponding buffering role. When the pressure of the pressure relief needs to be adjusted, first rotate the threaded section 7. Since the threaded section 7 is threadedly connected to the threaded ring 6, it can drive the sealing ring to move up and down, and the spring 12 is compressed synchronously, and then the elastic force of the spring 12 will be changed, thereby changing the sealing pressure. Since the sealing sleeve 8 can move synchronously, when the pressure relief pressure needs to increase, the follow-up sealing sleeve 8 blocks the outlet pipe 9, which can reduce the opening degree of the outlet pipe 9, thereby completing the adjustment process. When the outlet pipe 9 needs to be completely sealed, the sealing groove 15 is threadedly connected to the receiving sleeve 14, thereby completing the sealing process.

[0034] When the pressure in the airbag 3 needs to be adjusted, first press on the pressure head 22. Since the pressure rod 21 is connected to the pressure head 22 and the block 18, then release the block 18 and the bottom groove 19, and then the internal gas leaks out through the airbag 3. The return of the block 18 is guaranteed by the return spring 23, and then the pressure adjustment process can be completed.

[0035] In all the schemes mentioned above, the connection between two parts can be selected according to actual conditions by welding, bolt and nut matching connection, bolt or screw connection or other well-known connection methods, which are not described here one by one. In the above, all fixed connections are preferably welded. Although the embodiments of the utility model have been shown and described, it can be understood by ordinary technicians in this field that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principle and spirit of the utility model. The scope of the utility model is defined by the attached claims and their equivalents.

Claims

1. A drone landing protection device, comprising a support frame (1), characterized in that: The support frame (1) is provided with a pressure relief mechanism, which comprises a transverse rod (2), an airbag (3), a bottom sleeve (4), a pressure relief pipe (5), a one-way mechanism, a threaded ring (6), a threaded section (7), a sealing sleeve (8) and a pressure regulating mechanism. The transverse rod (2) is mounted on the support frame (1), the airbag (3) is sleeved on the transverse rod (2), the bottom sleeve (4) is mounted on the airbag (3), the pressure relief pipe (5) is connected to the bottom sleeve (4), the one-way mechanism is mounted on the pressure relief pipe (5), the threaded ring (6) is mounted in the pressure relief pipe (5), the threaded section (7) is threadedly connected to the threaded ring (6), the sealing sleeve (8) is mounted on the threaded section (7), and the pressure regulating mechanism is mounted on the threaded section (7).

2. The UAV landing protection device according to claim 1 is characterized in that: An air outlet pipe (9) is connected to the side wall of the pressure relief pipe (5), and a sealing sleeve (8) is attached to the inner wall of the pressure relief pipe (5).

3. The UAV landing protection device according to claim 2 is characterized in that: The one-way mechanism comprises a bonding disc (10) and a one-way disc (11); the bonding disc (10) is installed in the pressure relief pipe (5), and the one-way disc (11) is pressed on the bonding disc (10).

4. The UAV landing protection device according to claim 3 is characterized by: The threaded section (7) is provided with a spring (12), the spring (12) presses on the one-way disk (11), and a rotating sleeve (13) is coaxially provided on the threaded section (7).

5. The UAV landing protection device according to claim 4 is characterized in that: A receiving sleeve (14) is arranged inside the pressure relief pipe (5), a sealing groove (15) is provided on the sealing sleeve (8), and the sealing groove (15) is threadedly connected to the receiving sleeve (14).

6. The UAV landing protection device according to claim 5 is characterized by: The pressure regulating mechanism comprises an intermediate tube (16), a limiting sleeve (17) and a stopper (18); the intermediate tube (16) is slidably connected in the threaded section (7); a bottom groove (19) is provided on the intermediate tube (16); the stopper (18) is slidably connected in the bottom groove (19); a limiting sleeve (17) is installed in the pressure relief tube (5); and the intermediate tube (16) is slidably connected in the limiting sleeve (17).

7. The UAV landing protection device according to claim 6 is characterized by: A plurality of guide plates (20) are arranged in the intermediate tube (16), a pressure rod (21) is arranged on the stopper (18), and the pressure rod (21) is slidably connected between the plurality of guide plates (20).

8. The UAV landing protection device according to claim 7 is characterized by: The pressure rod (21) is provided with a pressure head (22), the pressure head (22) is provided with a return spring (23), the intermediate tube (16) is provided with a pull plate (24), and the return spring (23) abuts against the pull plate (24).

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