A buffer structure for a launch system based on an unmanned aerial vehicle (UAV)

Abstract

This invention provides a buffer structure for a launch system mounted on a drone, comprising a drone and a buffer structure at its bottom. The buffer structure includes a buffer component 1 and a buffer component 2 slidably connected to the buffer component 1. The launch system is mounted on the buffer component 2. The buffer component 2 is connected to a rotating rod assembly, which is connected to the drone. The rotating rod assembly is also connected to an airbag buffer assembly, which is mounted on a support frame at the bottom of the drone. This invention provides a buffer structure for a launch system mounted on a drone, avoiding the problems of insufficient launch accuracy and damage to the drone caused by large recoil during launch.

Description

Technical Field

[0001] This utility model belongs to the field of cold launch technology, specifically relating to a buffer structure for a launch system based on a drone. Background Technology

[0002] With the continuous development of aerospace and natural science and technology, the demand for payloads such as drones, high-altitude probes, and artificial rainmaking projectiles is increasing. Existing payloads mainly use hot launch and cold launch methods such as gas, compressed air, and gas-steam. Although these launch methods can achieve the intended launch mission objectives, they have the practical problem of large recoil, which is particularly evident in small drones. For example, if the launch system is mounted on a drone, the entire drone will be subjected to recoil force, causing severe vibration. This not only easily leads to insufficient launch accuracy but may also cause vibration damage to the drone. Utility Model Content

[0003] The purpose of this invention is to provide a buffer structure for a launch system based on a drone, which solves the technical problem that the launch system has insufficient launch accuracy and causes damage to the drone due to the large recoil force during launch.

[0004] A launch system buffer structure based on a drone includes a drone, a buffer structure 1 is provided at the bottom of the drone, the buffer structure 1 includes a buffer component 1 and a buffer component 2 slidably connected to the buffer component 1, a launch system is provided on the buffer component 2, the buffer component 2 is connected to a rotating rod assembly, the rotating rod assembly is connected to the drone 2, the rotating rod assembly is connected to an airbag buffer assembly, and the airbag buffer assembly is provided on a support frame at the bottom of the drone 2.

[0005] The buffer assembly includes a horizontal column horizontally disposed below the drone, a slider slidably disposed on the horizontal column, and two springs respectively disposed on both sides of the slider. There are two horizontal columns, and fixed seats are fixedly disposed at both ends of the horizontal columns. The fixed seats are positioned below the drone. The springs are slidably disposed on the horizontal columns.

[0006] The second buffer assembly includes a support base fixedly connected to the bottom end of the slider, a guide post with one end horizontally passing through the support base, a spring I sleeved on the guide post, and a baffle fixed to one end of the guide post. The support base is disposed between the spring I and the baffle. There are two guide posts. A movable seat is fixedly disposed at the other end of the guide post. A launching system is disposed on the support base.

[0007] The rotating rod assembly includes a rotating rod with one end hinged to the movable seat and a positioning seat hinged to the other end of the rotating rod. The positioning seat is fixedly mounted on the support frame, and the support frame is fixed to the bottom of the UAV II.

[0008] The airbag cushioning assembly includes an arc-shaped column with one end fixedly connected to the bottom end of the rotating rod, and an arc-shaped cylinder slidably connected to the other end of the arc-shaped column. The other end of the arc-shaped cylinder is fixed to the support frame. The arc-shaped cylinder is connected to one end of the air tube, and the other end of the air tube is connected to the airbag.

[0009] The arc center of the arc-shaped column and the arc-shaped cylinder is located at the hinge center of the positioning seat.

[0010] A piston is provided at the other end of the arc-shaped column, and the piston is slidably disposed in the arc-shaped cylinder.

[0011] The airbag is positioned and supported on the support frame.

[0012] For any technical details not explicitly stated in this solution, those skilled in the art can operate based on conventional understanding and practice. The principle is to solve the technical problems described in this solution. As for equipment installation, debugging, and adjustments to part models and dimensions, these can be adapted to the actual situation and will not be detailed here.

[0013] This utility model achieves the following significant effects:

[0014] (1) A buffer structure is provided, including buffer component one and buffer component two. The two cooperate with each other. The recoil force causes the slider to move on the horizontal column and contact the spring two to achieve the first buffer. Then the support seat slides on the guide column and contacts the spring one to achieve the second buffer. The two buffers are carried out simultaneously, which greatly offsets the recoil force, ensures the launch accuracy, and reduces the damage to the UAV one.

[0015] (2) A rotating rod assembly is provided, which works in conjunction with the airbag buffer assembly. The two work together. When the guide column moves, it pushes the rotating rod assembly to work, the rotating rod rotates, and drives the arc-shaped column to slide in the arc-shaped cylinder. Air is pumped into the airbag through the air tube. This process achieves the buffering effect again. In addition, the air pressure in the airbag increases, which helps the arc-shaped column to reset in order to achieve balance with the outside world.

[0016] (3) In this scheme, the recoil force is reduced to a minimum through the three-stage buffering of buffer component one, buffer component two and airbag buffer component. After actual simulation and verification, the launch has high accuracy, which is 78-89% higher than the existing technology. Furthermore, according to the feedback of the vibration sensor, the damage to the UAV is reduced by 89-94%. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the launch system buffer structure in this utility model.

[0018] Figure 2 This is a front view of the launch system buffer structure in this utility model.

[0019] Figure 3 This is a schematic diagram of the first buffer structure in this utility model.

[0020] Figure 4 This is a schematic diagram of the connection structure of the airbag buffer assembly in this utility model.

[0021] The attached diagram is labeled as follows: 1. UAV 1; 2. Fixed base; 21. Horizontal column; 22. Spring 2; 3. Baffle; 4. Support base; 41. Slider; 5. Launch system; 6. Spring 1; 7. Guide column; 8. Movable base; 9. Rotating rod; 10. Positioning base; 11. Air tube; 12. Support frame; 121. UAV 2; 13. Airbag; 14. Arc-shaped cylinder; 15. Arc-shaped column. Detailed Implementation

[0022] To more clearly illustrate the technical features of this solution, the following detailed implementation method will be used to explain the solution.

[0023] See Figures 1-4 A launch system buffer structure based on a drone includes a drone 1. The bottom of the drone 1 is provided with a buffer structure 1. The buffer structure 1 includes a buffer component 1 and a buffer component 2 slidably connected to the buffer component 1. The launch system 5 is provided on the buffer component 2. The buffer component 2 is connected to a rotating rod component. The rotating rod component is connected to the drone 2 121. The rotating rod component is connected to an airbag buffer component. The airbag buffer component is provided on a support frame 12 at the bottom of the drone 2 121.

[0024] In the attached diagram, the launch system 5 in this scheme is a schematic diagram and can be installed and implemented according to actual circumstances. To simplify the design, UAV 1 and UAV 2 121 are only shown schematically in the attached diagram and are not drawn in detail.

[0025] The buffer assembly includes a horizontal column 21 horizontally positioned below the UAV 1, a slider 41 slidably positioned on the horizontal column 21, and springs 22 respectively positioned on both sides of the slider 41. There are two horizontal columns 21, and fixed seats 2 are fixedly positioned at both ends of the horizontal column 21. The fixed seats 2 are positioned below the UAV 1. Springs 22 are slidably positioned on the horizontal column 21.

[0026] The second buffer assembly includes a support base 4 fixedly connected to the bottom end of the slider 41, a guide post 7 with one end horizontally passing through the support base 4, a spring 6 sleeved on the guide post 7, and a baffle 3 fixed to one end of the guide post 7. The support base 4 is located between the spring 6 and the baffle 3. There are two guide posts 7. A movable seat 8 is fixedly installed at the other end of the guide post 7. A launching system 5 is installed on the support base 4.

[0027] The rotating rod assembly includes a rotating rod 9 with one end hinged to the movable seat 8 and a positioning seat 10 with the other end hinged to the rotating rod 9. The positioning seat 10 is fixedly mounted on the support frame 12, and the support frame 12 is fixed to the bottom end of the UAV 2 121.

[0028] See Figure 4 The airbag cushioning assembly includes an arc-shaped column 15 with one end fixedly connected to the bottom end of the rotating rod 9, and an arc-shaped cylinder 14 slidably connected to the other end of the arc-shaped column 15. The other end of the arc-shaped cylinder 14 is fixed on the support frame 12. The arc-shaped cylinder 14 is connected to one end of the air tube 11, and the other end of the air tube 11 is connected to the airbag 13.

[0029] The arc center of the arc column 15 and the arc cylinder 14 is located on the hinge center of the positioning seat 10.

[0030] A piston is provided at the other end of the arc-shaped column 15, and the piston is slidably disposed in the arc-shaped cylinder 14. The piston is located in the arc-shaped cylinder 14, and for the sake of simplifying the design, it will not be described or labeled in detail.

[0031] The airbag 13 is positioned and supported on the support frame 12.

[0032] For details not described in the text of this plan, please refer to the attached diagrams.

[0033] The working process of this utility model is as follows:

[0034] A buffer structure is provided, including buffer component one and buffer component two. The two work together. When the launching system 5 is working, the strong recoil force causes the slider 41 to move on the horizontal column 21. The slider 41 contacts the spring 22, realizing the first buffer.

[0035] Then, slider 41 drives support base 4 to slide on guide post 7 and contact spring 6 to achieve a second buffer. The two buffers are carried out simultaneously, which greatly offsets the recoil force, ensures launch accuracy, and reduces damage to UAV 1.

[0036] A rotating rod assembly is provided, which works in conjunction with the airbag buffer assembly. When the guide post 7 moves, it pushes the rotating rod assembly to work, causing the rotating rod 9 to rotate and drive the arc-shaped post 15 to slide in the arc-shaped cylinder 14. At this time, the internal air pressure of the arc-shaped cylinder 14 increases, and gas is pumped into the airbag 13 through the air pipe 11, causing the airbag 13 to expand. This process achieves the buffering effect once again. In addition, as the air pressure in the airbag 13 increases, in order to achieve balance with the outside environment, the larger airbag in the airbag 13 will push the piston to reset, which helps the arc-shaped post 15 to reset.

[0037] This device actually uses two drones to carry the launch system into the air, which increases lift and avoids the problem of insufficient power from one drone. At the same time, the position of the two drones can be adjusted to a certain extent through the rotating rod assembly, which also has high flexibility and practical application value.

[0038] The technical features of this utility model not described can be implemented by or by using existing technology, and will not be repeated here. Of course, the above description is not a limitation of this utility model, and this utility model is not limited to the examples above. Any changes, modifications, additions or substitutions made by those skilled in the art within the scope of this utility model should also be within the protection scope of this utility model.

Claims

1. A launch system buffer structure based on an unmanned aerial vehicle (UAV), comprising an UAV (1), characterized in that, The bottom end of the UAV 1 (1) is provided with a buffer structure 1. The buffer structure 1 includes a buffer component 1 and a buffer component 2 that is slidably connected to the buffer component 1. The buffer component 2 is provided with a launch system (5). The buffer component 2 is connected to a rotating rod component. The rotating rod component is connected to the UAV 2 (121). The rotating rod component is connected to an airbag buffer component. The airbag buffer component is provided on a support frame (12) at the bottom end of the UAV 2 (121).

2. The buffer structure of a launch system based on a UAV as described in claim 1, characterized in that, The buffer assembly includes a horizontal column (21) horizontally disposed below the UAV (1), a slider (41) slidably disposed on the horizontal column (21), and two springs (22) respectively disposed on both sides of the slider (41). There are two horizontal columns (21), and fixed seats (2) are fixedly disposed at both ends of the horizontal column (21). The fixed seats (2) are positioned below the UAV (1). The springs (22) are slidably disposed on the horizontal column (21).

3. The buffer structure for a launch system based on a UAV as described in claim 2, characterized in that, The second buffer assembly includes a support base (4) fixedly connected to the bottom end of the slider (41), a guide post (7) with one end horizontally passing through the support base (4), a spring (6) sleeved on the guide post (7), and a baffle (3) fixed to one end of the guide post (7). The support base (4) is located between the spring (6) and the baffle (3). There are two guide posts (7). A movable seat (8) is fixedly provided at the other end of the guide post (7). A launching system (5) is provided on the support base (4).

4. The buffer structure of a launch system based on a UAV as described in claim 3, characterized in that, The rotating rod assembly includes a rotating rod (9) with one end hinged to the movable seat (8) and a positioning seat (10) with the other end hinged to the rotating rod (9). The positioning seat (10) is fixedly mounted on the support frame (12), and the support frame (12) is fixed to the bottom of the UAV II (121).

5. The buffer structure of a launch system based on a UAV as described in claim 4, characterized in that, The airbag cushioning assembly includes an arc-shaped column (15) with one end fixedly connected to the bottom end of the rotating rod (9), and an arc-shaped cylinder (14) slidably connected to the other end of the arc-shaped column (15). The other end of the arc-shaped cylinder (14) is fixed on the support frame (12). The arc-shaped cylinder (14) is connected to one end of the air tube (11), and the other end of the air tube (11) is connected to the airbag (13). The arc center of the arc column (15) and the arc cylinder (14) is located on the hinge center of the positioning seat (10).

6. The buffer structure of a launch system based on a UAV as described in claim 5, characterized in that, A piston is provided at the other end of the arc-shaped column (15), and the piston is slidably disposed in the arc-shaped cylinder (14).

7. The buffer structure of a launch system based on a UAV as described in claim 5, characterized in that, The airbag (13) is positioned and supported on the support frame (12).

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