Landing buffer device for unmanned aerial vehicle

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, and discloses an unmanned aerial vehicle landing buffer device which comprises an unmanned aerial vehicle body, the outer surface of the bottom of a supporting leg is fixedly connected with a containing cylinder, a piston cylinder is arranged below the containing cylinder, and the outer surface of the bottom of a piston rod is fixedly connected with a chassis. The other end of the piston rod is fixedly connected with a piston disc, the piston disc is movably connected with the interior of the piston cylinder, and an air bag is arranged on the inner surface of the containing cylinder. When the unmanned aerial vehicle body lands, a chassis makes contact with the ground, the chassis drives a piston rod to enable a piston disc to move in a piston barrel, an air bag is expanded, a connecting pipe is blocked through cooperation with a blocking block, air pressure backflow is avoided, and therefore the air bag is expanded through movement of the piston disc in the piston barrel; in this way, the impact force generated when the unmanned aerial vehicle body lands is buffered, a good buffering effect is achieved, and the safety of the unmanned aerial vehicle body is better guaranteed.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a landing buffer device for UAVs. Background Technology

[0002] Unmanned aerial vehicles (UAVs) are unmanned aircraft controlled by radio remote control equipment and their own program control devices, or operated autonomously by an onboard computer, either completely or intermittently. UAVs can be divided into military and civilian applications based on their application fields.

[0003] In existing technologies, most drone landing buffer devices use shock-absorbing springs to buffer the impact force. The rubber base first contacts the ground and transmits the vibration force generated by the ground to the shock-absorbing spring. The shock-absorbing spring and the inner shock-absorbing rod absorb the force significantly. The shock-absorbing spring can buffer the drone's landing. However, relying solely on the shock-absorbing spring for buffering and shock absorption is prone to shaking during use, resulting in unstable shock absorption effect for the drone. Therefore, a landing buffer device for drones is proposed. Utility Model Content

[0004] In view of the shortcomings of the prior art, this utility model provides a landing buffer device for drones to solve the problems mentioned in the background art.

[0005] To achieve the above objectives, this utility model provides the following technical solution: a landing buffer device for unmanned aerial vehicles (UAVs), comprising a UAV body, a plurality of supporting feet on the outer surface of the UAV body, a receiving cylinder fixedly connected to the bottom outer surface of the supporting feet, a piston cylinder below the receiving cylinder, a piston rod movably inserted into the inner surface of the piston cylinder, a chassis fixedly connected to the bottom outer surface of the piston rod, a piston disc fixedly connected to the other end of the piston rod, the piston disc movably connected to the interior of the piston cylinder, and an airbag on the inner surface of the receiving cylinder.

[0006] Furthermore, a connecting pipe is fixedly connected to the top outer surface of the piston cylinder, and a connecting pipe is fixedly connected to the top outer surface of the connecting pipe. The connecting pipe is connected to the airbag. A fixed plate is fixedly connected to the inner surface of the connecting pipe. A spring is fixedly connected to the bottom outer surface of the fixed plate. A blocking block is fixedly connected to the bottom outer surface of the spring. The blocking block is movably fitted inside the connecting pipe. A guide rod is fixedly connected to the outer surface of the blocking block. The guide rod movably passes through the outer surface of the fixed plate. The spring is sleeved on the outside of the guide rod.

[0007] Furthermore, an air supply pipe is fixedly connected to the outer surface of the airbag, and the other end of the air supply pipe extends to the outside of the receiving cylinder. A sealing plug is threaded to the end of the air supply pipe located outside the receiving cylinder.

[0008] Furthermore, a return pipe is fixedly connected to the top outer surface of the piston cylinder, and a one-way valve is installed inside the return pipe. The flow direction of the one-way valve is from the outside of the return pipe to the inside of the piston cylinder, and a through hole is opened on the bottom outer surface of the piston cylinder.

[0009] Furthermore, a counterweight is fixedly connected to the bottom outer surface of the chassis.

[0010] Furthermore, the plug is a frustum-shaped block that is thicker at the top and thinner at the bottom, and a sealing gasket is fixedly connected to the outer surface of the plug.

[0011] Furthermore, the outer surface of the fixed disk is provided with multiple through slots.

[0012] Compared with the prior art, the beneficial effects of this utility model are:

[0013] This drone uses a landing cushioning device. When the drone body lands, the chassis contacts the ground. The chassis drives the piston rod, causing the piston disc to move inside the piston cylinder, which inflates the airbag. In conjunction with the plug block, the connecting pipe is blocked to prevent air pressure backflow. Thus, the movement of the piston disc inside the piston cylinder causes the airbag to inflate. This method buffers the impact force when the drone body lands, achieving a better cushioning effect and better ensuring the safety of the drone body. Attached Figure Description

[0014] Figure 1 This is a front view structural diagram of the present invention;

[0015] Figure 2 This is a schematic diagram of the piston cylinder and related structures of this utility model;

[0016] Figure 3 This is a schematic diagram of the internal structure of the piston cylinder of this utility model;

[0017] Figure 4 This utility model Figure 3 Enlarged structural diagram at point A in the middle.

[0018] In the diagram: 1. Main body of the drone; 2. Support legs; 3. Receiving cylinder; 4. Piston cylinder; 5. Piston rod; 6. Chassis; 7. Piston disc; 8. Airbag; 9. Connecting pipe; 10. Connecting pipe; 11. Block; 12. Spring; 13. Fixing disc; 14. Air supply pipe; 15. Sealing plug; 16. Through hole. Detailed Implementation

[0019] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0020] Please refer to the following: Figures 1-4 This utility model provides a technical solution: a landing buffer device for unmanned aerial vehicles (UAVs), including a UAV body 1. Multiple support feet 2 are provided on the outer surface of the UAV body 1. A receiving cylinder 3 is fixedly connected to the bottom outer surface of the support feet 2. A piston cylinder 4 is provided below the receiving cylinder 3. A piston rod 5 is movably inserted into the inner surface of the piston cylinder 4. A chassis 6 is fixedly connected to the bottom outer surface of the piston rod 5. A piston disc 7 is fixedly connected to the other end of the piston rod 5. The piston disc 7 is movably connected to the interior of the piston cylinder 4. An airbag 8 is provided on the inner surface of the receiving cylinder 3. Specifically, when the UAV body 1 lands, the chassis 6 contacts the ground. As the UAV body 1 lands, the chassis 6 drives the piston rod 5, causing the piston disc 7 to move inside the piston cylinder 4. This causes a change in air pressure inside the piston cylinder 4, and the air pressure enters the airbag 8, causing the airbag 8 to inflate. The movement of the piston disc 7 within the piston cylinder 4 further inflates the airbag 8. This method buffers the impact force of the UAV body 1 during landing, achieving a better buffering effect and better ensuring the safety of the UAV body.

[0021] In this embodiment, a connecting pipe 9 is fixedly connected to the top outer surface of the piston cylinder 4, and a connecting pipe 10 is fixedly connected to the top outer surface of the connecting pipe 9. The connecting pipe 10 is connected to the airbag 8. A fixed plate 13 is fixedly connected to the inner surface of the connecting pipe 10, and a spring 12 is fixedly connected to the bottom outer surface of the fixed plate 13. A blocking block 11 is fixedly connected to the bottom outer surface of the spring 12. The blocking block 11 is in movable contact with the inside of the connecting pipe 9. A guide rod is fixedly connected to the outer surface of the blocking block 11. The guide rod moves through the outer surface of the fixed plate 13. The spring 12 is sleeved on the outside of the guide rod. Specifically, the air pressure inside the piston cylinder 4 changes, and the air pressure squeezes the blocking block 11, causing the blocking block 11 to detach from the inner wall of the connecting pipe 9, causing the spring 12 to deform. As a result, the air pressure causes the airbag 8 to expand, and then the blocking block 11 seals the connecting pipe 9 to prevent the air pressure from flowing back and squeezing the piston plate 7, causing the piston plate 7 to move downward and causing the chassis 6 to become unstable.

[0022] In this embodiment, an air supply pipe 14 is fixedly connected to the outer surface of the airbag 8. The other end of the air supply pipe 14 extends to the outside of the receiving cylinder 3. A sealing plug 15 is threaded to the end of the air supply pipe 14 located outside the receiving cylinder 3. Specifically, when the airbag 8 inflates to a certain extent, the gas inside the airbag 8 is discharged by unscrewing the sealing plug 15.

[0023] In this embodiment, a return pipe is fixedly connected to the top outer surface of the piston cylinder 4. A one-way valve is installed inside the return pipe. The flow direction of the one-way valve is from the outside of the return pipe to the inside of the piston cylinder 4. A through hole 16 is opened on the bottom outer surface of the piston cylinder 4. Specifically, when the piston disc 7 moves downward, the air at the bottom of the piston disc 7 is discharged through the through hole 16, and the outside air enters the inside of the piston cylinder 4 through the return pipe, thereby achieving air pressure balance.

[0024] In this embodiment, a counterweight is fixedly connected to the bottom outer surface of the chassis 6. Specifically, by adding a counterweight to the bottom of the chassis 6, the chassis 6 has a certain gravity. When the main body of the drone 1 takes off, the weight of the counterweight causes the chassis 6 to drive the piston rod 5, causing the piston disc 7 to slide inside the piston cylinder 4.

[0025] In this embodiment, the plug 11 is a frustum shape with a thicker top and a thinner bottom. A sealing gasket is fixedly connected to the outer surface of the plug 11. Specifically, the frustum shape of the plug 11 ensures that there is always one point on the plug 11 that corresponds to the inner diameter of the connecting pipe 9. The connecting pipe 9 is sealed by the plug 11, and the sealing gasket increases the sealing performance of the surface of the plug 11.

[0026] In this embodiment, the outer surface of the fixed disk 13 is provided with multiple through slots. Specifically, by opening through slots, space is provided for the airflow to pass through, and the airflow passes through the through slots and then through the fixed disk 13.

[0027] Working principle: When the drone body 1 lands, the chassis 6 contacts the ground. As the drone body 1 lands, the chassis 6 drives the piston rod 5, causing the piston disc 7 to move inside the piston cylinder 4. This causes a change in air pressure inside the piston cylinder 4. The air pressure compresses the plug 11, causing the plug 11 to detach from the inner wall of the connecting pipe 9. This causes the spring 12 to deform, and the air pressure causes the airbag 8 to inflate. Then, the plug 11 seals the connecting pipe 9, preventing air pressure from flowing back and compressing the piston disc 7, which could cause instability in the chassis 6. The movement of the piston disc 7 within the piston cylinder 4 causes the airbag 8 to inflate. This method buffers the impact force of the drone body 1 during landing, achieving a better buffering effect and better ensuring the safety of the drone body.

[0028] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A landing buffer device for unmanned aerial vehicles (UAVs), comprising the main body of the UAV (1), characterized in that: The outer surface of the main body (1) of the drone is provided with multiple support feet (2). The bottom outer surface of the support feet (2) is fixedly connected to a receiving cylinder (3). A piston cylinder (4) is provided below the receiving cylinder (3). A piston rod (5) is movably inserted into the inner surface of the piston cylinder (4). A chassis (6) is fixedly connected to the bottom outer surface of the piston rod (5). A piston disc (7) is fixedly connected to the other end of the piston rod (5). The piston disc (7) is movably connected to the inside of the piston cylinder (4). An airbag (8) is provided on the inner surface of the receiving cylinder (3).

2. The landing buffer device for unmanned aerial vehicles according to claim 1, characterized in that: The piston cylinder (4) has a connecting pipe (9) fixedly connected to its top outer surface. The connecting pipe (9) has a connecting pipe (10) fixedly connected to its top outer surface. The connecting pipe (10) is connected to the airbag (8). The connecting pipe (10) has a fixed plate (13) fixedly connected to its inner surface. The fixed plate (13) has a spring (12) fixedly connected to its bottom outer surface. The spring (12) has a block (11) fixedly connected to its bottom outer surface. The block (11) is in movable contact with the inside of the connecting pipe (9). The block (11) has a guide rod fixedly connected to its outer surface. The guide rod moves through the outer surface of the fixed plate (13). The spring (12) is sleeved on the outside of the guide rod.

3. The landing buffer device for unmanned aerial vehicles according to claim 1, characterized in that: The outer surface of the airbag (8) is fixedly connected to an air supply pipe (14), the other end of which extends to the outside of the receiving cylinder (3), and a sealing plug (15) is threaded to the end of the air supply pipe (14) located outside the receiving cylinder (3).

4. A landing buffer device for unmanned aerial vehicles according to claim 1, characterized in that: The piston cylinder (4) has a reflux pipe fixedly connected to its top outer surface. A one-way valve is installed inside the reflux pipe. The flow direction of the one-way valve is from the outside of the reflux pipe toward the inside of the piston cylinder (4). A through hole (16) is opened on the bottom outer surface of the piston cylinder (4).

5. A landing buffer device for unmanned aerial vehicles according to claim 1, characterized in that: A counterweight is fixedly connected to the bottom outer surface of the chassis (6).

6. A landing buffer device for unmanned aerial vehicles according to claim 2, characterized in that: The block (11) is a frustum shape with a thicker top and a thinner bottom, and a sealing gasket is fixedly connected to the outer surface of the block (11).

7. A landing buffer device for unmanned aerial vehicles according to claim 2, characterized in that: The outer surface of the fixed disk (13) is provided with multiple through slots.

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