Cargo unmanned aerial vehicle landing damping buffer structure

Abstract

The utility model discloses a freight unmanned plane landing damping buffer structure relates to freight unmanned plane landing damping technical field, aims at solving the single function of current damping buffer structure, in the process of damping, cannot carry out reverse push for the landing of unmanned plane, and there is deficiency in the landing speed reduction of damping simultaneously, and the practicability needs to improve, technical scheme main points include the air outlet seat, the air inlet port place fixed connection of air outlet seat has the gas reservoir, the end surface of air outlet seat is provided with a plurality of air outlet holes, and the air outlet direction of air outlet hole is vertically downward, and the port place piston connection of gas reservoir has the piston rod, one end fixed connection of piston rod has the piston block, and the piston block is located in the inside of gas reservoir, and the outside sleeve joint of gas reservoir and piston rod has the spring. Reach the effect of strong practicability of being able to spray gas downward while damping, and the reverse push of unmanned plane can effectively reduce the landing speed.

Description

Technical Field

[0001] This utility model relates to the field of landing vibration reduction technology for cargo drones, and in particular to a landing vibration reduction and buffer structure for cargo drones. Background Technology

[0002] With the development of technology, drone technology is advancing rapidly, and drones are being used in more and more fields. Among them, drones are used to transport goods instead of manual transportation, which has played a particularly outstanding role in the transportation of goods in mountainous environments. In order to ensure the safety of goods transportation, shock-absorbing and buffering structures are required to ensure that the aircraft lands stably and safely.

[0003] Existing shock absorption and buffer structures have limited functionality. During the shock absorption process, they cannot provide reverse propulsion for the landing of drones, and are insufficient in reducing landing speed while absorbing shock, thus their practicality needs to be improved. Utility Model Content

[0004] The purpose of this invention is to provide a landing vibration reduction and buffer structure for cargo drones that can spray gas downwards while reducing vibration, thereby pushing the drone backwards and effectively reducing its landing speed. It is highly practical.

[0005] To achieve the above objectives, the present invention provides the following technical solution:

[0006] A landing vibration damping and buffering structure for a cargo drone includes an air outlet seat. An air storage cylinder is fixedly connected to the air inlet port of the air outlet seat. Multiple air outlet holes are provided on the end face of the air outlet seat, and the air outlet holes are vertically downward. A piston rod is piston-connected to the port of the air storage cylinder. A piston block is fixedly connected to one end of the piston rod. The piston block is located inside the air storage cylinder. A spring is sleeved on the outside of the air storage cylinder and the piston rod.

[0007] By adopting the above technical solution, the gas inside the gas storage tank can be discharged from the vent during landing, which can provide reverse thrust for the aircraft and reduce the landing speed of the aircraft.

[0008] Furthermore, one end of the piston rod is fixedly connected to a connecting seat, and one end of the spring abuts against the end face of the connecting seat.

[0009] By adopting the above technical solution, the stability of the spring can be improved.

[0010] Furthermore, a weighing sensor is fixedly installed at the middle position of the lower end face of the connecting seat.

[0011] By adopting the above technical solution, the weight of goods can be monitored in real time using weighing sensors.

[0012] Furthermore, an alarm is installed on the outside of the gas storage cylinder and the piston rod, and the weighing sensor is electrically connected to the alarm.

[0013] By adopting the above technical solution, the alarm can receive data from the weighing sensor in real time, and the alarm will sound when the goods are too heavy.

[0014] Furthermore, a support foot is fixedly installed at one end of the weighing sensor.

[0015] By adopting the above technical solutions, stable support can be provided.

[0016] Furthermore, a flange structure is provided at the upper end of the air outlet seat.

[0017] By adopting the above technical solution, installation and fixation can be convenient.

[0018] In summary, the beneficial technical effects of this utility model are as follows:

[0019] 1. This utility model allows the supporting feet to rest on the ground during drone landing. As the drone continues to descend, the air tank and air outlet continuously descend. At this time, the piston rod drives the piston block to move inside the air tank. This action can push the air inside the air tank out of the air outlet hole of the air outlet hole. Since the air outlet hole is vertically downward, the reverse thrust generated by the air blown out of the air outlet hole can act on the landing drone, realizing the drone's landing deceleration operation. At the same time, during landing, the spring is compressed, and together with the piston block sliding inside the air tank, it can realize shock absorption. This structure can achieve shock absorption and buffering while also providing reverse thrust to the aircraft, reducing the landing speed of the aircraft. Both practicality and functionality are effectively improved.

[0020] 2. This utility model has a weighing sensor fixedly installed on the lower surface of the connecting seat. Therefore, the weighing sensor can be used to detect the weight of the cargo carried on the aircraft and transmit the detected data to the inside of the alarm. When the weight of the cargo drone exceeds the limit, the alarm will sound. Therefore, the weight of the cargo can be monitored in real time when the cargo is stacked, and the functionality and practicality are further improved. Attached Figure Description

[0021] Figure 1 This is a first-view perspective view of the three-dimensional structure of this utility model;

[0022] Figure 2 This is a second perspective view of the three-dimensional structure of this utility model;

[0023] Figure 3 This is a diagram of the internal structure of this utility model.

[0024] In the diagram: 1. Air outlet; 2. Air reservoir; 3. Piston rod; 4. Spring; 5. Alarm; 6. Connecting seat; 7. Weighing sensor; 8. Support foot; 9. Air outlet; 10. Piston block. Detailed Implementation

[0025] The method of this utility model will be further described in detail below with reference to the accompanying drawings.

[0026] Reference Figure 1 , Figure 2 , Figure 3 A landing vibration damping and buffering structure for a cargo drone includes an air outlet seat 1. An air storage cylinder 2 is fixedly connected to the air inlet port of the air outlet seat 1. Multiple air outlet holes 9 are provided on the end face of the air outlet seat 1, with the air outlet holes 9 venting vertically downwards. A piston rod 3 is piston-connected to the port of the air storage cylinder 2. A piston block 10 is fixedly connected to one end of the piston rod 3 and is located inside the air storage cylinder 2. A spring 4 is sleeved on the outside of the air storage cylinder 2 and the piston rod 3. A connecting seat 6 is fixedly connected to one end of the piston rod 3, and one end of the spring 4 abuts against the end face of the connecting seat 6. A flange structure is provided at the upper end of the air outlet seat 1, in which a support foot 8 can rest on the ground when the drone lands, and as the drone... As the drone continues to descend, the air reservoir 2 and the air outlet seat 1 continue to descend. At this time, the piston rod 3 drives the piston block 10 to move inside the air reservoir 2. This action can push the air inside the air reservoir 2 out of the air outlet hole 9 of the air outlet seat 1. Since the air outlet hole 9 is vertically downward, the reverse thrust generated by the air blown out of the air outlet hole 9 can act on the landing drone, which can realize the landing deceleration operation of the drone. At the same time, during landing, the spring 4 is compressed, and together with the piston block 10 sliding inside the air reservoir 2, it can realize the shock absorption operation. This structure can realize shock absorption and buffering, and can also push the aircraft in the opposite direction to reduce the landing speed of the aircraft. The practicality and functionality are effectively improved.

[0027] Reference Figure 1 A load cell 7 is fixedly installed at the middle position of the lower end face of the connecting seat 6. An alarm 5 is installed on the outside of the air tank 2 and the piston rod 3. The load cell 7 is electrically connected to the alarm 5. A support foot 8 is fixedly installed at one end of the load cell 7. Since the load cell 7 is fixedly installed on the lower surface of the connecting seat 6, the load cell 7 can be used to detect the weight of the cargo carried on the aircraft and transmit the detected data to the inside of the alarm 5. When the weight of the cargo drone exceeds the limit, the alarm 5 will sound an alarm. Therefore, when stacking cargo, the weight of the cargo can be monitored in real time, and the functionality and practicality are further improved.

[0028] Working principle: In use, first install the structure at the designated location, then stack the cargo. Since a load cell 7 is fixedly installed on the lower surface of the connecting seat 6, the load cell 7 can detect the weight of the cargo on the aircraft and transmit the data to the alarm 5. When the weight of the cargo drone exceeds the limit, the alarm 5 sounds. Therefore, the weight of the cargo can be monitored in real time during stacking. When the drone lands, the support legs 8 touch the ground. As the drone continues to descend, the air tank 2 and the air outlet seat 1 continue to descend. When piston rod 3 drives piston block 10 to move inside air cylinder 2, this action can push the air inside air cylinder 2 out of air outlet hole 9 of air outlet seat 1. Since the air outlet hole 9 is vertically downward, the reverse thrust generated by the air blown out of air outlet hole 9 can act on the landing drone, which can realize the landing deceleration operation of drone. At the same time, during landing, spring 4 is compressed, and together with piston block 10 sliding inside air cylinder 2, shock absorption operation can be realized. This structure can realize shock absorption and buffering, and can also push the aircraft in the opposite direction to reduce the landing speed of the aircraft.

[0029] The specific real-time examples described herein are preferred real-time examples of this utility model and are not intended to limit the scope of protection of this utility model. Therefore, all equivalent changes made to the structure, shape, and principle of this utility model should be included within the scope of protection of this utility model.

Claims

1. A landing vibration damping and buffer structure for a cargo drone, comprising an air outlet (1), characterized in that: An air storage cylinder (2) is fixedly connected to the air inlet port of the air outlet seat (1). Multiple air outlet holes (9) are provided on the end face of the air outlet seat (1). The air outlet holes (9) are vertically downward. A piston rod (3) is piston-connected to the port of the air storage cylinder (2). A piston block (10) is fixedly connected to one end of the piston rod (3). The piston block (10) is located inside the air storage cylinder (2). A spring (4) is sleeved on the outside of the air storage cylinder (2) and the piston rod (3).

2. The landing vibration damping and buffering structure for a cargo drone according to claim 1, characterized in that: One end of the piston rod (3) is fixedly connected to a connecting seat (6), and one end of the spring (4) abuts against the end face of the connecting seat (6).

3. The landing vibration damping and buffering structure for a cargo drone according to claim 2, characterized in that: A weighing sensor (7) is fixedly installed at the middle position of the lower end face of the connecting seat (6).

4. The landing vibration damping and buffering structure for a cargo drone according to claim 3, characterized in that: An alarm (5) is installed on the outside of the gas storage cylinder (2) and the piston rod (3), and the weighing sensor (7) is electrically connected to the alarm (5).

5. The landing vibration damping and buffering structure for a cargo drone according to claim 3, characterized in that: One end of the weighing sensor (7) is fixedly mounted with a support foot (8).

6. The landing vibration damping and buffering structure for a cargo drone according to claim 1, characterized in that: The upper end of the air outlet seat (1) is provided with a flange structure.

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