Heavy-load industrial unmanned aerial vehicle

Abstract

The utility model discloses a heavy-load industrial unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicles. The unmanned aerial vehicle comprises an unmanned aerial vehicle body and two landing supporting rods, wherein a mounting box is fixedly mounted at the bottom of the unmanned aerial vehicle body. The air pump can start an air extraction function, redundant air is extracted and stored, so that air pressure in the system is reduced, the damping assembly and the buffering assembly are prevented from being damaged due to too high pressure, and meanwhile the stability of the buffering effect is guaranteed. On the contrary, when the impact is weakened and the air pressure in the three-way valve is reduced to a certain degree, the control system commands the air pump to re-inject the previously stored air into the system to maintain the air pressure balance in the damping assembly and the buffering assembly and ensure that the buffering effect is continuously and effectively played; therefore, the serious problems of landing gear strut bending, fuselage frame deformation and the like caused by huge impact force generated by the self weight and the load during landing of the heavy-load industrial unmanned aerial vehicle are avoided, and a solid guarantee is provided for safe landing of the unmanned aerial vehicle.

Description

Technical Field

[0001] The utility model belongs to the technical field of unmanned aerial vehicles, and in particular relates to a heavy-load industrial unmanned aerial vehicle. Background Art

[0002] As the industrial sector continues to develop, heavy-load industrial drones have emerged as a new and influential technical equipment. Heavy-load industrial drones refer to unmanned aerial vehicles that can carry heavy loads and are designed and manufactured for industrial purposes. Different from ordinary drones, they have a powerful power system and a sturdy and durable body structure to ensure that they can carry a large amount of materials or equipment to perform tasks. Their load capacity is usually far greater than that of general consumer or lightweight industrial drones, and they can carry heavy objects ranging from tens of kilograms to several tons.

[0003] When a heavy-loaded industrial drone lands, the total weight it carries far exceeds that of an ordinary drone. The huge impact force acts directly on the landing gear. This powerful force first poses a severe test to the landing gear structure, which may cause the landing gear struts to bend or even the entire landing gear to separate from the fuselage. For the fuselage, the impact force will cause stress concentration in the internal structural parts of the fuselage, causing the fuselage frame to deform and the welds to crack.

[0004] Currently, no effective solution has been proposed for the problems in the related technologies. Utility Model Content

[0005] In view of the problems in the related technology, the utility model proposes a heavy-load industrial drone to overcome the above-mentioned technical problems existing in the existing related technology.

[0006] In order to solve the above technical problems, the utility model is realized by the following technical solutions:

[0007] The utility model discloses a heavy-load industrial drone, comprising a drone body and two landing support rods, a mounting box being fixedly mounted on the bottom of the drone body, connecting rods being symmetrically arranged at one end of the two landing support rods, shock absorbing components being symmetrically and rotatably mounted at the middle parts of the two connecting rods, the shock absorbing components being rotatably mounted with the mounting box, a sliding block being rotatably mounted at the other end of the connecting rod, the sliding block being slidably mounted on the mounting box, a buffer component being arranged at one end of the sliding block, a telescopic tube being connected at one end of the shock absorbing component, an air connecting tube being connected at one end of the buffer component, a three-way valve being connected at the other end of the telescopic tube, the air connecting tube being connected with the three-way valve, and an air pump being connected at one end of the three-way valve.

[0008] Furthermore, the shock absorbing assembly includes a first cylinder, which is rotatably mounted on the mounting box, a first piston is slidably mounted inside the first cylinder, and a first piston rod is fixedly mounted at one end of the first piston.

[0009] Furthermore, the connecting rod is rotatably mounted on the other end of the first piston rod, a spring is fixedly mounted on one end of the first piston, the other end of the spring is fixedly mounted on the inner wall of the first cylinder, and the first cylinder is connected to the telescopic tube.

[0010] Furthermore, a plurality of sliding rods for the sliding block to slide are fixedly installed inside the installation box, and a sliding groove for the sliding block to slide is opened inside the installation box.

[0011] Furthermore, the buffer assembly includes a second cylinder, the second cylinder is fixedly mounted on the mounting box, and a second piston is slidably mounted in the inner cavity of the second cylinder.

[0012] Furthermore, a second piston rod is fixedly mounted on one end of the second piston, and the other end of the second piston rod is fixedly mounted on the sliding block.

[0013] Furthermore, the second cylinder is communicated with the air connecting pipe, and the three-way valve is fixedly installed at the bottom of the installation box.

[0014] The utility model has the following beneficial effects:

[0015] 1. When the utility model detects that the air pressure rises sharply due to the strong landing impact force, indicating that the impact is too large, the control system sends a command to the air pump, and the air pump will start the gas extraction function to extract and store the excess gas, thereby reducing the air pressure in the system, preventing the shock absorbing components and buffer components from being damaged due to excessive pressure, and ensuring the stability of the buffering effect. Conversely, when the impact weakens and the air pressure in the three-way valve drops to a certain level, the control system will command the air pump to re-inject the previously stored gas into the system to maintain the air pressure balance inside the shock absorbing components and buffer components, ensuring that they continue to play an effective buffering role, thereby avoiding the huge impact force generated by the weight and load of the heavy-loaded industrial drone when landing, which causes serious problems such as bending of the landing gear struts and deformation of the fuselage frame, providing a solid guarantee for the safe landing of the drone.

[0016] 2. The sliding block rotatably installed at the other end of the connecting rod of the utility model starts to slide on the installation box, which is caused by the lever effect generated by the landing impact force pushing the connecting rod. During the sliding process of the sliding block, the buffer component arranged at one end thereof further intervenes in the buffering work. The buffer component will absorb and disperse the remaining impact force again according to the displacement and force conditions of the sliding block.

[0017] Of course, any product implementing the present invention does not necessarily need to achieve all of the advantages described above at the same time. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solutions of the utility model embodiments, the drawings required for describing the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0019] Figure 1 This is a three-dimensional structural diagram of the utility model;

[0020] Figure 2 It is a schematic diagram of the shock absorbing assembly of the utility model;

[0021] Figure 3 It is a schematic diagram of a sliding block of the utility model;

[0022] Figure 4 It is a schematic diagram of the first cylinder of the utility model;

[0023] Figure 5 It is a cross-sectional view of the second cylinder of the utility model;

[0024] Figure 6 This is a cross-sectional view of the first cylinder of the present utility model.

[0025] In the accompanying drawings, the components represented by the reference numerals are listed as follows:

[0026] 1. UAV body; 2. Installation box; 201. Sliding rod; 3. Connecting rod; 4. Landing support rod; 5. Shock absorber assembly; 501. First cylinder; 502. First piston; 503. First piston rod; 504. Spring; 6. Sliding block; 7. Buffer assembly; 701. Second cylinder; 702. Second piston; 703. Second piston rod; 8. Telescopic tube; 9. Air pipe; 10. Three-way valve; 11. Air pump. DETAILED DESCRIPTION

[0027] The following will be combined with the drawings in the utility model embodiments to clearly and completely describe the technical solutions in the utility model embodiments. Obviously, the described embodiments are only part of the utility model embodiments, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0028] In the description of the present utility model, it should be understood that the terms "opening", "upper", "lower", "top", "middle", "inside" and the like indicating orientation or positional relationship are only for the convenience of describing the utility model and simplifying the description, and do not indicate or imply that the components or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the utility model.

[0029] See also Figure 1-Figure 6 As shown, the utility model is a heavy-load industrial UAV, comprising a UAV body 1 and two landing support rods 4, a mounting box 2 is fixedly installed at the bottom of the UAV body 1, one end of the two landing support rods 4 is symmetrically provided with connecting rods 3, the middle parts of the two connecting rods 3 are symmetrically rotatably installed with shock absorbing components 5, the shock absorbing components 5 are rotatably installed with the mounting box 2, the other end of the connecting rod 3 is rotatably installed with a sliding block 6, the sliding block 6 is slidably installed on the mounting box 2, one end of the sliding block 6 is provided with a buffer component 7, one end of the shock absorbing component 5 is connected with a telescopic tube 8, one end of the buffer component 7 is connected with an air connecting pipe 9, the other end of the telescopic tube 8 is connected with a three-way valve 10, the air connecting pipe 9 is connected with the three-way valve 10, and one end of the three-way valve 10 is connected with an air pump 11.

[0030] At the moment of landing, the two landing support rods 4 first touch the ground. Since one end of the landing support rod 4 is connected to the installation box 2 through the connecting rod 3 and the shock absorbing assembly 5, and the shock absorbing assembly 5 symmetrically installed in the middle of the connecting rod 3 is rotationally connected to the installation box 2, when the huge landing impact force is transmitted along the landing support rod 4 to the connecting rod 3, the inside of the shock absorbing assembly 5 will be deformed due to the force. This deformation process can absorb a large amount of impact energy and preliminarily weaken the direct impact of the impact force on the drone body 1 through its own deformation buffering, just like the buffering effect of the shock absorbing spring of a car on a bumpy road;

[0031] At the same time, the sliding block 6 rotatably mounted at the other end of the connecting rod 3 starts to slide on the installation box 2, which is caused by the lever effect generated by the landing impact force pushing the connecting rod 3. During the sliding process of the sliding block 6, the buffer component 7 arranged at one end of the sliding block 6 further intervenes in the buffering work. The buffer component 7 will absorb and disperse the remaining impact force again according to the displacement and force of the sliding block 6.

[0032] A high-precision pressure sensor is installed at a key position inside the three-way valve 10 (the pressure sensor is a prior art and will not be elaborated on here, and is not shown in the figure). During the entire buffering process, effective detection of air pressure changes is achieved. When the shock absorbing component 5 is squeezed, the gas inside it is squeezed out through the connected telescopic tube 8, and when the buffer component 7 is pressurized, the internal gas is discharged through the air connecting pipe 9. These gases all flow to the three-way valve 10. The pressure sensor can sense the subtle changes in the air pressure inside the three-way valve 10 in real time, and quickly transmit the data to the microprocessor control system connected to the air pump 11 (the air pump 11 is a prior art and will not be elaborated on here). When it is detected that the air pressure rises sharply due to the strong landing impact force, indicating that the impact is too large, the control system sends a command to the air pump 11, and the air pump 11 will start the gas extraction function to extract and store excess gas, thereby reducing the air pressure in the system, preventing the shock absorbing component 5 and the buffer component 7 from being damaged due to excessive pressure, and ensuring the stability of the buffering effect. On the contrary, when the impact weakens and the air pressure in the three-way valve 10 drops to a certain level, the control system will command the air pump 11 to re-inject the previously stored gas into the system to maintain the air pressure balance inside the shock absorbing component 5 and the buffer component 7, ensuring that they continue to play a buffering role effectively, thereby avoiding the huge impact force generated by the heavy-loaded industrial drone's own weight and load when landing, which may cause serious problems such as bending of the landing gear struts and deformation of the fuselage frame, providing a solid guarantee for the safe landing of the drone.

[0033] In one embodiment, for the above-mentioned shock absorbing assembly 5, the shock absorbing assembly 5 includes a first cylinder 501, which is rotatably installed on the installation box 2, and a first piston 502 is slidably installed inside the first cylinder 501, and a first piston rod 503 is fixedly installed at one end of the first piston 502.

[0034] The other end of the first piston rod 503 is rotatably mounted on the connecting rod 3 , a spring 504 is fixedly mounted on one end of the first piston 502 , and the other end of the spring 504 is fixedly mounted on the inner wall of the first cylinder 501 , and the first cylinder 501 is connected to the telescopic tube 8 .

[0035] At the moment when the heavy-loaded industrial drone lands, the landing support rod 4 touches the ground first, and the strong impact force is quickly transmitted to the connecting rod 3 along the landing support rod 4. The connecting rod 3 and the first piston rod 503 are rotatably installed, and the first cylinder 501 is rotatably installed on the installation box 2, which makes the first piston rod 503 subject to the impact force;

[0036] The first piston rod 503 is fixed to the first piston 502 as a whole. Driven by the impact force, the first piston 502 starts to slide rapidly in the first cylinder 501. At this time, the spring 504 fixed at one end of the first piston 502 plays a key role. The other end of the spring 504 is fixedly connected to the inner wall of the first cylinder 501. When the first piston 502 slides, the spring 504 is compressed. The spring 504 has elastic potential energy. During the compression process, it will convert the landing impact energy into its own elastic potential energy, thereby generating reverse resistance to the movement of the first piston 502 and slowing down its sliding speed, just like the shock-absorbing spring of a car slowing down the vibration of the car body on a bumpy road, further absorbing and buffering a part of the impact force;

[0037] At the same time, the sliding of the first piston 502 will also produce a squeezing effect on the gas in the first cylinder 501. The gas in the first cylinder 501 is compressed and the pressure increases. Since the first cylinder 501 is connected to the telescopic tube 8, the compressed gas flows to the three-way valve 10 through the telescopic tube 8. This process is not only the flow of gas, but also the transmission of landing impact energy in the form of air pressure.

[0038] In one embodiment, for the installation box 2, a plurality of sliding rods 201 for the sliding block 6 to slide are fixedly installed inside the installation box 2, and a sliding groove for the sliding block 6 to slide is opened inside the installation box 2.

[0039] The buffer assembly 7 includes a second cylinder 701 , which is fixedly mounted on the mounting box 2 , and a second piston 702 is slidably mounted in the inner cavity of the second cylinder 701 .

[0040] A second piston rod 703 is fixedly mounted on one end of the second piston 702 , and the other end of the second piston rod 703 is fixedly mounted on the sliding block 6 .

[0041] The second cylinder 701 is in communication with the air connection pipe 9 , and the three-way valve 10 is fixedly installed at the bottom of the installation box 2 .

[0042] At the same time, the sliding block 6 rotatably mounted at the other end of the connecting rod 3 starts to slide on the installation box 2, which is caused by the lever effect generated by the landing impact force pushing the connecting rod 3. During the sliding process of the sliding block 6, the multiple sliding rods 201 fixed inside the installation box 2 and the sliding grooves provided provide guidance and stable support for the sliding of the sliding block 6, ensuring that it can slide smoothly along the predetermined track when the lever effect generated by the landing impact force pushing the connecting rod 3 is applied;

[0043] The sliding of the sliding block 6 drives the second piston rod 703 to move. Since the second cylinder 701 is fixedly mounted on the mounting box 2, one end of the second piston rod 703 is fixed to the second piston 702, and the other end is fixedly connected to the sliding block 6. When the sliding block 6 slides, the second piston 702 is pushed to slide in the second cylinder 701 by the second piston rod 703. The sliding of the second piston 702 squeezes the gas in the second cylinder 701, increasing its pressure. Since the second cylinder 701 is connected to the connecting pipe 9, the compressed gas flows to the three-way valve 10 through the connecting pipe 9.

[0044] During the entire buffering process, the three-way valve 10 fixedly installed at the bottom of the installation box 2 plays a key hub role. The pressure sensor installed inside it monitors the air pressure changes in real time. When it is detected that the air pressure rises sharply due to the strong landing impact force, indicating that the impact is too large, the pressure sensor quickly transmits the data to the microprocessor control system connected to the air pump 11. After receiving the signal, the control system sends an instruction to the air pump 11, and the air pump 11 starts the gas extraction function to extract and store the excess gas, reduce the air pressure in the system, prevent the second cylinder 701 and the first cylinder 501 from being damaged due to excessive pressure, and ensure the stability of the buffering effect. On the contrary, when the impact is weakened and the air pressure in the three-way valve 10 is reduced to a certain level, the control system commands the air pump 11 to re-inject the previously stored gas into the system to maintain the air pressure balance in the second cylinder 701 and the first cylinder 501, and ensure that it continues to play an effective buffering role, thereby avoiding the huge impact force generated by the weight and load of the heavy-loaded industrial drone when landing, resulting in serious problems such as bending of the landing gear struts and deformation of the fuselage frame, providing a solid guarantee for the safe landing of the drone.

[0045] In the description of this specification, the description with reference to the terms "one embodiment", "example", "specific example", etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the utility model. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0046] The preferred embodiments of the utility model disclosed above are only used to help explain the utility model. The preferred embodiments do not describe all the details in detail, nor do they limit the utility model to the specific implementation methods described. Obviously, many modifications and changes can be made according to the content of this specification. This specification selects and specifically describes these embodiments in order to better explain the principles and practical applications of the utility model, so that technicians in the relevant technical field can well understand and use the utility model. The utility model is limited only by the claims and their full scope and equivalents.

Claims

1. A heavy-load industrial drone, comprising a drone body (1) and two landing support rods (4), characterized in that: A mounting box (2) is fixedly mounted at the bottom of the drone body (1); a connecting rod (3) is symmetrically mounted at one end of the two landing support rods (4); a shock absorbing assembly (5) is symmetrically mounted in the middle of the two connecting rods (3); the shock absorbing assembly (5) is rotatably mounted on the mounting box (2); a sliding block (6) is rotatably mounted on the other end of the connecting rod (3); the sliding block (6) is slidably mounted on the mounting box (2); a buffer assembly (7) is provided at one end of the sliding block (6); one end of the shock absorbing assembly (5) is connected to a telescopic tube (8); one end of the buffer assembly (7) is connected to an air pipe (9); the other end of the telescopic tube (8) is connected to a three-way valve (10); the air pipe (9) is connected to the three-way valve (10); one end of the three-way valve (10) is connected to an air pump (11).

2. A heavy-load industrial drone according to claim 1, characterized in that: The shock absorbing assembly (5) comprises a first cylinder (501), the first cylinder (501) being rotatably mounted on the mounting box (2), a first piston (502) being slidably mounted inside the first cylinder (501), and a first piston rod (503) being fixedly mounted at one end of the first piston (502).

3. A heavy-load industrial drone according to claim 2, characterized in that: The other end of the first piston rod (503) is rotatably mounted on the connecting rod (3), one end of the first piston (502) is fixedly mounted with a spring (504), the other end of the spring (504) is fixedly mounted on the inner wall of the first cylinder (501), and the first cylinder (501) is connected to the telescopic tube (8).

4. A heavy-load industrial drone according to claim 1, characterized in that: A plurality of sliding rods (201) for the sliding block (6) to slide are fixedly installed inside the installation box (2), and a sliding groove for the sliding block (6) to slide is provided inside the installation box (2).

5. A heavy-load industrial drone according to claim 1, characterized in that: The buffer assembly (7) comprises a second cylinder (701), the second cylinder (701) being fixedly mounted on the mounting box (2), and a second piston (702) being slidably mounted in the inner cavity of the second cylinder (701).

6. A heavy-load industrial drone according to claim 5, characterized in that: A second piston rod (703) is fixedly mounted on one end of the second piston (702), and the other end of the second piston rod (703) is fixedly mounted on the sliding block (6).

7. A heavy-load industrial drone according to claim 6, characterized in that: The second cylinder (701) is in communication with the air connection pipe (9), and the three-way valve (10) is fixedly mounted on the bottom of the installation box (2).

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