CN222522854U - Heavy-duty industrial unmanned aerial vehicle - Google Patents
Heavy-duty industrial unmanned aerial vehicle Download PDFInfo
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- CN222522854U CN222522854U CN202520153646.7U CN202520153646U CN222522854U CN 222522854 U CN222522854 U CN 222522854U CN 202520153646 U CN202520153646 U CN 202520153646U CN 222522854 U CN222522854 U CN 222522854U
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- 230000035939 shock Effects 0.000 claims abstract description 26
- 239000000872 buffer Substances 0.000 claims abstract description 18
- 238000009434 installation Methods 0.000 claims description 13
- 230000003139 buffering effect Effects 0.000 abstract description 10
- 238000005452 bending Methods 0.000 abstract description 4
- 239000007787 solid Substances 0.000 abstract description 3
- 238000000605 extraction Methods 0.000 abstract 1
- 238000013016 damping Methods 0.000 description 13
- 238000010521 absorption reaction Methods 0.000 description 11
- 239000007789 gas Substances 0.000 description 10
- 238000000034 method Methods 0.000 description 6
- 230000008569 process Effects 0.000 description 6
- 230000008859 change Effects 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 230000001960 triggered effect Effects 0.000 description 3
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005381 potential energy Methods 0.000 description 2
- 238000005086 pumping Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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Abstract
本实用新型公开了一种重载工业无人机，涉及无人机技术领域。本实用新型包括无人机本体和两个着陆支撑杆，所述无人机本体的底部固定安装有安装箱。本实用新型气泵会启动抽取气体功能，将多余的气体抽出并存储起来，以此降低系统内的气压，防止减震组件和缓冲组件因过高压力而受损，同时确保缓冲效果的稳定性。反之，当冲击减弱，三通阀内气压降低到一定程度时，控制系统又会命令气泵将之前存储的气体重新注入系统，维持减震组件和缓冲组件内部的气压平衡，保障其持续有效地发挥缓冲作用，进而避免了重载工业无人机着陆时因自身重量和负载产生的巨大冲击力，而造成起落架支柱弯曲、机身框架变形等严重问题，为无人机的安全着陆提供坚实保障。
The utility model discloses a heavy-loaded industrial drone, and relates to the technical field of drones. The utility model includes a drone body and two landing support rods, and a mounting box is fixedly installed at the bottom of the drone body. The air pump of the utility model will start the gas extraction function, extract and store excess gas, thereby reducing the air pressure in the system, preventing the shock absorbing component and the buffer component from being damaged due to excessive pressure, and ensuring the stability of the buffering effect. Conversely, when the impact is weakened and the air pressure in the three-way valve is reduced 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 component and the buffer component, and ensure that they continue to effectively play a 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.
Description
Technical Field
The utility model belongs to the technical field of unmanned aerial vehicles, and particularly relates to a heavy-duty industrial unmanned aerial vehicle.
Background
Under the condition of continuous development in the industrial field, a heavy-duty industrial unmanned aerial vehicle is generated as novel and very influential technical equipment. The heavy-duty industrial unmanned aerial vehicle is an unmanned aerial vehicle which can bear a large weight load and is specially designed and manufactured for industrial use, and is different from a common unmanned aerial vehicle, and the unmanned aerial vehicle has a powerful power system and a firm and durable airframe structure so as to ensure that a large amount of materials or equipment can be carried to perform tasks. The loading capacity of the unmanned aerial vehicle is far beyond that of a general consumer grade or a lightweight industrial unmanned aerial vehicle, and the unmanned aerial vehicle can carry weights ranging from tens of kilograms to tons.
At the landing moment, the heavy-duty industrial unmanned aerial vehicle is far more than the common unmanned aerial vehicle in total weight due to the heavy weight carried by the heavy-duty industrial unmanned aerial vehicle, huge impact force directly acts on the landing gear, the strong force first causes severe test on the landing gear structure, the landing gear support is possibly bent, even the whole landing gear is separated from the landing gear, and the impact force can cause stress concentration of structural parts in the landing gear, so that the frame of the landing gear is deformed and welding spots are cracked.
For the problems in the related art, no effective solution has been proposed at present.
Disclosure of utility model
Aiming at the problems in the related art, the utility model provides a heavy-duty industrial unmanned aerial vehicle, which aims to overcome the technical problems in the prior related art.
In order to solve the technical problems, the utility model is realized by the following technical scheme:
The utility model relates to a heavy-duty industrial unmanned aerial vehicle, which comprises an unmanned aerial vehicle body and two landing support rods, wherein a mounting box is fixedly arranged at the bottom of the unmanned aerial vehicle body, connecting rods are symmetrically arranged at one ends of the two landing support rods, shock absorbing components are symmetrically and rotatably arranged at the middle parts of the two connecting rods, the shock absorbing components are rotatably arranged with the mounting box, a sliding block is rotatably arranged at the other end of the connecting rod, the sliding block is slidably arranged on the mounting box, a buffer component is arranged at one end of the sliding block, one end of the shock absorbing component is communicated with a telescopic pipe, one end of the buffer component is communicated with a gas connecting pipe, the other end of the telescopic pipe is communicated with a three-way valve, the gas connecting pipe is communicated with the three-way valve, and one end of the three-way valve is communicated with an air pump.
Further, the damping component comprises a first cylinder barrel, the first cylinder barrel is rotatably installed on the installation box, a first piston is slidably installed in the first cylinder barrel, and a first piston rod is fixedly installed at one end of the first piston.
Further, the other end of the first piston rod is rotatably mounted with the connecting rod, a spring is fixedly mounted at one end of the first piston, the other end of the spring is fixedly mounted on the inner wall of the first cylinder barrel, and the first cylinder barrel is communicated with the telescopic pipe.
Further, a plurality of sliding rods for sliding the sliding blocks are fixedly installed in the installation box, and sliding grooves for sliding the sliding blocks are formed in the installation box.
Further, the buffer assembly comprises a second cylinder barrel, the second cylinder barrel is fixedly installed in the installation box, and a second piston is slidably installed in an inner cavity of the second cylinder barrel.
Further, one end of the second piston is fixedly provided with a second piston rod, and the other end of the second piston rod is fixedly provided with the sliding block.
Further, the second cylinder is communicated with the connecting pipe, and the three-way valve is fixedly arranged at the bottom of the mounting box.
The utility model has the following beneficial effects:
1. When the air pressure is detected to rise sharply due to strong landing impact force, the control system sends an instruction to the air pump, the air pump can start the air pumping function to pump and store redundant air, so that the air pressure in the system is reduced, the shock absorption component and the shock absorption component are prevented from being damaged due to the excessive pressure, and meanwhile, the stability of the shock absorption effect is ensured. On the contrary, when 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 stored air into the system, so that the air pressure balance in the damping component and the damping component is maintained, the damping component is ensured to continuously and effectively play a role in buffering, further, the serious problems of bending of the landing gear support, deformation of the frame of the machine body and the like caused by huge impact force generated by the weight and the load of the heavy-duty industrial unmanned aerial vehicle during landing are avoided, and solid guarantee is provided for safe landing of the unmanned aerial vehicle.
2. The sliding block rotatably arranged at the other end of the connecting rod starts to slide on the mounting box and is triggered by the leverage generated by the landing impact force pushing the connecting rod, and the buffer component arranged at one end of the sliding block further intervenes in the buffer work in the sliding process of the sliding block and can absorb and disperse the residual impact force again according to the displacement and stress condition of the sliding block.
Of course, it is not necessary for any one product to practice the utility model to achieve all of the advantages set forth above at the same time.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the utility model, the drawings that are needed for the description of the embodiments will be briefly introduced below, it being obvious that the drawings in the following description are only some embodiments of the utility model, and that other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a perspective view of the structure of the present utility model;
FIG. 2 is a schematic view of a shock absorbing assembly of the present utility model;
FIG. 3 is a schematic diagram of a slider of the present utility model;
FIG. 4 is a schematic view of a first cylinder according to the present utility model;
FIG. 5 is a cross-sectional view of a second cylinder of the present utility model;
fig. 6 is a cross-sectional view of a first cylinder barrel of the present utility model.
In the drawings, the list of components represented by the various numbers is as follows:
1. The unmanned aerial vehicle comprises an unmanned aerial vehicle body, 2 parts of an installation box, 201 parts of a sliding rod, 3 parts of a connecting rod, 4 parts of a landing supporting rod, 5 parts of a damping component, 501 parts of a first cylinder barrel, 502 parts of a first piston, 503 parts of a first piston rod, 504 parts of a spring, 6 parts of a sliding block, 7 parts of a damping component, 701 parts of a second cylinder barrel, 702 parts of a second piston, 703 parts of a second piston rod, 8 parts of a telescopic pipe, 9 parts of a connecting pipe, 10 parts of a three-way valve, 11 parts of an air pump.
Detailed Description
The following description of the technical solutions in the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings in the embodiments of the present utility model, and it is apparent that the described embodiments are only some embodiments of the present utility model, not all embodiments. All other embodiments, based on the embodiments in the utility model, which a person of ordinary skill in the art would obtain without inventive faculty, are within the scope of the utility model.
In the description of the present utility model, it should be understood that the terms "open," "upper," "lower," "top," "middle," "inner," and the like indicate an orientation or positional relationship, merely for convenience of description and to simplify the description, and do not indicate or imply that the components or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus should not be construed as limiting the utility model.
Referring to fig. 1-6, the utility model discloses a heavy-duty industrial unmanned aerial vehicle, which comprises an unmanned aerial vehicle body 1 and two landing support rods 4, wherein a mounting box 2 is fixedly mounted at the bottom of the unmanned aerial vehicle body 1, one ends of the two landing support rods 4 are symmetrically provided with connecting rods 3, shock absorbing assemblies 5 are symmetrically rotatably mounted at the middle parts of the two connecting rods 3, the shock absorbing assemblies 5 are rotatably mounted with the mounting box 2, a sliding block 6 is rotatably mounted at the other end of the connecting rods 3, the sliding block 6 is slidably mounted on the mounting box 2, one end of the sliding block 6 is provided with a buffer assembly 7, one end of the shock absorbing assembly 5 is communicated with a telescopic pipe 8, one end of the buffer assembly 7 is communicated with a connecting pipe 9, the other end of the telescopic pipe 8 is communicated with a three-way valve 10, the connecting pipe 9 is communicated with the three-way valve 10, and one end of the three-way valve 10 is communicated with an air pump 11.
At the moment of landing, the two landing support rods 4 firstly contact the ground, as one end of the landing support rod 4 is connected with the mounting box 2 through the connecting rod 3 and the damping component 5, and the damping component 5 symmetrically and rotatably arranged in the middle of the connecting rod 3 is rotatably connected with the mounting box 2, when huge landing impact force is transmitted to the connecting rod 3 along the landing support rod 4, the inside of the damping component 5 can be deformed due to stress, and a large amount of impact energy can be absorbed in the deformation process, and the direct influence of the impact force on the unmanned aerial vehicle body 1 is primarily weakened through self deformation buffering, so that the impact effect of a damping spring of an automobile on a bumpy road is the same as the buffering effect of the damping spring of the automobile;
Meanwhile, the sliding block 6 rotatably arranged at the other end of the connecting rod 3 starts to slide on the mounting box 2, the sliding block 6 is triggered by leverage generated by the landing impact force pushing the connecting rod 3, a buffer component 7 arranged at one end of the sliding block 6 is further inserted into the buffer work in the sliding process, and the buffer component 7 can absorb and disperse the residual impact force again according to the displacement and stress condition of the sliding block 6;
The high-precision pressure sensor (the pressure sensor is the prior art and is not described in the drawings any more) is arranged at the key position inside the three-way valve 10, effective detection of air pressure change is realized in the whole buffering process, when the shock absorption component 5 is extruded, air inside the shock absorption component is extruded through the communicated telescopic pipe 8, when the shock absorption component 7 is pressed, the air inside the shock absorption component is discharged through the connecting pipe 9, all the air flows to the three-way valve 10, the pressure sensor can sense the tiny change of the air pressure inside the three-way valve 10 in real time, data can be quickly transmitted to the microprocessor control system connected with the air pump 11 (the air pump 11 is the prior art and is not described in the prior art any more), when the air pressure is detected to be rapidly increased due to strong landing impact force, the control system gives an instruction to the air pump 11, the air pump 11 can start to extract the air function, the redundant air is extracted and stored, the air pressure inside the system is reduced, the shock absorption component 5 and the shock absorption component 7 are prevented from being damaged due to the high pressure, and meanwhile, the stability of the buffering effect is ensured. On the contrary, when the impact is weakened and the air pressure in the three-way valve 10 is reduced to a certain extent, the control system commands the air pump 11 to re-inject the stored air into the system, so that the air pressure balance inside the shock absorption assembly 5 and the shock absorption assembly 7 is maintained, the continuous and effective buffer function is ensured, further, the serious problems of bending of the landing gear support, deformation of the frame of the machine body and the like caused by the huge impact force generated by the self weight and the load when the heavy-duty industrial unmanned aerial vehicle lands are avoided, and solid guarantee is provided for the safe landing of the unmanned aerial vehicle.
In one embodiment, for the shock absorbing assembly 5, the shock absorbing assembly 5 includes a first cylinder 501 rotatably mounted on the mounting case 2, a first piston 502 is slidably mounted in the first cylinder 501, and a first piston rod 503 is fixedly mounted at one end of the first piston 502.
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, 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 communicated with the telescopic tube 8.
At the moment that the heavy-duty industrial unmanned aerial vehicle lands, the landing support rod 4 firstly touches the ground, strong impact force is rapidly transmitted to the connecting rod 3 along the landing support rod 4, the connecting rod 3 is rotatably mounted with the first piston rod 503, and the first cylinder 501 is rotatably mounted on the mounting box 2, so that the first piston rod 503 is subjected to impact force;
The first piston rod 503 is integrally fixed with the first piston 502, and the first piston 502 starts to slide rapidly in the first cylinder 501 under the driving of the impact force, and 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 with 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, and in the compression process, landing impact energy can be converted into own elastic potential energy, so that reverse resistance is generated on the movement of the first piston 502, the sliding speed of the first piston is slowed down, and the automobile damping spring further absorbs and buffers a part of impact force just like the automobile damping spring slows down the vibration of an automobile body on a bumpy road surface;
At the same time, the sliding of the first piston 502 also produces a squeezing action on the gas in the first cylinder 501, which is compressed in the first cylinder 501, and the pressure rises, and since the first cylinder 501 is in communication with the bellows 8, these compressed gases flow through the bellows 8 to the three-way valve 10, which is not only the flow of gas, but also the transfer of landing impact energy in the form of air pressure.
In one embodiment, for the above-mentioned installation box 2, a plurality of sliding rods 201 for sliding the sliding blocks 6 are fixedly installed in the installation box 2, and a sliding groove for sliding the sliding blocks 6 is formed in the installation box 2.
The buffer assembly 7 comprises a second cylinder 701, the second cylinder 701 is fixedly arranged on the mounting box 2, and a second piston 702 is slidably arranged in the inner cavity of the second cylinder 701.
A second piston rod 703 is fixedly mounted at one end of the second piston 702, and the other end of the second piston rod 703 is fixedly mounted with the sliding block 6.
The second cylinder 701 is communicated with the gas connecting pipe 9, and the three-way valve 10 is fixedly arranged at the bottom of the installation box 2.
Simultaneously, the sliding block 6 rotatably arranged at the other end of the connecting rod 3 starts to slide on the mounting box 2, and is triggered by the leverage generated by the landing impact force pushing the connecting rod 3, and the sliding blocks 6 are provided with a plurality of sliding rods 201 and sliding grooves which are fixed in the mounting box 2 in the sliding process, so that guiding and stable support is provided for the sliding of the sliding blocks 6, and the sliding blocks can be ensured to stably slide along a set track when the sliding blocks are subjected to the leverage generated by the landing impact force pushing the connecting rod 3;
The sliding of the sliding block 6 drives the second piston rod 703 to move, because the second cylinder 701 is fixedly arranged on the mounting box 2, one end of the second piston rod 703 is fixedly connected with the second piston 702, and the other end of the second piston rod 703 is fixedly connected with 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, and the sliding of the second piston 702 extrudes the gas in the second cylinder 701 to raise the pressure, and because the second cylinder 701 is communicated with the gas connecting pipe 9, the compressed gas flows to the three-way valve 10 through the gas connecting pipe 9;
In the whole buffering process, the three-way valve 10 fixedly installed at the bottom of the installation box 2 plays a key pivot role, the pressure sensor installed in the three-way valve monitors the air pressure change in real time, when the air pressure is detected to rise sharply due to strong landing impact force, the impact is indicated to be too large, the pressure sensor rapidly transmits data to the microprocessor control system connected with the air pump 11, after the control system receives a signal, an instruction is sent to the air pump 11, the air pump 11 starts an air pumping function to pump and store redundant air, the air pressure in the system is reduced, the inside of the second cylinder 701 and the first cylinder 501 is prevented from being damaged due to too high pressure, the stability of the buffering effect is ensured, otherwise, when the impact is weakened, the air pressure in the three-way valve 10 is reduced to a certain degree, the control system instructs the air pump 11 to reinject the air stored before into the system, the air pressure balance between the inside of the second cylinder 701 and the first cylinder 501 is maintained, the continuous and effective buffering effect is ensured, and the serious problems of landing gear strut bending, frame deformation and the like caused by the huge impact force generated by the weight and load of a heavy-duty industrial unmanned aerial vehicle are avoided, and the landing of the unmanned aerial vehicle is provided.
In the description of the present specification, the descriptions of the terms "one embodiment," "example," "specific example," and the like, mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the utility model. In this specification, schematic representations of the above terms do not necessarily refer to the same embodiments or examples. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
The above disclosed preferred embodiments of the utility model are merely intended to help illustrate the utility model. The preferred embodiments are not exhaustive or to limit the utility model to the precise form disclosed. Obviously, many modifications and variations are possible in light of the above teaching. The embodiments were chosen and described in order to best explain the principles of the utility model and the practical application, to thereby enable others skilled in the art to best understand and utilize the utility model. The utility model is limited only by the claims and the full scope and equivalents thereof.
Claims (7)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202520153646.7U CN222522854U (en) | 2025-01-23 | 2025-01-23 | Heavy-duty industrial unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202520153646.7U CN222522854U (en) | 2025-01-23 | 2025-01-23 | Heavy-duty industrial unmanned aerial vehicle |
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| Publication Number | Publication Date |
|---|---|
| CN222522854U true CN222522854U (en) | 2025-02-25 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202520153646.7U Active CN222522854U (en) | 2025-01-23 | 2025-01-23 | Heavy-duty industrial unmanned aerial vehicle |
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| Country | Link |
|---|---|
| CN (1) | CN222522854U (en) |
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- 2025-01-23 CN CN202520153646.7U patent/CN222522854U/en active Active
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