CN211918988U - Carry on fuel cell's small-size four rotor unmanned aerial vehicle - Google Patents
Carry on fuel cell's small-size four rotor unmanned aerial vehicle Download PDFInfo
- Publication number
- CN211918988U CN211918988U CN201922017274.2U CN201922017274U CN211918988U CN 211918988 U CN211918988 U CN 211918988U CN 201922017274 U CN201922017274 U CN 201922017274U CN 211918988 U CN211918988 U CN 211918988U
- Authority
- CN
- China
- Prior art keywords
- unmanned aerial
- aerial vehicle
- vehicle body
- piston rod
- hydraulic oil
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Images
Landscapes
- Forklifts And Lifting Vehicles (AREA)
Abstract
The utility model discloses a carry on fuel cell's small-size four rotor unmanned aerial vehicle belongs to unmanned air vehicle technical field. The small-sized quad-rotor unmanned aerial vehicle carrying the fuel cell comprises an unmanned aerial vehicle body, wherein a buffering structure is arranged in the unmanned aerial vehicle body, the buffering structure comprises a hydraulic oil tank, hydraulic oil is arranged in the hydraulic oil tank, a central oil cavity is fixedly connected to the central bottom of the hydraulic oil tank, an extension oil cavity is fixedly connected to the lower end of the central oil cavity, a driving piston block is slidably connected to the central oil cavity and the extension oil cavity, a main piston rod is fixedly connected to the lower end of the driving piston block, and the lower end of the main piston rod penetrates through a bottom shell of the unmanned aerial vehicle; the bottom of the periphery of the hydraulic oil tank is fixedly connected with a buffer oil storage tank; the utility model discloses in through the buffer function when hydraulic oil realizes that the unmanned aerial vehicle body descends, can directly not transmit the impact force for the unmanned aerial vehicle body and cause the damage, solved the problem that exists among the prior art.
Description
Technical Field
The utility model relates to an unmanned air vehicle technique field specifically is the small-size four rotor unmanned aerial vehicle who carries on fuel cell.
Background
Unmanned aerial vehicles, or drones (abbreviated as UAVs), are Unmanned aircraft that are operated by means of radio remote control devices and self-contained program control devices, and can be divided into the following technical definitions: the unmanned helicopter is mainly a quad-rotor unmanned aerial vehicle, and the existing unmanned aerial vehicle mostly adopts a fuel cell as one of power sources of the unmanned aerial vehicle; the fuel cell generally comprises a cathode and an anode, and a permeable membrane is arranged between the two electrodes; hydrogen enters from the anode of the fuel cell, oxygen (or air) enters from the cathode into the fuel cell, and hydrogen molecules of the anode are decomposed into two protons and two electrons under the action of the catalyst, wherein the protons are attracted to the other side of the film by the oxygen, and the electrons reach the cathode after forming current through an external circuit, and under the action of the cathode catalyst, the protons, the oxygen and the electrons react to form water molecules; therefore, the fuel cell system has the advantages of high energy density, low noise, zero emission and the like, and is applied to the field of unmanned aerial vehicles in recent years, so that the driving range of the unmanned aerial vehicle is greatly improved, and the zero emission of carbon in the running process can be realized.
The four-rotor unmanned aerial vehicle in the prior art is limited by the operation precision or the prior art conditions, and when the unmanned aerial vehicle lands, the unmanned aerial vehicle is inevitably impacted by strong reaction force on the ground, and the body of the unmanned aerial vehicle and precision instruments erected on the unmanned aerial vehicle can be damaged to a certain extent, so that the unmanned aerial vehicle needs to be subjected to certain shock absorption treatment; the event this application provides an unmanned aerial vehicle that can play cushioning effect when descending to solve above-mentioned problem.
SUMMERY OF THE UTILITY MODEL
1. The to-be-solved technical problem of the utility model
An object of the utility model is to provide a carry on fuel cell's small-size four rotor unmanned aerial vehicle to solve the problem that proposes in the above-mentioned background art:
(1) unmanned aerial vehicle among the prior art can receive the strong reaction force impact of ground and cause the damage when descending.
2. Technical scheme
In order to achieve the above object, the utility model provides a following technical scheme:
the small-sized quad-rotor unmanned aerial vehicle carrying the fuel cell comprises an unmanned aerial vehicle body, wherein a buffering structure is arranged in the unmanned aerial vehicle body, the buffering structure comprises a hydraulic oil tank, hydraulic oil is arranged in the hydraulic oil tank, a central oil cavity is fixedly connected to the central bottom of the hydraulic oil tank, an extension oil cavity is fixedly connected to the lower end of the central oil cavity, a driving piston block is slidably connected to the central oil cavity and the extension oil cavity, a main piston rod is fixedly connected to the lower end of the driving piston block, and the lower end of the main piston rod penetrates through a bottom shell of the unmanned aerial vehicle; and the bottom of the periphery of the hydraulic oil tank is fixedly connected with a buffer oil storage tank.
Preferably, the inside sliding connection of buffering oil storage tank has the slave piston piece, slave piston piece lower extreme fixedly connected with deputy piston rod, deputy piston rod bottom runs through unmanned aerial vehicle body bottom surface casing swing joint and has gyro wheel A.
Preferably, be provided with spacing adsorption structure and stopper on the vice piston rod, spacing adsorption structure fixed connection is at the buffering oil storage tank lower extreme, stopper fixed connection is in unmanned aerial vehicle body bottom surface casing department, stopper and vice piston rod swing joint.
Preferably, the limiting adsorption structure comprises a supporting sucker and a rubber sucker, the supporting sucker is fixedly connected with the auxiliary piston rod, and the rubber sucker is connected with the auxiliary piston rod in a sliding mode.
Preferably, the buffer box body lower extreme has been seted up a plurality of and has been accomodate the groove, it has gyro wheel B to accomodate swing joint in the groove, gyro wheel B passes through telescopic link and unmanned aerial vehicle body bottom surface swing joint.
Preferably, the telescopic link includes upper strut and lower branch, upper strut and buffering box swing joint, upper strut upper end fixed connection is in unmanned aerial vehicle body bottom surface, the lower branch upper end cup joints inside upper strut through the spring, lower branch bottom and gyro wheel B's roller shaft swing joint.
3. Advantageous effects
When the utility model is used, the unmanned aerial vehicle body adopts the fuel cell-carrying quad-rotor unmanned aerial vehicle which can normally run in the prior art, and is improved based on the unmanned aerial vehicle body; the state of the device during flight is as follows: the buffering box body maintains the height of the roller B to be always lower than that of the roller A under the action of the gravity of the telescopic rod and each structure, so that the roller B is firstly contacted with the ground when the unmanned aerial vehicle body lands and lands, the roller B is acted by the upward acting force of the ground at the moment and then drives the buffering box body to move upwards, and then the main piston rod is driven to move upwards so that hydraulic oil in the central oil cavity is extruded and dispersed to the periphery of the hydraulic oil tank, the driven piston block is extruded by the hydraulic oil to drive the auxiliary piston rod to move downwards, and then the roller A is driven to move downwards, and the balance state can be maintained until the roller A lands and the hydraulic oil in the hydraulic oil tank; the utility model discloses in through the buffer function when hydraulic oil realizes that the unmanned aerial vehicle body descends, can directly not transmit the impact force for the unmanned aerial vehicle body and cause the damage, solved the problem that exists among the prior art.
Drawings
Fig. 1 is a schematic structural view of the present invention;
fig. 2 is a schematic structural diagram of the buffer structure of the present invention;
fig. 3 is a schematic structural view of the limiting adsorption structure of the present invention;
fig. 4 is a top view of the hydraulic oil tank of the present invention;
fig. 5 is a schematic view of the internal structure of the buffer box of the present invention.
The reference numbers in the figures illustrate:
1. an unmanned aerial vehicle body; 2. a hydraulic oil tank; 3. hydraulic oil; 4. a buffer box body; 5. a buffer oil storage tank; 6. a main piston rod; 7. a drive piston block; 8. an auxiliary piston rod; 9. a driven piston block; 10. a limiting block; 11. a roller A; 12. a limiting adsorption structure; 13. a central oil chamber; 14. a supporting suction cup; 15. a rubber suction cup; 16. a lower support rod; 17. a roller B; 18. a receiving groove; 19. an upper support rod; 20. an oil chamber extends.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
Example 1:
referring to fig. 1-2 and 4-5, a small-sized quad-rotor unmanned aerial vehicle carrying a fuel cell comprises an unmanned aerial vehicle body 1, a buffering structure is arranged in the unmanned aerial vehicle body 1, the buffering structure comprises a hydraulic oil tank 2, hydraulic oil 3 is arranged in the hydraulic oil tank 2, a central oil cavity 13 is fixedly connected to the central bottom of the hydraulic oil tank 2, an extension oil cavity 20 is fixedly connected to the lower end of the central oil cavity 13, a driving piston block 7 is slidably connected to the central oil cavity 13 and the extension oil cavity 20, a main piston rod 6 is fixedly connected to the lower end of the driving piston block 7, and the lower end of the main piston rod 6 penetrates through a bottom; the bottom of the periphery of the hydraulic oil tank 2 is fixedly connected with a buffer oil storage tank 5;
a driven piston block 9 is connected inside the buffer oil storage tank 5 in a sliding manner, the lower end of the driven piston block 9 is fixedly connected with an auxiliary piston rod 8, and the bottom end of the auxiliary piston rod 8 penetrates through a bottom shell of the unmanned aerial vehicle body 1 and is movably connected with a roller A11;
the auxiliary piston rod 8 is provided with a limiting adsorption structure 12 and a limiting block 10, the limiting adsorption structure 12 is fixedly connected to the lower end of the buffer oil storage tank 5, the limiting block 10 is fixedly connected to the bottom surface shell of the unmanned aerial vehicle body 1, and the limiting block 10 is movably connected with the auxiliary piston rod 8;
the lower end of the buffer box body 4 is provided with a plurality of accommodating grooves 18, the accommodating grooves 18 are movably connected with rollers B17, and the rollers B17 are movably connected with the bottom surface of the unmanned aerial vehicle body 1 through telescopic rods;
the telescopic rod comprises an upper support rod 19 and a lower support rod 16, the upper support rod 19 is movably connected with the buffer box body 4, the upper end of the upper support rod 19 is fixedly connected to the bottom surface of the unmanned aerial vehicle body 1, the upper end of the lower support rod 16 is sleeved inside the upper support rod 19 through a spring, and the bottom end of the lower support rod 16 is movably connected with a roller shaft of a roller B17;
when the utility model is used, the unmanned aerial vehicle body 1 adopts the fuel cell-carrying quad-rotor unmanned aerial vehicle which can normally run in the prior art, and is improved based on the unmanned aerial vehicle body 1; the state of the device during flight is as follows: the height of the roller B17 of the buffer box body 4 is always lower than that of the roller A11 under the action of the gravity of the telescopic rod and each structure, so that the roller B17 is firstly contacted with the ground when the unmanned aerial vehicle body 1 lands, at the moment, the roller B17 is acted by the upward acting force of the ground, the buffer box body 4 is driven to move upwards, the main piston rod 6 is driven to move upwards, the hydraulic oil 3 in the central oil cavity 13 is extruded and dispersed around the hydraulic oil tank 2, the driven piston block 9 is extruded by the hydraulic oil 3 to drive the auxiliary piston rod 8 to move downwards, the roller A11 is driven to move downwards, and the balance state can be maintained until the roller A11 lands and the hydraulic oil 3 in the hydraulic oil tank 2 restores to balance with the unmanned aerial vehicle body 1; the utility model discloses in through the buffer function when hydraulic oil 3 realizes the descending of unmanned aerial vehicle body 1, can directly not transmit the impact force for unmanned aerial vehicle body 1 and cause the damage, solved the problem that exists among the prior art.
Example 2:
referring to fig. 2-3, the limiting and adsorbing structure 12 includes a supporting sucker 14 and a rubber sucker 15, the supporting sucker 14 is fixedly connected with the auxiliary piston rod 8, and the rubber sucker 15 is slidably connected with the auxiliary piston rod 8;
the process that main piston rod 6 passes through hydraulic oil 3 drive vice piston rod 8 and goes up and down may appear relapseing, so support sucking disc 14 and rubber suction cup 15's effect realize vice piston rod 8 quick positioning when the intensity of motion of hydraulic oil 3 is less, reduce gyro wheel A11 and gyro wheel B18 and go up and down repeatedly and tend to balanced time, its concrete principle is: rubber suction cup 15 stops when moving down with the contact of 1 bottom surface of unmanned aerial vehicle body along with vice piston rod 8, because of rubber suction cup 15 and vice piston rod 8 swing joint, event vice piston rod 8 still sustainably is down and drives and support sucking disc 14 and last down, extrude rubber suction cup 15 after supporting sucking disc 14 and contacting with rubber suction cup 15 down, until all forming vacuum environment with rubber chassis 15 and 1 bottom surface of unmanned aerial vehicle body and support sucking disc 14 itself, spacing adsorption structure 12 whole fixed position and restriction vice piston rod 8 can't continue to go up and down, thereby prescribe a limit to the position of gyro wheel A11, make unmanned aerial vehicle body 1 maintain at balanced state.
The above description is only the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can substitute or change the technical solution and the improvement concept of the present invention within the technical scope disclosed in the present invention.
Claims (6)
1. Carry on fuel cell's small-size four rotor unmanned aerial vehicle, including unmanned aerial vehicle body (1), be provided with buffer structure in unmanned aerial vehicle body (1), its characterized in that: the buffering structure comprises a hydraulic oil tank (2), hydraulic oil (3) is arranged inside the hydraulic oil tank (2), a central oil cavity (13) is fixedly connected to the bottom of the center of the hydraulic oil tank (2), an extension oil cavity (20) is fixedly connected to the lower end of the central oil cavity (13), a driving piston block (7) is slidably connected to the central oil cavity (13) and the extension oil cavity (20), a main piston rod (6) is fixedly connected to the lower end of the driving piston block (7), and the lower end of the main piston rod (6) penetrates through a bottom shell of the unmanned aerial vehicle body (1) and is fixedly connected with a buffering box body (4); and the peripheral bottom of the hydraulic oil tank (2) is fixedly connected with a buffer oil storage tank (5).
2. The small quad-rotor drone with a fuel cell of claim 1, wherein: buffer oil storage tank (5) inside sliding connection has slave piston piece (9), slave piston piece (9) lower extreme fixedly connected with auxiliary piston rod (8), auxiliary piston rod (8) bottom is run through unmanned aerial vehicle body (1) bottom surface casing swing joint and is had gyro wheel A (11).
3. The small quad-rotor drone with a fuel cell of claim 2, wherein: be provided with spacing adsorption structure (12) and stopper (10) on vice piston rod (8), spacing adsorption structure (12) fixed connection is at buffering oil storage tank (5) lower extreme, stopper (10) fixed connection is in unmanned aerial vehicle body (1) bottom surface casing department, stopper (10) and vice piston rod (8) swing joint.
4. The small quad-rotor drone with a fuel cell of claim 3, wherein: spacing adsorption structure (12) are including supporting sucking disc (14) and rubber suction cup (15), support sucking disc (14) and vice piston rod (8) fixed connection, rubber suction cup (15) and vice piston rod (8) sliding connection.
5. The small quad-rotor drone with a fuel cell of claim 1, wherein: buffer box (4) lower extreme has been seted up a plurality of and has been accomodate groove (18), swing joint has gyro wheel B (17) in accomodating groove (18), gyro wheel B (17) pass through telescopic link and unmanned aerial vehicle body (1) bottom surface swing joint.
6. The small quad-rotor drone with a fuel cell of claim 5, wherein: the telescopic link includes upper strut (19) and lower branch (16), upper strut (19) and buffer box (4) swing joint, upper strut (19) upper end fixed connection is in unmanned aerial vehicle body (1) bottom surface, lower branch (16) upper end cup joints inside upper strut (19) through the spring, the roller shaft swing joint of lower branch (16) bottom and gyro wheel B (17).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922017274.2U CN211918988U (en) | 2019-11-21 | 2019-11-21 | Carry on fuel cell's small-size four rotor unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922017274.2U CN211918988U (en) | 2019-11-21 | 2019-11-21 | Carry on fuel cell's small-size four rotor unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211918988U true CN211918988U (en) | 2020-11-13 |
Family
ID=73318833
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922017274.2U Expired - Fee Related CN211918988U (en) | 2019-11-21 | 2019-11-21 | Carry on fuel cell's small-size four rotor unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211918988U (en) |
-
2019
- 2019-11-21 CN CN201922017274.2U patent/CN211918988U/en not_active Expired - Fee Related
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106697278A (en) | Direct-driven type oil-driving fixed-rotating-speed propeller pitch changing multi-rotor unmanned aerial vehicle and controlling method thereof | |
| CN105034729A (en) | Deformable multi-mode ground and air flying robot | |
| CN211918988U (en) | Carry on fuel cell's small-size four rotor unmanned aerial vehicle | |
| CN107187588A (en) | A kind of Intelligent unattended machine with safety and shock-absorption function | |
| CN203593163U (en) | Multi-rotor unmanned aerial vehicle | |
| CN206606352U (en) | A kind of strong unmanned plane of endurance | |
| CN211001806U (en) | Unmanned aerial vehicle undercarriage | |
| CN215285259U (en) | Unmanned aerial vehicle is used in specialty inspection | |
| CN211996125U (en) | Unmanned aerial vehicle with shock-absorbing function | |
| CN212709950U (en) | Undercarriage damping device of fixed wing gasoline power unmanned aerial vehicle | |
| CN113277080A (en) | Flapping wing platform for charging unmanned aerial vehicle and charging method thereof | |
| CN211519835U (en) | Aircraft detection equipment with high cruising ability | |
| CN212332959U (en) | Novel unmanned aerial vehicle shock attenuation foot rest | |
| CN215323264U (en) | Unmanned helicopter | |
| CN210284596U (en) | Unmanned aerial vehicle air cushion type rising and falling support leg structure frame | |
| CN207889971U (en) | A kind of dual-purpose undercarriage of unmanned plane | |
| CN212243804U (en) | Unmanned aerial vehicle that stability is good | |
| CN211033008U (en) | Frame structure for unmanned aerial vehicle | |
| CN218022164U (en) | Wind power station patrol unmanned aerial vehicle | |
| CN111661318A (en) | Unmanned aerial vehicle buffering landing gear | |
| CN204297044U (en) | A kind of Near Space Flying Vehicles | |
| CN208264554U (en) | A kind of UAV Landing buffer unit | |
| CN212870920U (en) | Airplane inflation simulation target direction adjusting device | |
| CN209321234U (en) | A kind of VTOL fixed-wing unmanned plane | |
| CN211494502U (en) | Be used for unmanned aerial vehicle automatic balance support |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20201113 Termination date: 20211121 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |