CN206087273U - Unmanned aerial vehicle hydraulic pressure shock attenuation undercarriage - Google Patents
Unmanned aerial vehicle hydraulic pressure shock attenuation undercarriage Download PDFInfo
- Publication number
- CN206087273U CN206087273U CN201621116911.1U CN201621116911U CN206087273U CN 206087273 U CN206087273 U CN 206087273U CN 201621116911 U CN201621116911 U CN 201621116911U CN 206087273 U CN206087273 U CN 206087273U
- Authority
- CN
- China
- Prior art keywords
- spring
- unmanned plane
- installing plate
- sleeve pipe
- connecting rod
- 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
Landscapes
- Vibration Dampers (AREA)
Abstract
The utility model belongs to the technical field of unmanned aerial vehicle undercarriage technique and specifically relates to an unmanned aerial vehicle hydraulic pressure shock attenuation undercarriage, including first mounting panel and pulley, the bottom interval of first mounting panel is provided with a plurality of hydraulic shock absorber, the one end that hydraulic shock absorber kept away from first mounting panel is connected with the second mounting panel, the equal vertical sleeve pipe that is provided with in both sides of second mounting panel, the sheathed tube is inside to be provided with first spring, and the bottom of first spring is connected with branch, branch inserting is established inside the sheathed tube, the one end that first spring was kept away from to branch is connected with the connecting rod, the outside cover of branch is equipped with the second spring, and the both ends of second spring link to each other with sleeve pipe, connecting rod respectively, the one end that the second spring was kept away from to the connecting rod is connected with the bottom plate. The utility model has the advantages of the structure is firm, reasonable in design, convenient to use, can effectively carry out the shock attenuation to the fuselage.
Description
Technical field
The utility model is related to unmanned plane undercarriage technical field, more particularly to a kind of unmanned plane hydraulic shock-absorption undercarriage.
Background technology
UAV abbreviation unmanned plane, is manipulated not using radio robot and self-contained program's control device
Manned aircraft.Unmanned plane most occurs early in the twenties in 20th century, is used as the target drone of training, and it is mostly should
Used in military field, the development in century more than one is experienced now, it is widely applied to civil area, for example：Taking photo by plane, agriculture
The fields such as industry plant protection, mapping, have greatly expanded the purposes of unmanned plane itself.
Conventional unmanned plane takes off and the mode that withdraws is limited by condition, is reclaimed with catapult-assisted take-off and parachuting mostly and is occupied
It is many, but nowadays, a kind of unmanned plane for taking off vertically is had been developed, the unmanned plane for taking off vertically is no undue using more convenient
Limited by environment.For the unmanned plane of VTOL, its undercarriage is usually column support type, and end does not set pulley, is hanging down
When straight landing, the precision or the restriction of prior art condition due to manipulation, unmanned plane can be subject to strong when ground is touched
Strong vibrations, the precision instrument that can be damaged inside unmanned plane to a certain extent or the overall structure of unmanned plane, therefore for this
Plant the unmanned plane of VTOL, it usually needs certain damping is carried out to this and is processed, first method is exactly to unmanned plane body
Interior main precision components machine carries out damping process, and second method is exactly to carry out damping to it from unmanned plane overall structure
Process, wherein, the research for carrying out damping process to unmanned plane undercarriage is more.Practicality such as application number 201520092468.8 is new
Type patent, it discloses a kind of unmanned plane undercarriage, including an elongated bottom, and the bottom has can be connect with outside thing
Touch and provide the supporting surface and the joint face back to the supporting surface for supporting to the bottom, the unmanned plane undercarriage also includes
It is fixed on the joint face and the length direction along the bottom separates two supporting parts of predeterminable range, the end of the supporting part
End is provided with the clamping part being detachably connected for the slurry arm with unmanned plane, and the material of the unmanned plane undercarriage is with elasticity
Material.The utility model reaches the purpose of buffering and is mainly determined by the material of elasticity, not for damping in structure
Purpose makes transformation, and elastic material causes undercarriage rigidity not enough, if improving the rigidity of elastic material, the resiliency of undercarriage
Also can decline therewith, in actual applications, the damping, buffering performance of the undercarriage is simultaneously bad.
Traditional damping device structure is all complex, and weight is huge, and damping effect is also not enough, for unmanned plane comes
Say, excessive weight is clearly for it a kind of burden, affects flying quality.
Utility model content
The purpose of this utility model is unstable in order to solve the deficiency of damping effect present in prior art, shock-damping structure
The shortcomings of, and a kind of unmanned plane hydraulic shock-absorption undercarriage for proposing.
To achieve these goals, the utility model employs following technical scheme：
Design a kind of unmanned plane hydraulic shock-absorption undercarriage, including the first installing plate and pulley, the bottom of first installing plate
Portion is arranged at intervals with multiple hydraulic damper, and the hydraulic damper is connected with the second installation away from one end of the first installing plate
Plate, the both sides of second installing plate are vertically arranged with sleeve pipe, and described sleeve pipe is internally provided with the first spring, and the first bullet
The bottom of spring is connected with pole, and the pole is plugged in the inside of sleeve pipe, and the pole is connected with away from one end of the first spring
Connecting rod, the outside of the pole is arranged with second spring, and the two ends of second spring are connected respectively with sleeve pipe, connecting rod, institute
State connecting rod and be connected with base plate away from one end of second spring, the bottom of the base plate offers along its length chute, institute
Stated the both sides be provided with pulley at the top of pulley connector, and pulley connector and be provided with projection, and pulley connector passes through
Projection is flexibly connected with chute.
Preferably, it is provided with support bar between two described sleeve pipes.
Preferably, the chute is set to C-channel.
Preferably, it is provided with bolt on the pulley connector.
Preferably, first installing plate is provided with damping rubber pad away from the side of hydraulic damper.
The utility model proposes a kind of unmanned plane hydraulic shock-absorption undercarriage, beneficial effect is：The utility model makes
Used time, the first installing plate can be arranged on unmanned aerial vehicle body bottom, hydraulic damper can carry out first and buffer again to fuselage, when the
When two installing plates are pushed, second spring is in compressive state, and pole to inside pipe casing insertion is compressed to the first spring, with this shape
Buffer again into second, double buffering effect has good damping effect.The utility model have stabilized structure, it is reasonable in design,
Easy to use the advantages of, effectively damping can be carried out to fuselage.
Description of the drawings
Fig. 1 be the utility model proposes a kind of unmanned plane hydraulic shock-absorption undercarriage structural representation；
Fig. 2 be the utility model proposes a kind of unmanned plane hydraulic shock-absorption undercarriage sleeve structure schematic diagram；
Fig. 3 be the utility model proposes a kind of unmanned plane hydraulic shock-absorption undercarriage the structural representation of base plate 6.
In figure：First installing plate 1, sleeve pipe 2, connecting rod 3, pulley connector 4, pulley 5, base plate 6, the second installing plate 7, liquid
Pressure damper 8, pole 9, the first spring 10, second spring 11, chute 12, projection 13.
Specific embodiment
Below in conjunction with the accompanying drawing in the utility model embodiment, the technical scheme in the utility model embodiment is carried out
Clearly and completely describe, it is clear that described embodiment is only a part of embodiment of the utility model, rather than whole
Embodiment.
Reference picture 1-3, a kind of unmanned plane hydraulic shock-absorption undercarriage, including the first installing plate 1 and pulley 5, the first installing plate 1
The side of hydraulic damper 8 is provided with damping rubber pad, damping rubber pad has good damping effect, the first installing plate 1
Bottom interval is provided with multiple hydraulic damper 8, and hydraulic damper 8 is connected with the second installation away from one end of the first installing plate 1
Plate 7, the both sides of the second installing plate 7 are vertically arranged with sleeve pipe 2, and support bar is provided between two sleeve pipes 2, and support bar can make two
Connection between individual sleeve pipe 2 is more stable, can make overall damping effect more preferably, and sleeve pipe 2 is internally provided with the first spring 10,
And first the bottom of spring 10 be connected with pole 9, pole 9 is plugged in the inside of sleeve pipe 2.
Pole 9 is connected with connecting rod 3 away from one end of the first spring 10, and the outside of pole 9 is arranged with second spring 11, and
The two ends of second spring 11 are connected respectively with sleeve pipe 2, connecting rod 3, and connecting rod 3 is connected with base plate away from one end of second spring 11
6, the bottom of base plate 6 offers along its length chute 12, and chute 12 is set to C-channel, be easy to projection 13 and chute 12 it
Between connection it is more stable, be more convenient for using, pulley connector 4 is provided with pulley 5, positioning is provided with pulley connector 4
Bolt, the position of pulley connector 4 can automatically move in chute 12, can carry out position by bolt after movement and fix,
The user that is more convenient for is adjusted according to actually used situation to the spacing of pulley 5, and the both sides at the top of pulley connector 4 are respectively provided with
There is projection 13, and pulley connector 4 is flexibly connected by projection 13 with chute 12.
First installing plate 1 when in use, can be arranged on unmanned aerial vehicle body bottom by the utility model, and hydraulic damper 8 can
First is carried out to fuselage to buffer again, when the second installing plate 7 is pushed, second spring 11 is in compressive state, and pole 9 is into sleeve pipe 2
Portion's insertion is compressed to the first spring 10, forms second with this and buffers again, and double buffering effect has good damping effect.
The above, only the utility model preferably specific embodiment, but protection domain of the present utility model is not
Be confined to this, any those familiar with the art in the technical scope that the utility model is disclosed, according to this practicality
New technical scheme and its utility model design in addition equivalent or change, all should cover in protection model of the present utility model
Within enclosing.
Claims (5)
1. a kind of unmanned plane hydraulic shock-absorption undercarriage, including the first installing plate (1) and pulley (5), it is characterised in that described first
The bottom interval of installing plate (1) is provided with multiple hydraulic damper (8), and the hydraulic damper (8) is away from the first installing plate (1)
One end be connected with the second installing plate (7), the both sides of second installing plate (7) are vertically arranged with sleeve pipe (2), described sleeve pipe
(2) be internally provided with the first spring (10), and the bottom of the first spring (10) is connected with pole (9), and the pole (9) plugs
In the inside of sleeve pipe (2), the pole (9) is connected with connecting rod (3), the pole (9) away from one end of the first spring (10)
Outside be arranged with second spring (11), and the two ends of second spring (11) are connected respectively with sleeve pipe (2), connecting rod (3), described
Connecting rod (3) is connected with base plate (6) away from one end of second spring (11), and the bottom of the base plate (6) is opened along its length
Chute (12) is provided with, the both sides being provided with the top of pulley connector (4), and pulley connector (4) on the pulley (5) are respectively provided with
There is projection (13), and pulley connector (4) is flexibly connected by projection (13) with chute (12).
2. a kind of unmanned plane hydraulic shock-absorption undercarriage according to claim 1, it is characterised in that two described sleeve pipes (2)
Between be provided with support bar.
3. a kind of unmanned plane hydraulic shock-absorption undercarriage according to claim 1, it is characterised in that the chute (12) is arranged
For C-channel.
4. a kind of unmanned plane hydraulic shock-absorption undercarriage according to claim 1, it is characterised in that the pulley connector
(4) bolt is provided with.
5. a kind of unmanned plane hydraulic shock-absorption undercarriage according to claim 1, it is characterised in that first installing plate
(1) side of hydraulic damper (8) is provided with damping rubber pad.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621116911.1U CN206087273U (en) | 2016-10-12 | 2016-10-12 | Unmanned aerial vehicle hydraulic pressure shock attenuation undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621116911.1U CN206087273U (en) | 2016-10-12 | 2016-10-12 | Unmanned aerial vehicle hydraulic pressure shock attenuation undercarriage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206087273U true CN206087273U (en) | 2017-04-12 |
Family
ID=58483592
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621116911.1U Expired - Fee Related CN206087273U (en) | 2016-10-12 | 2016-10-12 | Unmanned aerial vehicle hydraulic pressure shock attenuation undercarriage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206087273U (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107187589A (en) * | 2017-05-08 | 2017-09-22 | 深圳市雷凌广通技术研发有限公司 | A kind of Intelligent unattended machine |
| CN107344614A (en) * | 2017-07-19 | 2017-11-14 | 胡俊 | A kind of undercarriage buffer unit |
| CN107985568A (en) * | 2017-11-29 | 2018-05-04 | 中山市小榄企业服务有限公司 | Aircraft wing for aerospace |
| CN108382602A (en) * | 2018-01-30 | 2018-08-10 | 孙吉毅 | A kind of novel unmanned plane anti-collision protection device |
| CN108502200A (en) * | 2018-04-09 | 2018-09-07 | 杭州杭睿科技有限公司 | A kind of unmanned plane with buffer structure and medicine charging function rises and falls platform |
| CN108613657A (en) * | 2018-05-07 | 2018-10-02 | 浙江省隧道工程公司 | A kind of plotting board and a kind of mapping method based on municipal works |
| CN108622381A (en) * | 2018-06-13 | 2018-10-09 | 郑州秉茂达电子科技有限公司 | A kind of aircraft landing buffering plate |
| CN109625265A (en) * | 2018-12-11 | 2019-04-16 | 青海三新农电有限责任公司 | A kind of unmanned plane synchronous integrated survey and design system |
-
2016
- 2016-10-12 CN CN201621116911.1U patent/CN206087273U/en not_active Expired - Fee Related
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107187589A (en) * | 2017-05-08 | 2017-09-22 | 深圳市雷凌广通技术研发有限公司 | A kind of Intelligent unattended machine |
| CN107187589B (en) * | 2017-05-08 | 2019-08-23 | 安徽七曜航空技术有限公司 | A kind of Intelligent unattended machine |
| CN107344614A (en) * | 2017-07-19 | 2017-11-14 | 胡俊 | A kind of undercarriage buffer unit |
| CN107985568A (en) * | 2017-11-29 | 2018-05-04 | 中山市小榄企业服务有限公司 | Aircraft wing for aerospace |
| CN107985568B (en) * | 2017-11-29 | 2021-03-23 | 山东桐强防务科技有限公司 | Aircraft wing for aerospace |
| CN108382602A (en) * | 2018-01-30 | 2018-08-10 | 孙吉毅 | A kind of novel unmanned plane anti-collision protection device |
| CN108502200A (en) * | 2018-04-09 | 2018-09-07 | 杭州杭睿科技有限公司 | A kind of unmanned plane with buffer structure and medicine charging function rises and falls platform |
| CN108613657A (en) * | 2018-05-07 | 2018-10-02 | 浙江省隧道工程公司 | A kind of plotting board and a kind of mapping method based on municipal works |
| CN108622381A (en) * | 2018-06-13 | 2018-10-09 | 郑州秉茂达电子科技有限公司 | A kind of aircraft landing buffering plate |
| CN108622381B (en) * | 2018-06-13 | 2020-10-16 | 嵊州市鉴亭新材料科技有限公司 | Landing buffering base for aircraft |
| CN109625265A (en) * | 2018-12-11 | 2019-04-16 | 青海三新农电有限责任公司 | A kind of unmanned plane synchronous integrated survey and design system |
| CN109625265B (en) * | 2018-12-11 | 2022-03-18 | 青海三新农电有限责任公司 | Unmanned aerial vehicle synchronous integrated survey design system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN206087273U (en) | Unmanned aerial vehicle hydraulic pressure shock attenuation undercarriage | |
| CN106184721B (en) | A kind of small drone buffering foot prop | |
| CN204956943U (en) | Unmanned vehicles's shock -absorbing structure and unmanned vehicles | |
| CN105204541B (en) | A kind of high-precision Stewart Active Vibration Isolation Platforms | |
| CN204822065U (en) | Unmanned aerial vehicle's undercarriage | |
| CN205312980U (en) | High stability elevating platform | |
| CN209146223U (en) | A kind of agricultural unmanned plane damping device | |
| CN206039403U (en) | Damping device for computer | |
| CN213566522U (en) | Suspension type unmanned aerial vehicle aeromagnetic detection device and nacelle thereof | |
| CN204964118U (en) | A focus adjusting device for having more rotor unmanned aerial vehicle | |
| CN206802189U (en) | High stable remote sensor with shock-damping structure | |
| CN213229120U (en) | Remote sensing surveying and mapping unmanned aerial vehicle with accurate positioning | |
| CN211391697U (en) | Pesticide storage box for agricultural unmanned aerial vehicle | |
| CN208498812U (en) | A kind of unmanned plane mapping scene evidence taking device | |
| CN208820974U (en) | A kind of modified server data exchange network safety device | |
| CN204399470U (en) | Four rotor wing unmanned aerial vehicle frames and four rotor wing unmanned aerial vehicles | |
| CN106295061A (en) | A kind of full dynamics model main landing gear method for designing and simplification structure | |
| CN206311312U (en) | Aircraft is embraced to grab and docks experimental rig with handgrip | |
| CN104792490A (en) | External store side-sway frequency and yaw frequency decoupling device of wind tunnel flutter model | |
| CN205770208U (en) | A kind of test fixture of big back amount formula motion | |
| CN106275382B (en) | A kind of unmanned plane fast assembling-disassembling wing | |
| CN214500470U (en) | A shock absorber support for building | |
| CN108099194A (en) | A kind of antigravity 3D printer | |
| CN210769996U (en) | Shock absorption support in unmanned aerial vehicle | |
| CN207311817U (en) | A kind of unmanned plane undercarriage and unmanned plane |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170412 Termination date: 20191012 |