CN205931290U - Miniature fixed wing uavs revises shock -absorbing structure of cloud platform - Google Patents
Miniature fixed wing uavs revises shock -absorbing structure of cloud platform Download PDFInfo
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- CN205931290U CN205931290U CN201620911435.6U CN201620911435U CN205931290U CN 205931290 U CN205931290 U CN 205931290U CN 201620911435 U CN201620911435 U CN 201620911435U CN 205931290 U CN205931290 U CN 205931290U
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Abstract
The utility model provides a miniature fixed wing uavs revises shock -absorbing structure of cloud platform, the brushless motor that sets up including the level and with brushless motor tip fixed connection's fixed plate, the fixed plate sets up perpendicularly, the last cover of brushless motor is equipped with aircraft grid frame board, aircraft grid frame board parallels with the fixed plate, a plurality of first through -holes have evenly been seted up around its circumferencial direction to aircraft grid frame board, the second through -hole has been seted up on the fixed plate, be connected with damping connecting part between aircraft grid frame board and the fixed plate, damping connecting part includes elastic rod and suit elastic stop block on the elastic rod, the one end of elastic rod is passed first through -hole and is installed circlip, the other end of elastic rod passes the second through -hole and installs circlip. The utility model discloses simple structure, the shock attenuation is effectual, can prevent that unmanned aerial vehicle from shaking the influence to the camera at high frequency or the low frequency that the flight in -process produced, guarantees that the camera obtains high quality image data at the flight in -process.
Description
Technical field
This utility model is related to a kind of shock-damping structure and in particular to a kind of MAV camera rolling brushless electric machine correction
Head.
Background technology
At present, known UAV flight's camera head many using traditional horizontal lifting type or horizontally suspend formula.Using
This mode causes head and installs to miniature fixed-wing unmanned aerial vehicle internal body space, the especially requirement of warehouse height relatively
For harshness, general Minitype electric fixed-wing unmanned plane cannot use, and need in advance in unmanned plane body level fix
Plate.This mode of head causes camera step in assembling, dismounting particularly loaded down with trivial details simultaneously, head maintenance also extremely inconvenience.
Utility model content
Technical problem to be solved in the utility model is for above-mentioned the deficiencies in the prior art, there is provided a kind of miniature
The shock-damping structure of fixed-wing unmanned plane correction head.This shock-damping structure is simple, and good damping effect can prevent unmanned plane from flying
The impact to camera for the high frequency or low-frequency vibration producing in journey is it is ensured that camera obtains high-quality image data in flight course.
For solving above-mentioned technical problem, the technical solution adopted in the utility model is：A kind of unmanned machine maintenance of miniature fixed-wing
The shock-damping structure of positive head is it is characterised in that including horizontally disposed brushless electric machine and being fixedly connected with brushless electric machine end
Fixed plate, described fixed plate is vertically arranged, and described brushless electric machine is set with the aircraft gridiron plate paralleled with described fixed plate,
Circumferentially direction uniformly offers multiple first through holes to described aircraft gridiron plate, described fixed plate offers logical with described first
The second corresponding through hole of hole site, is connected with shock-damping connector between described aircraft gridiron plate and fixed plate, and described damping is even
Fitting includes elastic rod and is sleeved on flexible block on described elastic rod, and one end of described elastic rod passes through described first through hole peace
Equipped with circlip, the other end of described elastic rod is provided with circlip through described second through hole, described flexible block
One side is close to described machine gridiron plate, and the another side of described flexible block is close to described fixed plate.
The shock-damping structure of above-mentioned a kind of miniature fixed-wing unmanned plane correction head it is characterised in that described elastic rod with
Flexible block is integrally formed.
The shock-damping structure of above-mentioned a kind of miniature fixed-wing unmanned plane correction head is it is characterised in that described elastic rod, bullet
Property block and circlip are integrally formed.
The shock-damping structure of above-mentioned a kind of miniature fixed-wing unmanned plane correction head is it is characterised in that described elastic rod, bullet
Property block and circlip are all made using gum elastic.
The shock-damping structure of above-mentioned a kind of miniature fixed-wing unmanned plane correction head is it is characterised in that described flexible block
For drum like structure.
This utility model compared with prior art has advantages below：
1st, this utility model, because unmanned plane is in flight course, can produce the vibrations of certain frequency, and this vibrations are passed to
The aircraft gridiron plate being directly fixedly connected, can weaken this vibrations it is ensured that on head by revising the damping of head
Camera will not be affected by unmanned plane self vibration.
2nd, the aircraft gridiron plate that this utility model is sleeved on brushless electric machine will revise head vertical hanging in unmanned plane
Lower section, this mounting means substantially reduces to the space requirement of fixed-wing unmanned plane internal body, without in unmanned plane body
The internal fixed plate installing level in advance, can be directly fixed on revising head on unmanned plane by aircraft gridiron plate.
3rd, shock-damping connector easy accessibility of the present utility model, can lay shock-damping connector according to the weight adjustment of head
Quantity, good damping effect, can be applicable.
With reference to the accompanying drawings and examples this utility model is described in further detail.
Brief description
Fig. 1 is structural representation of the present utility model.
Fig. 2 is the structural representation of this utility model shock-damping connector.
Description of reference numerals：
1 brushless electric machine；2 fixed plates；3 aircraft gridiron plates；
4-1 elastic rod；4-2 flexible block；4-3 circlip.
Specific embodiment
As depicted in figs. 1 and 2, this utility model is included horizontally disposed brushless electric machine 1 and is fixed with brushless electric machine 1 end
The fixed plate 2 that connects, described fixed plate 2 is vertically arranged, and described brushless electric machine 1 is set with and parallels with described fixed plate 2
Aircraft gridiron plate 3, circumferentially direction uniformly offers multiple first through holes to described aircraft gridiron plate 3, and described fixed plate 2 opens up
There is second through hole corresponding with described first through hole position, be connected with damping between described aircraft gridiron plate 3 and fixed plate 2 even
Fitting, described shock-damping connector includes elastic rod 4-1 and is sleeved on flexible block 4-2 on described elastic rod 4-1, described elastic rod
One end of 4-1 is provided with circlip 4-3 through described first through hole, and the other end of described elastic rod 4-1 passes through described second
Through hole is provided with circlip 4-3, and the one side of described flexible block 4-2 is close to described machine gridiron plate 3, described flexible block
The another side of 4-2 is close to described fixed plate 2.
In the present embodiment, described elastic rod 4-1, flexible block 4-2 and circlip 4-3 are integrally formed.
In the present embodiment, described elastic rod 4-1, flexible block 4-2 and circlip 4-3 are all made using gum elastic,
The high frequency producing during unmanned plane during flying can be cut down or low-frequency vibration, prevent it from just penetrating bat to revising the camera installed on head
According to impact.
In the present embodiment, described flexible block 4-2 is drum like structure.
In the present embodiment, described fixed plate 2 is bolted on brushless electric machine 1.
In the present embodiment, described elastic rod 4-1, flexible block 4-2 and circlip 4-3 are integrally formed.
In the present embodiment, described elastic rod 4-1, flexible block 4-2 and circlip 4-3 are all made using gum elastic.
When this utility model uses, first aircraft gridiron plate 3 is enclosed within brushless electric machine 1, then will be fixed by fixing bolt
Plate 2 is fixed on the end of brushless electric machine, and because described shock-damping connector is rubber, matter is soft, can be directly by circlip 4-3
Through described first through hole and described second through hole, described aircraft gridiron plate 3 is resiliently connected together with fixed plate 2, permissible
The vibrations of the generation during effectively reducing unmanned plane during flying by shock-damping structure, thus do not affect taking photo by plane of camera.
The above, be only preferred embodiment of the present utility model, not this utility model imposed any restrictions.Every
Any simple modification, change and the equivalence changes factually substantially above example made with new technique, all still fall within this
In the protection domain of utility model technical scheme.
Claims (5)
1. a kind of shock-damping structure of miniature fixed-wing unmanned plane correction head is it is characterised in that include horizontally disposed brushless electricity
Machine (1) and the fixed plate (2) being fixedly connected with brushless electric machine (1) end, described fixed plate (2) is vertically arranged, described brushless electricity
Aircraft gridiron plate (3) paralleled with described fixed plate (2), described aircraft gridiron plate (3) circumferentially direction are set with machine (1)
Uniformly offer multiple first through holes, described fixed plate (2) offers second corresponding with described first through hole position and leads to
Hole, is connected with shock-damping connector between described aircraft gridiron plate (3) and fixed plate (2), described shock-damping connector includes elastic rod
(4-1) and be sleeved on the upper flexible block (4-2) of described elastic rod (4-1), one end of described elastic rod (4-1) passes through described first
Through hole is provided with circlip (4-3), and the other end of described elastic rod (4-1) is provided with circlip through described second through hole
(4-3), the one side of described flexible block (4-2) is close to described machine gridiron plate (3), described flexible block (4-2) another
Side is close to described fixed plate (2).
2. a kind of shock-damping structure of miniature fixed-wing unmanned plane correction head according to claim 1 is it is characterised in that institute
State elastic rod (4-1) to be integrally formed with flexible block (4-2).
3. a kind of shock-damping structure of miniature fixed-wing unmanned plane correction head according to claim 1 is it is characterised in that institute
State elastic rod (4-1), flexible block (4-2) and circlip (4-3) to be integrally formed.
4. the shock-damping structure of a kind of miniature fixed-wing unmanned plane correction head according to claim 1,2 or 3, its feature exists
In described elastic rod (4-1), flexible block (4-2) and circlip (4-3) are all made using gum elastic.
5. the shock-damping structure of a kind of miniature fixed-wing unmanned plane correction head according to claim 1,2 or 3, its feature exists
In described flexible block (4-2) is drum like structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620911435.6U CN205931290U (en) | 2016-08-20 | 2016-08-20 | Miniature fixed wing uavs revises shock -absorbing structure of cloud platform |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620911435.6U CN205931290U (en) | 2016-08-20 | 2016-08-20 | Miniature fixed wing uavs revises shock -absorbing structure of cloud platform |
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| CN205931290U true CN205931290U (en) | 2017-02-08 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107240979A (en) * | 2017-05-24 | 2017-10-10 | 河南师范大学 | A kind of motor shock-absorbing device |
| CN109383832A (en) * | 2017-08-09 | 2019-02-26 | 昊翔电能运动科技(昆山)有限公司 | Rotary limit device |
| CN109538685A (en) * | 2018-12-07 | 2019-03-29 | 徐州创航科技有限公司 | A kind of unmanned plane magnetic shock-absorbing device |
-
2016
- 2016-08-20 CN CN201620911435.6U patent/CN205931290U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107240979A (en) * | 2017-05-24 | 2017-10-10 | 河南师范大学 | A kind of motor shock-absorbing device |
| CN109383832A (en) * | 2017-08-09 | 2019-02-26 | 昊翔电能运动科技(昆山)有限公司 | Rotary limit device |
| CN109538685A (en) * | 2018-12-07 | 2019-03-29 | 徐州创航科技有限公司 | A kind of unmanned plane magnetic shock-absorbing device |
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