CN206087271U - Aircraft undercarriage convenient to adjust - Google Patents
Aircraft undercarriage convenient to adjust Download PDFInfo
- Publication number
- CN206087271U CN206087271U CN201621118371.0U CN201621118371U CN206087271U CN 206087271 U CN206087271 U CN 206087271U CN 201621118371 U CN201621118371 U CN 201621118371U CN 206087271 U CN206087271 U CN 206087271U
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- CN
- China
- Prior art keywords
- support bar
- adjust
- block
- groove
- bar
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- 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.)
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Abstract
The utility model belongs to the technical field of aircraft undercarriage technique and specifically relates to an aircraft undercarriage convenient to adjust, including the unmanned aerial vehicle body, two intraductal all the pegging graft of cover has the horizontal pole, horizontal pole upper end is even is equipped with a plurality of line array's of being spacing groove, be equipped with two second recesses on the sheathed tube inner wall, second recess bottom is equipped with vertical iron core, the iron core outside is around being equipped with the coil, the first stopper of still establishing horizontal iron plate in the second recess and matcing with the spacing groove, upper end fixed connection in the horizontal iron plate of first stopper, be equipped with two second stoppers that match with horizontal iron plate on the inner wall of second recess, two the second stopper is located the lower extreme of horizontal iron plate. This aircraft undercarriage convenient to adjust, the height of undercarriage is convenient for adjust by simple structure, has guaranteed that unmanned aerial vehicle can normally work.
Description
Technical field
The utility model is related to aircraft landing gear technical field, more particularly to a kind of aircraft for being easy to adjust rises and falls
Frame.
Background technology
Aircraft is the apparatus in endoatmosphere or exoatmosphere space flight, such as artificial earth satellite, manned spaceship, sky
Between detector, space shuttle and unmanned plane etc., wherein unmanned plane may cause because undercarriage is unadjustable in use
Unmanned plane crash, the unmanned plane being for example monitored, operationally, it is often necessary in lower flight, if undercarriage is located always
In lower position, branch may be scraped, cause unmanned plane cannot normal work, affect normal monitoring, if unmanned plane
The more position of stone is dropped to, when undercarriage is relatively low, unmanned plane and detection means can be also broken, for this purpose, it is proposed that one
Plant the aircraft landing gear for being easy to adjust.
Utility model content
The purpose of this utility model be in order to solve prior art in exist unmanned plane undercarriage highly it is uncontrollable lack
Point, and a kind of aircraft landing gear for being easy to adjust for proposing.
To achieve these goals, the utility model employs following technical scheme：
A kind of aircraft landing gear for being easy to adjust of design, including unmanned plane body, the lower end of the unmanned plane body sets
Have the first groove, first bottom portion of groove it is symmetrical be provided with two fixed seats, be rotatably connected in the fixed seat respectively
One support bar and second support bar, the first support bar is provided with the first contiguous block, and the second support bar is provided with second
Contiguous block, is rotatably connected to electric expansion bar, the electric expansion bar level between first contiguous block and the second contiguous block
Arrange, the first support bar and second support bar are connected to sleeve pipe away from one end of fixed seat, in two described sleeve pipes
Cross bar is plugged with, the cross bar upper end is uniformly provided with the stopper slot of multiple linear arrangements, sets on the inwall of described sleeve pipe
There are two the second grooves, second bottom portion of groove is provided with vertical iron core, the iron core outside is arranged with coil, described second
The first limited block for horizontal iron block being additionally provided with groove and being matched with stopper slot, the upper end of first limited block is fixedly connected on
Horizontal iron block, the inwall of second groove is provided with two the second limited blocks matched with horizontal iron block, two described second
Limited block is located at the lower end of horizontal iron block.
Preferably, the first support bar and second support bar rotate with sleeve pipe be connected respectively.
Preferably, the junction of first limited block and the second limited block is provided with Universal caster.
Preferably, the iron core is provided with the projection for preventing coil from sliding away from one end of the second bottom portion of groove.
Preferably, the two ends of the cross bar are equipped with the limiting plate for preventing sleeve pipe from skidding off.
The utility model proposes a kind of aircraft landing gear for being easy to adjust, beneficial effect is：The utility model exists
During operation, unmanned plane is adjusted according to the height of flight environment of vehicle to the height of undercarriage, first when flight environment of vehicle interference is more
It is first the coil electricity being provided with so that iron core produces magnetic so that laterally iron block drives the first limited block to pick up from stopper slot,
The electric expansion bar work that next is provided with, the angle between first support bar and second support bar becomes big so that cross bar is moved upwards
It is dynamic, finally it is broken as the circuit of coil electricity so that the first limited block falls under gravity in stopper slot, realize to horizontal stroke
The fixation of bar and the regulation to undercarriage height, when unmanned plane needs to drop to the more position of the hard objects such as stone, first
Secondly for coil electricity so that the first limited block is separated with stopper slot, electric expansion bar is shunk so that first support bar and
Angle between second support bar diminishes so that cross bar is moved down, and is finally broken as the circuit of coil electricity so that the first limit
Position block falls under gravity in stopper slot, realizes the fixation and the regulation to undercarriage height to cross bar, and this is easy to adjust
The aircraft landing gear of section, simple structure is easy to the height of adjusting landing gear, it is ensured that unmanned plane being capable of normal work.
Description of the drawings
Fig. 1 be the utility model proposes it is a kind of be easy to adjust aircraft landing gear structural representation；
Fig. 2 be the utility model proposes it is a kind of be easy to adjust aircraft landing gear the second inside grooves structural representation
Figure.
In figure：Unmanned plane body 1, the first groove 2, fixed seat 3, first support bar 4, second support bar 5, the first contiguous block
6th, the second contiguous block 7, electric expansion bar 8, sleeve pipe 9, cross bar 10, stopper slot 11, the second groove 12, coil 13, iron core 14, laterally
Iron block 15, the first limited block 16, the second limited block 17.
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.
With reference to Fig. 1-2, a kind of aircraft landing gear for being easy to adjust, including unmanned plane body 1, under unmanned plane body 1
End is provided with the first groove 2, and the bottom symmetrical of the first groove 2 is provided with two fixed seats 3, is rotatably connected to the in fixed seat 3 respectively
One support bar 4 and second support bar 5, first support bar 4 is provided with the first contiguous block 6, and second support bar 5 is provided with the second connection
Block 7, is rotatably connected to electric expansion bar 8 between the first contiguous block 6 and the second contiguous block 7, electric expansion bar 8 is horizontally disposed with, the
One support bar 4 and second support bar 5 are connected to sleeve pipe 9 away from one end of fixed seat 3, and first support bar 4 and second is supported
Bar 5 rotates with sleeve pipe 9 be connected respectively, and in two sleeve pipes 9 cross bar 10 is plugged with, and the two ends of cross bar 10 are equipped with prevents sleeve pipe 9
The limiting plate for skidding off, the upper end of cross bar 10 is uniformly provided with the stopper slot 11 of multiple linear arrangements.
The inwall of sleeve pipe 9 is provided with two the second grooves 12, and the bottom of the second groove 12 is provided with vertical iron core 14, iron core 14
Outside is arranged with coil 13, and iron core 14 is provided with the projection for preventing coil 13 from sliding away from one end of the bottom of the second groove 12, and second
The first limited block 16 for being additionally provided with horizontal iron block 15 and matching with stopper slot 11 in groove 12, the upper end of the first limited block 16 is fixed
Horizontal iron block 15 is connected to, the inwall of the second groove 12 is provided with two the second limited blocks 17 matched with horizontal iron block 15, the
The junction of one limited block 16 and the second limited block 17 is provided with Universal caster so that the first limited block 16 under gravity and to
Frictional force is less during lower slider, and two the second limited blocks 17 are located at the lower end of horizontal iron block 15.
In operation, unmanned plane is adjusted the utility model according to the height of flight environment of vehicle to the height of undercarriage, when
When flight environment of vehicle interference is more, first the coil 13 to be provided with is powered so that iron core 14 produces magnetic so that the horizontal band of iron block 15
Dynamic first limited block 16 is picked up from stopper slot 11, and the electric expansion bar 8 that next is provided with works, first support bar 4 and second
Angle between strut 5 becomes big so that cross bar 10 is moved up, and is finally broken as the circuit of the energization of coil 13 so that the first limit
Position block 16 falls under gravity in stopper slot 11, realizes the fixation and the regulation to undercarriage height to cross bar 10, when
Unmanned plane needs to drop to the more position of the hard objects such as stone, is powered for coil 13 first so that the first limited block 16 with
Stopper slot 11 is separated, and electric expansion bar 8 is shunk so that the angle between first support bar 4 and second support bar 5 becomes
It is little so that cross bar 10 is moved down, finally it is broken as the circuit of the energization of coil 13 so that the first limited block 16 is under gravity
Fall in stopper slot 11, realize the fixation and the regulation to undercarriage height to cross bar 10, this is easy to the aircraft for adjusting to rise
Fall frame, simple structure, is easy to the height of adjusting landing gear, it is ensured that unmanned plane being capable of normal work.
More than, only the utility model preferably specific embodiment, but protection domain of the present utility model is not limited to
In this, any those familiar with the art in the technical scope that the utility model is disclosed, according to the utility model
Technical scheme and its utility model design in addition equivalent or change, all should cover protection domain of the present utility model it
It is interior.
Claims (5)
1. a kind of aircraft landing gear for being easy to adjust, including unmanned plane body (1), the lower end of the unmanned plane body (1) sets
There is the first groove (2), the first groove (2) bottom symmetrical is provided with two fixed seats (3), it is characterised in that the fixation
First support bar (4) and second support bar (5) are rotatably connected to respectively on seat (3), and the first support bar (4) is provided with first
Contiguous block (6), the second support bar (5) is provided with the second contiguous block (7), first contiguous block (6) and the second contiguous block
(7) be rotatably connected to electric expansion bar (8) between, the electric expansion bar (8) is horizontally disposed with, the first support bar (4) and
Second support bar (5) is connected to sleeve pipe (9) away from one end of fixed seat (3), and in two described sleeve pipes (9) horizontal stroke is plugged with
Bar (10), cross bar (10) upper end is uniformly provided with the stopper slot (11) of multiple linear arrangements, the inwall of described sleeve pipe (9)
Two the second grooves (12) are provided with, the second groove (12) bottom is provided with vertical iron core (14), and the iron core (14) is outward
Side is arranged with first in coil (13), second groove (12) being additionally provided with horizontal iron block (15) and matching with stopper slot (11)
Limited block (16), the upper end of first limited block (16) is fixedly connected on horizontal iron block (15), second groove (12)
Inwall is provided with two the second limited blocks (17) matched with horizontal iron block (15), and two second limited blocks (17) are positioned at horizontal stroke
To the lower end of iron block (15).
2. it is according to claim 1 it is a kind of be easy to adjust aircraft landing gear, it is characterised in that the first support bar
(4) rotate with sleeve pipe (9) be connected respectively with second support bar (5).
3. it is according to claim 1 it is a kind of be easy to adjust aircraft landing gear, it is characterised in that first limited block
(16) it is provided with Universal caster with the junction of the second limited block (17).
4. a kind of aircraft landing gear for being easy to adjust according to claim 1, it is characterised in that the iron core (14) is remote
The projection for preventing coil (13) from sliding is provided with from one end of the second groove (12) bottom.
5. it is according to claim 1 it is a kind of be easy to adjust aircraft landing gear, it is characterised in that the cross bar (10)
Two ends are equipped with the limiting plate for preventing sleeve pipe (9) from skidding off.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621118371.0U CN206087271U (en) | 2016-10-12 | 2016-10-12 | Aircraft undercarriage convenient to adjust |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621118371.0U CN206087271U (en) | 2016-10-12 | 2016-10-12 | Aircraft undercarriage convenient to adjust |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206087271U true CN206087271U (en) | 2017-04-12 |
Family
ID=58482792
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621118371.0U Expired - Fee Related CN206087271U (en) | 2016-10-12 | 2016-10-12 | Aircraft undercarriage convenient to adjust |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206087271U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112429237A (en) * | 2020-12-14 | 2021-03-02 | 合肥科技职业学院 | Rocker unmanned aerial vehicle with ice and snow monitoring devices |
-
2016
- 2016-10-12 CN CN201621118371.0U patent/CN206087271U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112429237A (en) * | 2020-12-14 | 2021-03-02 | 合肥科技职业学院 | Rocker unmanned aerial vehicle with ice and snow monitoring devices |
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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: 20170412 Termination date: 20191012 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |