CN209617492U - A kind of unmanned plane intake type undercarriage - Google Patents
A kind of unmanned plane intake type undercarriage Download PDFInfo
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- CN209617492U CN209617492U CN201920344995.1U CN201920344995U CN209617492U CN 209617492 U CN209617492 U CN 209617492U CN 201920344995 U CN201920344995 U CN 201920344995U CN 209617492 U CN209617492 U CN 209617492U
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- support bar
- unmanned plane
- installation cavity
- sliding
- accommodating groove
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Abstract
The utility model discloses a kind of unmanned plane intake type undercarriages, including fuselage, fuselage both ends sidewall symmetry is set there are four accommodating groove, upper end is rotatablely connected by short axle and first support bar one end in accommodating groove, first support bar activity is connected in accommodating groove, the free end of first support bar, which extends to outside accommodating groove, is fixedly connected with second support bar, the other end sliding of second support bar is connected with stabilizer blade, installation cavity is equipped in fuselage, installation cavity inner bottom surface is fixedly installed with motor, the turning end of motor is fixedly installed with thread spindle, the top of thread spindle is rotatably connected on installation cavity inner top surface, and the outer wall thread of thread spindle is socketed with sliding block, sliding block top surface four corners are hinged with connecting rod, the other end of connecting rod is side walls hinged by the first support bar being rotatablely connected in slot and accommodating groove that installation cavity is connected to, this device compares traditional unmanned plane, Undercarriage can be stored at any time, after gathering, the windage that is subject to when advantageously reducing unmanned plane during flying.
Description
Technical field
The utility model relates to air vehicle technique field, specially a kind of unmanned plane intake type undercarriage.
Background technique
Unmanned plane is the not manned vehicle operated using radio robot and self-contained program's control device.Currently,
Unmanned plane be widely used it is meteorological, agricultural, explore, photograph, preventing and reducing natural disasters, Crop Estimation, drug law enforcement anti-smuggling, border are patrolled
It patrols, the fields such as public security anti-terrorism, the undercarriage of traditional unmanned plane is typically all the strip undercarriage of fuselage two sides setting, and not
Foldable, folding and unfolding freely or the assembling structure that cannot achieve undercarriage are complicated, prior art introduction and defect, thus I
Propose a kind of unmanned plane intake type undercarriage for solving the above problems.
Utility model content
The purpose of this utility model is to provide a kind of unmanned plane intake type undercarriages, to solve to mention in above-mentioned background technique
Out the problem of.
To achieve the above object, the utility model provides the following technical solutions: a kind of unmanned plane intake type undercarriage, including
Fuselage, fuselage both ends sidewall symmetry are set there are four accommodating groove, and upper end passes through short axle and first support bar in the accommodating groove
One end rotation connection, the first support bar activity is connected in accommodating groove, and the free end of first support bar extends to storage
Second support bar is fixedly connected with outside slot, the other end sliding of the second support bar is connected with stabilizer blade, is equipped in the fuselage
Installation cavity, the installation cavity inner bottom surface are fixedly installed with motor, and the turning end of the motor is fixedly installed with thread spindle, the spiral shell
The top of line axis is rotatably connected on installation cavity inner top surface, and the outer wall thread of thread spindle is socketed with sliding block, the sliding block top surface four
Connecting rod, first be rotatablely connected in slot and accommodating groove that the other end of the connecting rod is connected to by installation cavity are hinged at angle
Support rod is side walls hinged.
Obtuse angle as a kind of optimal technical scheme of the utility model, between the first support bar and second support bar
Angle is 130 degree.
As a kind of optimal technical scheme of the utility model, sliding block both ends side wall is fixed with limited block, described
Cavity wall is installed and limited block cooperation is equipped with limiting slot.
As a kind of optimal technical scheme of the utility model, the stabilizer blade is taper.
As a kind of optimal technical scheme of the utility model, the second support bar is set far from one end of first support bar
Fluted, one end sliding of the stabilizer blade is connected in groove, and stabilizer blade is fixedly connected close to one end side wall of first support bar
There is spring, the other end of the spring is fixedly connected with the slot bottom with groove.
As a kind of optimal technical scheme of the utility model, groove both ends side wall is equipped with locating slot, the stabilizer blade
One end in groove is corresponding with locating slot to be fixed with locating piece, and the locating piece sliding is connected in locating slot.
As a kind of optimal technical scheme of the utility model, opened on the sliding block there are four sliding slot, the one of the connecting rod
End is slide hinged by hinged shaft and sliding slot.
Compared with prior art, the utility model has the beneficial effects that
1. this device compares traditional unmanned plane, undercarriage can be stored at any time, easy to operate effective, and after gathering,
The wind surface for reducing unmanned plane, the windage being subject to when advantageously reducing unmanned plane during flying.
2. stabilizer blade is taper, can be when being contacted with ground, more firm, one end sliding of stabilizer blade is connected in groove, is led to
Spring connection to be crossed, stable landing of the unmanned plane on uneven ground can be conducive to, the big bullet that is pressurized can be compressed shorter,
Therefore the difference in height between each stabilizer blade can be finely tuned, keeps balance after so that unmanned plane is landed as far as possible.
Detailed description of the invention
FIG. 1 is a schematic structural view of the utility model；
Fig. 2 is cross-sectional view in the utility model；
Fig. 3 is structure enlarged structure schematic diagram at A in the utility model Fig. 2；
Fig. 4 is the connection explosive view of the utility model sliding block and connecting rod.
In figure: 1 fuselage, 11 installation cavitys, 12 accommodating grooves, 13 limiting slots, 14 through slot, 2 motors, 21 thread spindles, 22 sliding blocks,
23 connecting rods, 24 first support bars, 25 short axles, 26 second support bars, 27 stabilizer blades, 28 grooves, 29 springs, 210 limited blocks, 211 are determined
Position slot, 212 locating pieces, 3 sliding slots, 4 hinged shafts.
Specific embodiment
The following will be combined with the drawings in the embodiments of the present invention, carries out the technical scheme in the embodiment of the utility model
Clearly and completely describe, it is clear that the described embodiments are only a part of the embodiments of the utility model, rather than whole
Embodiment.Based on the embodiments of the present invention, those of ordinary skill in the art are without making creative work
Every other embodiment obtained, fall within the protection scope of the utility model.
Fig. 1-4 is please referred to, the utility model provides a kind of technical solution: a kind of unmanned plane intake type undercarriage, including machine
Body 1,1 both ends sidewall symmetry of fuselage are set there are four accommodating groove 12, and upper end passes through short axle 25 and first support bar 24 in accommodating groove 12
One end rotation connection, 24 activity of first support bar is connected in accommodating groove 12, and the free end of first support bar 24 extends to receipts
Slot 12 of receiving is fixedly connected with second support bar 26 outside, and the obtuse angle angle between first support bar 24 and second support bar 26 is 100
30 degree, the other end sliding of second support bar 26 is connected with stabilizer blade 27, and installation cavity 11, bottom in installation cavity 11 are equipped in fuselage 1
Face is fixedly installed with motor 2, and (it is other for realizing unmanned plane normal operation that power supply and control panel etc. are additionally provided in installation cavity 11
Electronic component, these have many disclosed technical solutions, and the utility model for the current market of electronic component of unmanned plane
Technical solution be stowable undercarriage part thus not the structure to electronic components such as power supply, control panels and principle do it is superfluous
State), the turning end of motor 2 is fixedly installed with thread spindle 21, and the top of thread spindle 21 is rotatably connected on 11 inner top surface of installation cavity, and
The outer wall thread of thread spindle 21 is socketed with sliding block 22, and 22 top surface four corners of sliding block are hinged with connecting rod 23, and the other end of connecting rod 23 is logical
The side walls hinged through slot 14 and the first support bar 24 of rotation connection in accommodating groove 12 of the connection of installation cavity 11 is crossed, when unmanned plane needs
When landing, for control panel according to the program being previously set by cable starter motor 2, the turning end of motor 2 drives thread spindle
21 rotations, make sliding block 22 that can do linear motion up and down reciprocatingly on thread spindle 21, transport when sliding block 22 to the direction close to motor 2
When dynamic, sliding block 22 drives connecting rod 23 to move downward together, since connecting rod 23 and sliding block 22 and first support bar 24 are hinged, therefore even
Bar 23 pulls first support bar 24, expands first support bar 24 to accommodating groove 12, utilizes the stabilizer blade 27 in second support bar 26
Sliding block 22 is moved to the direction far from motor 2, and first support bar 24 is received if need to store with ground face contact
After holding together, the wind surface of unmanned plane is reduced, the windage being subject to when advantageously reducing unmanned plane during flying.
Specific 22 both ends side wall of sliding block is fixed with limited block 210, and 11 inner wall of installation cavity is equipped with the cooperation of limited block 210
Limiting slot 13, limiting slot 1 and the sliding of limited block 210 are clamped, and make what sliding block 22 can be stable on thread spindle 21 to move in a straight line.
Please referring to Fig. 3 stabilizer blade 27 is taper, and second support bar 26 is equipped with groove 28, branch far from one end of first support bar 24
One end sliding of foot 27 is connected in groove 28, and stabilizer blade 27 is fixedly connected with spring close to one end side wall of first support bar 24
29, the other end of spring 29 is fixedly connected with groove 28 close to one end of first support bar 24, stabilizer blade 27 be taper, can with ground
More firm when face contact, one end sliding of stabilizer blade 27 is connected in groove 28, is connected by spring 29, can be conducive to nobody
Stable landing of the machine on uneven ground, the bullet 29 for being pressurized big can be compressed shorter, therefore can finely tune each stabilizer blade
Difference in height between 27 keeps balance as far as possible after so that unmanned plane is landed.
Referring to Fig. 3,28 both ends side wall of groove is equipped with locating slot 211, stabilizer blade 27 is located at one end and positioning in groove 28
Slot 211 is corresponding to be fixed with locating piece 212, and the sliding of locating piece 212 is connected in locating slot 211, avoids stabilizer blade 27 and groove 28
It is detached from.It will form the displacement difference of horizontal direction after moving up and down additionally, due to sliding block 22, opened on the sliding block 22 there are four sliding slot
3, one end of the connecting rod 23 is slide hinged to make up this distance change by hinged shaft 4 and sliding slot 3, and connecting rod 23 is another
One end is hinged by another hinged shaft 4 and first support bar 24.
Working principle: when the utility model is used, the turning end of motor 2 drives thread spindle 21 to rotate, make sliding block 22 can
Linear motion up and down reciprocatingly is done on thread spindle 21, when motor 2 rotates forward, sliding block 22 is moved to the direction close to motor 2
When, sliding block 22 drives connecting rod 23 to move downward together, since connecting rod 23 and sliding block 22 and first support bar 24 are hinged, therefore connecting rod
23 pull first support bars 24, make first support bar 24 to accommodating groove 12 expand, using in second support bar 26 stabilizer blade 27 with
Ground face contact, if need to store, motor 2 is rotated backward according to the good program of pre-edit, by sliding block 22 to far from motor 2
Direction movement, and first support bar 24 collapse after, reduce the wind surface of unmanned plane, advantageously reduce unmanned plane during flying
When the windage that is subject to, stabilizer blade 27 is taper, can be when being contacted with ground, more firm, one end sliding of stabilizer blade 27 is connected to recessed
It in slot 28, is connected by spring 29, stable landing of the unmanned plane on uneven ground can be conducive to, the spring 29 for being pressurized big
It can be compressed shorter, therefore the difference in height between each stabilizer blade 27 can be finely tuned, keep balance after so that unmanned plane is landed as far as possible.
While there has been shown and described that the embodiments of the present invention, for the ordinary skill in the art,
It is understood that these embodiments can be carried out with a variety of variations in the case where not departing from the principles of the present invention and spirit, repaired
Change, replacement and variant, the scope of the utility model is defined by the appended claims and the equivalents thereof.
Claims (7)
1. a kind of unmanned plane intake type undercarriage, including fuselage (1), it is characterised in that: fuselage (1) both ends sidewall symmetry is set
There are four accommodating groove (12), the interior upper end of the accommodating groove (12) is connected by short axle (25) and the rotation of first support bar (24) one end
It connects, first support bar (24) activity is connected in accommodating groove (12), and the free end of first support bar (24) extends to receipts
Slot (12) of receiving is fixedly connected with second support bar (26) outside, and the other end sliding of the second support bar (26) is connected with stabilizer blade
(27), installation cavity (11) are equipped in the fuselage (1), installation cavity (11) inner bottom surface is fixedly installed with motor (2), the horse
Turning end up to (2) is fixedly installed with thread spindle (21), and the top of the thread spindle (21) is rotatably connected in installation cavity (11)
Top surface, and the outer wall thread of thread spindle (21) is socketed with sliding block (22), sliding block (22) top surface four corners are hinged with connecting rod
(23), the rotation connection in slot (14) and accommodating groove (12) that the other end of the connecting rod (23) is connected to by installation cavity (11)
First support bar (24) it is side walls hinged.
2. a kind of unmanned plane intake type undercarriage according to claim 1, it is characterised in that: the first support bar (24)
Obtuse angle angle between second support bar (26) is 130 degree.
3. a kind of unmanned plane intake type undercarriage according to claim 1, it is characterised in that: (22) two end side of sliding block
Wall is fixed with limited block (210), and installation cavity (11) inner wall and limited block (210) cooperation are equipped with limiting slot (13).
4. a kind of unmanned plane intake type undercarriage according to claim 1, it is characterised in that: the stabilizer blade (27) is cone
Shape.
5. a kind of unmanned plane intake type undercarriage according to claim 1, it is characterised in that: the second support bar (26)
One end far from first support bar (24) is equipped with groove (28), and one end sliding of the stabilizer blade (27) is connected in groove (28),
And one end side wall of the stabilizer blade (27) close to first support bar (24) is fixedly connected with spring (29), the other end of the spring (29)
It is fixedly connected with the slot bottom of groove (28).
6. a kind of unmanned plane intake type undercarriage according to claim 5, it is characterised in that: (28) two end side of groove
Wall is equipped with locating slot (211), and the stabilizer blade (27) is located at be fixed with corresponding with locating slot (211) of one end in groove (28) and determines
Position block (212), locating piece (212) sliding are connected in locating slot (211).
7. a kind of unmanned plane intake type undercarriage according to claim 1, it is characterised in that: be provided on the sliding block (22)
One end of four sliding slots (3), the connecting rod (23) is slide hinged by hinged shaft (4) and sliding slot (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920344995.1U CN209617492U (en) | 2019-03-19 | 2019-03-19 | A kind of unmanned plane intake type undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920344995.1U CN209617492U (en) | 2019-03-19 | 2019-03-19 | A kind of unmanned plane intake type undercarriage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209617492U true CN209617492U (en) | 2019-11-12 |
Family
ID=68457200
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920344995.1U Expired - Fee Related CN209617492U (en) | 2019-03-19 | 2019-03-19 | A kind of unmanned plane intake type undercarriage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209617492U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111498091A (en) * | 2020-04-14 | 2020-08-07 | 北京共创晶桔科技服务有限公司 | Unmanned aerial vehicle of long-range face iris discernment safety authentication of developments |
| CN113460307A (en) * | 2021-06-16 | 2021-10-01 | 贵州大学 | Plant protection unmanned aerial vehicle sprays stirring medical kit that biocontrol bacterium was used |
-
2019
- 2019-03-19 CN CN201920344995.1U patent/CN209617492U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111498091A (en) * | 2020-04-14 | 2020-08-07 | 北京共创晶桔科技服务有限公司 | Unmanned aerial vehicle of long-range face iris discernment safety authentication of developments |
| CN113460307A (en) * | 2021-06-16 | 2021-10-01 | 贵州大学 | Plant protection unmanned aerial vehicle sprays stirring medical kit that biocontrol bacterium was used |
| CN113460307B (en) * | 2021-06-16 | 2023-01-24 | 贵州大学 | Plant protection unmanned aerial vehicle sprays stirring medical kit that biocontrol bacterium was used |
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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 | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20191112 Termination date: 20200319 |