CN206679248U - Unmanned plane undercarriage - Google Patents
Unmanned plane undercarriage Download PDFInfo
- Publication number
- CN206679248U CN206679248U CN201720464216.2U CN201720464216U CN206679248U CN 206679248 U CN206679248 U CN 206679248U CN 201720464216 U CN201720464216 U CN 201720464216U CN 206679248 U CN206679248 U CN 206679248U
- Authority
- CN
- China
- Prior art keywords
- support bar
- unmanned plane
- fuselage
- elevator
- plane undercarriage
- 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
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Abstract
The utility model discloses a kind of unmanned plane undercarriage, for unmanned plane, the unmanned plane has cylindrical body, unmanned plane undercarriage includes motor, elevator and supporting leg, the motor is fixed on fuselage inner bottom part, motor output shaft is thread spindle, elevator coordinates with motor output shaft screw thread, four supporting legs are arranged circumferentially along fuselage, the supporting leg includes first support bar, second support bar and the 3rd support bar, described first support bar one end is slide hinged in elevator top surface, the other end is vertically fixed on second support bar top, second support bar bottom is fixedly connected with the 3rd support bar, and the 3rd support bar to inboard tilt, second support bar and the 3rd support bar are located at fuselage outer side, the close junction with second support bar is hinged on fuselage in first support bar.The utility model is adapted to the landing on uneven ground, and supporting leg can collapse, and advantageously reduces the windage being subject to during unmanned plane during flying, and damping performance is outstanding.
Description
Technical field
The utility model belongs to unmanned air vehicle technique field, more particularly to a kind of unmanned plane undercarriage.
Background technology
Unmanned plane is the not manned vehicle operated using radio robot and self-contained program's control device.At present,
Unmanned plane be widely used meteorological, agricultural, explore, photograph, preventing and reducing natural disasters, Crop Estimation, drug law enforcement anti-smuggling, border are patrolled
Patrol, the field such as public security anti-terrorism.The undercarriage of prior art unmanned plane is typically all the strip undercarriage that fuselage both sides are set, and
It can not fold, therefore, be unfavorable for the landing on concavo-convex ground, and awing undercarriage can increase flight resistance, and power consumption is big.
Therefore, how to solve the defects of above-mentioned prior art is present becomes the direction that art personnel make great efforts.
Utility model content
The purpose of this utility model is just to provide a kind of unmanned plane undercarriage, can be fully solved above-mentioned the deficiencies in the prior art
Part.
The purpose of this utility model is realized by following technical proposals：
A kind of unmanned plane undercarriage, for unmanned plane, the unmanned plane has cylindrical body, and unmanned plane undercarriage includes
Motor, elevator and supporting leg, the motor are fixed on fuselage inner bottom part, and motor output shaft is thread spindle, elevator with
Motor output shaft screw thread coordinates, and is arranged circumferentially four supporting legs along fuselage, the supporting leg includes first support bar, second
Support bar and the 3rd support bar, described first support bar one end is slide hinged in elevator top surface, and the other end is vertically fixed on
Two supporting bar tops, second support bar bottom is fixedly connected with the 3rd support bar, and the 3rd support bar tilts to inboard, and second
Support bar and the 3rd support bar are located at fuselage outer side, and the close junction with second support bar is hinged in the first support bar
On fuselage.
Preferably, also including connecting rod, the fuselage inwall is provided with vertical chute, and one end and the elevator side wall of connecting rod are consolidated
Fixed connection, the other end are slidably fitted in chute.The design of such a structure can play a part of being oriented to elevator, and protect
Demonstrate,prove stability of the elevator in motion process.
Preferably, the angle between the second support bar and the 3rd support bar is 120~150 °.Such a structure is set
Meter can make it that the 3rd support bar is in vertical state and plays a part of support supporting leg after certain angle is flipped up,
Also ensure that supporting leg does not have to overturn too high and with top propeller generation interference simultaneously.
Preferably, also including bracing piece, the top of bracing piece is hinged on fuselage outer wall, and bottom is slide hinged at second
On strut.The design of bracing piece can further strengthen the supporting role of supporting leg, strengthen the bearing capacity of supporting leg.
Preferably, the 3rd support bar bottom is provided with leg, blind hole, the top of leg are opened up in the 3rd support bar bottom
End is slidably fitted in blind hole, and is provided with damping spring between leg top and blind via bottom.Use this structure can be with
The cushioning ability of supporting leg is improved, when unmanned plane lands, significantly reduces impulsive force.
Preferably, the feet bottom is taper.This stand bar structure is not only beneficial to UAV Landing and supported, and
The windage being subject to can be reduced in flight.
Preferably, the fuselage outer wall is provided with the groove matched with second support bar and the 3rd support bar, work as supporting leg
During in rounding state, second support bar and the 3rd support bar coordinate in a groove.The design of this structure can reduce nobody
Resistance during machine flight, reduce energy consumption.
Compared with prior art, the beneficial effects of the utility model are：It is simple in construction, reasonable in design, fuselage circumference cloth
Four supporting legs are equipped with, are advantageous to the landing on uneven ground, and supporting leg can collapse, and advantageously reduce unmanned plane
The windage being subject to during flight, and damping performance is outstanding.
Brief description of the drawings
Fig. 1 is the structural representation that the utility model supporting leg is in rounding state；
Fig. 2 is the structural representation that the utility model supporting leg is in open configuration；
Fig. 3 is the attachment structure schematic diagram of the 3rd support bar and leg；
Fig. 4 is the annexation figure of elevator and fuselage.
Embodiment
The utility model is further described with reference to specific embodiments and the drawings.
As shown in Figures 1 to 4, a kind of unmanned plane undercarriage, the unmanned plane have cylindrical body 1, and unmanned plane rises and falls
Frame includes motor 2, elevator 3 and supporting leg.
Motor mounting space 4 is provided with the bottom of fuselage 1, the motor 2 is reverse mounted to be fixed on the bottom of motor mounting space 4
Portion, motor output shaft are thread spindle, and elevator 3 is circle, and center opens up screwed hole, elevator 3 and motor output shaft screw thread
Coordinate.
Four supporting legs are arranged circumferentially along fuselage 1, the supporting leg includes first support bar 5, the and of second support bar 6
3rd support bar 7, described one end of first support bar 5 is slide hinged to be vertically fixed on the second support in the top surface of elevator 3, the other end
The top of bar 6, the bottom of second support bar 6 are fixedly connected with the 3rd support bar 7, close with second support bar 6 in the first support bar 5
Junction it is be hinged on the fuselage 1.3rd support bar 7 tilts to the inner side of fuselage 1, and second support bar 6 and the 3rd supports
Angle between bar 7 is 140 °, and the support bar 7 of second support bar 6 and the 3rd is located at the outside of fuselage 1.
Corresponding four first support bars 5 of the top surface of elevator 3 radially open up chute 8, and be slidably matched sliding block in chute 8
9, the end of first support bar 5 is hinged on the top of sliding block 9.The both ends of chute 8 are cecum, so as to play spacing effect.
In order to ensure the stability of the motion of elevator 3, and elevator 3 is oriented to, be provided with the inwall of motor mounting space 4
Vertical chute 10, vertical chute 10 is parallel with motor output shaft, and 4 connecting rods 11 are provided between elevator 3 and vertical chute 10,
4 connecting rods 11 are uniformly arranged along elevator 3 is circumferential, and one end of the connecting rod 11 is fixedly connected with the side wall of elevator 3, and the other end is slided
It is dynamic to coordinate in chute 10.
In order to strengthen the supporting role of supporting leg and bearing capacity, bracing piece 12 is additionally provided with, the top of bracing piece 12 is hinged
It is slide hinged in second support bar 6 in the outer wall of fuselage 1, bottom.
The bottom of bracing piece 12 is corresponded in the second support bar 6 and opens up chute, chute is set along second support bar length direction
Put, be slidably matched sliding block in chute, and the bottom of bracing piece 12 is hinged on slider top.The chute both ends are cecum, so as to play
Spacing effect.
The bottom of 3rd support bar 7 is provided with leg 13, and the bottom of leg 13 is taper, is opened in the bottom of the 3rd support bar 7
If blind hole, the top of leg 13 is slidably fitted in blind hole, and damping bullet is provided between the top of leg 13 and blind via bottom
Spring 14.The cushioning ability of supporting leg can be improved using this structure, when unmanned plane lands, significantly reduces impulsive force.
The outer wall of fuselage 1 is provided with the groove 15 matched with the support bar 7 of second support bar 6 and the 3rd, when supporting leg is in
During rounding state, the support bar 7 of second support bar 6 and the 3rd coordinates in groove 15.The design of this structure can reduce nobody
Resistance during machine flight, reduce energy consumption.
In unmanned plane during flying, first support bar 5 is located at horizontality, and the support bar 7 of second support bar 6 and the 3rd coordinates
In the groove 15 of the outer wall of fuselage 1.In UAV Landing, motor output shaft rotation, so as to drive elevator 3 to move down, and then band
Dynamic first support bar 5 is rotated down, and the first support bar 5 is rotated down using the pin joint with fuselage 1 as fulcrum, meanwhile, second
The support bar 7 of support bar 6 and the 3rd is rotated up, untill the 3rd support bar 7 is in vertical state.
The utility model has four supporting legs, is supported in four direction during UAV Landing, is advantageous to unmanned plane and exists
Stable landing on uneven ground, and damping spring 14 is provided between the support bar 7 of leg 13 and the 3rd, be pressurized big subtract
Shake spring 14 compresses shorter, therefore can finely tune the difference in height between each leg 13, unmanned plane is kept as far as possible after landing
Balance.And after supporting leg collapses, the wind surface of unmanned plane is reduced, advantageously reduces the windage being subject to during unmanned plane during flying.
Preferred embodiment of the present utility model is the foregoing is only, it is all at this not to limit the utility model
All any modification, equivalent and improvement made within the spirit and principle of utility model etc., should be included in the utility model
Protection domain within.
Claims (7)
1. a kind of unmanned plane undercarriage, for unmanned plane, the unmanned plane has cylindrical body, it is characterised in that：Unmanned plane
Undercarriage includes motor, elevator and supporting leg, and the motor is fixed on fuselage inner bottom part, and motor output shaft is screw thread
Axle, elevator coordinate with motor output shaft screw thread, are arranged circumferentially four supporting legs along fuselage, the supporting leg includes first
Support bar, second support bar and the 3rd support bar, described first support bar one end is slide hinged to hang down in elevator top surface, the other end
Second support bar top directly is fixed on, second support bar bottom is fixedly connected with the 3rd support bar, and the 3rd support bar is into fuselage
Roll oblique, second support bar and the 3rd support bar are located at fuselage outer side, close with second support bar in the first support bar
Junction is hinged on fuselage.
2. unmanned plane undercarriage according to claim 1, it is characterised in that：Also include connecting rod, the fuselage inwall is provided with
Vertical chute, one end of connecting rod are fixedly connected with elevator side wall, and the other end is slidably fitted in chute.
3. unmanned plane undercarriage according to claim 1, it is characterised in that：The second support bar and the 3rd support bar it
Between angle be 120~150 °.
4. unmanned plane undercarriage according to claim 3, it is characterised in that：Also include bracing piece, the top hinge of bracing piece
Fuselage outer wall is connected on, bottom is slide hinged in second support bar.
5. unmanned plane undercarriage according to claim 4, it is characterised in that：The 3rd support bar bottom is provided with leg,
Blind hole is opened up in the 3rd support bar bottom, the top of leg is slidably fitted in blind hole, and leg top and blind via bottom it
Between damping spring is installed.
6. unmanned plane undercarriage according to claim 5, it is characterised in that：The feet bottom is taper.
7. according to the unmanned plane undercarriage described in claim any one of 1-6, it is characterised in that：The fuselage outer wall is provided with and the
Two support bars and the groove of the 3rd support bar matching, when supporting leg is in rounding state, second support bar and the 3rd support bar
Coordinate in a groove.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720464216.2U CN206679248U (en) | 2017-04-27 | 2017-04-27 | Unmanned plane undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720464216.2U CN206679248U (en) | 2017-04-27 | 2017-04-27 | Unmanned plane undercarriage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206679248U true CN206679248U (en) | 2017-11-28 |
Family
ID=60406204
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720464216.2U Expired - Fee Related CN206679248U (en) | 2017-04-27 | 2017-04-27 | Unmanned plane undercarriage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206679248U (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107914867A (en) * | 2017-12-06 | 2018-04-17 | 南京航空航天大学 | The adaptive deformation alighting carriage of friction lock and its control method |
| CN108860579A (en) * | 2018-05-22 | 2018-11-23 | 郑州晨昱硕电子科技有限公司 | A kind of contractile shock-absorbing type unmanned plane undercarriage |
| CN110109474A (en) * | 2019-05-13 | 2019-08-09 | 刘钢 | Rotor wing unmanned aerial vehicle complicated landform autobalance landing chassis and control method |
| CN110239713A (en) * | 2019-06-28 | 2019-09-17 | 赵安朝 | It is a kind of that in the gradient, level land can not keep going up and down stable unmanned machine equipment |
| CN110979644A (en) * | 2019-12-20 | 2020-04-10 | 洛阳福格森机械装备有限公司 | Unmanned aerial vehicle undercarriage |
| CN111216880A (en) * | 2020-02-05 | 2020-06-02 | 新昌县羽林街道智西机械厂 | Undercarriage control mechanism of small aircraft |
| 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 |
| CN113184173A (en) * | 2021-06-07 | 2021-07-30 | 广西电网有限责任公司电力科学研究院 | VTOL fixed wing unmanned aerial vehicle with damping device |
| CN114030593A (en) * | 2021-11-03 | 2022-02-11 | 南京甲子智能科技有限公司 | Vertical take-off and landing unmanned aerial vehicle |
-
2017
- 2017-04-27 CN CN201720464216.2U patent/CN206679248U/en not_active Expired - Fee Related
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107914867A (en) * | 2017-12-06 | 2018-04-17 | 南京航空航天大学 | The adaptive deformation alighting carriage of friction lock and its control method |
| CN107914867B (en) * | 2017-12-06 | 2023-10-27 | 南京航空航天大学 | Friction locking self-adaptive deformation landing gear and control method thereof |
| CN108860579A (en) * | 2018-05-22 | 2018-11-23 | 郑州晨昱硕电子科技有限公司 | A kind of contractile shock-absorbing type unmanned plane undercarriage |
| CN110109474A (en) * | 2019-05-13 | 2019-08-09 | 刘钢 | Rotor wing unmanned aerial vehicle complicated landform autobalance landing chassis and control method |
| CN110239713A (en) * | 2019-06-28 | 2019-09-17 | 赵安朝 | It is a kind of that in the gradient, level land can not keep going up and down stable unmanned machine equipment |
| CN110239713B (en) * | 2019-06-28 | 2020-12-01 | 南京謇张大数据科技有限公司 | Unmanned aerial vehicle equipment capable of keeping stable lifting on uneven slope |
| CN110979644B (en) * | 2019-12-20 | 2023-03-07 | 洛阳福格森机械装备有限公司 | Unmanned aerial vehicle undercarriage |
| CN110979644A (en) * | 2019-12-20 | 2020-04-10 | 洛阳福格森机械装备有限公司 | Unmanned aerial vehicle undercarriage |
| CN111216880A (en) * | 2020-02-05 | 2020-06-02 | 新昌县羽林街道智西机械厂 | Undercarriage control mechanism of small aircraft |
| 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 |
| CN113184173B (en) * | 2021-06-07 | 2023-04-21 | 广西电网有限责任公司电力科学研究院 | Vertical take-off and landing fixed wing unmanned aerial vehicle with damping device |
| CN113184173A (en) * | 2021-06-07 | 2021-07-30 | 广西电网有限责任公司电力科学研究院 | VTOL fixed wing unmanned aerial vehicle with damping device |
| CN114030593B (en) * | 2021-11-03 | 2022-09-13 | 南京甲子智能科技有限公司 | Vertical take-off and landing unmanned aerial vehicle |
| CN114030593A (en) * | 2021-11-03 | 2022-02-11 | 南京甲子智能科技有限公司 | Vertical take-off and landing unmanned aerial vehicle |
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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: 20171128 Termination date: 20180427 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |