CN104443366B - Length adjustable undercarriage for depopulated helicopter - Google Patents
Length adjustable undercarriage for depopulated helicopter Download PDFInfo
- Publication number
- CN104443366B CN104443366B CN201410720793.4A CN201410720793A CN104443366B CN 104443366 B CN104443366 B CN 104443366B CN 201410720793 A CN201410720793 A CN 201410720793A CN 104443366 B CN104443366 B CN 104443366B
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- China
- Prior art keywords
- rectangular frame
- support bar
- undercarriage
- depopulated helicopter
- length adjustable
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- 230000001276 controlling effect Effects 0.000 abstract 1
- 230000001105 regulatory effect Effects 0.000 abstract 1
- 239000007787 solid Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000002244 precipitate Substances 0.000 description 1
- 230000008054 signal transmission Effects 0.000 description 1
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Abstract
The invention discloses a kind of length adjustable undercarriage for depopulated helicopter, including rectangular frame, four spacing rings, four support bars and four individual motor, rectangular frame is fixed on below unmanned plane, four spacing rings are separately positioned on four corners of rectangular frame, four support bars lay respectively in four spacing rings, inside sliding rib it is provided with in spacing ring, the chute corresponding with sliding rib it is provided with on support bar, it is provided with tooth bar on the lateral surface of support bar, four individual motor are separately fixed at the corner of rectangular frame and its torque output shaft is engaged with the tooth bar on support bar by gear, four individual motor are connected with the control signal receptor of unmanned plane respectively.The present invention is by controlling the upper and lower of four support bars rotating control undercarriage of motor, such that it is able to the length of four support bars of undercarriage is regulated flexibly according to concrete bottom surface environment, it is possible to effectively avoid toppling over of the unmanned plane caused because bottom surface is uneven.
Description
Technical field
The present invention relates to the undercarriage of unmanned plane, particularly relate to a kind of length adjustable for depopulated helicopter
Undercarriage.
Background technology
Obtain the field condition of disaster, burst accident in time, ride vital in whole disaster relief work
Effect, in the face of precipitate disaster and accident, traditional technological means is difficult to obtain in time on-the-spot situation.
By carrying relevant equipment, unmanned plane can complete special task from the air, unmanned plane have low cost,
The advantages such as flexibility ratio height, strong adaptability, have stronger application potential in various burst accidents, traditional
Unmanned plane is all to use fixing undercarriage, when unmanned plane performs task in the occasion that ground environment is complicated,
If needing to land, probably due to bottom surface is uneven and make unmanned plane topple over, cause the damage of unmanned plane body
The damage of the relevant device gone bad or carry.
Summary of the invention
The purpose of the present invention is that provides a kind of length for depopulated helicopter to solve the problems referred to above
Adjustable undercarriage.
The present invention is achieved through the following technical solutions above-mentioned purpose:
A kind of length adjustable undercarriage for depopulated helicopter, including rectangular frame, four spacing rings,
Four support bars and four individual motor, described rectangular frame is fixed on below described unmanned plane, described in four
Spacing ring is separately positioned on four corners of described rectangular frame, and four described support bars lay respectively at four institutes
State in spacing ring, in described spacing ring, be provided with inside sliding rib, described support bar is provided with and described cunning
The chute that rib is corresponding, the lateral surface of described support bar is provided with tooth bar, and four described individual motor are solid respectively
The corner and its torque output shaft that are scheduled on described rectangular frame are nibbled with the tooth bar on described support bar by gear
Closing, four described individual motor are connected with the control signal receptor of described unmanned plane respectively.
Support bar is made to move up and down along spacing ring by controlling the rotation of individual motor, thus the height to undercarriage
Degree is adjusted.
Further, described undercarriage also includes L-type fixed mount, and the first end of described L-type fixed mount is with described
The lower surface of rectangular frame is fixing to be connected, and the second end of described L-type fixed mount is provided with auxiliary stopper ring, institute
State auxiliary stopper ring and be positioned at the lower section of described spacing ring, and the axis of described auxiliary stopper ring is spacing with described
The axis of ring overlaps, and is provided with the sliding rib corresponding with described spacing ring and tooth bar in described auxiliary stopper ring.
The mode using two point control avoids support bar to occur.
Preferably, the number of sliding rib and described auxiliary in the number of the chute on described support bar, described spacing ring
Help the number of sliding rib in spacing ring to be two, and respectively in 180 ° of angles, the tooth bar on described support bar with
Described chute is 90 ° of angles.
Further, the lower end of described support bar is provided with gripper shoe.
In order to strengthen the stability of undercarriage, in described rectangular frame, it is provided with crisscross fixer.
The beneficial effects of the present invention is:
The present invention controls to rise and fall by controlling the rotation of motor for the length adjustable undercarriage of depopulated helicopter
Four support bars of frame upper and lower, such that it is able to according to concrete bottom surface environment to four support bars of undercarriage
Length regulates flexibly, it is possible to effectively avoid toppling over of the unmanned plane caused because bottom surface is uneven.
Accompanying drawing explanation
Fig. 1 is the side view of the length adjustable undercarriage for depopulated helicopter of the present invention；
Fig. 2 is the A-A upward view of Fig. 1；
Fig. 3 is the structural representation of spacing ring of the present invention；
Fig. 4 is the sectional view of support bar of the present invention.
Detailed description of the invention
The invention will be further described below in conjunction with the accompanying drawings:
As shown in Figure 1, Figure 2, Figure 3 and Figure 4, the present invention rises and falls for the length adjustable of depopulated helicopter
Frame, solid including 1, four spacing rings of rectangular frame, 3, four individual motor 4 of 2, four support bars and L-type
Determining frame 6, rectangular frame 1 is fixed on below unmanned plane, and four spacing rings 2 are separately positioned on rectangular frame 1
Four corners, four support bars 3 lay respectively in four spacing rings 2, are provided with inside in spacing ring 2
Sliding rib 11, support bar 3 is provided with the chute 9 corresponding with sliding rib 11, the lateral surface of support bar 3 is arranged
Having a tooth bar 10, four individual motor 4 are separately fixed at the corner of rectangular frame 1 and its torque output shaft passes through
Gear 5 engages with the tooth bar 10 on support bar 3, four individual motor 4 respectively with the control signal of unmanned plane
Receptor connects, and the first end of L-type fixed mount 6 is fixing with the lower surface of rectangular frame 1 to be connected, and L-type is fixed
Second end of frame 6 is provided with auxiliary stopper ring, and auxiliary stopper ring is positioned at the lower section of spacing ring 2, and auxiliary limit
The axis of ring, position overlaps with the axis of spacing ring 2, is provided with corresponding with spacing ring 2 in auxiliary stopper ring
Sliding rib 11 and tooth bar 10, the number of sliding rib 11 in the number of chute 9 on support bar 3, spacing ring 2
The number of sliding rib 11 is two with in auxiliary stopper ring, and respectively in 180 ° of angles, on support bar 3
Tooth bar 10 and chute 9 are in 90 ° of angles, and the lower end of support bar 3 is provided with gripper shoe 8, in rectangular frame 1
It is provided with crisscross fixer 7.
The present invention is as follows for the operation principle of the length adjustable undercarriage of depopulated helicopter:
When unmanned plane needs landing, manipulation personnel send control signal according to concrete environment by controller,
Control signal transmission, to individual motor 4, controls the rotation of individual motor 4, and individual motor 4 receives control letter
After number, can be with forward or reverse, the torque output shaft of individual motor 4 is by gear 5 and support bar 3
Tooth bar 10 engages so that it is slide up and down, thus regulates the distance of support bar 3 and ground, it is to avoid occur toppling over；
Chute 9 can avoid support bar 3 to rotate in spacing ring 2 and cause gear 5 and tooth bar with sliding rib 11 simultaneously
10 occur not engaging.
Technical scheme is not limited to the restriction of above-mentioned specific embodiment, every technology according to the present invention
The technology deformation that scheme is made, within each falling within protection scope of the present invention.
Claims (5)
1. the length adjustable undercarriage for depopulated helicopter, it is characterised in that: include rectangular frame,
Four spacing rings, four support bars and four individual motor, described rectangular frame is fixed under described unmanned plane
Side, four described spacing rings are separately positioned on four corners of described rectangular frame, and four described support bars divide
It is not positioned at four described spacing rings, is provided with inside sliding rib in described spacing ring, described support bar sets
Be equipped with the chute corresponding with described sliding rib, the lateral surface of described support bar be provided with tooth bar, four described solely
Vertical motor is separately fixed at the corner of described rectangular frame and its torque output shaft by gear and described support bar
On tooth bar engagement, four described individual motor are connected with the control signal receptor of described unmanned plane respectively.
Length adjustable undercarriage for depopulated helicopter the most according to claim 1, its feature exists
In: described undercarriage also includes L-type fixed mount, the first end of described L-type fixed mount and described rectangular frame
Lower surface fixing connect, the second end of described L-type fixed mount is provided with auxiliary stopper ring, and described auxiliary limits
Position ring is positioned at the lower section of described spacing ring, and the axis of the axis of described auxiliary stopper ring and described spacing ring
Line overlaps, and is provided with the sliding rib corresponding with described spacing ring and tooth bar in described auxiliary stopper ring.
Length adjustable undercarriage for depopulated helicopter the most according to claim 2, its feature exists
In: slide the number of rib and described auxiliary stopper ring in the number of the chute on described support bar, described spacing ring
The number of interior sliding rib is two, and respectively in 180 ° of angles, the tooth bar on described support bar and described chute
In 90 ° of angles.
Length adjustable undercarriage for depopulated helicopter the most according to claim 1, its feature exists
In: the lower end of described support bar is provided with gripper shoe.
Length adjustable undercarriage for depopulated helicopter the most according to claim 1, its feature exists
In: it is provided with crisscross fixer in described rectangular frame.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410720793.4A CN104443366B (en) | 2014-12-02 | 2014-12-02 | Length adjustable undercarriage for depopulated helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410720793.4A CN104443366B (en) | 2014-12-02 | 2014-12-02 | Length adjustable undercarriage for depopulated helicopter |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104443366A CN104443366A (en) | 2015-03-25 |
| CN104443366B true CN104443366B (en) | 2016-08-24 |
Family
ID=52890287
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410720793.4A Expired - Fee Related CN104443366B (en) | 2014-12-02 | 2014-12-02 | Length adjustable undercarriage for depopulated helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104443366B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105109674B (en) * | 2015-09-14 | 2017-06-20 | 南京工程学院 | Multi-rotor aerocraft intelligence alighting carriage and its control system and method |
| GB2558150B (en) | 2015-11-05 | 2021-05-26 | Walmart Apollo Llc | Apparatus and method for stabilizing an unmanned aerial system |
| CN107215474A (en) * | 2017-05-17 | 2017-09-29 | 李坤煌 | The control method and control system of landing are balanced for aircraft |
| CN107140185B (en) * | 2017-05-22 | 2018-12-28 | 广东利美隆文化股份有限公司 | A kind of intelligence multi-rotor unmanned aerial vehicle |
| CN112591107B (en) * | 2020-12-30 | 2022-07-08 | 江汉大学 | Safety protection device and protection method for offshore operation rotor unmanned aerial vehicle |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4401285A (en) * | 1980-04-30 | 1983-08-30 | British Aerospace Public Limited Company | Aircraft undercarriage unit |
| CN2663390Y (en) * | 2003-11-28 | 2004-12-15 | 关汝壁 | Indoors lift platform structure |
| CN203294310U (en) * | 2013-04-27 | 2013-11-20 | 湖北易瓦特科技有限公司 | Retractable undercarriage of unmanned aerial vehicle |
| GB2511856A (en) * | 2013-03-15 | 2014-09-17 | Goodrich Actuation Systems Ltd | Damping arrangement for aircraft landing gear, for example a nosewheel |
| CN204297070U (en) * | 2014-12-02 | 2015-04-29 | 成都好飞机器人科技有限公司 | For the length adjustable undercarriage of depopulated helicopter |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB0416740D0 (en) * | 2004-07-27 | 2004-09-01 | Messier Dowty Ltd | Aircraft landing gear |
-
2014
- 2014-12-02 CN CN201410720793.4A patent/CN104443366B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4401285A (en) * | 1980-04-30 | 1983-08-30 | British Aerospace Public Limited Company | Aircraft undercarriage unit |
| CN2663390Y (en) * | 2003-11-28 | 2004-12-15 | 关汝壁 | Indoors lift platform structure |
| GB2511856A (en) * | 2013-03-15 | 2014-09-17 | Goodrich Actuation Systems Ltd | Damping arrangement for aircraft landing gear, for example a nosewheel |
| CN203294310U (en) * | 2013-04-27 | 2013-11-20 | 湖北易瓦特科技有限公司 | Retractable undercarriage of unmanned aerial vehicle |
| CN204297070U (en) * | 2014-12-02 | 2015-04-29 | 成都好飞机器人科技有限公司 | For the length adjustable undercarriage of depopulated helicopter |
Non-Patent Citations (1)
| Title |
|---|
| 起落架布局设计技术;张淑兰;《飞机设计》;20040630(第2期);第16-26页 * |
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| Publication number | Publication date |
|---|---|
| CN104443366A (en) | 2015-03-25 |
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| SE01 | Entry into force of request for substantive examination | ||
| C41 | Transfer of patent application or patent right or utility model | ||
| CB03 | Change of inventor or designer information |
Inventor after: Li Yingtao Inventor after: Wang Yongsheng Inventor after: Wang Shiwei Inventor after: Wu Mingwei Inventor after: Zhao Xuezhou Inventor after: Zhang Chengfeng Inventor after: Zhao Hongyuan Inventor after: Cao Huaming Inventor after: Xu Zitao Inventor after: Zhu Qinggang Inventor after: Wang Lei Inventor after: Wang Chao Inventor before: Qiu Dianchen |
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| COR | Change of bibliographic data | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20160622 Address after: 261000 Weicheng, Shandong, Dongfeng District, No. West Street, No. 425 Applicant after: STATE GRID SHANDONG ELECTRIC POWER COMPANY WEIFANG POWER SUPPLY Co. Applicant after: State Grid Corporation of China Address before: 610041 Chengdu high tech Zone, Sichuan cooperation Road, No. 89 Applicant before: CHENGDU HAOFEI ROBOT TECHNOLOGY Co.,Ltd. |
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| C14 | Grant of patent or utility model | ||
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160824 Termination date: 20211202 |
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| CF01 | Termination of patent right due to non-payment of annual fee |