CN206569260U - A kind of damping tail wheel applied to fixed-wing unmanned plane - Google Patents
A kind of damping tail wheel applied to fixed-wing unmanned plane Download PDFInfo
- Publication number
- CN206569260U CN206569260U CN201720242925.6U CN201720242925U CN206569260U CN 206569260 U CN206569260 U CN 206569260U CN 201720242925 U CN201720242925 U CN 201720242925U CN 206569260 U CN206569260 U CN 206569260U
- Authority
- CN
- China
- Prior art keywords
- crossbeam
- linking arm
- wheel
- unmanned plane
- support bar
- 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
Links
- 238000013016 damping Methods 0.000 title claims abstract description 20
- 239000006096 absorbing agent Substances 0.000 claims abstract description 21
- 230000035939 shock Effects 0.000 claims abstract description 21
- 230000000694 effects Effects 0.000 claims abstract description 6
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical group [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 3
- 229910052782 aluminium Inorganic materials 0.000 claims description 3
- 239000004411 aluminium Substances 0.000 claims description 3
- 229910052799 carbon Inorganic materials 0.000 claims description 3
- 230000009471 action Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Landscapes
- Vehicle Body Suspensions (AREA)
Abstract
The utility model provides a kind of damping tail wheel applied to fixed-wing unmanned plane, including wheel 1, left linking arm 2, right linking arm 3, the 1st crossbeam 4, the 2nd crossbeam 5, support bar 6, the 3rd crossbeam 7 and shock absorber part 8；When UAV Landing, support bar 6 is acted vertically downward, and then promotes left linking arm 2 and right linking arm 3 to carry out rotation downwards counterclockwise around wheel wheel shaft；Meanwhile, when support bar 6 is acted vertically downward, drive the 3rd crossbeam 7 to move downward, and when the 3rd crossbeam 7 is moved downward, pressure is applied to shock absorber part 8, shock absorber part 8 is shunk and is reached cushioning effect.Advantage is：The heavy－duty requirement of unmanned plane can be met, the flying quality of unmanned plane is improved, the equipment that can meet UAV flight's heavy－duty meets several work requirement.Meanwhile, the design of damping tail wheel can provide the more stable steering capability of unmanned plane and the support to fuselage.
Description
Technical field
The utility model belongs to unmanned plane studying technological domain, and in particular to a kind of damping applied to fixed-wing unmanned plane
Tail wheel.
Background technology
Due to developing rapidly for unmanned plane industry in recent years, unmanned plane is in order to possess the skills such as more preferable stability and heavy－duty
Art feature, its structure and composition are also constantly updating.Wherein, the tail pulley part of fixed-wing unmanned plane is allocated as turning for whole unmanned plane
To, it is sliding run, one of the part of load-bearing, the operation to unmanned plane also plays vital effect.Conventional tail pulley structure, it is main
If connecting airframe wheel shaft by the single connecting rod of structure.
Above-mentioned tail pulley structure mainly has following deficiency：(1) in taxiing procedures, wheel shaft is easily deflected, it is impossible to give machine
The enough stability of body, while steering capability can also deflect, does not reach expected purpose, dramatically influences unmanned plane
Security, easily causes accident.(2) in unmanned plane descent, due to single connecting rod bindiny mechanism, tend not to provide foot
Enough weight capacities, if aircraft load-carrying is excessive, when tail wheel can not bear or contact ground it is too quickly when, unmanned plane can be directly resulted in
The damage of fuselage.However, due to the difference to carrying equipment, the load-carrying to unmanned plane requires also increasing, therefore, improves tail
Wheel is thing in the urgent need to address at present.
Utility model content
The defect existed for prior art, the utility model provides a kind of damping tail applied to fixed-wing unmanned plane
Wheel, can effectively solve the above problems.
The technical solution adopted in the utility model is as follows：
The utility model provides a kind of damping tail wheel applied to fixed-wing unmanned plane, including wheel (1), left linking arm
(2), right linking arm (3), the 1st crossbeam (4), the 2nd crossbeam (5), support bar (6), the 3rd crossbeam (7) and shock absorber part (8)；
The left linking arm (2) and the right linking arm (3) be arranged in parallel, the left linking arm (2) and the right connection
Parallel distance between arm (3) is equal with the wheel wheel axial extent of the wheel (1)；The bottom of the left linking arm (2) and institute
Left and right ends of the bottom of right linking arm (3) respectively with wheel wheel shaft are stated to be fixedly connected；The top of the left linking arm (2) and institute
The 1st crossbeam (4) is fixedly mounted between the top for stating right linking arm (3)；The left linking arm (2) and the right linking arm
(3) the 2nd crossbeam (5) is also fixedly mounted between；Also, the 1st crossbeam (4) and the 2nd crossbeam (5) with wheel wheel
Axle is parallel；2nd crossbeam (5) is located at the lower section of the 1st crossbeam (4)；
The support bar (6) is vertically arranged, and the top of the support bar (6) is used to be fixedly connected with unmanned aerial vehicle body；Institute
The bottom of support bar (6) is stated with being fixedly connected in the middle part of the 1st crossbeam (4)；Extend level in the top of the support bar (6)
The 3rd crossbeam (7) set；The top of the shock absorber part (8) is fixedly connected with the tail end of the 3rd crossbeam (7), described to subtract
The bottom of part (8) is shaken with being fixedly connected in the middle part of the 2nd crossbeam (5)；When UAV Landing, support bar (6) is vertically downward
Action, and then promote the left linking arm (2) and the right linking arm (3) to be carried out counterclockwise downwards around the wheel wheel shaft
Rotation；Meanwhile, when the support bar (6) acts vertically downward, drive the 3rd crossbeam (7) to move downward, and when described the
When 3 crossbeams (7) are moved downward, pressure is applied to the shock absorber part (8), the shock absorber part (8) is shunk and is reached cushioning effect.
It is preferred that, the left linking arm (2) and the right linking arm (3) they are carbon plate.
It is preferred that, the 1st crossbeam (4), the 2nd crossbeam (5) and the 3rd crossbeam (7) they are aluminium bar.
It is preferred that, the shock absorber part (8) is spring.
A kind of damping tail wheel applied to fixed-wing unmanned plane that the utility model is provided has advantages below：
A kind of damping tail wheel applied to fixed-wing unmanned plane that the utility model is provided, can meet the big load of unmanned plane
It is important to ask, the flying quality of unmanned plane is improved, the equipment that UAV flight's heavy－duty can be met, meeting several work will
Ask.Meanwhile, the design of damping tail wheel can provide the more stable steering capability of unmanned plane and the support to fuselage.
Brief description of the drawings
A kind of structural representation for damping tail wheel applied to fixed-wing unmanned plane that Fig. 1 provides for the utility model.
Embodiment
In order that technical problem, technical scheme and beneficial effect that the utility model is solved are more clearly understood, below
With reference to drawings and Examples, the utility model is further elaborated.It should be appreciated that specific implementation described herein
Example only to explain the utility model, is not used to limit the utility model.
With reference to Fig. 1, the utility model provides a kind of damping tail wheel applied to fixed-wing unmanned plane, including wheel 1, Zuo Lian
Connect arm 2, right linking arm 3, the 1st crossbeam 4, the 2nd crossbeam 5, support bar 6, the 3rd crossbeam 7 and shock absorber part 8；
Left linking arm 2 and right linking arm 3 can use carbon plate, and left linking arm 2 and right linking arm 3 be arranged in parallel, left connection
Parallel distance between arm 2 and right linking arm 3 is equal with the wheel wheel axial extent of wheel 1；The bottom of left linking arm 2 and right connection
Left and right ends of the bottom of arm 3 respectively with wheel wheel shaft are fixedly connected；The top of left linking arm 2 and the top of right linking arm 3 it
Between be fixedly mounted the 1st crossbeam 4；The 2nd crossbeam 5 is also fixedly mounted between left linking arm 2 and right linking arm 3；Also, the He of the 1st crossbeam 4
2nd crossbeam 5 is parallel with wheel wheel shaft；2nd crossbeam 5 is located at the lower section of the 1st crossbeam 4；
Support bar 6 is vertically arranged, and the top of support bar 6 is used to be fixedly connected with unmanned aerial vehicle body；The bottom of support bar 6 with
The middle part of 1st crossbeam 4 is fixedly connected；Extend horizontally disposed 3rd crossbeam 7 in the top of support bar 6；The top of shock absorber part 8 with
The tail end of 3rd crossbeam 7 is fixedly connected, and the bottom of shock absorber part 8 is fixedly connected with the middle part of the 2nd crossbeam 5；When UAV Landing,
Support bar 6 is acted vertically downward, and then promotes left linking arm 2 and right linking arm 3 to be carried out counterclockwise downwards around wheel wheel shaft
Rotation；Meanwhile, when support bar 6 is acted vertically downward, drive the 3rd crossbeam 7 to move downward, and when the 3rd crossbeam 7 is moved downward
When, apply pressure to shock absorber part 8, shock absorber part 8 is shunk and is reached cushioning effect.
In practical application, the 1st crossbeam 4, the 2nd crossbeam 5 and the 3rd crossbeam 7 are aluminium bar.Shock absorber part 8 uses spring.
A kind of damping tail wheel applied to fixed-wing unmanned plane that the utility model is provided, primary features are as follows：
(1) one end of left linking arm and right linking arm is fixed with wheel wheel shaft, and the other end is connected by support bar with fuselage,
Therefore, during unmanned plane is slided and run, the position-limiting action of left and right linking arm is passed through, it is ensured that unmanned plane will not deflect.
(2) shock absorber part is connected by bulb, and bottom is fixed on above the 2nd crossbeam, and top is connected by the 3rd crossbeam and support bar
Connect, therefore, in aircraft landing, left and right linking arm can change its angle between ground by the stress of shock absorber part, from
And a part of gravity can be disperseed, play cushioning effect.
A kind of damping tail wheel applied to fixed-wing unmanned plane that the utility model is provided, can meet the big load of unmanned plane
It is important to ask, the flying quality of unmanned plane is improved, the equipment that UAV flight's heavy－duty can be met, meeting several work will
Ask.Meanwhile, the design of damping tail wheel can provide the more stable steering capability of unmanned plane and the support to fuselage.
Described above is only preferred embodiment of the present utility model, it is noted that for the common skill of the art
For art personnel, on the premise of the utility model principle is not departed from, some improvements and modifications can also be made, these improve and
Retouching should also regard protection domain of the present utility model.
Claims (4)
1. a kind of damping tail wheel applied to fixed-wing unmanned plane, it is characterised in that including wheel (1), left linking arm (2), the right side
Linking arm (3), the 1st crossbeam (4), the 2nd crossbeam (5), support bar (6), the 3rd crossbeam (7) and shock absorber part (8)；
The left linking arm (2) and the right linking arm (3) be arranged in parallel, the left linking arm (2) and the right linking arm (3)
Between parallel distance it is equal with the wheel wheel axial extent of the wheel (1)；The bottom of the left linking arm (2) and the right company
Left and right ends of the bottom of arm (3) respectively with wheel wheel shaft are connect to be fixedly connected；The top of the left linking arm (2) and the right company
The 1st crossbeam (4) is fixedly mounted between the top for connecing arm (3)；Between the left linking arm (2) and the right linking arm (3)
The 2nd crossbeam (5) is also fixedly mounted；Also, the 1st crossbeam (4) and the 2nd crossbeam (5) are parallel with wheel wheel shaft；
2nd crossbeam (5) is located at the lower section of the 1st crossbeam (4)；
The support bar (6) is vertically arranged, and the top of the support bar (6) is used to be fixedly connected with unmanned aerial vehicle body；The branch
The bottom of strut (6) in the middle part of the 1st crossbeam (4) with being fixedly connected；Extend horizontally disposed in the top of the support bar (6)
The 3rd crossbeam (7)；The top of the shock absorber part (8) is fixedly connected with the tail end of the 3rd crossbeam (7), the shock absorber part
(8) bottom in the middle part of the 2nd crossbeam (5) with being fixedly connected；When UAV Landing, support bar (6) is acted vertically downward,
And then promote the left linking arm (2) and the right linking arm (3) to carry out turn downwards counterclockwise around the wheel wheel shaft
It is dynamic；Meanwhile, when the support bar (6) acts vertically downward, drive the 3rd crossbeam (7) to move downward, and when the described 3rd horizontal stroke
When beam (7) is moved downward, pressure is applied to the shock absorber part (8), the shock absorber part (8) is shunk and is reached cushioning effect.
2. a kind of damping tail wheel applied to fixed-wing unmanned plane according to claim 1, it is characterised in that the left company
It is carbon plate to connect arm (2) and the right linking arm (3).
3. a kind of damping tail wheel applied to fixed-wing unmanned plane according to claim 1, it is characterised in that the described 1st
Crossbeam (4), the 2nd crossbeam (5) and the 3rd crossbeam (7) are aluminium bar.
4. a kind of damping tail wheel applied to fixed-wing unmanned plane according to claim 1, it is characterised in that the damping
Part (8) is spring.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720242925.6U CN206569260U (en) | 2017-03-13 | 2017-03-13 | A kind of damping tail wheel applied to fixed-wing unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720242925.6U CN206569260U (en) | 2017-03-13 | 2017-03-13 | A kind of damping tail wheel applied to fixed-wing unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206569260U true CN206569260U (en) | 2017-10-20 |
Family
ID=60055737
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720242925.6U Expired - Fee Related CN206569260U (en) | 2017-03-13 | 2017-03-13 | A kind of damping tail wheel applied to fixed-wing unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206569260U (en) |
-
2017
- 2017-03-13 CN CN201720242925.6U patent/CN206569260U/en not_active Expired - Fee Related
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106428535A (en) | Nose landing gear of unmanned aerial vehicle | |
| CN207809790U (en) | A kind of unmanned logistics transportation machine of binary | |
| CN205707310U (en) | A kind of unmanned plane damping undercarriage | |
| CN108454834A (en) | A kind of unmanned helicopter buffer-type undercarriage | |
| CN207225646U (en) | A kind of type aircraft undercarriage | |
| CN206797691U (en) | A kind of wooden Fixed Wing AirVehicle of high aspect ratio | |
| CN106183687A (en) | A kind of driving dynamic autonomous stabilization chassis overhang | |
| CN205554569U (en) | Aerospace's undercarriage is exclusively used in | |
| CN206569260U (en) | A kind of damping tail wheel applied to fixed-wing unmanned plane | |
| CN205652139U (en) | Rail vehicle bogie draw gear of central authorities and bogie | |
| CN207466962U (en) | A kind of rotor wing unmanned aerial vehicle damping undercarriage | |
| US2326210A (en) | Aircraft landing gear | |
| CN108058830A (en) | A kind of unmanned logistics transportation machine of binary | |
| CN105480410B (en) | Take-off and landing device for small-sized unmanned aerial vehicle | |
| CN205293070U (en) | A device that takes off and land for small -size unmanned vehicles | |
| CN212709950U (en) | Undercarriage damping device of fixed wing gasoline power unmanned aerial vehicle | |
| CN206797692U (en) | Can handling goods aircraft fuselage loading cabin | |
| US11433992B2 (en) | Rotorcraft having at least one undercarriage with at least one inclined wheel, and a method | |
| CN206050048U (en) | A kind of unmanned plane high-strength welding structure fuselage | |
| CN206307262U (en) | A kind of VUAV undercarriage | |
| CN206171800U (en) | Unmanned helicopter undercarriage | |
| CN105836110B (en) | A kind of improved lifting gear for small-sized unmanned aircraft | |
| CN112278250A (en) | Fixed wing unmanned aerial vehicle capable of taking off and landing on snow | |
| CN206344740U (en) | A kind of Multifunctional navigation engine transfering car | |
| CN104192155A (en) | Lifting mechanism of schnabel car |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20211224 Address after: 161000 No. 50, dangxiao street, Jianhua District, Qiqihar City, Heilongjiang Province Patentee after: QIQIHAR SURVEYING AND PLANNING INSTITUTE OF LAND AND RESOURCES Co.,Ltd. Address before: 161000 room 01, floor 01, unit 00, east of Wenhua street, Jianhua District, Qiqihar City, Heilongjiang Province Patentee before: QIQIHAR JULONG TECHNOLOGY CO.,LTD. |
|
| 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: 20171020 |