CN105980250A - Landing gear and an unmanned aerial vehicle using the landing gear - Google Patents
Landing gear and an unmanned aerial vehicle using the landing gear Download PDFInfo
- Publication number
- CN105980250A CN105980250A CN201580004257.7A CN201580004257A CN105980250A CN 105980250 A CN105980250 A CN 105980250A CN 201580004257 A CN201580004257 A CN 201580004257A CN 105980250 A CN105980250 A CN 105980250A
- Authority
- CN
- China
- Prior art keywords
- support member
- undercarriage
- mounting seat
- described support
- undercarriages
- 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.)
- Granted
Links
- 230000003139 buffering effect Effects 0.000 claims abstract description 9
- 238000009434 installation Methods 0.000 claims description 30
- 239000013536 elastomeric material Substances 0.000 claims description 2
- 230000000694 effects Effects 0.000 abstract description 7
- 238000013016 damping Methods 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 2
- 230000003014 reinforcing effect Effects 0.000 description 2
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000000741 silica gel Substances 0.000 description 1
- 229910002027 silica gel Inorganic materials 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
- B64C25/60—Oleo legs
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Prevention Devices (AREA)
- Manipulator (AREA)
Abstract
The invention provides an unmanned aerial vehicle comprising a fuselage and a landing gear, the landing gear including a support leg wherein the support leg includes a support provided on the body and a buffer for buffering the impact of the landing gear when the unmanned aerial vehicle landed, the support being provided with a support for mounting the bumper. The bumper is disposed at an end of the support away from the fuselage. The unmanned aerial vehicle landing gear achieves better buffer effect when the unmanned aerial vehicle lands.
Description
Technical field
The present invention relates to a kind of undercarriage and use the unmanned vehicle of this undercarriage.
Background technology
Unmanned vehicle generally comprises fuselage and is installed in the undercarriage on described fuselage, and described undercarriage includes at least
Two spikes.The weight overall for alleviating described unmanned vehicle, and ensure described unmanned vehicle stablizing when flight
Property, described spike is generally multiple support bar and is rigidly connected to each other and forms, and described support bar is connected on described fuselage, as
The support during landing of described unmanned vehicle.But, the rigidity of described spike is relatively big, when described unmanned vehicle lands,
Its cushioning effect is limited.
Summary of the invention
In view of the foregoing, it is necessary to a kind of relatively good undercarriage of buffering effect is provided, and uses this undercarriage
Unmanned vehicle.
A kind of undercarriage, is applied in unmanned vehicle, and described undercarriage includes a spike.Described spike includes supporting
Part and for buffer described unmanned vehicle landing time described undercarriage impact buffer, described support member sets
There is the installation portion for installing described buffer.
Further, described buffer is hydraulic damper or air damper.
Further, described support member one end is for connecting end, and other end is landing end, and described installation portion is arranged at described
The landing end of support member.
Further, the connection end of described support member is provided with connecting portion, described connecting portion for described nobody fly
The horn of row device is detachably connected.
Further, described spike also includes the mounting seat of the horn for connecting described unmanned vehicle, described company
The portion of connecing is removably attachable in described mounting seat.
Further, in described connecting portion and described mounting seat is provided with female thread, described connecting portion and institute
State in mounting seat another on be provided with the external screw thread matched with described female thread, described female thread and described external screw thread phase
It is screwed together；
Or, in described connecting portion and described mounting seat is provided with elastic clamping hook, described connecting portion and described
Being provided with the draw-in groove matched with described elastic clamping hook on another in mounting seat, described elastic clamping hook is mutual with described draw-in groove
Clamping connects.
Further, described spike also includes that girth member, described girth member one end are arranged in described mounting seat, another
End is connected on described support member；Described mounting seat, described girth member and described support member are the structure of Tripod.
Further, described girth member includes the installation end being arranged in described mounting seat, and is arranged at described installation
End also extends to described support member and is connected to the supporting part on described support member.
Further, described installation end is connected in described mounting seat by a securing member, and described installation end can be around institute
State fastener rotation to drive described supporting part to rotate relative to described mounting seat.
Further, described girth member also include being arranged on described supporting part and with the clamping of described support member phase clamping
Portion.
Further, described holding section being provided with holding hole, described holding section is sheathed on described by described holding hole
On support member.
Further, described spike also includes the locating part being arranged on described support member, and described locating part is with described
Mounting seat offsets.
Further, described locating part includes that fixed cover is located at the sleeved part on described support member and is arranged at described set
If the limiting section in portion, described limiting section offsets with described mounting seat.
Further, described buffer includes being arranged at the body on described support member and being housed in described movably
Movable part in body, described movable part is connected with described body piston and partly protrudes out described body and described support member
Outward.
Further, described body is contained in described support member, and described buffer also includes being arranged on described body
Location division, described location division is held in the end of described support member；
And/or, described the internal elastic reset part that is provided with, described elastic reset part one end is connected on described body,
The other end is connected on described movable part.
Further, described spike also includes that guard member, described guard member are sheathed on described support member and are coated on
Outside described movable part.
Further, described guard member is the protection set that elastomeric material is made.
Further, described spike is obliquely installed relative to vertical direction.
Further, angle formed by described support member and vertical direction is more than or equal to degree and less than or equal to degree.
A kind of unmanned vehicle, it includes fuselage and as above undercarriage described in any one, and described support member is arranged at institute
Stating on fuselage, described buffer is arranged at described support member one end away from described fuselage.
Further, described unmanned vehicle also includes the horn being arranged on described fuselage and is arranged at described horn
On power set, described power set with think described unmanned vehicle provide flying power.
Further, described power set are obliquely installed relative to vertical direction；
And/or, described support member is fixing with described horn to be connected, or is rotatably connected.
Further, described power set include the actuator being arranged on described horn and are connected on described actuator
Propeller, described actuator is in order to drive described propeller rotational.
Further, described power set are correspondingly arranged with described support member.
Above-mentioned unmanned vehicle, its undercarriage is provided with buffer, and described buffer is positioned at the bottom of described spike, works as institute
When stating unmanned vehicle landing, first described buffer accepts to come from the impulsive force on ground, makes described movable part relatively described
Body slides, and then plays the effect of damping energy-absorbing, and its buffering effect is relatively preferable, reduce drop impact to described nobody fly
The infringement that row device entirety causes.
Accompanying drawing explanation
Fig. 1 is the schematic perspective view of unmanned vehicle in an embodiment of the present invention.
Fig. 2 is the enlarged diagram of the region II of unmanned vehicle shown in Fig. 1.
Fig. 3 is the part-structure decomposing schematic representation of unmanned vehicle shown in Fig. 2.
Main element symbol description
Following detailed description of the invention will further illustrate the present invention in conjunction with above-mentioned accompanying drawing.
Detailed description of the invention
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is carried out clear, complete
Describe, it is clear that described embodiment is only a part of embodiment of the present invention rather than whole embodiments wholely.Based on
Embodiment in the present invention, it is every other that those of ordinary skill in the art are obtained under not making creative work premise
Embodiment, broadly falls into the scope of protection of the invention.
It should be noted that when assembly is referred to as " being fixed on " another assembly, and it can be directly on another assembly
Or assembly placed in the middle can also be there is.When an assembly is considered as " connection " another assembly, and it can be to be directly connected to
To another assembly or may be simultaneously present assembly placed in the middle.When an assembly is considered as " being arranged at " another assembly, it
Can be to be set directly on another assembly or may be simultaneously present assembly placed in the middle.Term as used herein is " vertical
", " level ", "left", "right" and similar statement for illustrative purposes only.
Unless otherwise defined, all of technology used herein and scientific terminology and the technical field belonging to the present invention
The implication that technical staff is generally understood that is identical.The term used the most in the description of the invention is intended merely to describe tool
The purpose of the embodiment of body, it is not intended that in limiting the present invention.Term as used herein " and/or " include one or more phase
Arbitrary and all of combination of the Listed Items closed.
Referring to Fig. 1, the unmanned vehicle 100 of an embodiment of the present invention, it includes body 20 and is arranged at described
Power set 40 on body 20 and undercarriage 60.Described power set 40 are for providing the flight of described unmanned vehicle 100
Power, described undercarriage 60 is arranged at bottom described body 20, buffering when landing as described unmanned vehicle 100 and
Support.
Described body 20 includes fuselage 22 and is arranged at the horn 24 on described fuselage 22.It is provided with in described fuselage 22
For controlling the automatically controlled module of described power set 40.Described horn 24 is used for carrying described power set 40.
In the present embodiment, the quantity of described horn 24 is four, and four described horns 24 set around described fuselage 22
Put, and the direction facing away from described fuselage 22 extends.
In the present embodiment, the quantity of described power set 40 is four, and each described power set 40 are arranged at one
The end of individual described horn 24.Described power set 40 include the actuator 42 being arranged on described horn 24 and are arranged at described
Propeller 44 on actuator 42, described actuator 42 can drive 44 turns of described propeller under the control of described automatically controlled module
Dynamic, thus drive described unmanned vehicle 100 to fly.Described actuator 42 can be that the rotation such as brush motor, brushless electric machine is driven
Moving part, to drive described propeller 44 to rotate.
Please refer to Fig. 2 and Fig. 3, described undercarriage 60 is arranged on described horn 24, and is positioned at described horn 24 phase
To the side away from described power set 40.In the present embodiment, described undercarriage 60 includes four spikes 61, Mei Gezhi
Spike 61 is arranged on a described horn 24.Prop up spike 61 to include the mounting seat 62 being arranged on described horn 24, be arranged at
Support member 64 in described mounting seat 62 and be arranged at the buffer 66 on described support member 64 and guard member 68.
Described mounting seat 62 is sheathed on the end of described horn 24 regularly, and it is used for installing described power set 40 and institute
State support member 64.The described actuator 42 of described power set 40 is installed in the side of described mounting seat 62.Described mounting seat 62
On be formed with female thread (not shown), described female thread is in order to be connected with described support member 64.
Described support member 64 is installed in described mounting seat 62 and deviates from the side of described power set 40.In present embodiment
In, described support member 64 is substantially in hollow shaft-like, and it is approximately perpendicular to described horn 24 and arranges.The two ends of described support member 64 are divided
Not for connect end and landing end, described connection end is connected on described horn 24, and described landing end is arranged away from described horn 24.
Being provided with connecting portion 641 on the connection end of described support member 64, described connecting portion 641 is for being connected with described mounting seat 62.
Being formed with external screw thread on described connecting portion 641, it is inserted in described mounting seat 62, and by described external screw thread and described installation
Seat 62 is removably attachable to together.Being provided with installation portion 643 on the landing end of described support member 64, described installation portion 643 is used
In installing described buffer 66.
In the illustrated embodiment, described horn 24 is for being horizontally disposed with, and its angle formed by with horizontal direction is 0 degree；Institute
Stating support member 64 to be obliquely installed relative to vertical direction, it is in a certain angle with vertical direction, so that multiple described spike 61
Forming an angle the holding power of described body 20 with ground, the support of described spike 61 is the most firm.Specifically, described
Angle formed by support member 64 and vertical direction is more than or equal to 1 degree and less than or equal to 5 degree.Preferably, described support member 64 is with vertical
The angle that direction shortens into is 3 degree.
On described support member 64, neighbouring described connecting portion 641 is provided with locating part 65, and described locating part 65 is used for limiting institute
State the installation site of the most described mounting seat of support member 64 62.Described locating part 65 includes sleeved part 651 and is arranged at described
Limiting section 653 in sleeved part 651.
Described generally cylindrical, its of sleeved part 651 is sheathed on described support member 64, and is positioned at described connecting portion 641
Side away from described mounting seat 62.In the present embodiment, described sleeved part 651 is by interference fit and described support member 64
It is connected together with being relatively fixed.Described limiting section 653 is formed at described sleeved part 651 one end near described mounting seat 62,
It is substantially in flange shape.After described support member 64 is screwed together in described mounting seat 62 by described connecting portion 641, described spacing
Portion 653 is held in described mounting seat 62, to limit the installation site of the described the most described mounting seat of support member 64 62.
Described buffer 66 is arranged on the described installation portion 643 of described support member 64, and is partly contained in described
In support member 64.In the present embodiment, described buffer 66 is hydraulic damper, and it is used for buffering external force to described unmanned flight
The impact that device 100 entirety causes.Described buffer 66 includes body 661 and is arranged at the location division 663 on described body 661
With movable part 665.It is appreciated that described buffer 66 can also be air-pressure damping device, or gas-liquid mixed antivibrator etc..
Described body 661 is contained in described support member 64 regularly.The described generally hollow structure of body 661, in it
It is filled with damping fluid.Described location division 663 is arranged at one end of described body 661, and is held in the end of described support member 64.
Described location division 663 is for limiting the described buffer 66 installation position relative to described support member 64.
In the present embodiment, described movable part 665 is piston rod.One end of described movable part 665 plugs slidably
In described body 661, and it is connected with the internal piston of described body 661.The other end of described movable part 665 protrudes out described
Outside body 661.When one or two in described movable part 665 and described body 661 is by an external impacts, described work
Can slide by the most described body 661 in dynamic portion 665, the change of the two relative position, it is possible to absorb the impact that described external force is brought,
Thus play cushioning effect when described spike 61 entirety is by external impacts.Further, also set up in described body 661
The return units such as flexible body, described return unit one end is connected on described body, and the other end is connected on described movable part 665；
After described external force is cancelled, under the effect of described return unit, described movable part 665 is returned to initial position.
Described guard member 68 is arranged at the end of described support member 64, and is coated on outside described movable part 665.Described guarantor
Guard 68 is for buffering described the external impacts that spike 61 is subject to, and as the barrier of described buffer 66, protects described slow
Rush device 66 do not polluted by external environment condition or corrode, to extend the service life of described buffer 66.
In the present embodiment, the protection set that described guard member 68 is rubber and/or silica gel material is made, it is set in institute
State on movable part 665, and be sheathed on the end of described support member 64 regularly.When described unmanned vehicle 100 drops to ground
Time upper, described spike 61 is by coming from the impulsive force on ground, and described guard member 68 is compressed by ground and elasticity occurs
Deformation, thus oppress described movable part 665, make the described the most described body of movable part 665 661 slide, and then play damping suction
The effect of energy.
Being additionally provided with girth member 69 in described mounting seat 62 and described support member 64, described girth member 69 is used for reinforcing described
Prop up the overall structure of spike 61.Described girth member 69 protects installation end 691, the supporting part 693 being arranged on described installation end 691
And it is arranged at the holding section 695 on described supporting part 693.
Described installation end 691 is installed in described mounting seat 62 regularly, and (is referred to by securing members 6911 such as screws
Fig. 2) it is connected with described mounting seat 62.Described securing member 6911 is arranged on described installation end 691 near described support member 64
Side.Described installation end 691 is under external force, it is possible to the axis around described securing member 6911 turns an angle, to use
Family can regulate the installation position of described girth member 69.
Described supporting part 693 is formed at the described installation end 691 side near described support member 64, and towards described support
Part 64 extends, and arranges in predetermined angle with described support member 64.
Described holding section 695 is formed at described supporting part 693 one end near described support member 64, and sheathed and be fastened in
On described support member 64.The most in the illustrated embodiment, described holding section 695 is formed with holding hole 6951, described clamping
Hole 6951 is incomplete circular hole, makes described holding section 695 can be sheathed on described support member 64 by described holding hole 6951
On, or, make described support member 64 can be screwed through described holding hole 6951 with described mounting seat 62, described holding section
The installation of described support member 64 can be play the guiding role by 695 simultaneously.Described mounting seat 62, described support member 64 and described reinforcing
Substantially attachment structure in Tripod between part 69 three, makes that the overall structure of described spike 61 is firm to be unlikely to deform or move
Position.
When described installation end 691 is under external force around the axis minor rotation of described securing member 6911, described support
Portion 693 can drive described holding section 695 to rotate predetermined angular relative to described mounting seat 62, so that described holding section 695 can
It is fastened on described support member 64.Even if there is certain rigging error between each part of described spike 61, it is also possible to logical
Cross and rotate described girth member 69 to adjust the assembly relation between described girth member 69 and described support member 64, make described undercarriage
60 are easier to assembling.
Above-mentioned unmanned vehicle 100, its undercarriage 60 is provided with buffer 66, and described buffer 66 is positioned at described spike 61
Bottom, when described unmanned vehicle 100 lands, first described buffer 66 accepts to come from the impulsive force on ground, makes institute
Stating the most described body of movable part 665 661 to slide, and then play the effect of damping energy-absorbing, its buffering effect is relatively preferable, reduces
The infringement that described unmanned vehicle 100 entirety is caused by drop impact.
It addition, together with described support member 64 is threaded connection and is removably attachable to described mounting seat 62, make described
Undercarriage 60 is easy to assembly and disassembly.
The quantity being appreciated that described horn 24 can be one or more, such as, and two, three, six etc..With
Sample ground, the quantity of described power set 40 can also be one or more.
It is appreciated that other positions that described buffer 66 can be installed on described support member 64.Such as, described buffering
Device 66 can be arranged between described mounting seat 62 and described support member 64.Specifically, described mounting seat 62 and described body 661
And in described movable part 665 one is fixing connects, described support member 64 with in described body 661 and described movable part 665
Another connects, and is screwed by described connecting portion 641 and another in described body 661 and described movable part 665.Again
As, described support member 64 can be designed as the support bar with two consecutive supporting parts, and one of them supporting part is installed in
In described mounting seat 62, another supporting part is connected on one supporting part by described buffer 66.
The connected mode being appreciated that between described support member 64 and described mounting seat 62 is not limited to as described above
Connected mode, it can use other mechanical connection manners.Such as, described connecting portion 641 is formed with female thread, described installation
On seat 62, corresponding described female thread is formed with male threaded joint；Described female thread is screwed with described male threaded joint, with
Together with described support member 64 is installed in regularly with described mounting seat 62.For another example, described connecting portion 641 is formed with engaging
Portion, one during in described mounting seat 62, corresponding described holding section is formed with auxiliary section, described holding section and described auxiliary section is
Elastic clamping hook, another is draw-in groove；The mutual clamping in described holding section and described auxiliary section coordinates, with by described support member 64 and institute
State mounting seat 62 to be installed in regularly together.
It is appreciated that described mounting seat 62 can be omitted, and directly described support member 64 is installed on described horn 24,
The two ends of described girth member 69 are connected on described horn 24 and described support member 64；Wherein, described support member 64 can
It is connected with fixing with described horn 24 or be rotatably connected.
Embodiment of above is only in order to illustrate technical scheme and unrestricted, although with reference to embodiment of above pair
The present invention has been described in detail, and it will be understood by those within the art that, can carry out technical scheme
Amendment or equivalent the most should not depart from the spirit and scope of technical solution of the present invention.
Claims (24)
1. a undercarriage, is applied in unmanned vehicle, and described undercarriage includes a spike；It is characterized in that: described support
Foot includes support member and for buffering the buffer of described undercarriage impact when described unmanned vehicle lands, described
Support member is provided with the installation portion for installing described buffer.
2. undercarriage as claimed in claim 1, it is characterised in that: described buffer is hydraulic damper or air damper.
3. undercarriage as claimed in claim 1, it is characterised in that: described support member one end is for connecting end, and other end is
Lu Duan, described installation portion is arranged at the landing end of described support member.
4. undercarriage as claimed in claim 3, it is characterised in that: it is provided with connecting portion on the connection end of described support member, institute
State connecting portion for detachably connected with the horn of described unmanned vehicle.
5. undercarriage as claimed in claim 4, it is characterised in that: described spike also includes for connecting described unmanned flight
The mounting seat of the horn of device, described connecting portion is removably attachable in described mounting seat.
6. undercarriage as claimed in claim 5, it is characterised in that: in described connecting portion and described mounting seat is upper to be arranged
Have in female thread, described connecting portion and described mounting seat another on be provided with the external screw thread matched with described female thread,
Described female thread is screwed with described external screw thread and is connected；
Or, in described connecting portion and described mounting seat is provided with elastic clamping hook, described connecting portion and described installation
The draw-in groove matched with described elastic clamping hook, described elastic clamping hook and the mutual clamping of described draw-in groove it is provided with on another in Zuo
Connect.
7. undercarriage as claimed in claim 5, it is characterised in that: described spike also includes girth member, described girth member one
End is arranged in described mounting seat, and the other end is connected on described support member；Described mounting seat, described girth member and described support
Part is the structure of Tripod.
8. undercarriage as claimed in claim 7, it is characterised in that: described girth member includes the peace being arranged in described mounting seat
Dress end, and be arranged at described installation end and extend to described support member and be connected to the supporting part on described support member.
9. undercarriage as claimed in claim 8, it is characterised in that: described installation end is connected to described installation by a securing member
On seat, described installation end can be around described fastener rotation to drive described supporting part to rotate relative to described mounting seat.
10. undercarriage as claimed in claim 8, it is characterised in that: described girth member also includes being arranged on described supporting part
And with the holding section of described support member phase clamping.
11. undercarriages as claimed in claim 10, it is characterised in that: it is provided with holding hole, described clamping on described holding section
Portion is sheathed on described support member by described holding hole.
12. undercarriages as claimed in claim 5, it is characterised in that: described spike also includes being arranged on described support member
Locating part, described locating part offsets with described mounting seat.
13. undercarriages as claimed in claim 12, it is characterised in that: described locating part includes that fixed cover is located at described support member
On sleeved part and be arranged at the limiting section in described sleeved part, described limiting section offsets with described mounting seat.
14. undercarriages as claimed in claim 1, it is characterised in that: described buffer includes being arranged on described support member
Body and be housed in the movable part in described body movably, described movable part is connected with described body piston and partly
Protrude out outside described body and described support member.
15. undercarriages as claimed in claim 14, it is characterised in that: described body is contained in described support member, described slow
Rushing the location division that device also includes being arranged on described body, described location division is held in the end of described support member；
And/or, described the internal elastic reset part that is provided with, described elastic reset part one end is connected on described body, another
End is connected on described movable part.
16. undercarriages as claimed in claim 14, it is characterised in that: described spike also includes guard member, described guard member
It is sheathed on described support member and is coated on outside described movable part.
17. undercarriages as claimed in claim 16, it is characterised in that: described guard member is the protection set that elastomeric material is made.
18. undercarriages as according to any one of claim 1～17, it is characterised in that: described spike is relative to vertically side
To being obliquely installed.
19. undercarriages as claimed in claim 18, it is characterised in that: angle formed by described support member and vertical direction is more than
Equal to 1 degree and less than or equal to 5 degree.
20. 1 kinds of unmanned vehicles, it includes fuselage, it is characterised in that: described unmanned vehicle also includes claim 1～19
According to any one of undercarriage, described support member is arranged on described fuselage, and it is remote that described buffer is arranged at described support member
One end from described fuselage.
21. unmanned vehicles as claimed in claim 20, it is characterised in that: described unmanned vehicle also includes being arranged at described
Horn on fuselage and be arranged at the power set on described horn, described power set are with thinking that described unmanned vehicle carries
For flying power.
22. unmanned vehicles as claimed in claim 21, it is characterised in that: described power set tilt relative to vertical direction
Arrange；
And/or, described support member is fixing with described horn to be connected, or is rotatably connected.
23. unmanned vehicles as claimed in claim 21, it is characterised in that: described power set include being arranged at described horn
On actuator and be connected to the propeller on described actuator, described actuator is in order to drive described propeller rotational.
24. unmanned vehicles as claimed in claim 21, it is characterised in that: described power set are corresponding with described support member to be set
Put.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/CN2015/078952 WO2016179827A1 (en) | 2015-05-14 | 2015-05-14 | Undercarriage and unmanned aerial vehicle using same |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105980250A true CN105980250A (en) | 2016-09-28 |
| CN105980250B CN105980250B (en) | 2018-09-04 |
Family
ID=56988319
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201580004257.7A Expired - Fee Related CN105980250B (en) | 2015-05-14 | 2015-05-14 | Undercarriage and the unmanned vehicle for using the undercarriage |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN105980250B (en) |
| WO (1) | WO2016179827A1 (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106882374A (en) * | 2017-04-11 | 2017-06-23 | 黄延乔 | Artificial animal aircraft |
| CN107054629A (en) * | 2017-01-19 | 2017-08-18 | 广东工业大学 | A kind of unmanned plane and its undercarriage |
| CN107985564A (en) * | 2017-12-28 | 2018-05-04 | 深圳市道通智能航空技术有限公司 | Undercarriage and the unmanned vehicle with the undercarriage |
| WO2018133192A1 (en) * | 2017-01-18 | 2018-07-26 | 深圳市大疆创新科技有限公司 | Stand assembly and unmanned aerial vehicle |
| CN109334956A (en) * | 2018-11-07 | 2019-02-15 | 农业部南京农业机械化研究所 | Adaptive landing gear and control method for complex terrain of plant protection unmanned aircraft |
| CN109552602A (en) * | 2018-12-24 | 2019-04-02 | 深圳市道通智能航空技术有限公司 | A kind of unmanned vehicle |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2022009319A1 (en) * | 2020-07-07 | 2022-01-13 | 株式会社エアロネクスト | Flying body and power device |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4630788A (en) * | 1983-11-09 | 1986-12-23 | Messier-Hispano-Bugatti (S.A.) | Aircraft landing gear, in particular for helicopters |
| CN2309284Y (en) * | 1997-07-08 | 1999-03-03 | 马金山 | Shock-absorbing leg for undercarriage |
| CN202783777U (en) * | 2012-08-24 | 2013-03-13 | 董韬 | Unmanned aerial vehicle undercarriage |
| CN203806137U (en) * | 2013-12-30 | 2014-09-03 | 广州供电局有限公司 | Multi-rotor shock-absorbing landing stand |
| US20140339355A1 (en) * | 2013-05-15 | 2014-11-20 | Draganfly Innovations Inc. | Compact unmanned rotary aircraft |
| CN104192303A (en) * | 2014-09-15 | 2014-12-10 | 沈阳飞机工业（集团）有限公司 | Small nose landing gear for unmanned aerial vehicle |
| CN204197279U (en) * | 2014-10-31 | 2015-03-11 | 湖北易瓦特科技有限公司 | A kind of retractable landing gear |
| CN104443352A (en) * | 2014-12-02 | 2015-03-25 | 芜湖中艺企业管理咨询有限公司 | Small aircraft with safe undercarriage |
| CN104527979A (en) * | 2014-11-21 | 2015-04-22 | 中国科学院长春光学精密机械与物理研究所 | Automatic dispenser for air-based tear gas bomb |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR953113A (en) * | 1946-09-13 | 1949-11-30 | Firestone Tire & Rubber Co | Improvements to shock absorbers intended in particular for aircraft landing gear |
| US6247687B1 (en) * | 1999-03-29 | 2001-06-19 | Lord Corporation | Elastomer damper |
| CN202499275U (en) * | 2011-12-29 | 2012-10-24 | 湖北易瓦特科技有限公司 | Hydraulic damping undercarriage of unmanned plane |
| CN204037895U (en) * | 2014-04-24 | 2014-12-24 | 天津宏宇天翔科技有限公司 | A kind of unmanned plane alighting gear |
| CN204674822U (en) * | 2015-05-14 | 2015-09-30 | 深圳市大疆创新科技有限公司 | Alighting gear and use the unmanned vehicle of this alighting gear |
-
2015
- 2015-05-14 CN CN201580004257.7A patent/CN105980250B/en not_active Expired - Fee Related
- 2015-05-14 WO PCT/CN2015/078952 patent/WO2016179827A1/en active Application Filing
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4630788A (en) * | 1983-11-09 | 1986-12-23 | Messier-Hispano-Bugatti (S.A.) | Aircraft landing gear, in particular for helicopters |
| CN2309284Y (en) * | 1997-07-08 | 1999-03-03 | 马金山 | Shock-absorbing leg for undercarriage |
| CN202783777U (en) * | 2012-08-24 | 2013-03-13 | 董韬 | Unmanned aerial vehicle undercarriage |
| US20140339355A1 (en) * | 2013-05-15 | 2014-11-20 | Draganfly Innovations Inc. | Compact unmanned rotary aircraft |
| CN203806137U (en) * | 2013-12-30 | 2014-09-03 | 广州供电局有限公司 | Multi-rotor shock-absorbing landing stand |
| CN104192303A (en) * | 2014-09-15 | 2014-12-10 | 沈阳飞机工业（集团）有限公司 | Small nose landing gear for unmanned aerial vehicle |
| CN204197279U (en) * | 2014-10-31 | 2015-03-11 | 湖北易瓦特科技有限公司 | A kind of retractable landing gear |
| CN104527979A (en) * | 2014-11-21 | 2015-04-22 | 中国科学院长春光学精密机械与物理研究所 | Automatic dispenser for air-based tear gas bomb |
| CN104443352A (en) * | 2014-12-02 | 2015-03-25 | 芜湖中艺企业管理咨询有限公司 | Small aircraft with safe undercarriage |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018133192A1 (en) * | 2017-01-18 | 2018-07-26 | 深圳市大疆创新科技有限公司 | Stand assembly and unmanned aerial vehicle |
| CN109641651A (en) * | 2017-01-18 | 2019-04-16 | 深圳市大疆创新科技有限公司 | Foot prop component and unmanned vehicle |
| CN109641651B (en) * | 2017-01-18 | 2022-06-10 | 深圳市大疆创新科技有限公司 | Foot rest component and unmanned aerial vehicle |
| CN107054629A (en) * | 2017-01-19 | 2017-08-18 | 广东工业大学 | A kind of unmanned plane and its undercarriage |
| CN106882374A (en) * | 2017-04-11 | 2017-06-23 | 黄延乔 | Artificial animal aircraft |
| CN107985564A (en) * | 2017-12-28 | 2018-05-04 | 深圳市道通智能航空技术有限公司 | Undercarriage and the unmanned vehicle with the undercarriage |
| CN107985564B (en) * | 2017-12-28 | 2024-10-15 | 深圳市道通智能航空技术股份有限公司 | Landing gear and unmanned aerial vehicle with landing gear |
| CN109334956A (en) * | 2018-11-07 | 2019-02-15 | 农业部南京农业机械化研究所 | Adaptive landing gear and control method for complex terrain of plant protection unmanned aircraft |
| CN109552602A (en) * | 2018-12-24 | 2019-04-02 | 深圳市道通智能航空技术有限公司 | A kind of unmanned vehicle |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2016179827A1 (en) | 2016-11-17 |
| CN105980250B (en) | 2018-09-04 |
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