CN206374971U - A kind of fixed-wing unmanned plane rear leg retracting device - Google Patents
A kind of fixed-wing unmanned plane rear leg retracting device Download PDFInfo
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- CN206374971U CN206374971U CN201720031299.6U CN201720031299U CN206374971U CN 206374971 U CN206374971 U CN 206374971U CN 201720031299 U CN201720031299 U CN 201720031299U CN 206374971 U CN206374971 U CN 206374971U
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Abstract
The utility model discloses a kind of fixed-wing unmanned plane rear leg retracting device, including foot stool crossbeam, wing plate fixed seat, locking support mechanism, buffer damping mechanism, fold mechanism and one group of aircraft wheel assembly, the foot stool crossbeam rear both sides are respectively fixed with wing plate fixed seat, the aircraft wheel assembly includes wheel body fixed seat and aircraft wheel, the fold mechanism includes packing up hinged seat, supporting linkage and packs up cylinder, the locking support actuator base is hinged with fixed scissors-type arm middle part, is flexibly connected at the top of locking support mechanism with foot stool crossbeam；The buffer damping mechanism includes shock-absorbing cylinder, the top of the shock-absorbing cylinder is hingedly mounted in shock-absorbing fixed seat, the shock-absorbing fixed seat is held away from the wing plate fixed seat end of foot stool crossbeam, foot stool support strength of the present utility model is good, the coefficient of stability is high, using multi-shaft interlocked steering fold mechanism, is occupied little space after packing up, take off or land safe and reliable, good damping effect.
Description
Technical field
The utility model is related to unmanned vehicle and folds rear leg technical field, specifically a kind of fixed-wing unmanned plane rear foot
Frame retracting device.
Background technology
Fixed wing aircraft abbreviation fixed wing machine, often by again be referred to as aircraft, refer to by power set produce advance thrust or
Pulling force, produces lift, the airborne vehicle for overweighting air flown in endoatmosphere by the fixation wing of fuselage.It is fixed-wing aviation
One kind of device, is also most common one kind, and another Fixed-Wing is aerodone.The engine class that aircraft is used according to it
Type can be divided into jet airplane and propeller aeroplane again.In recent years, unmanned plane field is developed rapidly, wherein, fixed-wing nobody fly
The frequency that row device is used also more and more higher.
Folded however, the rear leg of current fixed-wing unmanned aerial vehicle is turned to using single shaft mostly, it is impossible to so that rear side
Aircraft wheel level pack up, the space-consuming after packing up is larger；Reduce the utilization rate in fuselage interior space, resistance to overturning
Difference；In addition, the integrated buffer damping effect of rear foot frame mechanism is poor, it is unfavorable for the quick of aircraft and takes off or land.
Utility model content
The purpose of this utility model is to provide a kind of intensity good, and the coefficient of stability is high, using multi-shaft interlocked steering folding machine
Structure, occupies little space after packing up, and takes off or lands safe and reliable, and the fixed-wing unmanned plane rear leg of good damping effect packs up dress
Put, to solve the problems mentioned in the above background technology.
To achieve the above object, the utility model provides following technical scheme：
A kind of fixed-wing unmanned plane rear leg retracting device, including foot stool crossbeam, wing plate fixed seat, locking support mechanism,
Buffer damping mechanism, fold mechanism and one group of aircraft wheel assembly, the foot stool crossbeam rear both sides are respectively fixed with wing plate and fixed
Seat, the aircraft wheel assembly includes wheel body fixed seat and aircraft wheel, and the wheel body fixed seat front end turning set is connected equipped with wheel body
Fixed scissors-type arm is hinged with head, wheel body connector；
The fold mechanism includes packing up hinged seat, supporting linkage and packing up cylinder, and the hinged seat of packing up is fixed on
Close to the wing plate fixed seat end of foot stool crossbeam, the top of the supporting linkage is hinged with packing up hinged seat rotation, and support connects
Extension bar bottom rotates with the end of fixed scissors-type arm and is connected, and the cylinder of packing up is hingedly mounted on foot stool horizontal stroke by cylinder fixed seat
Liang Shang, the outer wall of the telescopic end and supporting linkage of packing up cylinder is movably hinged；
The locking support actuator base is hinged with fixed scissors-type arm middle part, horizontal with foot stool at the top of locking support mechanism
Beam is flexibly connected；The buffer damping mechanism includes shock-absorbing cylinder, and the top of the shock-absorbing cylinder is hingedly mounted in shock-absorbing fixed seat,
The shock-absorbing fixed seat is held away from the wing plate fixed seat end of foot stool crossbeam, and the basal sliding of the shock-absorbing cylinder, which is combined with, to keep away
Cylinder core is shaken, shock-absorbing cylinder core bottom is movably connected in wheel body fixed seat by cylinder core fixed seat.
It is used as further program of the utility model：The locking support mechanism include be hinged first fold hub and
Solution lock cylinder is hinged with successively from back to front on second folding hub, the first folding hub and fixed cuts arm, and the fixed cuts arm
Telescopic-cylinder bar rotation of the wherein arm end with solving lock cylinder is hinged, and fixed cuts another arm end of arm and is connected boom end turn with cutting arm
Dynamic to be hinged, the second folding hub and the first folding hub hinged place are extended with lug boss, the other end for cutting arm connecting rod and
Lug boss is rotated and is hinged, and described second folds hub away from the first end for folding hub and fixed scissors-type arm middle part rotating hinge
Connect.
It is used as further program of the utility model：The end of the first folding hub is hingedly mounted on folding hub fixed seat
On, it is described to fold the folding hub steering spindle that hub mounting seat is connected that folds being provided with hub fixed seat with foot stool crossbeam.
It is used as further program of the utility model：The shock-absorbing cylinder core bottom is articulated and connected with cylinder core fixed seat, described
Cylinder core fixed seat turning set is in wheel body fixed seat.
It is used as further program of the utility model：The aircraft wheel includes rotating shaft, the wheel hub being connected with wheel body fixed seat
And tire, the rotating shaft coordinated by bearing and hub rotation, and tire is set with the wheel hub.
It is used as further program of the utility model：Fixed dam is fixed with the foot stool crossbeam front end face, foot stool is horizontal
The crossbeam bottom plate fixed with fixed dam is fixed with the bottom surface of beam front end.
It is used as further program of the utility model：Fixed cover is equipped with gas on the Telescopic-cylinder bar outside solution lock cylinder
Cylinder catch, locking spring is fixed between the cylinder catch and the end face for solving lock cylinder.
It is used as further program of the utility model：The shock-absorbing cylinder top is provided with the shock-absorbing connected with shock-absorbing tube inner chamber
Valve, shock-absorbing cylinder is internal to be fixed with pitch brace, and the end of pitch brace is fixed with shock-absorbing piston, and the shock-absorbing piston activity is set
Put in shock-absorbing cylinder in-core wall, gap is left between the outer circumferential walls and shock-absorbing cylinder in-core wall of shock-absorbing piston.
Compared with prior art, the beneficial effects of the utility model are：During unblock, the Telescopic-cylinder bar of solution lock cylinder is stretched
It is long, so as to promote fixed to cut arm rotation so that fixed is cut arm and moved upwards with cutting the axle center that is hinged of arm connecting rod, so that solid
Sizing cuts arm and cuts the lock opening of arm connecting rod, and now, the wheel body fixed seat for being provided with aircraft wheel could be to fuselage interior
Foot stool crossbeam is close to folding；Then, cylinder operation is packed up, supporting linkage is driven to the close folding of foot stool crossbeam；First folds
End of the hub away from the second folding hub is rotated with fixed scissors-type arm middle part to be hinged, supporting linkage bottom and fixed scissors-type arm
End rotate connection, be arranged such, it is ensured that aircraft wheel to foot stool crossbeam it is close folding while so that aircraft wheel being capable of water
Flat receipts are stacked in fuselage, substantially reduce the space-consuming after rear leg is packed up；By being fixedly set on Telescopic-cylinder bar
The cooperation of cylinder catch and locking spring so that the locking support mechanism of foot stool remains expansion when solution lock cylinder does not work
State, it is to avoid aircraft is folded and packed up because of frictional resistance between ground and tire in ground run, it is ensured that take off or
The security of landing；The basal sliding of shock-absorbing cylinder is combined with shock-absorbing cylinder core, and shock-absorbing cylinder core bottom is connected by the activity of cylinder core fixed seat
It is connected in wheel body fixed seat, leaves gap between the outer circumferential walls and shock-absorbing cylinder in-core wall of shock-absorbing piston, shock-absorbing piston is in shock-absorbing
When cylinder in-core can be reciprocated, the fluid of shock-absorbing cylinder in-core is flowed to separately by the gap between shock-absorbing piston and shock-absorbing cylinder in-core wall
Outer side, therefore, the vibration damping of oil and the friction just shape paired pressure of shock-absorbing cylinder in-core wall, it is ensured that when tire is with ground surface
Possesses good damping effect.
Brief description of the drawings
Fig. 1 is a kind of structural representation of fixed-wing unmanned plane rear leg retracting device；
Fig. 2 is locking support mechanism, buffer damping mechanism, folding machine in a kind of fixed-wing unmanned plane rear leg retracting device
Structure and the structural representation of aircraft wheel assembly connection；
Fig. 3 is a kind of structural representation of locking support mechanism in fixed-wing unmanned plane rear leg retracting device；
Fig. 4 is the structural representation that is connected with shock-absorbing cylinder core of shock-absorbing cylinder in a kind of fixed-wing unmanned plane rear leg retracting device
Figure.
In figure：1- foot stool crossbeams, 2- crossbeam bottom plates, 3- fixed dams, 4- wing plate fixed seats, 5- cylinder fixed seats, 6- is received
Cylinder is played, 7- shock-absorbings cylinder, 71- shock-absorbing valves, 72- pitch braces, 73- shock-absorbing pistons, 8- second folds hub, 9- locking supports
Mechanism, 91- first folds hub, and 92- Telescopic-cylinder bars, 93- locking springs, 94- cylinder catch, 95- fixes scissors-type arm, 96- solutions
Lock cylinder, 97- cuts arm connecting rod, and 10- folds hub fixed seat, and 11- folds hub steering spindle, 12- supporting linkages, 13- shock-absorbing cylinders
Core, 14- shock-absorbing fixed seats, 15- packs up hinged seat, 16- wheel hubs, 17- tires, 18- rotating shafts, 19- wheel body connectors, 20- cylinder cores
Fixed seat, 21- fixes scissors-type arm.
Embodiment
Below in conjunction with the accompanying drawing in the utility model embodiment, the technical scheme in the utility model embodiment is carried out
Clearly and completely describe, it is clear that described embodiment is only a part of embodiment of the utility model, rather than whole
Embodiment.Based on the embodiment in the utility model, those of ordinary skill in the art are not under the premise of creative work is made
The every other embodiment obtained, belongs to the scope of the utility model protection.
Refer in Fig. 1~4, the utility model embodiment, a kind of fixed-wing unmanned plane rear leg retracting device, including pin
Frame crossbeam 1, wing plate fixed seat 4, locking support mechanism 9, buffer damping mechanism, fold mechanism and one group of aircraft wheel assembly, it is described
The rear both sides of foot stool crossbeam 1 are respectively fixed with wing plate fixed seat 4, and the aircraft wheel assembly includes wheel body fixed seat and aircraft wheel,
The wheel body fixed seat front end turning set is equipped with wheel body connector 19, wheel body connector 19 and is hinged with fixed scissors-type arm 21；
The fold mechanism includes packing up hinged seat 15, supporting linkage 12 and packing up cylinder 6, described to pack up hinged seat 15
It is fixed on close to the end of wing plate fixed seat 4 of foot stool crossbeam 1, the top of the supporting linkage 12 is with packing up 15 turns of hinged seat
Dynamic to be hinged, the bottom of supporting linkage 12 is rotated with the end of fixed scissors-type arm 21 and is connected, and the cylinder 6 of packing up is fixed by cylinder
Seat 5 is hingedly mounted on foot stool crossbeam 1, and the outer wall for packing up the telescopic end and supporting linkage 12 of cylinder 6 is movably hinged；
The bottom of locking support mechanism 9 is hinged with the fixed middle part of scissors-type arm 21, the top of locking support mechanism 9 with
Foot stool crossbeam 1 is flexibly connected；The buffer damping mechanism includes shock-absorbing cylinder 7, and the top of the shock-absorbing cylinder 7, which is hingedly mounted on, to be kept away
Shake in fixed seat 14, the shock-absorbing fixed seat 14 is held away from the end of wing plate fixed seat 14 of foot stool crossbeam 1, the shock-absorbing cylinder
7 basal sliding is combined with shock-absorbing cylinder core 13, and the bottom of shock-absorbing cylinder core 13 is movably connected in wheel body by cylinder core fixed seat 20 and fixed
On seat.
Wherein, the first folding hub 91 and second that locking support mechanism includes being hinged folds hub 8, and first folds hub 91
On be hinged with solution lock cylinder 96 successively from back to front and fixed cuts arm 95, the fixed cuts the wherein arm end of arm 95 and unblock
The Telescopic-cylinder bar 92 of cylinder 96 is rotated and is hinged, and fixed is cut another arm end of arm 95 and is hinged with cutting the rotation of the end of arm connecting rod 97,
The second folding folding of hub 8 and first hub 91 hinged place is extended with lug boss, the other end for cutting arm connecting rod 97 with it is convex
The portion of rising rotates and is hinged, and described second folds hub 8 rotates away from the first end for folding hub 91 and the fixed middle part of scissors-type arm 95
It is hinged.
Wherein, the end of the first folding hub 91 is hingedly mounted in folding hub fixed seat 10, and the folding hub is fixed
It is provided with seat 10 and the folding hub steering spindle 11 that hub mounting seat is connected that folds on foot stool crossbeam 1.
Wherein, the bottom of shock-absorbing cylinder core 13 is articulated and connected with cylinder core fixed seat 20, the turning set of cylinder core fixed seat 20
In wheel body fixed seat.
Wherein, the aircraft wheel includes rotating shaft 18, wheel hub 16 and the tire 17 being connected with wheel body fixed seat, the rotating shaft 18
It is rotatably assorted by bearing with wheel hub 16, tire 17 is set with the wheel hub 16.
Wherein, be fixed with the front end face of foot stool crossbeam 1 on fixed dam 3, the front end bottom surface of foot stool crossbeam 1 be fixed with
The crossbeam bottom plate 2 that fixed dam 3 is fixed, the tire 17 after folding can be in foot stool crossbeam 1, fixed dam 3 and crossbeam bottom plate 2
In the space surrounded.
Wherein, fixed cover is equipped with cylinder catch 94, the cylinder gear on the Telescopic-cylinder bar outside solution lock cylinder 96
Locking spring 93 is fixed between piece 94 and the end face for solving lock cylinder 96.
Wherein, the top of shock-absorbing cylinder 7 is provided with the shock-absorbing valve 71 connected with 7 inner chambers of shock-absorbing cylinder, and the inside of shock-absorbing cylinder 7 is solid
Surely there is pitch brace 72, the end of pitch brace 72 is fixed with shock-absorbing piston 73, and the shock-absorbing piston 73 is movably arranged on shock-absorbing
In the inwall of cylinder core 13, gap is left between the outer circumferential walls and the inwall of shock-absorbing cylinder core 13 of shock-absorbing piston 73.
Operation principle of the present utility model is：First fold hub 91 and second fold hub 8 deploy when, fixed cut arm 95 with
That cuts arm connecting rod 97 is hinged axle center for A axle center, and the axle center that is hinged that fixed cuts the folding hub 91 of arm 95 and first is the B axle heart, is cut
Arm connecting rod 97 and lug boss are hinged axle center for C axle center, A axle center now not in the top of the B axle heart and C axial connecting lines, Gu
Surely the locking spring 93 being sleeved on Telescopic-cylinder bar is in natural shrinking state, and solution lock cylinder 96 is in most short status, mechanism
Locking state is in, the second folding hub 8 can not realize the locking support machine of the relative first relative rotation, i.e. foot stool for folding hub 91
Structure solve lock cylinder 96 do not work when remain deployed condition so that be prevented effectively from aircraft in ground run because ground with
Frictional resistance between tire 17 and fold and pack up, it is ensured that the security taken off or landed；During unblock, the gas of lock cylinder 96 is solved
Cylinder expansion link 92 extends, and is rotated so as to promote fixed to cut arm 95 so that fixed cuts arm 95 with cutting being hinged for arm connecting rod 97
Move upwards in axle center so that A axle center is located at the top of the B axle heart and C axial connecting lines, is connected so that fixed cuts arm 95 with cutting arm
Lock between bar 97 is opened, and now, being provided with the wheel body fixed seat of aircraft wheel could lean on to the foot stool crossbeam 1 of fuselage interior
It is near to fold；Then, pack up cylinder 6 to work, drive supporting linkage 12 to foot stool crossbeam 1 close to folding；First folding hub 91 is remote
End from the second folding hub 8 is hinged with the fixed middle part of scissors-type arm 21 rotation, the bottom of supporting linkage 12 and fixed scissors-type
The end rotation connection of arm 21, during receipts are folded, the end meeting relative support connecting rod 12 of fixed scissors-type arm 21 is rotated, Gu
Wheel body connector 19 can be pulled by determining scissors-type arm 21 so that wheel body fixed seat is turned to, it is ensured that aircraft wheel is close to foot stool crossbeam 1
While folding so that aircraft wheel can level receive be stacked in fuselage, substantially reduce the space-consuming after rear leg is packed up；Keep away
The basal sliding of shake cylinder 7 is combined with shock-absorbing cylinder core 13, and the bottom of shock-absorbing cylinder core 13 is movably connected in wheel body by cylinder core fixed seat 20
In fixed seat, gap is left between the outer circumferential walls and the inwall of shock-absorbing cylinder core 13 of shock-absorbing piston 73, shock-absorbing piston 73 is in shock-absorbing cylinder
When the interior energy of core 13 is reciprocated, the fluid in shock-absorbing cylinder core 13 is by the gap between shock-absorbing piston 73 and the inwall of shock-absorbing cylinder core 13
Flow to other side, therefore, the vibration damping of oil and the friction just shape paired pressure of the inwall of shock-absorbing cylinder core 13, it is ensured that tire 17 with
Possesses good damping effect during ground surface；The support strength of whole rear leg is good, and the coefficient of stability is high.
It is obvious to a person skilled in the art that the utility model is not limited to the details of above-mentioned one exemplary embodiment, and
And in the case of without departing substantially from spirit or essential attributes of the present utility model, can realize that this practicality is new in other specific forms
Type.Therefore, no matter from the point of view of which point, embodiment all should be regarded as exemplary, and is nonrestrictive, this practicality is new
The scope of type limits by appended claims rather than described above, it is intended that the equivalency fallen in claim is contained
All changes in justice and scope are included in the utility model.Any reference in claim should not be considered as limitation
Involved claim.
Claims (8)
1. a kind of fixed-wing unmanned plane rear leg retracting device, including it is foot stool crossbeam, wing plate fixed seat, locking support mechanism, slow
Rush damping, fold mechanism and one group of aircraft wheel assembly, it is characterised in that the foot stool crossbeam rear both sides are respectively fixed with
Wing plate fixed seat, the aircraft wheel assembly includes wheel body fixed seat and aircraft wheel, and the wheel body fixed seat front end turning set is equipped with
Fixed scissors-type arm is hinged with wheel body connector, wheel body connector；
The fold mechanism includes packing up hinged seat, supporting linkage and packs up cylinder, it is described pack up hinged seat be fixed on it is close
The wing plate fixed seat end of foot stool crossbeam, the top of the supporting linkage is hinged with packing up hinged seat rotation, supporting linkage
Bottom rotates with the end of fixed scissors-type arm and is connected, and the cylinder of packing up is hingedly mounted on foot stool crossbeam by cylinder fixed seat
On, the outer wall of the telescopic end and supporting linkage of packing up cylinder is movably hinged；
The locking support actuator base is hinged with fixed scissors-type arm middle part, is lived at the top of locking support mechanism with foot stool crossbeam
Dynamic connection；The buffer damping mechanism includes shock-absorbing cylinder, and the top of the shock-absorbing cylinder is hingedly mounted in shock-absorbing fixed seat, described
Shock-absorbing fixed seat is held away from the wing plate fixed seat end of foot stool crossbeam, and the basal sliding of the shock-absorbing cylinder is combined with shock-absorbing cylinder
Core, shock-absorbing cylinder core bottom is movably connected in wheel body fixed seat by cylinder core fixed seat.
2. a kind of fixed-wing unmanned plane rear leg retracting device according to claim 1, it is characterised in that the locking branch
Support mechanism includes being hinged with unblock successively from back to front on the first folding hub being hinged and the second folding hub, the first folding hub
Cylinder and fixed cut arm, and the fixed is cut Telescopic-cylinder bar rotation of the arm wherein arm end with solving lock cylinder and is hinged, fixed
Type, which cuts another arm end of arm and is connected boom end rotating hinge with cutting arm, to be connect, and the second folding hub folds hub hinged place with first and is extended with
Lug boss, the other end for cutting arm connecting rod is rotated with lug boss and is hinged, and described second folds hub folds hub away from first
End rotates with fixed scissors-type arm middle part and is hinged.
3. a kind of fixed-wing unmanned plane rear leg retracting device according to claim 2, it is characterised in that first folding
The end of folded hub is hingedly mounted in folding hub fixed seat, is provided with and the folding on foot stool crossbeam in the folding hub fixed seat
The folding hub steering spindle that hub mounting seat is connected.
4. a kind of fixed-wing unmanned plane rear leg retracting device according to claim 1, it is characterised in that the shock-absorbing cylinder
Core bottom is articulated and connected with cylinder core fixed seat, and the cylinder core fixed seat turning set is in wheel body fixed seat.
5. a kind of fixed-wing unmanned plane rear leg retracting device according to claim 1, it is characterised in that the aircraft wheel
Including the rotating shaft being connected with wheel body fixed seat, wheel hub and tire, the rotating shaft is coordinated by bearing and hub rotation, the wheel hub
On be set with tire.
6. a kind of fixed-wing unmanned plane rear leg retracting device according to claim 1, it is characterised in that the foot stool is horizontal
The crossbeam bottom plate for being fixed with and being fixed with fixed dam on fixed dam, foot stool crossbeam front end bottom surface is fixed with beam front end face.
7. a kind of fixed-wing unmanned plane rear leg retracting device according to Claims 2 or 3, it is characterised in that positioned at solution
Fixed cover is equipped with cylinder catch on Telescopic-cylinder bar outside lock cylinder, solid between the cylinder catch and the end face for solving lock cylinder
Surely there is locking spring.
8. a kind of fixed-wing unmanned plane rear leg retracting device according to claim 1, it is characterised in that the shock-absorbing cylinder
Top is provided with the shock-absorbing valve connected with shock-absorbing tube inner chamber, and shock-absorbing cylinder is internal to be fixed with pitch brace, the end of pitch brace
Shock-absorbing piston is fixed with, the shock-absorbing piston is movably arranged in shock-absorbing cylinder in-core wall, the outer circumferential walls and shock-absorbing of shock-absorbing piston
Gap is left between cylinder in-core wall.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720031299.6U CN206374971U (en) | 2017-01-09 | 2017-01-09 | A kind of fixed-wing unmanned plane rear leg retracting device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720031299.6U CN206374971U (en) | 2017-01-09 | 2017-01-09 | A kind of fixed-wing unmanned plane rear leg retracting device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206374971U true CN206374971U (en) | 2017-08-04 |
Family
ID=59404642
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720031299.6U Expired - Fee Related CN206374971U (en) | 2017-01-09 | 2017-01-09 | A kind of fixed-wing unmanned plane rear leg retracting device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206374971U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108528680A (en) * | 2018-06-06 | 2018-09-14 | 荆门畅享光年机电技术服务有限公司 | A kind of undercarriage using clamp button of the spring |
| CN108860607A (en) * | 2018-06-19 | 2018-11-23 | 智飞智能装备科技东台有限公司 | It is a kind of from steady wind resistance unmanned plane |
| CN109502315A (en) * | 2018-12-29 | 2019-03-22 | 广东增峰智能装备有限公司 | Folding material supporting rack |
-
2017
- 2017-01-09 CN CN201720031299.6U patent/CN206374971U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108528680A (en) * | 2018-06-06 | 2018-09-14 | 荆门畅享光年机电技术服务有限公司 | A kind of undercarriage using clamp button of the spring |
| CN108860607A (en) * | 2018-06-19 | 2018-11-23 | 智飞智能装备科技东台有限公司 | It is a kind of from steady wind resistance unmanned plane |
| CN109502315A (en) * | 2018-12-29 | 2019-03-22 | 广东增峰智能装备有限公司 | Folding material supporting rack |
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Legal Events
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20200423 Address after: No.3 Institute of Xiangyu aviation, Jinshan Road, Airport Economic Development Zone, Shuanggou Town, Suining County, Xuzhou City, Jiangsu Province Patentee after: Xuzhou Yiling Aviation Technology Co.,Ltd. Address before: 223800 Suqian City, Jiangsu province Suyu District Shunhe Town Industrial Park Road No. 4 Patentee before: SUQIAN FEIYING MOLD DEVELOPMENT TECHNOLOGY Co.,Ltd. |
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| TR01 | Transfer of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170804 Termination date: 20220109 |
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| CF01 | Termination of patent right due to non-payment of annual fee |