CN205396520U - Undercarriage installation component , undercarriage subassembly and aircraft - Google Patents
Undercarriage installation component , undercarriage subassembly and aircraft Download PDFInfo
- Publication number
- CN205396520U CN205396520U CN201521139565.4U CN201521139565U CN205396520U CN 205396520 U CN205396520 U CN 205396520U CN 201521139565 U CN201521139565 U CN 201521139565U CN 205396520 U CN205396520 U CN 205396520U
- Authority
- CN
- China
- Prior art keywords
- undercarriage
- aircraft
- supporting leg
- mounting seat
- main supporting
- 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.)
- Active
Links
- 238000009434 installation Methods 0.000 title abstract 5
- 210000003141 lower extremity Anatomy 0.000 claims description 21
- 238000000034 method Methods 0.000 abstract description 9
- 230000004308 accommodation Effects 0.000 abstract 1
- 230000033001 locomotion Effects 0.000 description 10
- 230000000694 effects Effects 0.000 description 5
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000008602 contraction Effects 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 230000000007 visual effect Effects 0.000 description 2
- 241000276425 Xiphophorus maculatus Species 0.000 description 1
- 210000001015 abdomen Anatomy 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
Abstract
The utility model discloses an undercarriage installation component, undercarriage subassembly and aircraft belongs to aircraft and zero technical field. The utility model provides an undercarriage installation component includes the mount pad for be connected with the fuselage of aircraft, the linear guide of two parallels, linear guide's both ends link firmly respectively on the mount pad, the lead screw of parallel arrangement between two linear guide, set up on the lead screw and rather than matched with sliding nut and with screw connection's driving motor, driving motor is used for drive screw rotatory, the sliding nut both sides are connected with a sharp slider respectively, sharp slider slides and sets up on the linear guide rather than corresponding. The utility model provides an undercarriage installation component, small friction, and two undercarriage main parts synchronism in undercarriage accommodation process is good, the precision is high. The utility model provides an undercarriage subassembly and aircraft are owing to adopted above -mentioned undercarriage installation component, and the synchronism is good, the regulation precision is high.
Description
Technical field
This utility model relates to aircraft and parts technical field thereof, particularly relates to a kind of undercarriage mounting assembly, the landing gear assembly including this mounting assembly and aircraft.
Background technology
At present, utilize aircraft especially unmanned vehicle to carry out the mode of taking photo by plane to have been obtained for being widely applied.Take photo by plane and aircraft used connects filming apparatus, adopt automatic shooting or the mode that remotely controls to complete corresponding shooting action.
Wherein, aircraft includes the parts such as fuselage, propeller and undercarriage, and the effect of undercarriage is when, after aircraft lands, fuselage playing the effect of support.In actual application, in order to avoid undercarriage blocks The Cloud Terrace, affect shooting results, it is necessary to shunk by undercarriage.And at present, conventional contraction mode is directly undercarriage to be opened to both sides the lower section being placed in fuselage and propeller.But, adopting this kind of mode, undercarriage outwards launches, and the air force of aircraft can be produced interference, affect the performance of aircraft.Meanwhile, when aircraft does not use, no matter undercarriage part is being launched or contraction state, the space that aircraft takies all can be caused relatively big, be unfavorable for storage and the transport of aircraft.
Although the undercarriage that folding mode shrinks can also be adopted, such as, undercarriage includes support portion and tractive unit, the cross-brace lower limb that wherein support portion includes a main supporting leg being rotationally connected with undercarriage mounting assembly and the other end with main supporting leg is rotationally connected, tractive unit is used for driving support portion to be folded up or drops down, and lower limb is closed under abdomen during similar Bird Flight by folding undercarriage, the lower section of fuselage can be contracted in completely, without extra outside extension.
But the undercarriage that this employing folding mode shrinks requires over a undercarriage mounting assembly and is connected on the fuselage of aircraft, wherein, the bottom of the mounting seat of undercarriage mounting assembly needs to be provided with a driving device, driving device connects the upper end of tractive unit, and driving device can be for linear motion in mounting seat, and then drive tractive unit motion, tractive unit and then drive support portion folding or open.But, during tractive unit motion, resistance is big, and the poor synchronization of two the landing gear assembly main bodys in left side and right side, precision are low.
Utility model content
A purpose of the present utility model is in that to propose the undercarriage mounting assembly of a kind of resistance, the synchronicity improved in undercarriage adjustment process and precision that can reduce in undercarriage adjustment process；
Another purpose of the present utility model is in that to propose the undercarriage that a kind of synchronicity is good, degree of regulation is high, can effectively fold and open；
Further object of the present utility model is in that to propose the aircraft that a kind of aerodynamic interference is little, shooting effect good, be easy to deposit transport.
For reaching this purpose, on the one hand, the utility model proposes following technical scheme:
A kind of undercarriage mounting assembly, including: mounting seat, for being connected with the fuselage of aircraft；Two parallel line slideways, the two ends of described line slideway are respectively fixedly connected with in described mounting seat；The sliding nut be set in parallel in the leading screw between two described line slideways, being arranged on described leading screw and being matched therewith and the drive motor being connected with described leading screw, described drive motor is used for driving described leading screw to rotate, described sliding nut both sides are connected to a linear slider, and described linear slider is slideably positioned on corresponding described line slideway.
Further, also including two keepers being relatively arranged in described mounting seat, the two ends of described line slideway are respectively fixedly connected with on two described keepers, and described leading screw is at least arranged on one of them described keeper.
Further, described leading screw is trapezoidal screw or rectangle leading screw.
Further, described drive motor is installed in described mounting seat.
Further, described mounting seat is provided with two articulated sections, two described articulated section conllinear and being oppositely arranged with two described linear slider, it is rotationally connected for the parts with undercarriage.
Further, described mounting seat is provided with the installing hole for being connected with aircraft fuselage.
On the other hand, the utility model proposes following technical scheme:
A kind of landing gear assembly including any of the above-described described undercarriage mounting assembly, including at least two group undercarriage main bodys, often organizes described undercarriage main body and includes support arrangement and a traction apparatus；Described support arrangement includes main supporting leg and cross-brace lower limb, and one end of described main supporting leg is rotationally connected with in described mounting seat, and described main supporting leg is rotationally connected with described cross-brace lower limb away from one end of described mounting seat；Described traction apparatus includes traction lever, first draw bar and the second draw bar, one end of described traction lever is rotationally connected with in described linear slider, one end of the other end and described first draw bar is rotationally connected, the middle part of described traction lever and described main supporting leg are rotationally connected, described first draw bar is connected by sliding axle with described second draw bar away from one end of described traction lever, described main supporting leg is provided with the bar shaped spacing hole extended along described main supporting leg length direction, described sliding axle is located in described bar shaped spacing hole, described second draw bar is rotationally connected with described cross-brace lower limb away from one end of described first draw bar, angle between described main supporting leg and described cross-brace lower limb is less than 90 °.
Further, the length of described main supporting leg is not less than the length of described cross-brace lower limb.
Further, it is rotationally connected described in and connects into rotating shaft.
Another further aspect, the utility model proposes following technical scheme:
A kind of aircraft, including fuselage, described fuselage is connected to the landing gear assembly described in any of the above-described item.
The beneficial effects of the utility model are:
The undercarriage mounting assembly that this utility model provides, sliding nut can drive two linear slider difference linearly guide rail movements, and then two linear slider drive two undercarriage bulk motion on left side and right side respectively, frictional force is little, and two undercarriage main bodys in undercarriage adjustment process, synchronicity is good, precision is high.
The landing gear assembly that this utility model provides is owing to have employed above-mentioned undercarriage mounting assembly, and landing gear assembly synchronicity in adjustment process is good, degree of regulation is high；And the landing gear assembly that this utility model provides can be contracted in the lower section of fuselage completely, it is to avoid the air force of aircraft is produced interference, 360 ° of ring all unscreened shooting visuals field when aircraft is taken photo by plane can be realized simultaneously；Meanwhile, folding structure also makes the transportation volume of complete machine less, makes transport more convenient.
The aircraft that this utility model provides is owing to have employed above-mentioned landing gear assembly, and its aerodynamic interference is little, shooting effect good, be easy to deposit transport.
Accompanying drawing explanation
Fig. 1 is the perspective view of the undercarriage mounting assembly that embodiment one of the present utility model provides；
Fig. 2 is the upward view of the undercarriage mounting assembly that embodiment one of the present utility model provides；
Fig. 3 is the top view of the undercarriage mounting assembly that embodiment one of the present utility model provides；
Fig. 4 is one of structural representation of landing gear assembly of embodiment two of the present utility model offer；
Fig. 5 is the two of the structural representation of the landing gear assembly that embodiment two of the present utility model provides.
In figure, 1, mounting seat；2, line slideway；3, leading screw；4, sliding nut；5, drive motor；6, linear slider；7, keeper；8, articulated section；9, main supporting leg；10, cross-brace lower limb；11, traction lever；12, the first draw bar；13, the second draw bar；14, sliding axle；15, bar shaped spacing hole.
Detailed description of the invention
The technical solution of the utility model is further illustrated below in conjunction with accompanying drawing and by detailed description of the invention.
Embodiment one:
Present embodiments providing a kind of undercarriage mounting assembly, as shown in Figure 1 to Figure 3, it includes mounting seat 1, for being connected with the fuselage of aircraft；Two parallel line slideways 2, the two ends of line slideway 2 are respectively fixedly connected with in mounting seat 1；The sliding nut 4 be set in parallel in the leading screw 3 between two line slideways 2, being arranged on leading screw 3 and being matched therewith and the drive motor 5 being connected with leading screw 3, drive motor 5 is for driving leading screw 3 to rotate the rectilinear motion being converted to sliding nut 4 with the rotary motion by leading screw 3, sliding nut 4 both sides are connected to a linear slider 6, and linear slider 6 is slideably positioned on corresponding line slideway 2.Mounting seat 1 is preferably installing plate, so that the structure of undercarriage mounting assembly is simpler；Drive motor 5 is preferable over and is installed in mounting seat 1, so that overall structure is more compact.Certainly, mounting seat 1 can also be set to other version according to specific needs, and drive motor 5 can also be connected on the fuselage of aircraft, it is possible to the rotary motion of leading screw 3 is converted to the rectilinear motion of sliding nut 4 the most at last.
In the present embodiment, sliding nut 4 can drive two linear slider 6 respectively linearly guide rail 2 move, and then two linear slider 6 drive the tractive unit motion of two undercarriage main bodys on left side and right side respectively, frictional force is little, and two undercarriage main bodys in undercarriage adjustment process, synchronicity is good, precision is high.
As embodiment more specifically, also including two keepers 7 being relatively arranged in mounting seat 1 in above-described embodiment, keeper 7 is preferably platy structure, and the two ends of line slideway 2 are respectively fixedly connected with on two keepers 7, and leading screw 3 is arranged on two keepers 7.In the present embodiment, the mounting means of line slideway 2 is simple, and two keepers 7 are that leading screw 3 and sliding nut 4 and linear slider 6 provide position-limiting action, and in undercarriage adjustment process, synchronicity is better, precision is higher.Certainly, the fixed form of line slideway 2 and the mounting means of leading screw 3 are not limited to above-mentioned situation, for instance, leading screw 3 is only arranged on one of them keeper 7；Again such as, each line slideway 2 is fixedly installed in mounting seat 1 respectively through different keepers.
As further embodiment, leading screw 3 is function trapezoidal screw or the rectangle leading screw with self-locking, to ensure stability when undercarriage uses.
As further embodiment, mounting seat 1 is provided with two articulated sections, two articulated section conllinear and being oppositely arranged with two linear slider 6, it is rotationally connected for the parts with undercarriage.
As embodiment more specifically, mounting seat 1 is provided with the installing hole for being connected with aircraft fuselage, mounting seat 1 can be passed through bolt or screw etc. and be connected with the fuselage of aircraft, when needs attaching/detaching undercarriage, have only to separate mounting seat 1 with fuselage, and other parts on undercarriage are connected with mounting seat 1, this kind of form is easy to manufacture, and conveniently fuselage and undercarriage is carried out maintenance maintenance.
Embodiment two:
Present embodiments providing the landing gear assembly of a kind of undercarriage mounting assembly included described in embodiment one, as shown in Figure 4 and Figure 5, it includes at least two group undercarriage main bodys, and often group undercarriage main body includes support arrangement and a traction apparatus；Prop up support arrangement and include main supporting leg 9 and cross-brace lower limb 10, one end of main supporting leg 9 is rotationally connected with on the position relative with described linear slider 6 of mounting seat 1, such as, being installed on the articulated section 8 described in embodiment one, one end of the remotely mounted seat 1 of main supporting leg 9 and cross-brace lower limb 10 are rotationally connected；Traction apparatus includes traction lever 11, first draw bar 12 and the second draw bar 13, one end of traction lever 11 is rotationally connected with in linear slider 6, one end of the other end and the first draw bar 12 is rotationally connected, the middle part of traction lever 11 and main supporting leg 9 are rotationally connected, first draw bar 12 is connected by sliding axle 14 with the second draw bar 13 away from one end of traction lever 11, main supporting leg 9 is provided with the bar shaped spacing hole 15 extended along main supporting leg 9 length direction, sliding axle 14 is located in bar shaped spacing hole 15, second draw bar 13 is rotationally connected with cross-brace lower limb 10 away from one end of the first draw bar 12, angle between main supporting leg 9 and cross-brace lower limb 10 is less than 90 °.
As embodiment more specifically, main supporting leg 9 is provided with the slotted eye extended along main supporting leg 9 length direction of hollow out, and the middle part of traction lever 11 is connected to central shaft, central shaft and the first draw bar 12 and is located in slotted eye；Bar shaped spacing hole 15 is located on the sidewall of slotted eye, and sliding axle 14 is positioned at slotted eye, and the end of sliding axle 14 is connected on bar shaped spacing hole 15.
In use procedure, rely on the mechanical action of traction apparatus to control the action that a support arrangement completes to shrink/launch, wherein, traction apparatus is arranged on the inside of a support arrangement, more safe and reliable, reduce the probability that traction apparatus is collided with, damaged；Meanwhile, the tailored appearance of undercarriage understands, increases aesthetic property.
Further, the length of main supporting leg 9 is not less than the length of cross-brace lower limb 10.Wherein, in a contracted state, cross-brace lower limb 10 is bonded to each other with main supporting leg 9, main supporting leg 9 is then bonded to each other with fuselage, if the length of cross-brace lower limb 10 is relatively big, still it is likely to occur its length long, and extends outward outside the vertical range of fuselage, it is likely to air force is caused interference, and is also unfavorable for storage and transport.
Further, main supporting leg 2, cross-brace lower limb the 10, first draw bar 12 and the second draw bar 13 are equipped with hollow hole.Each parts arrange hollow hole to alleviate the weight of whole undercarriage and be beneficial to the flight of aircraft.
Above-mentioned being rotationally connected connects into rotating shaft.In this landing gear assembly, being rotationally connected of each several part is rotating shaft connection, include in junction two pieces be oppositely arranged to plate, two pieces to plate between be provided with one block of plate, wherein, be respectively provided with perforation on plate and plate, rotating shaft is through boring a hole, screwed retaining ring is set at the two ends of rotating shaft, wherein, plate and plate is connected to any parts.End to plate is round and smooth shape, it is to avoid occur colliding with and the phenomenon having some setbacks in rotation process.Such as, articulated section 8 namely can two pieces be oppositely arranged to plate, to the perforation being provided for rotating shaft traverse on plate.
Landing gear assembly in the present embodiment have employed above-mentioned undercarriage mounting assembly, the upper end of the tractive unit in its two groups of undercarriage main bodys can be rotationally connected with in a linear slider 6 respectively, owing to linear slider 6 is slideably positioned on line slideway 2 respectively, the synchronicity of landing gear assembly is good, degree of regulation is high；And the landing gear assembly that the present embodiment provides can be contracted in the lower section of fuselage completely, it is to avoid the air force of aircraft is produced interference, 360 ° of ring all unscreened shooting visuals field when aircraft is taken photo by plane can be realized simultaneously；Meanwhile, folding structure also makes the transportation volume of complete machine less, makes transport more convenient.
Embodiment three:
Present embodiments providing a kind of aircraft, including fuselage, fuselage is connected to the landing gear assembly as described in embodiment two.
Aircraft in the present embodiment is owing to have employed above-mentioned landing gear assembly, and its aerodynamic interference is little, shooting effect good, be easy to deposit transport.
Know-why of the present utility model is described above in association with specific embodiment.These describe and are intended merely to explanation principle of the present utility model, and can not be construed to the restriction to this utility model protection domain by any way.Based on explanation herein, those skilled in the art need not pay performing creative labour can associate other detailed description of the invention of the present utility model, and these modes fall within protection domain of the present utility model.
Claims (10)
1. a undercarriage mounting assembly, it is characterised in that including:
Mounting seat (1), for being connected with the fuselage of aircraft；
Two parallel line slideways (2), the two ends of described line slideway (2) are respectively fixedly connected with in described mounting seat (1)；
Be set in parallel in the leading screw (3) between two described line slideways (2), to be arranged at described leading screw (3) upper and the sliding nut (4) that is matched therewith and the drive motor (5) being connected with described leading screw (3), described drive motor (5) is used for driving described leading screw (3) to rotate, described sliding nut (4) both sides are connected to a linear slider (6), and described linear slider (6) is slideably positioned on corresponding described line slideway (2).
2. undercarriage mounting assembly according to claim 1, it is characterized in that, also include two keepers (7) being relatively arranged in described mounting seat (1), the two ends of described line slideway (2) are respectively fixedly connected with on two described keepers (7), and described leading screw (3) is at least arranged on one of them described keeper (7).
3. undercarriage mounting assembly according to claim 1, it is characterised in that described leading screw (3) is trapezoidal screw or rectangle leading screw.
4. undercarriage mounting assembly according to claim 1, it is characterised in that described drive motor (5) is installed in described mounting seat (1).
5. according to the arbitrary described undercarriage mounting assembly of Claims 1-4, it is characterized in that, described mounting seat (1) is provided with two articulated sections, two described articulated section conllinear and being oppositely arranged with two described linear slider, it is rotationally connected for the parts with undercarriage.
6. according to the arbitrary described undercarriage mounting assembly of Claims 1-4, it is characterised in that described mounting seat is provided with the installing hole for being connected with aircraft fuselage on (1).
7. one kind include as arbitrary in claim 1 to 6 as described in the landing gear assembly of undercarriage mounting assembly, it is characterised in that include at least two group undercarriage main bodys, often organize described undercarriage main body and include support arrangement and a traction apparatus；
Described support arrangement includes main supporting leg (9) and cross-brace lower limb (10), one end of described main supporting leg (9) is rotationally connected with in described mounting seat (1), and described main supporting leg (9) is rotationally connected with described cross-brace lower limb (10) away from one end of described mounting seat (1)；
nullDescribed traction apparatus includes traction lever (11)、First draw bar (12) and the second draw bar (13)，One end of described traction lever (11) is rotationally connected with in described linear slider (6)，One end of the other end and described first draw bar (12) is rotationally connected，The middle part of described traction lever (11) and described main supporting leg (9) are rotationally connected，Described first draw bar (12) is connected by sliding axle (14) with described second draw bar (13) away from one end of described traction lever (11)，Described main supporting leg (9) is provided with the bar shaped spacing hole (15) extended along described main supporting leg (9) length direction，Described sliding axle (14) is located in described bar shaped spacing hole (15)，Described second draw bar (13) is rotationally connected with described cross-brace lower limb (10) away from one end of described first draw bar (12)，Angle between described main supporting leg (9) and described cross-brace lower limb (10) is less than 90 °.
8. landing gear assembly according to claim 7, it is characterised in that the length of described main supporting leg (9) is not less than the length of described cross-brace lower limb (10).
9. the landing gear assembly according to claim 7 or 8, it is characterised in that described in be rotationally connected into rotating shaft connect.
10. an aircraft, including fuselage, it is characterised in that described fuselage is connected to the landing gear assembly described in any one of claim 7-9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521139565.4U CN205396520U (en) | 2015-12-31 | 2015-12-31 | Undercarriage installation component , undercarriage subassembly and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521139565.4U CN205396520U (en) | 2015-12-31 | 2015-12-31 | Undercarriage installation component , undercarriage subassembly and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205396520U true CN205396520U (en) | 2016-07-27 |
Family
ID=56449386
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201521139565.4U Active CN205396520U (en) | 2015-12-31 | 2015-12-31 | Undercarriage installation component , undercarriage subassembly and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205396520U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110418753A (en) * | 2017-10-30 | 2019-11-05 | 深圳市大疆创新科技有限公司 | A kind of unmanned vehicle and its ascending, descending frame |
-
2015
- 2015-12-31 CN CN201521139565.4U patent/CN205396520U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110418753A (en) * | 2017-10-30 | 2019-11-05 | 深圳市大疆创新科技有限公司 | A kind of unmanned vehicle and its ascending, descending frame |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103963958B (en) | Unmanned plane wingfold mechanism | |
| CN203047530U (en) | Aircraft foot stand and aircraft with same | |
| CN105253296B (en) | A kind of undercarriage control device | |
| CN106564349A (en) | Triphibian unmanned aerial vehicle | |
| CN106081060B (en) | A kind of VTOL composite layouts unmanned plane rotor draw off gear | |
| CN105882940A (en) | Arrangement for effecting movement of a wing tip device between a flight configuration and a ground configuration | |
| CN104176239A (en) | Flap arrangement for a wing of an aircraft and an aircraft with a wing comprising such a flap arrangement | |
| CN204173155U (en) | A kind of delta-wing aircraft | |
| CN106672204A (en) | Tilting mechanism for tilting rotor wing airplane | |
| CN204452926U (en) | The dynamic many rotor wing unmanned aerial vehicles of variable pitch shaft drive of oil | |
| CN205087134U (en) | Bionical undercarriage and aircraft | |
| CN104590535A (en) | Propelling device for airship power device | |
| CN104260873B (en) | A kind of delta-wing aircraft | |
| CN205396520U (en) | Undercarriage installation component , undercarriage subassembly and aircraft | |
| CN110753631A (en) | Turnover type propeller device | |
| CN209192208U (en) | One kind can folding and unfolding unmanned plane undercarriage | |
| CN203143002U (en) | Connective wing synchronous variable sweep-mobile mechanism | |
| CN106976547A (en) | A kind of built-in folding airstair of aircraft airborne | |
| CN109573008A (en) | For the aircraft on the water with land takeoff and landing | |
| CN203767065U (en) | Wing folding mechanism of unmanned aerial vehicle | |
| CN215554252U (en) | Parking machine for miniature unmanned aerial vehicle | |
| CN113716024A (en) | Unmanned aerial vehicle undercarriage convenient to expand and adjust | |
| CN109353489B (en) | Multifunctional flap structure of unmanned aerial vehicle | |
| CN206679257U (en) | Collapsible unmanned plane | |
| CN102556342A (en) | Wing combination |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Undercarriage installation component , undercarriage subassembly and aircraft Effective date of registration: 20170327 Granted publication date: 20160727 Pledgee: XinDa national equity investment fund (Shanghai) partnership (L.P.)|Beijing Civil Aviation Heyuan Investment Center (L.P.) Pledgor: ZEROTECH (BEIJING) INTELLIGENCE TECHNOLOGY Co.,Ltd. Registration number: 2017990000242 |
|
| PP01 | Preservation of patent right | ||
| PP01 | Preservation of patent right |
Effective date of registration: 20190906 Granted publication date: 20160727 |
|
| PD01 | Discharge of preservation of patent | ||
| PD01 | Discharge of preservation of patent |
Date of cancellation: 20220406 Granted publication date: 20160727 |
|
| PP01 | Preservation of patent right | ||
| PP01 | Preservation of patent right |
Effective date of registration: 20220406 Granted publication date: 20160727 |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20221008 Granted publication date: 20160727 Pledgee: XinDa national equity investment fund (Shanghai) partnership (L.P.)|Beijing Civil Aviation Heyuan Investment Center (L.P.) Pledgor: ZEROTECH (BEIJING) INTELLIGENCE TECHNOLOGY Co.,Ltd. Registration number: 2017990000242 |
|
| PD01 | Discharge of preservation of patent | ||
| PD01 | Discharge of preservation of patent |
Date of cancellation: 20220918 Granted publication date: 20160727 |
|
| PP01 | Preservation of patent right | ||
| PP01 | Preservation of patent right |
Effective date of registration: 20220918 Granted publication date: 20160727 |