CN218839750U - Aircraft take-off and landing device - Google Patents
Aircraft take-off and landing device Download PDFInfo
- Publication number
- CN218839750U CN218839750U CN202222993277.1U CN202222993277U CN218839750U CN 218839750 U CN218839750 U CN 218839750U CN 202222993277 U CN202222993277 U CN 202222993277U CN 218839750 U CN218839750 U CN 218839750U
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- pole
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- 239000007787 solid Substances 0.000 claims abstract description 12
- 230000008602 contraction Effects 0.000 claims description 25
- 238000013016 damping Methods 0.000 claims description 20
- 230000035939 shock Effects 0.000 claims description 16
- 230000003139 buffering effect Effects 0.000 claims description 15
- 239000006096 absorbing agent Substances 0.000 claims description 10
- 230000006837 decompression Effects 0.000 abstract description 6
- 230000006835 compression Effects 0.000 abstract description 3
- 238000007906 compression Methods 0.000 abstract description 3
- 230000007935 neutral effect Effects 0.000 abstract 1
- 230000000694 effects Effects 0.000 description 5
- 230000005484 gravity Effects 0.000 description 4
- 238000005299 abrasion Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 2
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 230000006872 improvement Effects 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Vibration Dampers (AREA)
Abstract
The utility model discloses an aircraft take-off and landing device belongs to the aerospace field, including installing in the fixed end plate and the solid pole commentaries on classics board of bottom of the organism relatively, fixed end plate upper surface sets up the contact piece that is used for connecting the organism. The utility model discloses a fixed end plate, including fixed end plate, rotation section and rotation pole board swing joint, the bottom mounting of rotation pole board has the fixed plate end, fixed plate end bottom is connected with the interior pole pipe that contracts, the bottom of the interior pole pipe that contracts is connected with the decompression pole, and the decompression pole passes middle part fixed connection's support end plate and the solid end fixed connection of the end brace of bottom, the solid end bottom symmetry fixedly connected with of end brace is solid takes turns the board, be equipped with the rotation wheel between the solid wheel board. This application, can alleviate the pressure that wheel body subassembly received when the aircraft falls to the ground to reduce the neutral produced pressure of self aircraft, reduce the wearing and tearing when the tire lands, and then promote wheel body and other subassemblies and resistance to compression life.
Description
Technical Field
The utility model relates to an aerospace field, more specifically say, relate to an aircraft take off and land device.
Background
The landing gear device is an important bearing and maneuvering part of the aircraft, and plays an extremely important role in the safe taking-off and landing process of the aircraft. The landing gear is one of the main parts of the airplane, the advantages and disadvantages of the landing gear are directly related to the use safety of the airplane, the airplane is violently impacted with the ground when landing in the ground or sliding on an uneven runway at a high speed, and besides the pneumatic tire can play a small part of a buffering role, most of the impact energy needs to be absorbed by a shock absorber.
Modern aircraft are widely applied to oil-air shock absorbers, and when the shock absorbers are compressed by impact, air acts as a spring to store energy. The oil liquid passes through the small holes at a very high speed to absorb a large amount of impact energy and convert the impact energy into heat energy, so that the airplane can quickly and stably get down after being impacted, and the airplane does not jolt.
When the aircraft descends, the partial landing gear is great in the atress of shock attenuation position and support site, bears the life that great effort easily made landing gear suddenly and shortens, influences its security to, landing gear is descending the back that lands, and the phenomenon of skidding appears in the tire meeting backward pressurized, leads to the distance of sliding to increase, for this reason, the utility model discloses an aircraft landing gear is proposed to above problem.
SUMMERY OF THE UTILITY MODEL
1. Technical problem to be solved
To the problem that exists among the prior art, the utility model aims to provide an aircraft take off and land device for solve the above-mentioned problem that proposes.
2. Technical scheme
In order to solve the above problems, the utility model adopts the following technical proposal.
The utility model provides an aircraft take-off and landing device, includes fixed end plate and the solid pole commentaries on classics board of installing in the organism bottom relatively, fixed end plate upper surface sets up the contact piece that is used for connecting the organism.
The fixed end plate is movably connected with the rotating rod plate through a rotating joint fixedly mounted on the side face, the bottom fixing device of the rotating rod plate is provided with a fixed plate end, the bottom of the fixed plate end is connected with an inner telescopic rod pipe, the bottom of the inner telescopic rod pipe is connected with a pressure reducing rod, the pressure reducing rod penetrates through a supporting end plate fixedly connected with the middle of the pressure reducing rod and a bottom supporting fixed end fixedly connected with the bottom, bottom supporting fixed end bottom symmetrical and fixedly connected with fixed wheel plates, and rotating wheels are arranged between the fixed wheel plates.
The utility model discloses a damping device, including the rotation pole board, the rotation pole board has the rotation folding rod through the articulated seat of the folding rod of side fixed, the waist type downthehole portion of seting up of rotation folding rod bottom is provided with mobilizable horizontal pole that bulldozes that alternates perpendicularly, it is equipped with the shock attenuation slide bar to bulldoze horizontal pole bottom symmetry, the shock attenuation slide bar runs through the fixed plate end and supports the end plate and moves the eccentric rod articulated with the top through the bumper shock absorber that the middle part set up, the top is moved the eccentric rod and is connected with solid wheel plate rotation through the deflection ejector pin of bottom mounting, the bumper shock absorber is located and is used for buffering fuselage pressure between fixed plate end and the support end plate.
Preferably, the flexible sleeve is sleeved on the outer side of the shock absorber.
Preferably, a rotating structure is formed between the deflection rotating shaft and the bottom support fixing end, a fixing end block is fixedly installed at the bottom end of the bottom support fixing end, a buffering shrinkage rod is connected to the side face of the fixing end block, a buffering spring is arranged on the outer side of the buffering shrinkage rod, the buffering spring is fixedly connected with a shrinkage end support rod, the shrinkage end support rod is bonded with a contact pressure pad, and the contact pressure pad is used for being abutted against the deflection ejector rod to generate friction force.
Preferably, the rotating rod plate is hinged with the retracting rod through a hinged seat fixed on the side face, the retracting rod is arranged inside the hydraulic rod in a telescopic mode, the hydraulic rod is rotatably connected with a fixed rod rotating plate located at the top end of the hydraulic rod, the hydraulic rod is hinged with the rotating elastic rod through a sliding rod joint fixed at the bottom, a rotating shaft spring is sleeved in the middle of the rotating elastic rod, and the tail end of the rotating elastic rod is rotatably connected with a folding rod rear joint.
Preferably, the other end of the rotary folding rod penetrates through the rotary rod plate to be rotatably connected with a folding rod rear section, the rotary folding rod and the hydraulic rod are arranged in a crossed mode, and the other side of the folding rod rear section is connected with an inward-contracting end rod.
3. Advantageous effects
Compared with the prior art, the utility model has the advantages of:
(1) According to the scheme, the pressure on the inner side is reduced through the hydraulic rod, the contraction rod is contracted towards the inner side of the hydraulic rod, the rotating rod plate is driven to rotate in an overturning manner with the fixed end plate through the top rotating joint by the hinge seat connected with the contraction rod, and then the rotating rod plate and other components fall down through overturning, so that the relative position of the rotating rod plate and the fixed end plate is vertical, and when the rotating rod plate slides in contact with the ground, stable support can be provided, and the probability that the support structure is broken due to impact is reduced;
(2) When the contraction rod and the hydraulic rod contract, the relative position of the hydraulic rod and the fixed rod rotating plate also deflects, the hydraulic rod deflects to change the positions of the rotating elastic rod and the inner contraction end rod through the rear section of the folding rod, the rotating elastic rod rotates through the sliding rod section when rotating, the rotating elastic rod deflects upwards, the folding rod rear section drives the rotating folding rod to deflect, the rotating folding rod deflects upwards and rotates with the hinge seat of the folding rod, the rotating folding rod pushes and presses the transverse rod and the damping sliding rod to move downwards when rotating, the shock absorber in the flexible sleeve is in an extension state at the moment, the decompression rod in the inner contraction rod pipe extends downwards, the distance between the end of the fixed plate and the end plate is gradually increased, the jacking deflection rod deflects through the extension of the damping sliding rod, the deflection ejector rod rotates to deflect the fixed wheel plate and the fixed end of the bottom support, the received force can be transmitted upwards when the aircraft lands, and the self received gravity of the aircraft is reduced so as to reduce the pressure;
(3) When the rotating wheel is contacted with the ground, the rotating wheel is influenced by vertical gravity, the fixed wheel plate is deflected through the deflection rotating shaft, the jacking deflection rod and the damping slide rod move upwards, the support end plate drives the damper inside the flexible sleeve to extrude while moving along with the support end plate, so that a damping effect is achieved, the structure is used for damping in a pressure transmission mode, the overall state of the aircraft after landing is stable, and deflection caused by buffering is avoided;
(4) When the internal contraction rod pipe contracts with the pressure reducing rod, a piston ring on the top end of the pressure reducing rod slides in a sliding groove in the internal contraction rod pipe, and provides stable support during damping action, then the damping sliding rod moves to drive the rotary folding rod to deflect, the tail end of the rear side of the rotary folding rod swings downwards while rotating the elastic rod to deflect downwards, meanwhile, the rear section of the folding rod is driven to be close to a sliding rod section, and a rotating shaft spring is extruded, so that the effect of transmitting vibration is achieved, then the fixed rod rotating plate rebounds after falling to the ground, and the deflection ejector rod is gradually contacted with a contact pressure pad at the front end of the contraction end supporting rod, the contraction end supporting rod is compressed to the inner side of the damping contraction rod, so that the damping spring is extruded, and the structure is used as integral support through a fixed end block, the structure can relieve the pressure on a wheel body assembly when falling to the ground, so as to reduce the pressure generated by the self aircraft, reduce the abrasion of the wheel when landing, and further prolong the compression life of the wheel body and other assemblies.
Drawings
Fig. 1 is a schematic front perspective view of the present invention;
FIG. 2 is a schematic structural view of the flexible sleeve of the present invention;
FIG. 3 is a schematic side plan view of the present invention;
FIG. 4 is a schematic view of the fixed end block structure of the present invention
Fig. 5 is a schematic view of the structure of the rotating elastic rod of the present invention.
The numbering in the figures illustrates:
1. fixing the end plate; 2. a contact block; 3. a rotating joint; 4. a rotating lever plate; 5. the folding rod is hinged with the seat; 6. rotating the folding rod; 7. fixing the plate end; 8. pushing and pressing the cross bar; 9. a damping slide bar; 10. an inner telescopic rod pipe; 11. a pressure reducing lever; 12. supporting the end plate; 13. a flexible sleeve; 14. a bottom support fixing end; 15. a deflection rotating shaft; 16. a wheel fixing plate; 17. pushing the movable deflection rod; 18. deflecting the ejector rod; 19. a rotating wheel; 20. a hinged seat; 21. a shock absorber; 22. a retracting lever; 23. a hydraulic lever; 24. a sliding bar section; 25. rotating the elastic rod; 26. a spindle spring; 27. a rear section of the folding rod; 28. the rod is retracted; 29. fixing the rod and rotating the plate; 30. a sliding groove; 31. a piston ring; 32. a fixed end block; 33. buffering the telescopic rod; 34. a buffer spring; 35. end-contracting brace rods; 36. a touch pad.
Detailed Description
The technical solution in the embodiment of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiment of the present invention; obviously, the described embodiments are only a part of the embodiments of the present invention, and not all embodiments, and all other embodiments obtained by those skilled in the art without any inventive work are within the scope of the present invention based on the embodiments of the present invention.
Referring to fig. 1-5, an aircraft taking-off and landing device includes a fixed end plate 1 and a fixed rod rotating plate 29, which are oppositely installed at the bottom of the aircraft body, and a contact block 2 for connecting the aircraft body is disposed on the upper surface of the fixed end plate 1.
Specifically, fixed end plate 1 passes through side fixed mounting's rotation festival 3 and 4 swing joint of rotation rod board, the bottom mounting of rotation rod board 4 has fixed plate end 7, fixed plate end 7 bottom is connected with interior pole pipe 10 that contracts, the bottom of interior pole pipe 10 is connected with decompression pole 11, and decompression pole 11 passes middle part fixed connection's support end plate 12 and the end shoring of bottom and holds 14 fixed connection admittedly, end shoring holds 14 bottom symmetry fixedly connected with solid wheel board 16 admittedly, be equipped with between the solid wheel board 16 and rotate the wheel 19.
Specifically, the rotating rod plate 4 is hinged to a rotating folding rod 6 through a folding rod hinging seat 5 fixed on the side face, a movable pushing and pressing cross rod 8 is vertically inserted in a waist-shaped hole formed in the bottom end of the rotating folding rod 6, a damping slide rod 9 is symmetrically arranged at the bottom of the pushing and pressing cross rod 8, the damping slide rod 9 penetrates through a fixed plate end 7 and a supporting end plate 12 through a damper 21 arranged in the middle and is hinged to a jacking movable eccentric rod 17, the jacking movable eccentric rod 17 is rotatably connected with a fixed wheel plate 16 through a deflection ejector rod 18 fixed at the bottom end, and the damper 21 is located between the fixed plate end 7 and the supporting end plate 12 and used for buffering the pressure of the machine body.
Specifically, the flexible sleeve 13 is sleeved outside the damper 21.
Specifically, a rotating structure is formed between the deflection rotating shaft 15 and the bottom support fixed end 14, a fixed end block 32 is fixedly mounted at the bottom end of the bottom support fixed end 14, a buffer shrinkage rod 33 is connected to the side surface of the fixed end block 32, a buffer spring 34 is arranged on the outer side of the buffer shrinkage rod 33, the buffer spring 34 is fixedly connected with a shrinkage end support rod 35, the shrinkage end support rod 35 is bonded with a contact pad 36, the contact pad 36 is used for being abutted against the deflection ejector rod 18 to generate friction force, the pressure borne by the wheel body assembly can be relieved when the landing is performed, the pressure generated by the aircraft body assembly is reduced, the abrasion of the wheel body when the landing is reduced, and the compression life of the wheel body and other assemblies is prolonged.
Specifically, the rotating rod plate 4 is hinged with the contraction rod 22 through the hinged seat 20 fixed on the side, the contraction rod 22 is arranged inside the hydraulic rod 23 in a telescopic mode, the hydraulic rod 23 is rotatably connected with the fixed rod rotating plate 29 positioned on the top end of the hydraulic rod, the force which can be received when the aircraft lands can be transmitted upwards, the gravity which is received by the aircraft is reduced so as to reduce pressure, the hydraulic rod 23 is hinged with the rotating elastic rod 25 through the sliding rod section 24 fixed at the bottom, the rotating elastic rod 25 is sleeved with the rotating shaft spring 26 in the middle, and the tail end of the rotating elastic rod is rotatably connected with the folding rod rear section 27 to absorb shock through the pressure transmission mode, so that the overall state of the aircraft after landing is stable, and deflection is generated when buffering is avoided.
Specifically, the other end of the rotary folding rod 6 penetrates through the rotary rod plate 4 to be rotatably connected with a folding rod rear section 27, the rotary folding rod 6 and the hydraulic rod 23 are arranged in a crossed manner, and the other side of the folding rod rear section 27 is connected with an inward-contracting end rod 28.
When in use: firstly, a fixed end plate 1 and a fixed rod rotating plate 29 are integrally installed at a specified position through a threaded hole formed above, the fixed end plate 1 is contacted with the whole body through a contact block 2 after being installed and fixed, then the inner side pressure is reduced through a hydraulic rod 23, a contraction rod 22 is contracted towards the inner side of the hydraulic rod 23, a hinge seat 20 connected with the contraction rod 22 drives a rotating rod plate 4 to rotate in an overturning way with the fixed end plate 1 through a top end rotating joint 3, and then the rotating rod plate 4 and other components fall down through overturning, so that the relative position of the rotating rod plate 4 and the fixed end plate 1 is vertical;
when the contraction rod 22 and the hydraulic rod 23 contract, the relative position of the hydraulic rod 23 and the fixed rod rotating plate 29 also deflects, the hydraulic rod 23 deflects to change the positions of the rotating elastic rod 25 and the inner contraction end rod 28 through the folding rod rear section 27, and rotates through the sliding rod section 24 when the rotating elastic rod 25 rotates, at this time, the rotating elastic rod 25 deflects upwards, and the rotating folding rod 6 is driven by the folding rod rear section 27 to deflect, so that the rotating folding rod 6 deflects upwards and rotates with the folding rod hinge base 5, when the rotating folding rod 6 rotates, the pushing and pressing transverse rod 8 and the damping sliding rod 9 are pushed to move downwards, at this time, the damper 21 in the flexible sleeve 13 is in an extension state, the decompression rod 11 in the inner contraction rod pipe 10 extends downwards, so that the distance between the fixed plate end 7 and the support end plate 12 is gradually increased, and through the extension of the damping sliding rod 9, the pushing and moving offset rod 17 is deflected, so that the ejector rod 18 rotates to deflect the fixed wheel plate 16 and the bottom support fixed end 14;
when the rotating wheel 19 is contacted with the ground, the rotating wheel is influenced by vertical gravity, the fixed wheel plate 16 is deflected through the deflection rotating shaft 15, the jacking deflection rod 17 and the damping slide rod 9 move upwards, and the supporting end plate 12 drives the damper 21 on the inner side of the flexible sleeve 13 to extrude while moving along with the movement of the supporting end plate, so that the damping effect is achieved;
when the internal contraction rod pipe 10 contracts with the pressure reducing rod 11, a piston ring 31 on the top end of the pressure reducing rod 11 slides in a sliding groove 30 in the internal contraction rod pipe 10, and provides stable support during damping action, then the damping slide rod 9 moves to drive the rotary folding rod 6 to deflect, the tail end of the rear side of the rotary folding rod 6 swings downwards, and meanwhile the rotary elastic rod 25 deflects towards the lower side, and meanwhile the rear section 27 of the folding rod is driven to approach the slide rod section 24, and the rotary shaft spring 26 is extruded, so that the effect of transmitting vibration is achieved, then the fixed rod rotating plate 29 falls to the ground and rebounds backwards, and the deflection ejector rod 18 is gradually contacted with a contact pressure pad 36 at the front end of the contraction end support rod 35, the contraction end support rod 35 is pressed to contract towards the inner side of the buffer contraction rod 33, and further the buffer spring 34 is extruded, and the fixed end block 32 is used as integral support.
The above description is only the preferred embodiment of the present invention; the scope of the present invention is not limited thereto. Any person skilled in the art should also be able to cover the technical scope of the present invention by replacing or changing the technical solution and the improvement concept of the present invention with equivalents and modifications within the technical scope of the present invention.
Claims (5)
1. The utility model provides an aircraft take-off and landing device, includes relatively installs in fixed end plate (1) and solid pole commentaries on classics board (29) of organism bottom, fixed end plate (1) upper surface sets up contact block (2) that are used for connecting the organism, its characterized in that:
the fixed end plate (1) is movably connected with a rotating rod plate (4) through a rotating joint (3) fixedly mounted on the side face, a fixed plate end (7) is fixedly arranged at the bottom end of the rotating rod plate (4), an inner contraction rod pipe (10) is connected to the bottom of the fixed plate end (7), a pressure reducing rod (11) is connected to the bottom end of the inner contraction rod pipe (10), the pressure reducing rod (11) penetrates through a supporting end plate (12) fixedly connected to the middle of the fixed end plate and is fixedly connected with a bottom bracing fixing end (14) at the bottom end of the fixed end (14), wheel fixing plates (16) are symmetrically and fixedly connected to the bottom of the bottom bracing fixing end (14), and rotating wheels (19) are arranged between the wheel fixing plates (16);
the utility model discloses a damping device, including rotation pole board (4), waist type downthehole portion that rotation pole board (4) was seted up through the fixed articulated seat of folding rod in side (5) articulates there is rotation folding rod (6), the waist type downthehole portion that rotation folding rod (6) bottom was seted up alternates perpendicularly and is provided with mobilizable horizontal pole (8) that bulldozes, it is equipped with shock attenuation slide bar (9) to bulldoze horizontal pole (8) bottom symmetry, shock attenuation slide bar (9) run through fixed plate end (7) and support end plate (12) and move eccentric rod (17) with the top articulated, the top is moved eccentric rod (17) and is rotated with solid wheel plate (16) through bottom mounting's deflection ejector pin (18) and be connected, shock absorber (21) are located fixed plate end (7) and are supported and are used for buffering fuselage pressure between end plate (12).
2. An aircraft takeoff and landing assembly according to claim 1, wherein: the outer side of the shock absorber (21) is sleeved with a flexible sleeve (13).
3. An aircraft takeoff and landing assembly according to claim 1, wherein: a rotating structure is formed between the deflection rotating shaft (15) and the bottom support fixing end (14), a fixing end block (32) is fixedly installed at the bottom end of the bottom support fixing end (14), a buffering shrinkage rod (33) is connected to the side face of the fixing end block (32), a buffering spring (34) is arranged on the outer side of the buffering shrinkage rod (33), the buffering spring (34) is fixedly connected with a shrinkage end support rod (35), the shrinkage end support rod (35) is bonded with a contact pressure pad (36), and the contact pressure pad (36) is used for being abutted against the deflection ejector rod (18) to generate friction force.
4. An aircraft takeoff and landing assembly according to claim 1, wherein: the utility model discloses a hydraulic pressure swing arm, including rotation pole board (4), contraction pole (22) retractable sets up inside hydraulic stem (23), hydraulic stem (23) rotate with the solid pole commentaries on classics board (29) that is located its top and is connected, hydraulic stem (23) are articulated with rotation elastic rod (25) through fixed slide bar festival (24) in bottom, pivot spring (26) are established to the middle part cover that rotates elastic rod (25), and its end rotation is connected with a back festival (27) of folding rod.
5. An aircraft takeoff and landing assembly according to claim 1, wherein: the other end of the rotary folding rod (6) penetrates through the rotary rod plate (4) to be rotatably connected with a folding rod rear section (27), the rotary folding rod (6) and the hydraulic rod (23) are arranged in a crossed mode, and the other side of the folding rod rear section (27) is connected with an inward-contracting end rod (28).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222993277.1U CN218839750U (en) | 2022-11-10 | 2022-11-10 | Aircraft take-off and landing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222993277.1U CN218839750U (en) | 2022-11-10 | 2022-11-10 | Aircraft take-off and landing device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218839750U true CN218839750U (en) | 2023-04-11 |
Family
ID=87291954
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222993277.1U Active CN218839750U (en) | 2022-11-10 | 2022-11-10 | Aircraft take-off and landing device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218839750U (en) |
-
2022
- 2022-11-10 CN CN202222993277.1U patent/CN218839750U/en active Active
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20240306 Address after: No. 77 Beiwei Road, Gulou District, Nanjing City, Jiangsu Province, 210003 Patentee after: Zhan Tianming Country or region after: China Patentee after: Li Sumei Address before: 210000 room 1-616, No. 20, Xinghuo Road, Jiangbei new district, Nanjing, Jiangsu Province Patentee before: NANJING CHENGPU UAV Co.,Ltd. Country or region before: China |
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| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20240401 Address after: Room 406, Building D, Vitality Business Plaza, 185 Jumao Street, Yuanhe Street, Xiangcheng District, Suzhou City, Jiangsu Province, 215100 Patentee after: Suzhou Zhongyao Digital Technology Co.,Ltd. Country or region after: China Address before: No. 77 Beiwei Road, Gulou District, Nanjing City, Jiangsu Province, 210003 Patentee before: Zhan Tianming Country or region before: China Patentee before: Li Sumei |