CN105966592B - A kind of multi-rotor aerocraft delay, synergy, save external member from damage - Google Patents
A kind of multi-rotor aerocraft delay, synergy, save external member from damage Download PDFInfo
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- CN105966592B CN105966592B CN201610413020.0A CN201610413020A CN105966592B CN 105966592 B CN105966592 B CN 105966592B CN 201610413020 A CN201610413020 A CN 201610413020A CN 105966592 B CN105966592 B CN 105966592B
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- air bag
- rotor aerocraft
- floatage air
- axis
- floatage
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- 230000006378 damage Effects 0.000 title claims abstract description 18
- 239000000725 suspension Substances 0.000 claims abstract description 20
- 239000002775 capsule Substances 0.000 claims description 4
- 238000000034 method Methods 0.000 abstract description 5
- 230000001681 protective effect Effects 0.000 abstract description 3
- 239000007789 gas Substances 0.000 description 7
- 238000010586 diagram Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 208000027418 Wounds and injury Diseases 0.000 description 2
- 230000003139 buffering effect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 208000014674 injury Diseases 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 1
- HBBGRARXTFLTSG-UHFFFAOYSA-N Lithium ion Chemical compound [Li+] HBBGRARXTFLTSG-UHFFFAOYSA-N 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005183 dynamical system Methods 0.000 description 1
- 230000009187 flying Effects 0.000 description 1
- 239000001307 helium Substances 0.000 description 1
- 229910052734 helium Inorganic materials 0.000 description 1
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 description 1
- 244000144980 herd Species 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 229910001416 lithium ion Inorganic materials 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000007935 neutral effect Effects 0.000 description 1
- 238000010899 nucleation Methods 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000012857 repacking Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 238000009331 sowing Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/58—Arrangements or construction of gas-bags; Filling arrangements
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D45/04—Landing aids; Safety measures to prevent collision with earth's surface
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/30—Lighter-than-air aircraft, e.g. aerostatic aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B2201/00—Hybrid airships, i.e. airships where lift is generated aerodynamically and statically
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
- Other Liquid Machine Or Engine Such As Wave Power Use (AREA)
Abstract
The present invention relates to unmanned air vehicle technique field, and in particular to a kind of multi-rotor aerocraft delay, synergy, save external member from damage.The invention floatage air bag (1), connection suspension mechanism (2) and multi-rotor aerocraft；Wherein, the centrally disposed vacancy section of floatage air bag (1), connection suspension mechanism (2) is arranged on the vacancy section of floatage air bag (1), and floatage air bag (1) is connected to multi-rotor aerocraft；Floatage air bag (1) is with respect to the multi-rotor aerocraft axis rotary limited centered on X-axis, Y-axis respectively, the central shaft of X-axis limit hinge (24) and the orthogonality of center shaft of Y-axis limit hinge (25)；The outer surface of floatage air bag (1) is provided with more than one charge valve (4).The present invention can extend the flight time of multi-rotor aerocraft, improve payload, and to multi-rotor aerocraft in itself and the public plays a protective role.
Description
Technical field
The present invention relates to unmanned air vehicle technique field, in particular to a kind of multi-rotor aerocraft delay, synergy, saves from damage
External member.
Background technology
Multi-rotor aerocraft is a kind of multipurpose vertically taking off and landing flyer.Compared with traditional single-rotor helicopter, more rotors
For aircraft without complicated pitch-changing mechanism, maintenance is easy, easy to use efficient.At present, the application of multi-rotor aerocraft has been
Through cover agriculture, woods, herd, fishing, industry, building, scientific research, traffic, multiple industries such as amusement.Aeroplane photography, medical treatment can be performed
The tasks such as rescue, meteorological detection, aerial inspection, aerial seeding aerial sowing, aerial fertilising, play very important work in national economy
With.
Multi-rotor aerocraft is subject to the low restriction of energy content of battery storage density, its flight time frequently with driven by power
It far can not meet the active demand that social development is applied to voyage.In recent years, have Some Enterprises by fuel cell
Apply on multi-rotor aerocraft, make its flight time by rising to about one using 20 minutes or so of conventional lithium-ion battery
Or so a hour.But fuel cell technology is still immature, use cost is high, on consumer level multi-rotor aerocraft temporarily without
Method large-scale promotion.How on the basis of existing technology, in the case of not changing original power set, it is inexpensive significantly
Extend the flight time of multi-rotor aerocraft, increase payload becomes one extremely urgent demand of the art.
The security and operation stability of aircraft platforms are also to be paid special attention in current multi-rotor aerocraft technical field
The problem of.Using multiple rotors, rotation produces lift and controling power to multi-rotor aerocraft at a high speed, once breaking down, rotates at a high speed
Rotor blade and the fuselage of high-speed motion to periphery object and itself can cause serious harm.Have the notably entail dangers to public's
The security of the lives and property.In the technical field, engineers are made that certain effort, employ rotor redundancy, failure compensation etc.
Control method.But the fuselage that high-speed rotating rotor blade and high-speed motion can not be solved on physical layer is carried and moved
Energy component is endangered caused by periphery object and itself.Some multi-rotor aerocrafts are equipped with the machines such as crash-proof bracket and parachute
Structure, can reduce to periphery object and the injury of itself, but both the above mechanism reliability to a certain extent when aircraft fails
It is not high, and multi-rotor aerocraft payload can be reduced.
The content of the invention
It is an object of the invention to provide a kind of multi-rotor aerocraft delay, synergy, save external member from damage, more rotors can be extended
The flight time of aircraft, improves payload, and to multi-rotor aerocraft in itself and the public plays a protective role.
An embodiment of the present invention provides a kind of multi-rotor aerocraft delay, synergy, save external member from damage, including：Floatage air bag, company
Connect suspension mechanism and multi-rotor aerocraft；Wherein, the centrally disposed vacancy section of the floatage air bag, the connection suspension mechanism are set
Put in the vacancy section of the floatage air bag, and the floatage air bag is connected to multi-rotor aerocraft；The floatage air bag is opposite
The multi-rotor aerocraft axis rotary limited centered on X-axis, Y-axis respectively, central shaft and the Y of the X-axis limit hinge
The orthogonality of center shaft of axis limit hinge；The outer surface of the floatage air bag is provided with more than one charge valve.
In certain embodiments, it is preferably that the connection suspension framework includes：It is rigidly connected more with multi-rotor aerocraft
Rotor craft connecting bracket, and the rigidly connected floatage air bag connection ring of the floatage air bag, and it is connected to more rotations
Intermediate connecting ring between rotor aircraft connecting bracket and the floatage air bag connection ring；The multi-rotor aerocraft connection branch
Frame, the floatage air bag connection ring and the intermediate connecting ring three are set for concentric ring-type.The multi-rotor aerocraft
Connected between connecting bracket and the intermediate connecting ring by two coaxial X-axis limit hinges；The intermediate connecting ring and institute
State floatage air bag connection ring coaxial there is Y-axis limit hinge to connect by two；The central shaft of the X-axis limit hinge and institute
State the orthogonality of center shaft of Y-axis limit hinge.The floatage air bag and the connection suspension mechanism after exhaust are in folded state.Institute
State the airbag structure that floatage air bag is ring-shaped structure.The floatage air bag is made of one or more chambers.Two neighboring institute
State and air pressure double-beat drop valve is set on the connection air flue between chamber.Each chamber is both provided with most charge valves.
A kind of multi-rotor aerocraft delay provided in an embodiment of the present invention, synergy, save external member from damage, compared with prior art,
Multi-rotor aerocraft connects floatage air bag, can be more rotor flyings in use, full of the gas for being lighter than air inside floatage air bag
Device provides extra lift, extends the flight time of multi-rotor aerocraft, improves the flight load of multi-rotor aerocraft.And buoyancy
Air bag has cushioning effect, and injury of the collision to rotor craft itself loss and to personnel can be reduced in accident.Fill
Air valve is used to inflate and be vented to floatage air bag, without using when also allow for storing and carry.
Brief description of the drawings
Fig. 1 is multi-rotor aerocraft delay, synergy, the structure diagram for saving external member from damage in one embodiment of the invention；
Fig. 2 is the structure diagram that suspension mechanism is connected in Fig. 1 of the present invention；
Fig. 3 is the structure diagram of air pressure double-beat drop valve in Fig. 1 of the present invention；
Fig. 4 is the appearance schematic diagram of air pressure double-beat drop valve in Fig. 1 of the present invention.
Note：1st, floatage air bag；2nd, suspension mechanism is connected；3rd, air pressure double-beat drop valve；4th, charge valve, 5, air accumulator；10th, chamber；
21st, multi-rotor aerocraft connecting bracket；22nd, intermediate connecting ring；23rd, floatage air bag connection ring；24th, X-axis limit hinge；25th, Y-axis
Limit hinge；26th, X-axis；27th, Y-axis；31st, valve body；32nd, piston sheet；33rd, spring；34th, valve.
Embodiment
The present invention is described in further detail below by specific embodiment combination attached drawing.
The present invention provides a kind of multi-rotor aerocraft delay, synergy, save external member from damage, as shown in Figure 1, including：Buoyancy gas
Capsule 1, connection suspension mechanism 2 and multi-rotor aerocraft；Wherein, the centrally disposed vacancy section of floatage air bag 1, connects suspension mechanism 2
The vacancy section of floatage air bag 1 is arranged on, and floatage air bag 1 is connected on multi-rotor aerocraft.Floatage air bag 1 flies with more rotors
The association of row device is known as joint aircraft.The inside of floatage air bag 1 is provided full of the gas for being lighter than air for multi-rotor aerocraft
Extra lift.Floatage air bag 1 provides different magnitude of buoyancy according to the difference of appearance and size, but maximum buoyancy is less than more rotors
The flight full weight of aircraft.Due to the lift-rising effect of buoyancy, in the case that multi-rotor aerocraft carries same load, required is defeated
Going out power can accordingly reduce.In the case where not changing original dynamical system and deposit gross energy, multi-rotor aerocraft will obtain
Longer flight time and voyage.Under similarity condition, in the case where exporting original power, combine the payload meeting of aircraft
Corresponding increase.Floatage air bag 1 also has the function that buffering energy-absorbing.When accident occurs for multi-rotor aerocraft, floatage air bag 1 can be with
Protect multi-rotor aerocraft in itself, significantly reduce infringement of the intense impact to fuselage and equipment.At the same time, floatage air bag 1
Buffering energy-absorbing function the guarantee of essence also is played to the security of the lives and property of the public.For beginner, defencive function
It is most important, air crash risk can be greatly reduced, avoids larger damage.
Connection suspension mechanism 2 is the bindiny mechanism of multi-rotor aerocraft and floatage air bag 1.As shown in Fig. 2, the mechanism will float
The buoyancy that strength capsule 1 produces passes to multi-rotor aerocraft.Connection suspension mechanism 2 is made of three concentric circular ring structures.Most
Internal layer is multi-rotor aerocraft connecting bracket 21, and intermediate layer is intermediate connecting ring 22, and outermost layer is floatage air bag connection ring 23.It is more
Rotor craft connecting bracket 21 is rigidly connected with multi-rotor aerocraft.Floatage air bag connection ring 23 connects with the rigidity of floatage air bag 1
Connect.Multi-rotor aerocraft connecting bracket 21 is connected with intermediate connecting ring 22 by two coaxial X-axis limit hinges 24, the above two
Ring can be relatively rotated around X-axis 26 in certain angle.Intermediate connecting ring 22 is coaxial by two with floatage air bag connection ring 23
Y-axis limit hinge 25 connect, two ring of the above can be relatively rotated around Y-axis 27 in certain angle.24 center of X-axis limit hinge
Axis and 25 orthogonality of center shaft of Y-axis limit hinge.Multi-rotor aerocraft and floatage air bag 1 are connected using connection suspension mechanism 2, so that it may
To realize the limited change of multi-rotor aerocraft and 1 relative attitude of floatage air bag, such as using X-axis as rotation axis, or using Y-axis as rotation
The relative rotation of shaft.
Floatage air bag 1 is with respect to the multi-rotor aerocraft axis rotary limited centered on X-axis 26, Y-axis 27, and X-axis is spacing respectively
The central shaft of hinge 24 and the orthogonality of center shaft of Y-axis limit hinge 25, by varying floatage air bag connection ring 23 and floatage air bag 1
Between link position, it is possible to realize to relative position between 1 buoyancy point of floatage air bag and multi-rotor aerocraft center of gravity
Adjusting.Connect suspension mechanism 2 and keep the buoyancy point of floatage air bag 1 close to the center of gravity of multi-rotor aerocraft.Connection suspension
Mechanism 2 allows multi-rotor aerocraft to change relative attitude within the specific limits, in the case of not change of flight control method, drop
The energy that low control joint aircraft is paid.
Charge valve 4 is provided with the outer surface of floatage air bag 1, user will be lighter than the gas (ratio of air using air accumulator 5
Such as：Hydrogen, helium etc.) poured into by charge valve 4 in floatage air bag 1, floatage air bag 1 is expanded acquisition buoyancy.Work as use
When finishing, user can open charge valve 4 and discharge gas.Empty flat floatage air bag 1 and connection suspension mechanism 2 can fold,
It is easy to carry and transport, it is easy to match with multi-rotor aerocraft.
, to its resistance, floatage air bag 1 is set in the present embodiment to reduce air under 1 floating state of floatage air bag
For circular airbag structure.
As shown in Figure 1, floatage air bag 1 is made of one or more chambers 10, connection is set between two neighboring chamber 10
Air flue, connects and air pressure double-beat drop valve 3 is set on air flue, and air pressure double-beat drop valve 3 is multiple 10 air pressures of chamber in the inside of neutral buoyancy air bag 1
Regulating device, to improve the reliability of floatage air bag 1 and adapt to the carrying of a variety of more rotors.As shown in Figure 3,4, air pressure
Balanced valve 3 is made of the spring 33 of valve body 31, piston sheet 32 and two supporting piston pieces 32.Piston sheet 32 passes through two springs
33 are connected with valve body 31, can be moved left and right in 31 inner cavity of valve body, so as to open or close valve 34.When passing through valve body 31
When air velocity is unhappy, piston sheet 32 is in the centre position of 31 inner cavity of valve body under two supports for compressing spring 33, at this time
The gas of the left and right sides is connected, and both sides air pressure is basically identical.When gas flow rate is very fast, aerodynamic force makes piston sheet 32 to side
Movement, and then close valve 34.
When connecting two neighboring chamber 10 in floatage air bag 1 using air pressure double-beat drop valve 3, if what air pressure double-beat drop valve 3 connected
Two chambers 10 are intact, and the energy Shi Liang of air pressure double-beat drop valve 3 side cavities 10 connect, and play the role of equilibrium air pressure；If one of chamber
Breakage occurs for room 10, and air pressure declines rapidly, has high-speed flow by air pressure double-beat drop valve 3, compresses spring under Aerodynamic force action
33 close valve 34.The intact side cavity 10 of 3 self-closed of air pressure double-beat drop valve, plays a protective role, can greatly improve floating
The reliability of strength capsule 1.The shape of chamber 10 is specifically set according to the structure of the multi-rotor aerocraft connected.
There is provided different sizes and appearance seriation repacking external member design, can adapt to different users ' individualized requirements,
Meet diversified job task and a variety of meteorological condition requirements.
The foregoing is only a preferred embodiment of the present invention, is not intended to limit the invention, for the skill of this area
For art personnel, the invention may be variously modified and varied.Within the spirit and principles of the invention, that is made any repaiies
Change, equivalent substitution, improvement etc., should all be included in the protection scope of the present invention.
Claims (5)
1. a kind of multi-rotor aerocraft delay, synergy, save external member from damage, it is characterised in that including：Floatage air bag (1), connection suspension
Mechanism (2) and multi-rotor aerocraft；Wherein, the centrally disposed vacancy section of the floatage air bag (1), the connection suspension mechanism
(2) vacancy section of the floatage air bag (1) is arranged on, and the floatage air bag (1) is connected to multi-rotor aerocraft；It is described floating
The relatively described multi-rotor aerocraft of strength capsule (1) the axis rotary limited centered on X-axis, Y-axis respectively；The floatage air bag (1)
Outer surface is provided with more than one charge valve (4)；
The connection suspension mechanism (2) includes：Multi-rotor aerocraft connecting bracket (21) rigidly connected with multi-rotor aerocraft,
Floatage air bag connection ring (23) rigidly connected with the floatage air bag (1), and it is connected to the multi-rotor aerocraft connection
Intermediate connecting ring (22) between stent (21) and the floatage air bag (1) connection ring；The multi-rotor aerocraft connecting bracket
(21), the floatage air bag connection ring (23) and the intermediate connecting ring (22) three are set for concentric ring-type；
It is spacing by two coaxial X-axis between the multi-rotor aerocraft connecting bracket (21) and the intermediate connecting ring (22)
Hinge (24) connects；The intermediate connecting ring (22) is spacing by two coaxial Y-axis with the floatage air bag connection ring (23)
Hinge (25) connects；The central shaft of the X-axis limit hinge (24) and the orthogonality of center shaft of the Y-axis limit hinge (25)；
The floatage air bag (1) and the connection suspension mechanism (2) after exhaust are in folded state.
2. multi-rotor aerocraft delay as claimed in claim 1, synergy, save external member from damage, it is characterised in that the floatage air bag
(1) it is circular airbag structure.
3. such as the delay of claim 1-2 any one of them multi-rotor aerocraft, synergy, save external member from damage, it is characterised in that described
Floatage air bag (1) is made of one or more chambers (10).
4. multi-rotor aerocraft delay as claimed in claim 3, synergy, save external member from damage, it is characterised in that two neighboring described
Air pressure double-beat drop valve (3) is set on the connection air flue between chamber.
5. multi-rotor aerocraft delay as claimed in claim 4, synergy, save external member from damage, it is characterised in that each chamber
(10) most one charge valves (4) are both provided with.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610413020.0A CN105966592B (en) | 2016-06-13 | 2016-06-13 | A kind of multi-rotor aerocraft delay, synergy, save external member from damage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610413020.0A CN105966592B (en) | 2016-06-13 | 2016-06-13 | A kind of multi-rotor aerocraft delay, synergy, save external member from damage |
Publications (2)
| Publication Number | Publication Date |
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| CN105966592A CN105966592A (en) | 2016-09-28 |
| CN105966592B true CN105966592B (en) | 2018-05-01 |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107416199A (en) * | 2017-03-29 | 2017-12-01 | 北京华信智航科技有限公司 | A kind of small-sized anticollision multi-rotor unmanned aerial vehicle |
| CN107226192B (en) * | 2017-05-28 | 2020-10-23 | 珠海磐磊智能科技有限公司 | Composite board and aircraft |
| CN107226201B (en) * | 2017-05-28 | 2020-03-31 | 珠海磐磊智能科技有限公司 | Aircraft with a flight control device |
| CN110155306A (en) * | 2019-07-05 | 2019-08-23 | 徐更修 | Multi-rotor unmanned aerial vehicle with floating air-bag |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3083934A (en) * | 1961-10-12 | 1963-04-02 | Edward G Vanderlip | Rotary wing aircraft |
| CN2341893Y (en) * | 1998-07-24 | 1999-10-06 | 李春 | Small helicopter with light gas storage sac |
| DE10023269A1 (en) * | 2000-05-12 | 2001-11-29 | Josef Sykora | Aircraft with circular basic contour has lift component constructed as tubular tire with gondola located in middle symmetrical to tire and connected to it by retaining arms, and helicopter engine on upper side of cabin |
| CN103274045A (en) * | 2013-05-10 | 2013-09-04 | 华南农业大学 | Duct airship helicopter |
| CN205675213U (en) * | 2016-06-13 | 2016-11-09 | 北京瀚科瑞杰科技发展有限公司 | A kind of multi-rotor aerocraft time delay, synergy, save external member from damage |
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Address after: 100089 No. 167, 2nd floor of main building No. 6-9, No. 59 Banjing Road, Haidian District, Beijing Patentee after: Beijing Hanke Technology Group Co., Ltd. Address before: 100190 4A82B, 4th floor, Zhongguancun Science and Trade Electronic City, 18 Zhongguancun Street, Haidian District, Beijing Patentee before: Beijing Hanke Technology Group Co., Ltd. |
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| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20210419 Address after: 100190 No. 402, 901 / F, Zhongguancun, Haidian District, Beijing Patentee after: Chu Ruizhong Address before: 100089 No. 167, 2nd floor of main building No. 6-9, No. 59 Banjing Road, Haidian District, Beijing Patentee before: Beijing Hanke Technology Group Co.,Ltd. |