CN105966592A - Delay, efficiency-increasing and protection kit of multi-rotor aircraft - Google Patents
Delay, efficiency-increasing and protection kit of multi-rotor aircraft Download PDFInfo
- Publication number
- CN105966592A CN105966592A CN201610413020.0A CN201610413020A CN105966592A CN 105966592 A CN105966592 A CN 105966592A CN 201610413020 A CN201610413020 A CN 201610413020A CN 105966592 A CN105966592 A CN 105966592A
- Authority
- CN
- China
- Prior art keywords
- air bag
- rotor aerocraft
- floatage air
- potentiation
- damage
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
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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; ARRANGEMENTS 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
Abstract
The invention relates to the technical field of unmanned aerial vehicles, in particular to a delay, efficiency-increasing and protection kit of a multi-rotor aircraft. The delay, efficiency-increasing and protection kit of the multi-rotor aircraft comprises a buoyancy airbag (1), a connection hanging mechanism (2) and the multi-rotor aircraft, wherein a hollowed-out area is arranged at the center of the buoyancy airbag (1), the connection hanging mechanism (2) is arranged at the hollowed-out area of the buoyancy airbag (1) and connects the buoyancy airbag (1) to the multi-rotor aircraft; the buoyancy airbag (1) performs limit rotation relative to the multi-rotor aircraft by taking the shaft X and the shaft Y as the center shafts, and the center shaft of an X-shaft limit hinge (24) is orthogonal to the center shaft of a Y-shaft limit hinge (25); more than one inflation valve (4) is arranged on the outer surface of the buoyancy airbag (1). The delay, efficiency-increasing and protection kit of the multi-rotor aircraft can prolong the flight time of the multi-rotor aircraft, improves the payload, and protects the multi-rotor aircraft per se and the public.
Description
Technical field
The present invention relates to unmanned air vehicle technique field, in particular to a kind of multi-rotor aerocraft time delay, increasing
Imitate, save external member from damage.
Background technology
Multi-rotor aerocraft is a class multipurpose vertically taking off and landing flyer.Compared with tradition single-rotor helicopter,
Multi-rotor aerocraft do not have complexity pitch-changing mechanism, maintenance simplicity, easy to use efficiently.At present, many
The application of rotor craft covered agriculture, woods, herd, fishing, industry, building, scientific research, traffic, joy
Multiple industries such as pleasure.Can perform aeroplane photography, medical aid, meteorological detection, aerial inspection, aircraft are broadcast
The tasks such as kind, aerial fertilising, play very important effect in national economy.
Multi-rotor aerocraft is frequently with driven by power, and by the restriction that energy content of battery storage density is low, it flies
Row time and voyage can not meet far away the urgent needs that social development is applied to.In the last few years, existing portion
Divide enterprise by fuel cells applications on multi-rotor aerocraft so that it is the flight time is by using common lithium-ion electricity
Within about 20 minutes of pond, rise to about about one hour.But fuel cell technology is the most immature, make
With with high costs, temporarily cannot large-scale promotion on consumer level multi-rotor aerocraft.How in prior art
On the basis of, in the case of not changing original power set, the significantly prolongation multi-rotor aerocraft of low cost
Flight time, increase payload become one demand the most urgent of the art.
The safety of aircraft platforms and job stabilization are also non-in current multi-rotor aerocraft technical field
The problem of the normally off note.Multi-rotor aerocraft uses multiple rotor high speed rotating produce lift and control power, once
Breaking down, the rotor blade of high speed rotating and the fuselage of high-speed motion can be to periphery objects with self cause sternly
The harm of weight.There is the security of the lives and property of the notably entail dangers to public.In this technical field, engineers is made
Certain effort, have employed rotor redundancy, the control method such as failure compensation.But, can not be at physics
The fuselage of the rotor blade and high-speed motion that solve high speed rotating in aspect carries kinetic energy parts to periphery object
The harm caused with self.Some multi-rotor aerocraft is equipped with the mechanism such as crash-proof bracket and parachute, is flying
Machine can reduce to a certain extent to periphery object and the injury of self when losing efficacy, but both the above mechanism is reliable
Property is the highest, and can reduce multi-rotor aerocraft payload.
Summary of the invention
It is an object of the invention to provide a kind of multi-rotor aerocraft time delay, potentiation, save external member from damage, it is possible to prolong
The flight time of long multi-rotor aerocraft, improve payload, and multi-rotor aerocraft itself and the public are risen
To protective effect.
Embodiments provide a kind of multi-rotor aerocraft time delay, potentiation, save external member from damage, including: floating
Strength capsule, connection hitch and multi-rotor aerocraft；Wherein, the centrally disposed hollow out of described floatage air bag
District, described connection hitch is arranged on the vacancy section of described floatage air bag, and is connected by described floatage air bag
To multi-rotor aerocraft；During the most described multi-rotor aerocraft of described floatage air bag with X-axis, Y-axis is respectively
The central shaft of mandrel rotary limited, the central shaft of described X-axis limit hinge and described Y-axis limit hinge is just
Hand over；The outer surface of described floatage air bag is provided with more than one charge valve.
In certain embodiments, being preferably, the described suspension framework that connects includes: with multi-rotor aerocraft rigidity
The multi-rotor aerocraft connected connects support, and floatage air bag rigidly connected with described floatage air bag is connected ring,
And be connected to described multi-rotor aerocraft and connect the centre that is connected between ring with described floatage air bag of support and connect
T-Ring；Described multi-rotor aerocraft connects support, described floatage air bag connects ring and described intermediate connecting ring
Three is concentric ring-type setting.Described multi-rotor aerocraft connects between support and described intermediate connecting ring logical
Cross two coaxial X-axis limit hinges to connect；Described intermediate connecting ring is connected ring with described floatage air bag to be passed through
Two coaxial Y-axis limit hinges that have connect；The central shaft of described X-axis limit hinge and described Y-axis
The orthogonality of center shaft of limit hinge.Described floatage air bag and described connection hitch after aerofluxus are rugosity
State.Described floatage air bag is the airbag structure of circular ring.Described floatage air bag is by one or more chambers
Composition.On connection air flue between adjacent two described chambers, air pressure double-beat drop valve is set.Each described chamber is equal
It is provided with a most described charge valve.
The embodiment of the present invention provide a kind of multi-rotor aerocraft time delay, potentiation, save external member from damage, with existing skill
Art is compared, and multi-rotor aerocraft connects floatage air bag, and in using, internal being full of of floatage air bag is lighter than air
Gas, can provide extra lift for multi-rotor aerocraft, extend the flight time of multi-rotor aerocraft, carry
The flight load of high multi-rotor aerocraft.And floatage air bag has cushioning effect, it is possible to reduce when accident and touch
Hit rotor craft self loss and the injury to personnel.Charge valve is for floatage air bag inflation and row
Gas, also allows for depositing and carrying not using when.
Accompanying drawing explanation
Fig. 1 is that multi-rotor aerocraft time delay in one embodiment of the invention, potentiation, the structure of saving external member from damage are shown
It is intended to；
Fig. 2 is the structural representation connecting hitch in Fig. 1 of the present invention；
Fig. 3 is the structural representation 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: 1, floatage air bag；2, hitch is connected；3, air pressure double-beat drop valve；4, charge valve, 5,
Air accumulator；10, chamber；21, multi-rotor aerocraft connects support；22, intermediate connecting ring；23, buoyancy
Air bag connects ring；24, X-axis limit hinge；25, Y-axis limit hinge；26, X-axis；27, Y-axis；
31, valve body；32, piston sheet；33, spring；34, valve
Detailed description of the invention
Combine accompanying drawing below by specific embodiment the present invention is described in further detail.
The invention provides a kind of multi-rotor aerocraft time delay, potentiation, save external member from damage, as it is shown in figure 1, bag
Include: floatage air bag 1, connection hitch 2 and multi-rotor aerocraft；Wherein, the center of floatage air bag 1 sets
Put vacancy section, connect hitch 2 and be arranged on the vacancy section of floatage air bag 1, and floatage air bag 1 is connected to
On multi-rotor aerocraft.Floatage air bag 1 is referred to as associating aircraft with the association of multi-rotor aerocraft.Buoyancy
Air bag 1 is internal is full of the gas being lighter than air, provides extra lift for multi-rotor aerocraft.Floatage air bag 1
There is provided different magnitude of buoyancy according to the difference of overall dimensions, but maximum buoyancy is less than flying of multi-rotor aerocraft
Row full weight.Due to the lift-rising effect of buoyancy, in the case of multi-rotor aerocraft carries same load, required
Output can reduce accordingly.In the case of not changing original dynamical system and deposit gross energy, many rotors
Aircraft will obtain longer flight time and voyage.Under similarity condition, in the case of exporting original power,
The payload of associating aircraft can increase accordingly.Floatage air bag 1 also has the effect of buffering energy-absorbing.Many
When rotor craft occurs unexpected, floatage air bag 1 can be protected multi-rotor aerocraft itself, significantly reduce
Intense impact is to fuselage and the infringement of equipment.Meanwhile, the buffering energy-absorbing function of floatage air bag 1 is also to public affairs
Many securities of the lives and property play the guarantee of essence.For abecedarian, defencive function is most important,
Air crash risk can be reduced greatly, it is to avoid bigger damage.
Connect the bindiny mechanism that hitch 2 is multi-rotor aerocraft and floatage air bag 1.As in figure 2 it is shown, should
The buoyancy that floatage air bag 1 produces is passed to multi-rotor aerocraft by mechanism.Connect hitch 2 by three with one heart
Circular ring structure constitute.Innermost layer is that multi-rotor aerocraft connects support 21, and intermediate layer is intermediate connecting ring 22,
Outermost layer is that floatage air bag connects ring 23.Multi-rotor aerocraft connects support 21 with multi-rotor aerocraft rigidity even
Connect.Floatage air bag connects ring 23 and is rigidly connected with floatage air bag 1.Multi-rotor aerocraft connect support 21 with in
Between connect ring 22 and connected by two coaxial X-axis limit hinges 24, above two rings can be around X-axis 26 one
Relatively rotate in determining angle.Intermediate connecting ring 22 is connected ring 23 and is limited by two coaxial Y-axis with floatage air bag
Position hinge 25 connects, and above two rings can relatively rotate in certain angle around Y-axis 27.X-axis limit hinge
24 central shafts and Y-axis limit hinge 25 orthogonality of center shaft.Connection hitch 2 is used to connect multi-rotor aerocraft
With floatage air bag 1, it is possible to realize the limited change of multi-rotor aerocraft and floatage air bag 1 relative attitude, than
As with X-axis as rotary shaft, or relatively rotating with Y-axis as rotary shaft.
The relative multi-rotor aerocraft of floatage air bag 1 axle rotary limited centered by X-axis 26, Y-axis 27 respectively, and
The central shaft of X-axis limit hinge 24 and the orthogonality of center shaft of Y-axis limit hinge 25, by changing floatage air bag
Connect the link position between ring 23 and floatage air bag 1, it is possible to realize to floatage air bag 1 buoyancy point with
Relative to the regulation of position between multi-rotor aerocraft center of gravity.Connect hitch 2 and keep the buoyancy of floatage air bag 1
Application point is close to the center of gravity of multi-rotor aerocraft.Connecting hitch 2 allows multi-rotor aerocraft at certain model
Enclose interior change relative attitude, in the case of not change of flight control method, reduce control associating aircraft and pay
The energy gone out.
Being provided with charge valve 4 on the outer surface of floatage air bag 1, user uses air accumulator 5 will be lighter than the gas of air
Body (such as: hydrogen, helium etc.) is poured in floatage air bag 1 by charge valve 4, makes floatage air bag 1 expand
Get up to obtain buoyancy.When using complete, user can open charge valve 4 and be discharged by gas.Empty flat floating
Strength capsule 1 and connection hitch 2 can fold, it is simple to carry and transport, it is easy to join with multi-rotor aerocraft
Set uses.
In order to reduce the air resistance to it under floatage air bag 1 floating state, in the present embodiment by buoyancy gas
Capsule 1 is set to circular airbag structure.
As it is shown in figure 1, floatage air bag 1 is made up of one or more chambers 10, set between adjacent two chambers 10
Put connection air flue, connection air flue arranges air pressure double-beat drop valve 3, in air pressure double-beat drop valve 3 is neutral buoyancy air bag 1
The adjusting means of portion's multiple chamber 10 air pressure, to improve the reliability of floatage air bag 1 and to adapt to various different
The lift-launch of many rotors.As shown in Figure 3,4, air pressure double-beat drop valve 3 is propped up by valve body 31, piston sheet 32 and two
The spring 33 holding piston sheet 32 is constituted.Piston sheet 32 is connected with valve body 31 by two springs 33, can be at valve
Body 31 inner chamber moves left and right, thus opens or closes valve 34.When unhappy by the air velocity of valve body 31
Time, piston sheet 32 is in the centre position of valve body 31 inner chamber under the support of two compression springs 33, now left
The gas of right both sides is connected, and both sides air pressure is basically identical.When gas flow rate is very fast, aerodynamic force makes piston
Sheet 32 is to a lateral movement, and then closes valve 34.
In using air pressure double-beat drop valve 3 to connect floatage air bag 1 during adjacent two chambers 10, if air pressure double-beat drop valve 3
Two chambers 10 of connection are intact, and air pressure double-beat drop valve 3 Neng Shiliang side cavity 10 connects, and play equilibrium air pressure and make
With；If one of them chamber 10 occurs breakage, air pressure to decline rapidly, have high velocity air and put down by air pressure
Weighing apparatus valve 3, under Aerodynamic force action, compression spring 33 makes valve 34 close.Air pressure double-beat drop valve 3 self-closed is intact
One side cavity 10, plays a protective role, and the reliability of floatage air bag 1 can be greatly improved.The shape of chamber 10
Shape is specifically arranged according to the structure of the multi-rotor aerocraft connected.
There is provided the seriation repacking external member design of different size and outward appearance, it is possible to adapt to different user personalities
Change demand, satisfied variation job task and multiple meteorological condition use requirement.
The foregoing is only the preferred embodiments of the present invention, be not limited to the present invention, for ability
For the technical staff in territory, the present invention can have various modifications and variations.All in the spirit and principles in the present invention
Within, any modification, equivalent substitution and improvement etc. made, should be included in protection scope of the present invention it
In.
Claims (8)
1. a multi-rotor aerocraft time delay, potentiation, save external member from damage, it is characterised in that including: buoyancy
Air bag (1), connection hitch (2) and multi-rotor aerocraft；Wherein, the center of described floatage air bag (1) sets
Putting vacancy section, described connection hitch (2) is arranged on the vacancy section of described floatage air bag (1), and by described
Floatage air bag (1) is connected to multi-rotor aerocraft；Described floatage air bag (1) the most described multi-rotor aerocraft divides
Not axle rotary limited centered by X-axis, Y-axis, the central shaft of described X-axis limit hinge (24) and described Y
The orthogonality of center shaft of axle limit hinge (25)；The outer surface of described floatage air bag (1) is provided with more than one filling
Air valve (4).
2. as claimed in claim 1 multi-rotor aerocraft time delay, potentiation, saving external member from damage, its feature exists
In, described connection hitch (2) including: multi-rotor aerocraft rigidly connected with multi-rotor aerocraft
Connect support (21), be connected ring (23), Yi Jilian with described floatage air bag (1) rigidly connected floatage air bag
It is connected on described multi-rotor aerocraft to connect support (21) centre that is connected between ring with described floatage air bag (1) and connect
T-Ring (22)；Described multi-rotor aerocraft connect support (21), described floatage air bag connect ring (23) and
Described intermediate connecting ring (22) three is concentric ring-type setting.
3. as claimed in claim 2 multi-rotor aerocraft time delay, potentiation, saving external member from damage, its feature exists
In, described multi-rotor aerocraft connects between support (21) and described intermediate connecting ring (22) coaxial by two
X-axis limit hinge (24) connect；Described intermediate connecting ring (22) is connected ring (23) with described floatage air bag
Connected by two coaxial Y-axis limit hinges (25)；The central shaft of described X-axis limit hinge (24) with
The orthogonality of center shaft of described Y-axis limit hinge (25).
4. as claimed in claim 1 multi-rotor aerocraft time delay, potentiation, saving external member from damage, its feature exists
In, described floatage air bag (1) after aerofluxus and described connection hitch (2) are in folded state.
5. as claimed in claim 1 multi-rotor aerocraft time delay, potentiation, saving external member from damage, its feature exists
In, described floatage air bag (1) is circular airbag structure.
6. multi-rotor aerocraft time delay, potentiation as described in any one of claim 1-5, save external member from damage,
It is characterized in that, described floatage air bag (1) is made up of one or more chambers (10).
7. as claimed in claim 6 multi-rotor aerocraft time delay, potentiation, saving external member from damage, its feature exists
In, the connection air flue between adjacent two described chambers arranges air pressure double-beat drop valve (3).
8. as claimed in claim 6 multi-rotor aerocraft time delay, potentiation, saving external member from damage, its feature exists
In, each described chamber (10) is provided with a most described charge valve (4).
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 |
|---|---|
| CN105966592A true CN105966592A (en) | 2016-09-28 |
| CN105966592B CN105966592B (en) | 2018-05-01 |
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| CN201610413020.0A Active CN105966592B (en) | 2016-06-13 | 2016-06-13 | A kind of multi-rotor aerocraft delay, synergy, save external member from damage |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107226201A (en) * | 2017-05-28 | 2017-10-03 | 珠海磐磊智能科技有限公司 | Aircraft |
| CN107226192A (en) * | 2017-05-28 | 2017-10-03 | 珠海磐磊智能科技有限公司 | A kind of composite board and aircraft |
| 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 |
| CN110155306A (en) * | 2019-07-05 | 2019-08-23 | 徐更修 | Multi-rotor unmanned aerial vehicle with floating air-bag |
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| 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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| 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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| 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 |
| CN107226201A (en) * | 2017-05-28 | 2017-10-03 | 珠海磐磊智能科技有限公司 | Aircraft |
| CN107226192A (en) * | 2017-05-28 | 2017-10-03 | 珠海磐磊智能科技有限公司 | A kind of 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 |
| CN107226192B (en) * | 2017-05-28 | 2020-10-23 | 珠海磐磊智能科技有限公司 | Composite board and aircraft |
| CN110155306A (en) * | 2019-07-05 | 2019-08-23 | 徐更修 | Multi-rotor unmanned aerial vehicle with floating air-bag |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105966592B (en) | 2018-05-01 |
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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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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. |
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