CN205524959U - Fuel cell unmanned aerial vehicle - Google Patents
Fuel cell unmanned aerial vehicle Download PDFInfo
- Publication number
- CN205524959U CN205524959U CN201620201807.6U CN201620201807U CN205524959U CN 205524959 U CN205524959 U CN 205524959U CN 201620201807 U CN201620201807 U CN 201620201807U CN 205524959 U CN205524959 U CN 205524959U
- Authority
- CN
- China
- Prior art keywords
- fuel cell
- unmanned plane
- cell system
- propeller
- flight
- 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
Classifications
-
- 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
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02T90/40—Application of hydrogen technology to transportation, e.g. using fuel cells
Abstract
The utility model relates to a fuel cell unmanned aerial vehicle, including fuel cell system, flight promotion component, control mechanism, wherein, fuel cell system provides power for fuel cell unmanned aerial vehicle to make via control mechanism thereby flight promotes the screw rotation of component and flies, and this fuel cell system arranges in the screw below to make the screw do fuel cell system provides it in order to realize the required amount of wind of flight to the wind -force that produces with the help of the screw comes the heat dissipation for fuel cell system. With the help of the utility model discloses a fuel cell unmanned aerial vehicle, wind -force that accessible unmanned aerial vehicle's screw produced are the air mass flow and the pressure of fuel cell supply needs, also can provide abundant heat dissipation function for the fuel cell system to make fuel cell at allowable temperature within range reliability service.
Description
Technical field
This utility model relates to fuel cell unmanned plane field, particularly relate to a kind of simple in construction, lightweight,
Many rotors, there is the fuel cell unmanned plane of long continual mileage.
Background technology
Unmanned plane, i.e. UAV (Unmanned aerial vehicle, abridge UAV) are to utilize
The most manned aircraft that radio robot and the presetting apparatus provided for oneself are handled.Unmanned plane is actually nothing
People drives the general designation of aircraft, from technical standpoint definition can be divided into: depopulated helicopter, unmanned fixed-wing aircraft,
Unmanned multi-rotor aerocraft, unmanned airship and unmanned parasol etc..The feature of unmanned plane is without driving cabin on machine,
But the equipment such as automatic pilot, presetting apparatus is installed.On ground, naval vessels or machine tool remote control station personnel
By equipment such as radars, it be tracked, position, remote control, remote measurement and Digital Transmission.
In all kinds of unmanned plane, many rotary wind types unmanned plane is excellent owing to its manipulation is simple, reliability is high etc.
Point the most progressively becomes the mainstream type of Small and micro-satellite or model plane.But, in the continuation of the journey of many rotor wing unmanned aerial vehicles
Journey is always the weakness of its designs.Such as, the generally boat of the many rotor wing unmanned aerial vehicles with lithium battery as power
Time deficiency half an hour, thus can not effectively carry out over the horizon flight, especially be difficult to overcome mountain region, waters etc. multiple
Miscellaneous landform, therefore cannot complete the aerial mission that specialty is complicated.
At present it is known that use fuel cell to be used as the dynamic origin of unmanned plane.In general, fuel electricity
Pond comprises two electrodes of negative and positive, is then constituted by having infiltrative thin film between two electrodes.Hydrogen is by fuel
The anode of battery enters, and oxygen (or air) is then entered fuel cell by negative electrode.Via the effect of catalyst,
The hydrogen molecule making anode resolves into two protons and two electronics, and wherein proton is attracted to the another of thin film by oxygen
On one side, after electronics then forms electric current via external circuit, arrive negative electrode.Under the effect of cathod catalyst, matter
Son, oxygen and electronics, react formation hydrone.Therefore, fuel cell system have energy density high,
The advantage such as low noise and zero-emission, is applied to unmanned plane field in recent years, so that the driving of unmanned plane
Mileage has considerable lifting, and can realize the zero-emission of carbon in running.
Such as, research and development manufacture aerospace industry company of Israel (IAI) and Britain's hydrogen energy source of UAS
Cella Energy company of advanced new material enterprise attempts utilizing the solid hydrogen-fueled system technology of Cella company be
A " bird's eye " MAV under IAI develops a kind of fuel cell powered system.Cella company will
Hydrogen Technology instead of existing lithium polymer battery, is used as the energy source of MAV system.
The hydrogen storage material of Cella research and development can discharge when being heated to more than 100 degrees Celsius in several minutes.Every gram of material
The safe capacity of material corresponds approximately to the Gaseous Hydrogen of a liter.This " bird's eye " unmanned plane is surveyed by fuel cell
Examination makes flying power be promoted to 6 hours from 2 hours.
The most such as, market there is also at present made by Horizon Unmanned Systems company
Hycopter unmanned plane net weight about 5kg, it uses lithium battery and fuel cell as hybrid power.Hycopter
Unmanned plane is flight four hours as long as when without bearing a heavy burden, and endurance is eight to the ten of machine the most at the same level
Times, the flight load carrying 1kg realizes the flight time of 2.5 hours.
But, in order to increase course continuation mileage further, say from the angle of Flight Vehicle Design, reduce whole unmanned
The construction weight of machine is the target pursued all the time.Therefore, yet suffer from industry for fuel cell unmanned plane
The demand of weight reduction.
Utility model content
The most existing fuel cell unmanned plane uses the heat abstractor being exclusively used in fuel cell module
It is dispelled the heat so that operation of fuel cells its be suitable for operating temperature range in (such as, for
40 DEG C-60 DEG C).This heat abstractor typically cost dispelling the heat fuel cell module is the lowest and takies
Weight and volume relatively big, this runs in the opposite direction with the purpose of lightweight unmanned plane structure.
To this end, this utility model solves the problems referred to above by following a kind of fuel cell unmanned plane, this fuel
Battery unmanned plane, including fuel cell system, flight lifting member, controlling organization, wherein, fuel cell
System provides power for fuel cell unmanned plane, to make the spiral of described flight lifting member via controlling organization
Oar rotates thus flies, and this fuel cell system is arranged in below propeller, so that propeller is institute
State fuel cell system provide its in order to realize the required air quantity that flies, and by propeller produce wind-force
To dispel the heat for fuel cell system.
It is preferred that flight lifting member is by a bearing supporting of hollow tubular, fuel cell system is contained in and props up
In bearing, within being located immediately at the wind-force zone of action of described propeller.
Especially, this fuel cell unmanned plane also includes master controller, and this master controller is constructed to be permeable to calculate institute
Air quantity and the flight lifting member of stating fuel cell unmanned plane needs can be carried by the rotation of its propeller
The air quantity of confession.
Block as described controlling organization further, it is also possible to there also is provided control in a bearing, this control card
Input is the DC current supplied by fuel cell system, and its electricity being output as being supplied to flight lifting member
Stream.
Particularly, a bearing vertically extends, and the machine of the horizontal expansion with fuel cell unmanned plane
Arm is connected.
It is preferred that fuel cell system is vertically arranged in the underface of propeller.
This fuel cell system can also be arranged relative to described propeller tilt, to reduce described flight lifting
The air quantity that component provides to described fuel cell system.
Alternatively, the arranged beneath of the only a part propeller in multiple propellers has described fuel cell system
System, to reduce the air quantity that described flight lifting member provides to fuel cell system.
Accompanying drawing explanation
Fig. 1 schematically shows the structure chart of a kind of exemplary many rotors fuel cell unmanned plane；
Fig. 2 illustrates the topological structure of conventional fuel cell unmanned plane；And
Fig. 3 schematically shows the schematic configuration diagram according to fuel cell unmanned plane of the present utility model.
Detailed description of the invention
With reference to Fig. 1, many rotors fuel cell unmanned plane can include that fuel cell system 1, frame 2, flight carry
Rise component 3, controlling organization 4 etc..
Described frame 2 includes along its outwardly directed multiple, for example, four horns 30, these horns 30
Arrange at substantially equal intervals around frame 2, to guarantee the stability of unmanned plane during flying.Each horn is by first
Horn element 31 and the second horn element 33 are constituted.The root away from frame 2 at the first horn element 31
Folded piece it is provided with, to be connected with the second horn element 33 at portion.
It is understood, however, that the connection between the first horn element and the second horn element is not limited by folding
Overlapping piece, but can be realize both any known way of being stably connected with, the most hinged, be spirally connected.
The flight lifting member 3 of correspondence it is provided with in the end of each horn 30.Each flight lifting member
3 can such as include motor 41, propeller 43 and optional electron speed regulator.Motor 41 can control spiral shell
Rotation oar 43 rotates with different rotating speeds.
Controlling organization 4 is preferably provided the internal body in unmanned plane, to control unmanned plane during flying to specifying height
Spend and operate in high-altitude hovering etc..Such as, controlling organization 4 includes master controller 40, sensor, navigation system
System etc..
Generally, many rotor wing unmanned aerial vehicles are operated as follows: multiple sensor acquisition unmanned planes currently fly
Row attitude information is transferred to master controller, and master controller adjusts the output of electron speed regulator according to PID arithmetic,
And then adjustment motor 41 drives the moment of propeller 43, thus reach stable flight effect.
As power supply source, fuel cell system 1 is placed in frame 2 top of unmanned plane, thus is unmanned plane
Each mechanism such as master controller 40, sensor, motor and other auxiliary equipment are powered.As is known, combustion
Material battery system 1 is the TRT that the chemical energy being had by fuel directly becomes electric energy, wherein, advantageously
Use Proton Exchange Membrane Fuel Cells as the fuel cell for unmanned plane of the present utility model.Proton exchange
The startup of membrane cell is fast and running temperature is low.Proton Exchange Membrane Fuel Cells with hydrogen as fuel, and
Being supplied with air/oxygen, its product is unidirectional current and water.
Therefore, fuel cell system 1 one aspect connects with the hydrogen source 10 (such as, hydrogen bottle) of supply hydrogen,
The most also device with supply air (oxygen) is connected.Hydrogen source herein relates to provide hydrogen into unmanned plane
The feedway of gas.Generally, the hydrogen in hydrogen source be pressurized after compressed format.
As it is shown on figure 3, fuel cell system 1 is creatively placed directly under propeller by utility model people
Side's (hereinafter will be described in its position), thus one side utilizes the wind that the propeller of unmanned plane produces
Power is air mass flow and the pressure of fuel cell supply needs, on the other hand also can provide for fuel cell system
Sufficiently heat sinking function, so that fuel cell reliability service in allowed temperature range.
Fig. 2 illustrates the topological structure of conventional fuel cell unmanned plane, wherein, cloth near fuel cell system
It is equipped with heat abstractor.In contrast to this, in fuel cell unmanned plane of the present utility model, eliminate weight originally
Big and that cost is high heat abstractor (such as, radiator fan), thereby simplify the whole of fuel cell unmanned plane
Body structure.
In order to reach the purpose of the system structure of this fuel cell unmanned plane of actual simplification, fuel cell without
The difference of man-machine current operating conditions, can proceed as follows it or arrange:
In takeoff phase and the running status of fuel cell unmanned plane, on the one hand can be come by its master controller
Calculate (such as, borrowing for public attention pressure P1 and the gas flow m1 taken off of fuel cell unmanned plane needs
Help the characteristic curve being stored in this master controller, this characteristic curve can with the wind-force under the environment that takes off, air pressure,
Temperature etc. are correlated with).In other words, it can be deduced that under takeoff phase or operation phase, fuel cell unmanned plane needs
Want for the air quantity F (P1, m1) taken off.
On the other hand, at takeoff phase and normal operating phase, it is also possible to calculate fuel by master controller
The propeller (as illustrated four propellers in Fig. 1) of battery unmanned plane can be produced by its rotation
Public attention pressure P2 and flow m2, i.e. can draw the air quantity f (P2, m2) that propeller can provide.
Can if needing public attention pressure P1 taken off for unmanned plane and gas flow m1 to be more than propeller
Public attention pressure P2 provided and flow m2 (that is, P1 > P2, m1 > m2), then fuel cell is increased unmanned
Four arm propellers (such as, can be changed into six arm propellers or eight arm spirals by the number of the propeller arranged on machine
Oar), below each propeller, all arrange a fuel cell pack (fuel cell total amount keeps constant).Logical
Cross the sheet number reducing each fuel cell pack battery with reduction for the air quantity F taken off, from reaching F=f
Requirement.
May there is propeller number in the prior art more causes fuel cell system to need to provide at most
Power and the technology prejudice that also raises of the air quantity that thus needs.But, utility model of the present utility model
People notices, although the increase of propeller and power arm thereof can bring the overall weight of fuel cell unmanned plane really
The rising of amount, but also can reduce the load of the motor of propeller under same power simultaneously.
It practice, weight and merit must be followed during according to fuel cell unmanned aerial vehicle design of the present utility model
The coupling of rate binary, i.e. the most at least can be brought by this change in design due to the weight increase that change in design causes
The increase of power/power compensate.
Higher efficiency can be realized in low-load interval again due to the motor of propeller, so propeller
The increase of power arm system can realize lower power demand on the contrary and (namely require fuel cell system
Air quantity reduces), increase along with the increase of the number of propeller (power arm system) thus without there is F
Problem, be capable of the technique effect of F=f on the contrary, thus reach the purpose fully dispelled the heat.
Can if needing public attention pressure P1 taken off for unmanned plane and gas flow m1 to be less than propeller
Public attention pressure P2 provided and flow m2 (that is, P1 < P2, m1 < m2), then make fuel cell system
Orient relative to the angle of propeller and change, i.e. make fuel cell system relative to propeller by originally
(reduction acquisition angled with it is changed in substantially vertical position (to obtain the maximum quantity of wind of propeller)
The effective area of the air quantity of propeller).The change of this angle can be by the side using flight top rake to install
Formula or be disposed with dynamic controllable adjusting device and realize.
Alternatively, if needing public attention pressure P1 taken off for unmanned plane and gas flow m1 less than spiral shell
Revolve public attention pressure P2 and flow m2 that oar can provide, it is also possible in the propeller arranged beneath combustion of a part
Material battery system, such as, symmetry centered by the frame central about fuel cell unmanned plane of propeller
Position, and below remaining propeller, do not place fuel cell system, to reach to mate between F with f
Effect.
Such as, in one embodiment, fuel cell system can be split as 4 sub-fuel cells, and
And they are arranged in the lower section of four corresponding propellers of fuel cell unmanned plane, thus cancel radiation air
The application of fan.But it can also be envisaged that the number of sub-fuel cell is more or less than four, as long as propeller number
Corresponding therewith.
The most such as, fuel cell system can be split as many sub-cell of fuel cell of even number, and by them
It is arranged in a certain group of fuel cell unmanned plane or organizes the spiral of symmetry (centrosymmetry or axial symmetry) more
Below oar.
Fig. 3 schematically illustrates the knot of position near the propeller according to fuel cell unmanned plane of the present utility model
Structure side view, is shown as the flight lifting member 3 of unmanned plane the most enlargedly, this flight lifting member 3
Including propeller, motor and optional electron speed regulator, wherein, supply unidirectional current DC to motor, with
Propeller is driven to rotate with desired speed.
Flight lifting member 3 is supported, such as at middle position or the motor of propeller by a bearing 50
Place.Bearing 50 is general hollow tubulose, up-small and down-big tapered in cross section the most as shown in Figure 3
Form.This bearing 50 the most vertically extends, and is connected (example with the horn of horizontal expansion
As, as shown in fig. 1).It will be understood that shape and the orientation of a bearing are not limited to above-mentioned enumerating
Form, can be such as sloped position or other hollow shape.
Fuel cell system or sub-cell of fuel cell 1 can be contained in this bearing.It is preferred that in combustion
Connect between material battery system 1 and the motor of flight lifting member 3 and have control card 62 (as controlling organization 4
A part), this control card 62 can control the mixed dynamic of fuel cell and lithium battery (if if provided, with)
Ratio and the switch of electromagnetic valve.The input of this control card 62 is the direct current supplied by fuel cell system 1
Electric current, and its electric current (unidirectional current) being output as being supplied to flight lifting member 3 and to electromagnetic valve 64
Control.
In can be configured for keeping fuel cell system 1 with the electromagnetic valve 64 controlling card 62 electrical connection
Hydrogen Vapor Pressure, and can control with the accurate temperature carrying out fuel cell system 1 carrying out periodically opening and closing
And unnecessary water in eliminating fuel cell reactor.Electromagnetic valve 64 is driven controlling by controlling card 62.
As it was previously stated, the input being contained in the fuel cell system 1 within bearing 50 equally is airborne hydrogen
Gas.As shown in Figure 3, fuel cell system 1 is advantageously arranged in the propeller of flight lifting member 3
Lower section (such as, be positioned at immediately below it and near propeller), to be maintained at the wind-force effect of propeller or to cover
Within cover region territory, thus obtain the maximum quantity of wind of propeller.Thus, it is possible to realize compact layout and really
Protect effective public attention pressure of fuel cell system 1.
Claims (8)
1. a fuel cell unmanned plane, including fuel cell system (1), flight lifting member (3), control
Mechanism processed (4), wherein, described fuel cell system (1) provides power for described fuel cell unmanned plane,
Fly to make the propeller of described flight lifting member (3) rotate via described controlling organization (4)
OK, it is characterised in that described fuel cell system (1) is arranged in below described propeller, with by described
Propeller provides the air quantity needed for flight for it.
2. fuel cell unmanned plane as claimed in claim 1, it is characterised in that described flight lifting member
(3) by bearing (50) supporting of hollow tubular, described fuel cell system (1) is contained in described
In bearing (50), within being located immediately at the wind-force zone of action of described propeller.
3. fuel cell unmanned plane as claimed in claim 1, it is characterised in that also include master controller
(40), described master controller be constructed to be permeable to calculate air quantity (F) that described fuel cell unmanned plane needs and
The air quantity (f) that described flight lifting member (3) can be provided by the rotation of its propeller.
4. fuel cell unmanned plane as claimed in claim 2, it is characterised in that described bearing (50)
Inside there also is provided control card (62) as described controlling organization (4), the input of described control card (62) is
The DC current supplied by described fuel cell system (1), and it is output as being supplied to described flight and promotes
The electric current of component (3).
5. fuel cell unmanned plane as claimed in claim 2, it is characterised in that described bearing (50)
Vertically extend, and be connected with the horn of the horizontal expansion of described fuel cell unmanned plane.
6. fuel cell unmanned plane as claimed in claim 1, it is characterised in that described fuel cell system
(1) vertically arranged in the underface of described propeller.
7. fuel cell unmanned plane as claimed in claim 3, it is characterised in that described fuel cell system
Arrange relative to described propeller tilt, carry to described fuel cell system reducing described flight lifting member
The air quantity of confession.
8. fuel cell unmanned plane as claimed in claim 3, it is characterised in that in multiple propellers
The arranged beneath of only a part propeller has described fuel cell system, with reduce described flight lifting member to
The air quantity that described fuel cell system provides.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620201807.6U CN205524959U (en) | 2016-03-16 | 2016-03-16 | Fuel cell unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620201807.6U CN205524959U (en) | 2016-03-16 | 2016-03-16 | Fuel cell unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205524959U true CN205524959U (en) | 2016-08-31 |
Family
ID=56781745
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620201807.6U Active CN205524959U (en) | 2016-03-16 | 2016-03-16 | Fuel cell unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205524959U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107200119A (en) * | 2016-03-16 | 2017-09-26 | 上海重塑能源科技有限公司 | Fuel cell unmanned plane |
| DE202021105654U1 (en) | 2021-10-15 | 2022-01-18 | Choren Industrietechnik GmbH | Hydrogen fuel cell cargo drone with swappable hydrogen storage tanks |
-
2016
- 2016-03-16 CN CN201620201807.6U patent/CN205524959U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107200119A (en) * | 2016-03-16 | 2017-09-26 | 上海重塑能源科技有限公司 | Fuel cell unmanned plane |
| DE202021105654U1 (en) | 2021-10-15 | 2022-01-18 | Choren Industrietechnik GmbH | Hydrogen fuel cell cargo drone with swappable hydrogen storage tanks |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN205524958U (en) | Fuel cell unmanned aerial vehicle | |
| KR102483971B1 (en) | Evtol aircraft using large, variable speed tilt rotors | |
| US20170015417A1 (en) | Multi-Propulsion Design for Unmanned Aerial Systems | |
| US11548650B2 (en) | Hybrid airship | |
| EP3290334B1 (en) | Aircraft for vertical take-off and landing | |
| US11142309B2 (en) | Convertible airplane with exposable rotors | |
| US20210354810A1 (en) | Apparatus for providing rail-based vertical short takeoff and landing and operational control | |
| KR20200093560A (en) | VTOL aircraft with fixed and rotary wing configurations | |
| US20140252156A1 (en) | High Altitude Aircraft, Aircraft Unit and Method for Operating an Aircraft Unit | |
| CN105652886B (en) | A kind of internet unmanned plane persistently continued a journey | |
| KR101666373B1 (en) | Flight paths setting method for stratospheric long endurance of Unmanned Aerial Vehicle based on regenerative fuel cells and solar cells | |
| US20210276723A1 (en) | Power assembly, power system and unmanned aerial vehicle | |
| WO2016138173A1 (en) | Methods for providing a durable solar powered aircraft with a variable geometry wing | |
| CN105947192A (en) | Tilting double-duct unmanned aerial vehicle | |
| CN107140229A (en) | One kind is tethered at unmanned plane energy supplyystem | |
| CN106218849A (en) | Aerial wind energy power station formula aircraft and aerial fixing aircraft device | |
| CN105408202A (en) | High-altitude drone | |
| CN205524959U (en) | Fuel cell unmanned aerial vehicle | |
| CN115258149A (en) | Aircraft with multi-fan propulsion system for controlling flight orientation transitions | |
| Duy et al. | Review on the hybrid-electric propulsion system and renewables and energy storage for unmanned aerial vehicles | |
| CN107200120A (en) | Fuel cell unmanned plane | |
| CN205608525U (en) | Last internet unmanned aerial vehicle of continuation of journey | |
| CN111874222A (en) | Pure electric tandem double-rotor unmanned aerial vehicle system | |
| CN206719540U (en) | Tilting rotor type VUAV based on Flying-wing | |
| Kozakiewicz et al. | Electric aircraft propulsion |
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 |
Denomination of utility model: Unmanned aerial vehicle with fuel cells Effective date of registration: 20200204 Granted publication date: 20160831 Pledgee: Jiading Branch of Shanghai Bank Co., Ltd. Pledgor: Shanghai Chongsu Energy Technology Co., Ltd. Registration number: Y2020310000004 |
|
| PE01 | Entry into force 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: 20201225 Granted publication date: 20160831 Pledgee: Jiading Branch of Shanghai Bank Co.,Ltd. Pledgor: SHANGHAI RE-FIRE ENERGY TECHNOLOGY Co.,Ltd. Registration number: Y2020310000004 |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right |