CN109543270A - A kind of helicopter piggyback pod airfoil and Design of Aerodynamic Configuration method - Google Patents
A kind of helicopter piggyback pod airfoil and Design of Aerodynamic Configuration method Download PDFInfo
- Publication number
- CN109543270A CN109543270A CN201811354722.1A CN201811354722A CN109543270A CN 109543270 A CN109543270 A CN 109543270A CN 201811354722 A CN201811354722 A CN 201811354722A CN 109543270 A CN109543270 A CN 109543270A
- Authority
- CN
- China
- Prior art keywords
- piggyback pod
- airfoil
- helicopter
- tail
- aerodynamic
- 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
Links
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- Geometry (AREA)
- General Physics & Mathematics (AREA)
- Computer Hardware Design (AREA)
- General Engineering & Computer Science (AREA)
- Evolutionary Computation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Pure & Applied Mathematics (AREA)
- Mathematical Optimization (AREA)
- Mathematical Analysis (AREA)
- Computational Mathematics (AREA)
- Automation & Control Theory (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
This application provides a kind of helicopter piggyback pod airfoil and Design of Aerodynamic Configuration methods, belong to helicopter flight control design field.The piggyback pod airfoil setting is vented metastomium in helicopter back piggyback pod, air-flow at least partly stopping to flow from from piggyback pod exhaust outlet to empennage direction, this application increases piggyback pod airfoil in helicopter back piggyback pod exhaust metastomium, and vortex wake flow aerodynamic interference wind tunnel test is carried out to the helicopter of drive cabin airfoil, constantly modification piggyback pod airfoil, it finally takes a flight test, to determine the implementation result of piggyback pod airfoil.It is proposed by the present invention to solve the piggyback pod airfoil and its procedure of development that tail quivers, it can be effectively reduced influence of the gas of piggyback pod discharge to empennage, tail gone straight up to single rotor band tail-rotor configuration and quivers Resolving probiems with important references effect.
Description
Technical field
The invention belongs to helicopter flight control design field, in particular to a kind of helicopter piggyback pod airfoil and
Design of Aerodynamic Configuration method.
Background technique
It is a kind of depending on severity that tail, which quivers, may have a kind of phenomenon (see Fig. 2) of negative effect to unit effect, be one
Interference of the kind single rotor with the vortex wake flow formed on tail-rotor configuration by top incoming flow to rear member (such as horizontal tail, vertical fin).
The origin cause of formation of vortex wake flow is related to many factors, it is most important that main hub pneumatic design, is moved engine breathing pneumatic design
Power hatch cover shape pneumatic design and rotor and fuselage spacing.
Summary of the invention
At least one in order to solve the above-mentioned technical problem, this application provides a kind of helicopter piggyback pod airfoil and pneumatically
Exterior Surface Design.
The application first aspect provides a kind of helicopter piggyback pod airfoil, is mounted on the exhaust of helicopter back piggyback pod
Metastomium, the helicopter piggyback pod airfoil include extending to form from the exhaust outlet bottom end to the top of the exhaust outlet
Fixed plate, the exhaust outlet is divided into the two points of mouths in left and right to the fixed plate and baffle, the baffle are fixed on the fixation
On plate, and block at least partially open of described two points of mouths.
According at least one embodiment of the application, the fixed plate and helicopter backboard are integrally machined molding.
According at least one embodiment of the application, the baffle is detachably connected with the fixed plate.
According at least one embodiment of the application, the baffle is towards the tapered extension in the direction of exhaust outlet.
According at least one embodiment of the application, the fixed plate two sides are provided with slot, and the baffle is divided into
Two parts are plugged on respectively in the slot of the fixed plate two sides.
Second aspect of the present invention provides a kind of helicopter piggyback pod airfoil Design of Aerodynamic Configuration method, for determining
State the aerodynamic configuration of the helicopter piggyback pod airfoil of design, comprising:
Increase piggyback pod airfoil as described above, the piggyback pod aerofoil profile in helicopter back piggyback pod exhaust metastomium
Part at least partially stops piggyback pod exhaust outlet to the air-flow of helicopter tail rotor；
Vortex wake flow aerodynamic interference wind tunnel test is carried out to the helicopter of drive cabin airfoil, is further determined that various
The vortex tail flow field and its interference to rear member that overhead power cabin incoming flow under state of flight is formed, and identify that tail quivers
State of flight；
The aerodynamic configuration of piggyback pod airfoil is modified, until carrying out in vortex wake flow aerodynamic interference wind tunnel test, helicopter
Overhead power cabin incoming flow does not interfere rear member；
Piggyback pod airfoil is installed, and is taken a flight test, to determine the implementation result of piggyback pod airfoil.
According at least one embodiment of the application, the rear member includes at least horizontal tail and vertical fin.
According at least one embodiment of the application, the state of flight for identifying that tail quivers includes determining vortex wake flow
Interference and the relationship between air speed and vertical speed.
It further comprise flying before piggyback pod airfoil is installed various according at least one embodiment of the application
The vortex tail flow field and its aerodynamic interference to rear member that overhead power cabin incoming flow under row state is formed.
According at least one embodiment of the application, by pneumatically outer to helicopter before installing piggyback pod airfoil
Shape carries out vortex wake flow aerodynamic interference CFD analysis, obtains aerodynamic interference parameter.
Present applicant proposes a kind of piggyback pod airfoil that solution tail quivers and its procedure of development, can be effectively reduced piggyback pod
Influence of the gas of discharge to empennage goes straight up to tail to single rotor band tail-rotor configuration and quivers Resolving probiems with important references effect,
There is extensive engineering application value.
Detailed description of the invention
Fig. 1 is the flow chart of a preferred embodiment of the application helicopter piggyback pod airfoil Design of Aerodynamic Configuration method.
Fig. 2 is vortex wake radiation schematic diagram.
Fig. 3 is the airfoil scheme of installation of an embodiment of the application helicopter piggyback pod airfoil.
Specific embodiment
To keep the purposes, technical schemes and advantages of the application implementation clearer, below in conjunction with the application embodiment
In attached drawing, the technical solution in the application embodiment is further described in more detail.In the accompanying drawings, identical from beginning to end
Or similar label indicates same or similar element or element with the same or similar functions.Described embodiment is
A part of embodiment of the application, rather than whole embodiments.Embodiment below with reference to attached drawing description is to show
Example property, it is intended to for explaining the application, and should not be understood as the limitation to the application.Based on the embodiment in the application,
Every other embodiment obtained by those of ordinary skill in the art without making creative efforts belongs to this
Apply for the range of protection.Presently filed embodiment is described in detail with reference to the accompanying drawing.
In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of description of the present invention and simplification of the description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the present invention
The limitation of range.
The application first aspect provides a kind of helicopter piggyback pod airfoil, as shown in figure 3, being mounted on helicopter back
Piggyback pod is vented metastomium, and the helicopter piggyback pod airfoil includes from the exhaust outlet bottom end to the top of the exhaust outlet
The fixed plate extended to form, the exhaust outlet is divided into the two points of mouths in left and right to the fixed plate and baffle, the baffle are fixed
In the fixed plate, and block at least partially open of described two points of mouths.
Fixed plate can be fixed to helicopter back piggyback pod exhaust outlet between empennage by detachable connection method,
It can be used as a part at helicopter back, all-in-one machine adds, and the application is especially suitable for using the component as helicopter back
A part.
Fixed plate is limited to the blocking effect of air-flow, is for exhaust outlet to be divided into left and right two using the purpose of fixed plate
Point, so that the baffle installed in fixed plate can further block the gas excluded among exhaust outlet, in this way, baffle will change
Air-flow flows to the flow direction of empennage from exhaust outlet, and makes air-flow mobile to side rear, in some optional embodiments
In, the baffle is detachably connected with the fixed plate, so as to can be right at any time in the subsequent Design of Aerodynamic Configuration to baffle
New and old baffle is replaced.
In some alternative embodiments, the baffle is towards the tapered extension in the direction of exhaust outlet, it is possible to understand that
, during piggyback pod is vented outwards from exhaust outlet, the pyramidal structure that baffle inwardly opens up is conducive to air-flow to lateral flow,
Piggyback pod will not be vented and be impacted.
In some alternative embodiments, the fixed plate two sides are provided with slot, and the baffle is divided into two parts,
It is plugged in the slot of the fixed plate two sides respectively.In other embodiment, through-hole can be offered among fixed plate, this
When, baffle is single piece, is fixed in fixed plate after being inserted through the through-hole by bolt etc..
The application second aspect provides a kind of helicopter piggyback pod airfoil Design of Aerodynamic Configuration method, as shown in Figure 1,
Include:
Increase as above described in any item piggyback pod airfoils, the power in helicopter back piggyback pod exhaust metastomium
Cabin airfoil at least partially stops piggyback pod exhaust outlet to the air-flow of helicopter tail rotor；
Vortex wake flow aerodynamic interference wind tunnel test is carried out to the helicopter of drive cabin airfoil, is further determined that various
The vortex tail flow field and its interference to rear member that overhead power cabin incoming flow under state of flight is formed, and identify that tail quivers
State of flight；
The aerodynamic configuration of piggyback pod airfoil is modified, until carrying out in vortex wake flow aerodynamic interference wind tunnel test, helicopter
Overhead power cabin incoming flow does not interfere rear member；
Piggyback pod airfoil is installed, and is taken a flight test, to determine the implementation result of piggyback pod airfoil.
In some alternative embodiments, the rear member includes at least horizontal tail and vertical fin.
In some alternative embodiments, it is described identify state of flight that tail quivers include determine vortex wake radiation with
Relationship between air speed and vertical speed, and piggyback pod airfoil and installation are carried out improving and optimizating design depending on feelings, it is ground to be subsequent
Be formed with the tail problem of quivering being likely to occur do it is reserved.
It in some alternative embodiments, further comprise in various state of flights before piggyback pod airfoil is installed
Under overhead power cabin incoming flow formed vortex tail flow field and its interference to rear member.
In some alternative embodiments, by being carried out to helicopter aerodynamic configuration before installing piggyback pod airfoil
It is vortexed wake flow aerodynamic interference CFD analysis, determines the interference.
In above-described embodiment, piggyback pod airfoil is installed, and take a flight test, to determine the implementation effect of piggyback pod airfoil
Fruit, comprising:
Firstly, the tail for not installed piggyback pod airfoil quivers and takes a flight test, state of taking a flight test includes climbing, putting down winged and glide, really
Determine the vortex tail flow field of top incoming flow formation and quiver with the presence or absence of tail:
Such as there is tail to quiver, then the flight state that tail quivers occurs in identification；
If quivered there is no tail or the tail magnitude that quivers is acceptable, then freeze aerodynamic arrangement.
Next, installation piggyback pod airfoil, carries out tail according to the tail of identification flight state of quivering and quiver and take a flight test, and and not
The result of taking a flight test of installation piggyback pod airfoil compares, to determine the implementation result of piggyback pod airfoil:
It is such as effective, freeze aerodynamic arrangement；
If effect is unobvious, then carry out piggyback pod airfoil and installation improves and optimizates design.
Present applicant proposes a kind of piggyback pod airfoil that solution tail quivers and its design methods, can be effectively reduced piggyback pod
Influence of the gas of discharge to empennage goes straight up to tail to single rotor band tail-rotor configuration and quivers Resolving probiems with important references effect,
There is extensive engineering application value.
The above, the only specific embodiment of the application, but the protection scope of the application is not limited thereto, it is any
Within the technical scope of the present application, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
Cover within the scope of protection of this application.Therefore, the protection scope of the application should be with the scope of protection of the claims
It is quasi-.
Claims (10)
1. a kind of helicopter piggyback pod airfoil, which is characterized in that it is mounted on helicopter back piggyback pod exhaust metastomium, it is described
Helicopter piggyback pod airfoil includes the fixed plate extended to form from the exhaust outlet bottom end to the top of the exhaust outlet, described
The exhaust outlet is divided into the two points of mouths in left and right and baffle by fixed plate, and the baffle is fixed in the fixed plate, and is blocked
Described two points of mouths it is at least partially open.
2. helicopter piggyback pod airfoil as described in claim 1, which is characterized in that the fixed plate and helicopter backboard one
Body machine-shaping.
3. helicopter piggyback pod airfoil as described in claim 1, which is characterized in that the baffle and the fixed plate are removable
Unload connection.
4. helicopter piggyback pod airfoil as described in claim 1, which is characterized in that the baffle is in the side towards exhaust outlet
To tapered extension.
5. helicopter piggyback pod airfoil as described in claim 1, which is characterized in that the fixed plate two sides are provided with slotting
Slot, the baffle are divided into two parts, are plugged in the slot of the fixed plate two sides respectively.
6. a kind of helicopter piggyback pod airfoil Design of Aerodynamic Configuration method characterized by comprising
Increase piggyback pod airfoil as described in any one in claim 1-5, institute in helicopter back piggyback pod exhaust metastomium
Stating piggyback pod airfoil at least partially stops piggyback pod exhaust outlet to the air-flow of helicopter tail rotor；
Vortex wake flow aerodynamic interference wind tunnel test is carried out to the helicopter of drive cabin airfoil, is further determined that in various flights
The vortex tail flow field and its interference to rear member that overhead power cabin incoming flow under state is formed, and identify that tail quivers winged
Row state；
The aerodynamic configuration of piggyback pod airfoil is modified, until carrying out in vortex wake flow aerodynamic interference wind tunnel test, helicopter top
Piggyback pod incoming flow does not cause aerodynamic interference to rear member；
Piggyback pod airfoil is installed, and is taken a flight test, to determine the implementation result of piggyback pod airfoil.
7. piggyback pod airfoil Design of Aerodynamic Configuration method as claimed in claim 6, which is characterized in that the rear member is extremely
It less include horizontal tail and vertical fin.
8. piggyback pod airfoil Design of Aerodynamic Configuration method as claimed in claim 6, which is characterized in that described to identify that tail quivers
State of flight include determine vortex wake radiation and air speed and vertical speed between relationship.
9. piggyback pod airfoil Design of Aerodynamic Configuration method as described in claim 1, which is characterized in that in the installation piggyback pod wing
It further comprise vortex tail flow field that the overhead power cabin incoming flow under various state of flights is formed and its to tail portion before type part
The aerodynamic interference of component.
10. piggyback pod airfoil Design of Aerodynamic Configuration method as claimed in claim 9, which is characterized in that in installation piggyback pod
By carrying out vortex wake flow aerodynamic interference CFD analysis to helicopter aerodynamic configuration before airfoil, aerodynamic interference parameter is obtained.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811354722.1A CN109543270B (en) | 2018-11-14 | 2018-11-14 | Helicopter power cabin airfoil and aerodynamic shape design method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811354722.1A CN109543270B (en) | 2018-11-14 | 2018-11-14 | Helicopter power cabin airfoil and aerodynamic shape design method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109543270A true CN109543270A (en) | 2019-03-29 |
| CN109543270B CN109543270B (en) | 2023-01-31 |
Family
ID=65847558
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811354722.1A Active CN109543270B (en) | 2018-11-14 | 2018-11-14 | Helicopter power cabin airfoil and aerodynamic shape design method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109543270B (en) |
Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060121818A1 (en) * | 2003-06-21 | 2006-06-08 | Lee Chang Y | Micro aerial vehicle |
| WO2008045036A2 (en) * | 2006-10-05 | 2008-04-17 | Hinderks M V | Improved reciprocating devices |
| US20130062460A1 (en) * | 2011-09-13 | 2013-03-14 | Gennady Trofimovich KRESHCHISHINA | Fuselage and method for reducing drag |
| CN302435381S (en) * | 2012-12-28 | 2013-05-15 | 天津曙光敬业科技有限公司 | Rotor-wing unmanned helicopter airflow baffle |
| US20140061366A1 (en) * | 2012-07-27 | 2014-03-06 | Eurocopter Deutschland Gmbh | Compound helicopter with tail booms |
| WO2015127903A1 (en) * | 2014-02-28 | 2015-09-03 | 武汉蓝天翔航空科技有限公司 | Tiltrotor helicopter |
| CN105059525A (en) * | 2015-08-14 | 2015-11-18 | 北京贯中精仪科技有限公司 | Aerodynamic layout of small-sized vertical takeoff and landing aircraft |
| CN106777576A (en) * | 2016-11-30 | 2017-05-31 | 中国直升机设计研究所 | A kind of piggyback pod calculation of aerodynamic characteristics method |
| CN206664931U (en) * | 2017-03-15 | 2017-11-24 | 西北工业大学 | A kind of tilted propeller can VTOL high-speed aircraft |
| CN108045572A (en) * | 2017-12-03 | 2018-05-18 | 中国直升机设计研究所 | A kind of compound thrust high-speed helicopter of cross-arranging type |
| CN108090302A (en) * | 2018-01-04 | 2018-05-29 | 北京中航智科技有限公司 | A kind of helicopter flight mechanical simulation method and system |
| CN108462408A (en) * | 2018-04-05 | 2018-08-28 | 郑州航空港飘天下物联网科技有限公司 | Air suspension floats row article air generator group and its operation principle |
| CN108791838A (en) * | 2018-05-28 | 2018-11-13 | 北京通用航空江西直升机有限公司 | A kind of very light-duty someone's agricultural plant protection helicopter |
-
2018
- 2018-11-14 CN CN201811354722.1A patent/CN109543270B/en active Active
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060121818A1 (en) * | 2003-06-21 | 2006-06-08 | Lee Chang Y | Micro aerial vehicle |
| WO2008045036A2 (en) * | 2006-10-05 | 2008-04-17 | Hinderks M V | Improved reciprocating devices |
| US20130062460A1 (en) * | 2011-09-13 | 2013-03-14 | Gennady Trofimovich KRESHCHISHINA | Fuselage and method for reducing drag |
| US20140061366A1 (en) * | 2012-07-27 | 2014-03-06 | Eurocopter Deutschland Gmbh | Compound helicopter with tail booms |
| CN302435381S (en) * | 2012-12-28 | 2013-05-15 | 天津曙光敬业科技有限公司 | Rotor-wing unmanned helicopter airflow baffle |
| WO2015127903A1 (en) * | 2014-02-28 | 2015-09-03 | 武汉蓝天翔航空科技有限公司 | Tiltrotor helicopter |
| CN105059525A (en) * | 2015-08-14 | 2015-11-18 | 北京贯中精仪科技有限公司 | Aerodynamic layout of small-sized vertical takeoff and landing aircraft |
| CN106777576A (en) * | 2016-11-30 | 2017-05-31 | 中国直升机设计研究所 | A kind of piggyback pod calculation of aerodynamic characteristics method |
| CN206664931U (en) * | 2017-03-15 | 2017-11-24 | 西北工业大学 | A kind of tilted propeller can VTOL high-speed aircraft |
| CN108045572A (en) * | 2017-12-03 | 2018-05-18 | 中国直升机设计研究所 | A kind of compound thrust high-speed helicopter of cross-arranging type |
| CN108090302A (en) * | 2018-01-04 | 2018-05-29 | 北京中航智科技有限公司 | A kind of helicopter flight mechanical simulation method and system |
| CN108462408A (en) * | 2018-04-05 | 2018-08-28 | 郑州航空港飘天下物联网科技有限公司 | Air suspension floats row article air generator group and its operation principle |
| CN108791838A (en) * | 2018-05-28 | 2018-11-13 | 北京通用航空江西直升机有限公司 | A kind of very light-duty someone's agricultural plant protection helicopter |
Non-Patent Citations (5)
| Title |
|---|
| CONSTANTIN ROTAR 等: "New Solutions for Aircraft Wing and Helicopter Blade Airfoils", 《2016 THIRD INTERNATIONAL CONFERENCE ON MATHEMATICS AND COMPUTERS IN SCIENCES AND IN INDUSTRY》 * |
| 张伟等: "T尾结冰颤振特性研究", 《科学技术与工程》 * |
| 邓彦敏 等: "直升机旋翼与机体间气动干扰风洞实验研", 《北京航空航天大学学报》 * |
| 邱良军 等: "直升机气动布局参数对飞行性能的推荐域分析", 《直升机技术》 * |
| 金贺: "直升机旋翼/机身/尾面的气动干扰研究", 《中国优秀博硕士学位论文全文数据库(硕士) 工程科技Ⅱ辑》 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109543270B (en) | 2023-01-31 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101180209B (en) | Aerospace vehicle fairing systems and associated methods | |
| US10625847B2 (en) | Split winglet | |
| CN109918764B (en) | Method for measuring rolling risk degree of aircraft after encountering wake vortex | |
| EP2692632A1 (en) | High-lift device for aircraft | |
| CN107804469B (en) | Aircraft | |
| CN105857579A (en) | Propeller airplane | |
| US10611461B2 (en) | Flap and aircraft | |
| CN111319775A (en) | Forward swept wing aircraft with boundary layer suction and distributed electric propulsion system | |
| EP3626609B1 (en) | A wing tip device | |
| KR20200055036A (en) | Aircraft cupola pairing and method for manufacturing same | |
| US9440729B2 (en) | High-lift-device, wing, and noise reduction device for high-lift-device | |
| US11124310B2 (en) | Pressure recovery device for an aircraft engine air intake | |
| CN103612746B (en) | Fairing structure of suspension in wing suspension layout aircraft | |
| EP1371550B1 (en) | Trailing edge shape of laminar-flow airfoil | |
| CN109543270A (en) | A kind of helicopter piggyback pod airfoil and Design of Aerodynamic Configuration method | |
| US8573542B2 (en) | Aerofoil slot blowing | |
| US10464682B2 (en) | Negative lift evacuation slide | |
| EP0052360B1 (en) | Air aspiration device of aircraft-mounted gas-turbine engine | |
| CN109383765B (en) | Drag reducer for exposed landing gear cavity | |
| US10266275B1 (en) | Pressure recovery device for an aircraft engine air intake | |
| CN207902734U (en) | A kind of unmanned plane of aerodynamic arrangement | |
| CN101454201B (en) | Method of and apparatus for producing aerodynamic resistance on an aircraft | |
| CN109625241B (en) | Method for reducing pressure difference resistance of wing section of fixed wing aircraft | |
| CN110733626B (en) | Guide vane and method for improving rolling stability of airplane | |
| CN109533287A (en) | A kind of ducted fan by-pass air duct and unmanned plane |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |